PROJECTMERCURY

FAMILIARIZATIONMANUAL

NASA

M_LNNE D SATELLITE SPACE Cl_AFT

ON_ DAY MISS]ION

1 DECEMBER 1962

_ MCDONNELL

AIR FORCE, Mendle Press, Inc. 12/12/62 900 (McDonnell A/C Corp.)

'__NIL/. $EDR 104

_4s 4oc_zent is applicable to Spacecraft No. 20 and its one-

day o_bital mission an_ supersedes basic SEER 10_-18_ dated 1 June

I_:_ )ga_ _114_e Spacecraft 18-Orblt Co_aticn. _hls

doc,-_nt covers Spacecraft No. 20 as delivere_ but does not tn-

cluae changes generated after delivery.

The purpose of This _mnent is tO present a clear operatio--1

descrlptic_ of the spacecraft systems _ laa_or c_-ponents. A can-

parlsom between _-/¢ompcments _11,_. in previous spacecraft

aml those Installea in Spacecraft No. 20 can be made by the use of

earlier issues of +.l_s _ocw_ent. Spacecraft r,--_ered2, 3, 4, 5_

6, 7, Ii, an_ 14 are covered in the i Febx.,a_yi_i issue of

i0_ Revised i August 1961. Spacecraft n,_re_ 9, 13, 16, 18 and

19 are covered in the 1 November 1961 issue of _R i04-3 Revised

1 February 1962.

SECTION INDEX.

SECTION IINTRODUCTION

SECTION IICABIN

SECTION IIIMAJOR STRUCTURAL ASSEMBLIES

SECTION IVENVIRONMENTAL CONTROL SYSTEM

SECTION VSTABILIZATION CONTROL SYSTEM

SECTION VlSEQUENCE SYSTEM, LAUNCH,RETROGRADE OR ABORT

.SECTION VII._SEQUENCESYSTEM, LANDING THROUGH.RECOVERY

SECTION VIIIESCAPE AND JETTISON ROCKET SYSTEM

SECTION IXPOSIGRADE ROCKET SYSTEM

SECTION X.RETROGRADE ROCKET SYSTEM

SECTION XlELECTRICAL POWER AND INTERIOR LIGHTING SYSTEMS

SECTION Xll

CC_MMUNICATION SYSTEM _._SECTION XlII

NAVIGATIONAL AIDS

SECTION XlVINSTRUMENTATION SYSTEMS

SECTION I

INTRODUCTION

TABLE OF CONTENTS

_ TITLE PAGE

Description................ .................................. .1-3

Cabin ........................................................ ,1-5

Major Structural Assemblies .................... .1-5

Environmental Control System ................. I-5

Stabilization Control System...................... 1-5

Sequence System....................................... I-6

Rocket Motors ............................................ 1-6

ElectricalPower And

Interior Lighting System ............................. 1-6

% Communication System........................... .1-6

Navigational Aids ...................................... 1-8

Instrumentation System............................. .1-8

1-1

NNELL SEDR 104

SPIKE

PYLON JE1TISON ROCKET

SPACECRAFT ADAPTER

RETRO ROCKET ANDPOSIGRADE ROCKETS

ATLAS "D" MISSILE

FM18-43

Figure 1-1 Spacecraft Prelaunch Configuration

1-2

aqO_ONNm_J. $EDR 104,

I. I_ZROIUCTION TO PROJECT M_CURY

z.,z. immmzm zoMercury Spacecraft deserlbe_ in this manual is des_ for a

Qne-_sy earth-orbiting mtsslcn. _e ._eatc= is an extenstca of _

three-orbit an_ six-_btt flights of the Mercury vehicle.

_e 0he-Day Spacecraf_ is s_.41-- tO the earller e_tlons

:eas_t_ 7_ inches in _Ltmster at the v_lest part of the spscecra_t

and 115 inches (See Figmre 1-2) fro: the heat shield to the ena of the

recovery eyl_r. _he spacecraft shape res_les a _mmeate4 co_e

topped by a short cylinder --_ retopped by a shorter truncat_L cone.

2he first c_ contains the astr_ut and his m_pcrting s__-_-, the

Cyl-_-_l,_'r contain- the recovery al4s and parachutes fc_ la._4._, the _cc_1

co_e Is the 8n_-- falr_ which cc_$_L_s T_e bicone --_emma 8n_ hu_ison

senslng elements plus the drogue chute.

Str_ling the _t_-, f_ng is a trlm_ular-_mpe_ trusvork of

steel tublng fca_In_ the escape tower. Two soll_ propellaDt rookets are

mounted on top of the tower: one escape, _ _ettlscn.

At the base of _ spacecraft, a heat sbtel_ of shlatl_ _lass f_ber

composition 10 a_tached to _he Impact _ skirt. _ _,'_.le_e as_mb_

i_shel_ securely to _ spacecraft until I_. _* re_ rocket

motor pack is attaehea to the heat ._lel_ end is _ettlsoned after retro-

/_ fire.

first cone Is a _ouble-wall structure, the inner wall forming a

pressure vessel (the eshin) and the outer shell for_ a heat -_fel_.

_he following paragraphs briefly describe the material covere_ in

i3

NNELL SEDR 104

_a. < <

°_

FM18-150

Figure 1-2 Principal Dimensions

1-4

__NmJ_. SEDR 104

_'ne inner wall of the spacecraft form- the cs_n s_ure and

houses the astronaut in a pressurized envirca_ent. The equil_ent _rlthin

the cabin £s arrenge8 so that al • opera_ controls end emergency provi-

sions are accessible to _b_ astrc_au_ when in the normal restrained posi-

tica. See Sectl_ XL

_he structure is of a conventlonal _i-mo_ocoque cans_ruction

utillzing titanium for the pr1-,_y structure. _, c_ter shell is de-

slgned to protect the internal cabin from excessive heatlz_, noise a_

meteorite penetration. _e internal cabin is 8esigne8 to provide a

safe envir_ut for the astro_. See Section TTI.

mm'mmmr .aLcorn,tooL

• he Envirc_aentsJL Control System pr_ides a livable envircanent for

the astr_alrt by controlling the gaseous c_ositi_l, _erat_x_, ht_i&-

i_y and pressure as well as cooling _he electronlc eqttil_aentaboard the

spacecraft. See Sectlc_ IV.

1-._. STABXLXZATXONCC_IOL SYS_

_e Stabilization Control System proviSes stabl/£zattc_ a_ orients-

tic_ of the spacecraft from the tize of separ_tlon from launch vehicle

until antenna fairln_ separation. _e system operates either au_cmati-

cally or m..._ _y using h_drogen peroxide as a propellant. _e hydrogen

peroxide is force_ over a ca_vst vhere It dee_.oses Into steam and c:_en

producing the _st _et ccutroll_ the attitude of the spacecraft. See

Sectl_ V.

I-5

_J/VNRJU[. $EDR 104,

_ae Sequence System is set 4n operation at liftoff providAng the

initial signal _ich is a basic reference po_. _his reference is

used to establish the order of events in relat£c_ to _m_, _he sys-

tam functions f_m liftoff thr_;_h the post _ phases of the

fli_t in normal or abort sequences as flAght con_tious dictate. See

Sectla_s VI and VII.

•-7.

• _e escape rocket is used to carry the spaceeratt out of d_er

in the event of a failure. _e Jettiso_ rocket separates the tower fran

the spacecraft under n_al add abort condltlo_s. See Secti_ VIII.

_e poslgrade rocket motors are use_ to accomplish separation be-

tween the spacecraft and the booster. See Sectio_ IX.

_he retrograde rocket motors slow the spacecraft sufficientl_ to

re-enter the earth's a_osphere. See Section X.

_e spacecraft is supplied 6, 12, 18 and 2_ volt d-c power fr_n

six silver-zlnc batteries. Battery volta6e, T_msformed to 115 volt,

_00 cycle, sln_le-phase a-c power, is supplied by two main an8 one

standby _-_rters. _e interior li_htlng consists of two fluorescent

flood lights mounted on either side of the astronaut an_ a series of

teleli_hts on the instrument panels. See Section XI.

z-9. cammxr, m'zo

DU_ flight a_ recovery phases, c._.-.._catlo_equipment and tracking

ai_ are used. _he flight C.-,....m_cati0_ equipment includes U_ and HF

1-6

MCDONNELL .SEDR 104

IY

_NORMAL ORBITAL FLIGHT

ROLL XZ

:YYAW

/ }PITCH

PITCH _SDEFINEDAS THE ROTATION OF THESPACECRAFTABOUTITSX-AXIS. THE"PITCHANGLE IS ZERO DEGREES(0°) WHENTHEZ-AXIS

:LIES IN A HORIZONTAL pLANE. USING THEASTRONAUT'SRIGHTSIDEAS A REFERENCE,POSITIVEPITCH IS ACHIEVEDBYCOUNTERCLOCK-WISEROTATION FROMTHE ZERODEGREES(0°) PLANE. THE RATEOFTHISROTATION IS THE SPACECRAFTPITCH RATEAND IS POSITIVEIN THEDIRECTION SHOWNASARETHECONTROLMOVEMENTSWHICHCAUSEit. THECONTROL HANDLEMOVESTOWARDTHEASTRONAUTAND THEPOSITIVEurI PITCHREACTIONJETFIRES.

YAW

.YAW IS DEFINEDAS THE ROTATION OF THE SPACECRAFTABOUTIT'SY-AXIS. CLOCKWISEROTATION OF THE SPACECRAFT,WHENVIEWEDFROM ABOVETHE ASTRONAUT, IS CALLEDRIGHT YAW AND IS DE-

FINED AS POSITIVE (+).

THIS MQVEMENT IS PRODUCEDBYPOSITIVECONTI_OLMOTION. THECONTR®L HANDLE IS ROTATEDCLOCKWISE(ASVIEWEDFROMABOVE;THE ASTRONAUT)AND THE POSITIVE(+) YAW REACTIONJET FIRES.YAW ANGLE IS CONSIDEREDZERO DEGREES(0°) WHEN THE SPACE-CRAFT IS IN NORMAL ORBITAL POSITION (BLUNT END OF SPACE-'CRAFTFACING LINE OF FLIGHT). WHENTHE POSITIVEZ-AXIS OF THESPACECRAFTIS DIRECTEDALONGTHEOREITALFLIGHT PATH(RECOVERyEND OF SPACECRAFTFACING LINE OF FLIGHT), THE YAW ANGLE IS180 ° .

_ROLLROLL IS DEFINEDAS THE ROTATION OF THE SPACECRAFTABOUTITS".Z-AXI$. CLOCKWISEROTATION OF THE SPACECRAFT,AS VIEWED_FROMBEHIND THE ASTRONAUT, IS CALLEDRIGHT ROLLAND IS DE-"FINEDAS POSITIVE(÷). THIS MOVEMENT iS iNitiATED BY MOVINGTHE CONTROL HANDLE TO THERIGHT, THEREBYFIRING THEPOSITIVE

. (+) ROLLACTION JET. WHENTHEX-AXIS OFTHESPACECRAFTLIESIN/ :A HORIZONTALPLANE, THEROLLANGLE IS ZERODEGREES(0°).

JACCELEROMETER POLARITY WITH RESPECT TO GRAVITY

WITH THE SPACECRAFTIN THE LAUNCHPOSITIONTHE Z-AXIS WILLBE!PERPENDICULARTO THEEARTH'SSURFACEAND THEZ-AXIS ACCELERO-METER WILL READ+1 "G".

FM18-61A

Figure 1-8 Spacecraft Polarity Orientation With Respect To Astronau_

I-?

___a_m. $EDR 104

voice +ransattters and. receivers, er--._ recelver az_ decoder, _ele-

:etr_ tr*n_4_er az_ "C" ead "S" bsn_ beaca_s for r_a_r tracking.

recovery equtlment t_]:¢1es the amd.lAaz70_ Rescue azd the

Rescue Beat.s u_e_Lfoz ]_-bmi_ o_ the sl:eeeraft. _e _

a_ _F tz--_4t_ers a_ receiversare also ogecative ¢o at_ in recovery.

See Se_£_ X_.

l-lO. _VX_GKAL AXDS

XavlgstloaalAids neeesssr_to _-_ altl_ude,eouzse,

veloei_, sttlt_ sn_ _ of re-en_ sre locate4eaaveaie_t_ for

q_l_M reference_ the astr_. See Se_ XXXX.

1-11.•he T-_x_e_a_i_ Sy_ =_Dlt_s pzess_zes,_att_es, ope=a-

tlon _ various,m4_s _oW_ tMe s_ aa_ eveats that oe_r

+_o_ _he fli_¢. _ astronaut'sresplra¢l_ race sad volw,

t_age_ sa4 Meat actl_ are aoaitoce4 e_ti=no_sl_; blood _essuz_

is :oattoze4 l_wio4te-1 ly by s sta_-s_op measm_ent _le _ai_ re_p4_es

setlve ssCzomm¢ l_zttotpation in sts_iag the o_Ae. Heart sol;ion :_¢f.-.

tortag (_) is inte_ during bloo8 l:essoze mas_me:ea¢. Data is

'to_'Uae"te_ eq_il_eat an8 _o +-_ ¢a_e reccn_ler. See Sec_ca

X_.

1-8

SECTION II

CABIN

TABLE OF CONTENTS

TITLE PAGE/

Arrangement ........................................... 2-3

Support Couch ....................... .................. 2-3

Restraint System ...... . ................................ 2-6

Controls .................................................... 2-6

Instrument Panels .... ................................ 2-6

•_iniHmJHi_a."_i!iiiii_ Static System ........... ................................ 2-9..T........:...:.:..:.:.::._.:::.:_._._Z__

=ii_iiiiiiiii_i_!i!i__ Survival Equipment ., ............................. 2-13._".::.::_.::::.:::.:.:_====:===:==:::::::..::::_.-..--_:,_ ,_-

..........................................:-_:_:_-_ Food and Water ...................................... 2-13================================================================

_!!!!iiiiiiiiiii_i_iiiiiiiiiiiiiiiiiiillllliiiiiiiiiiii:..:..:.ii:._'=-'_

_i__i_i_i_i_ii_i_ Astronaut's Apparell ................................ 2-13":iii::iii _i:_'_!!'!!'!!'!._'_y_y_='_='_".='.:.:..'::_::y:.__ _ _£__£_

:_!!i_/:_:_iiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiHiiiiiiiiiiii!iiii''_' Spacecraft Recovery ................................ 2-16iiiiiiii!iiiiiiii!iiiiiiiiiiJiiiiiiili

2-1

NNELL SEDR 104

FM18-44 rA

Figure 2-1 Interior Arrangement.

2:2 _

'_'_NNJ/.L SEDR 104

II. CAEI_

_e equ/pment w£thin Sb_ eabin_ Fl6_u-es 2-1 and 2-2, is arr_d so

that all normal and e_erKency e_trols are 8ecess£ble to the astr_aut

_hen in _he normal restrained postfix. The cabin equipmJnt basle,l ly

consists af the support couch t and reJrt_'alntw3's'e.,em_,enY_nmental system,

nswlKatioual aids s fl_ht and abort e_trol handles 2 _s_t a_l d£splay

panels, food 8n_ water suppl_ sur_wL1 kit1 e_eation equll_ent_ e_ra

8n4 other equil_en_ as needed far the mtss£cn.

2<:.

5he astrcuatrt's support ec_ch_ F£Kure 2-3, is destKned to firmly sup-

perS, the astronaut's bo,_r_uri_ la, nah, m-.m'_? _ _ phases ot

+_-_ miselon. The support eou_h also protects _ astronaut from loss Of

consciou_nes8 __,_lnK peak accelerati_ perioa_8 end from possible 4-_uxy

at _aet. 5_e e__eh iS ¢_ lo_a_l acl_3eee_t t;o the larKe pressu_

bulkheaa.

_he e_-,-_s are _L_'rlAual3,y "ta.t.lore_ 1;o each astronaut. 5_ey c_nstst

Of a hc_ey_ mat_rlal_ eom_ to all ecuches_ ariaan indlvi0-,_!3y tailored

K3.aS8 fl_:' shell. _ shell is pa_3e4 with a fl%_ liner for the astro-

na_'s eo_ort. _ hc_yc,'-,_, material is er_-_-_,lee_-.,_..m an_. the ehe_

iS pol_es_er _esin-relnfc_e_ Klas8 fiber !m.lnate. Honeyc,-._material is

also a--t-_l between the larKe pressure b-_e8_ on_ the couch to absorb

4.-Ta_ lomls. 5_e couch Is fa_rleaT_l in sec_l_ _o enable inst-_aT_Lc_

2-3

NNELI,. SEDR 104

FMIS_I_-IA

Figure 2-2 Cabin Equipment (Sheet I of 2)

2-4

ttlCDONNELL SEDR 104

z_

L__ :-

£

u

Z

! °

IFM16-1 (_-_

Figure 2-2 Cabin Equipment (Sheet 2 of 2)

2-5

_N_[. SEDR 104

2-3. ms,m_e astronaut's restraint system, Figure 2-4, is destsned to

restret- the astrcuaut in the support couch _ _ a¢celeratic_,

deeeleratlc_ an_ tO aid posltic_ _ weightless condtttOQQS. _e

restraint system consists of sho_&er_ chest_ an_ crotch straps t lap belt,

end toe and heel _ds. _he shoulder utraps ms_ be adjusted to restrat_ or

release the astrc_ by a harness reel control handle, locat_l fca-_rd of

the upper left side of the support couch. _e chest an_ shoulder strsps

restrain the upper t_so. _e lap belt ena crotch strap supports

the lower tarso. _he toe and heel _ support the feet. _e _t's

hands and arms are restrained b_ _cippi_ _he abc_ and flA_ht c_xtro_ handles_

!ocate4 near the ends of the s_port cotwh am rests.

Spacecraft ¢celtrols are located forward of each am res_ of _he st_p_rt

couch. An _gency escape handle is loca_e_ fca_d of the e_ppc_t cov_

left ann rest. _e escape handle Is utilAze_ to initiate the abort sequence.

To prevent inadvertent ac_atio_ of the escape system_ the escape handle is

provided wASh a manual look. _ae _,,-_ cca_trol han_e_ located foTward of

the support couch right am rest, is utllAzed as an overri_e system to c_n-

trol _ a_titu_e of _he spacecraft in the event _he aut_-_tc system

fails o_ fc_ normal manual f:Llght control if desired for a pca_lon of the

mission.

2-5. DIS'J_¢_mT P_ELS

_e Insets an8 controls are located o_ the main lnstrmnent panel,

left _d r_ht c_soles. .%c FA_ree 2-5 an0.2-6. _he =a£n _t

2-6

,MCDONNELL SEDR 104

f

LEGSUPPORT

CONTOURED_/COUCH

FMI

Figure 2-3 Astronaut's Sul_port Couch

i2-7

_a.i. SEDR 104

/f

R HARNESS ." _

//

/// REELS

CONTROL HANDLE

/

ILOCKED

/ !

rt'_RNESS

CHEST ROTCH HARNESS

\/ I

/

LAP D! _ /

_' TOE GUARDS I

• _rMle-,_

Figure 2-4 Astronaut's Restraint System

2-8_

_O00NNELJ. $EDR 104

panel Is locate_ _LTeet_y In i_rcntof _he estronatrt'ssupport e_;gb as

/ v_ewe4 by the astrn-m_. _he sate;11te clock, attit_de indicator, c.-.-_,-

nicatic_ controls, wazm4,_ l_hts, electrical m_tches, and indicators

are located on _e main _Hzmment panel.

The left h._ cc_sole is located on the left slde of the maln panel

an(1 is accessible and visible to the astronaut vhe_ in the 1_1y restrained

posltion_ _he ec_sole Incluaes a telellght sequence, In_£cators and con-

trols. _e r_ght han_ console, located below the entrance hatch s Incl_des

c_trols far the envlrocmental control system. A separate coaxial switch

ls included cn _he right han_ side for HF ent_--a selection by the astro-

naut. _e Navi_atlonal Retlele_ which permits optical al_$ of the

retrofire attltu_e of the spacecra_, is suppcrte_ by a stoweble bracket.

_he reticle when stowed is located to _he left of the astronaut's _c_;

_hen in operating position, the il_a%e_ reticle is d£rectl_ In

w_th the astrcnatrt'ole_t eye and the wi_low an_ifc_m- an angle of _o

_th the lon_t;-,_!_e.l -,,_ of the spacecraft. A ¢m_ra support, _h_ch

causes a c_era _ a_-¢ of _, Ir£_h respect to the lc_gi_ axis

Of +_e spacecraft, is motmt_l to the right of the v4.ndow. AddttJ.onal equ:Lp-

merit _ be _ "to "the inetrmaent panels as it is nemb_. A _rt_,_ pole,

located adjacent a_ to the left of _e observatl_ _n_ov, enables the

a_ to act_te controls vith the su_t pressurized.

/

_e static system provi_s fo_ at_os__eric pressure meaa_x_mn_ necessary

for swLtches an_ _,_eatcrs to functlc_ in the spacecraft. _e altimeter,

rate of descent tndtest(n.; four baromr£_ee and a pressuz'e tr_r are

ecnneet;ed tO the s't,a'tle access port in this system. See _ 2-7.

2-9

_M_DONNELL; SEDR 104 :

.; :]

/--.

®°Figure 2-5 Main Instrument Panel

2-10

i,_ II_ICDOItlItlELL SEDR 104

RETRO ATT

Ag.M@ OFFRETROFIRED

©©©

I JEITREIRO05G

OFF

PUSH

:FM!_

_gure 2-6 Left,.,mdRightConsole

2-11

_MODONNELL SEDR ]04

\

FMI8-40

'Figure 2-7 Static System

2-12

"___ELL SEDR 104

2-7. _'aV'_AL __

/ The survival kit_ see Figure 2-8, sto_ed at the left side of the couch,

cc_tains __ following:

1 Water Container 1 First Aid Kit 1 Food Container

i Life Raft i Bar Soap 1 Container of Matches

1 Desaltlng Kit (For 8 pts) 3 Morphine and Anti- 1 WhistleSeasickness InJ.

1 Shark Repellant Package 1 Nylc_ Cord (i0 ft).1 Sun Glasses & Case

1 Tube Zinc Oxide 1 Signal Light1 SARAH Rescue

3 Dye Markers Beacon 1 Pocket _-Ife

1 Recelver-Beacon Transceiver 1 Signal Mirror

Plus additional items deemed necessary for the mission.

A flashllght is located adjacent and to the left of the observation window.z-

2-8. FOOD AND WA_

Food will be supplied as required by the m-1ssion. A six pound water

container provides the normal source of drinkin 8 water for the astronaut.

A secondary water supply containing up to five and one-half pounds of water

is locatedln the survival kit. Tank contalning forty-nine pounds of water

are provided to supply the Environmental Control System Cabin and suit cir-

cuit heat exchangers. The water remaining in these tanks, at the end of

the flight provides an additional backup source of drinking water.

2-.9. ASTRONAD_'S APPAREL

f The astronaut's apparel consists of a completely enveloping pressure

suit with helmet_ suitable undergarments, and boots. The helmet faceplate

can be opened while the spacecraft interior is pressurized although normal

2-13

_MCDONNELL SEDR ]04

_ ANDWINDOW PO_

SURVIVALKITSUPPORTASSY

SURVIVALKIT

KNIFE

J./

-tLIFERAFTANDWATERCONTAINER

MOUTH OPERATEDVALVE(WATERCONTAINER)

SIGNAL LIGHT

(IN SPONGE)

BATTERY I--'-,

R[_IEIVER DYEMARKER(3 REQ'D)

RESCUEBEACON

KNIFE

INJECTORS(3 REQ'D)

NHISTLE

10 FEET

KIT FOODICONTAINER_.--\FMI8-63 A

Figure 2-8 Survival Kit

:2-14.

_HCDONNELL SED]{ 104

• NAVIGATION J

..... I

OBSERVATION

CAMERA RRA,

_FMI8-146

.Figure 2-9 Pilots Camera

2-15

_m_Nl_N_ J 8EDR 104

procedure will be to keep the faceplate clos_l. _h astronaut is

speci-l_y fatted and trained to use his suit. O_q_n, regulated as

to +_mDe.rature, pressure an_ b,_44ity, is sUPPlied to the suit for

breathing an_ ventilation. Fur the astronaut's c_-_._ort, ventilating

air is supplied to the suit at all t4_s.

z- o.

A normal missiun is intended to ter_4-ate with the spacecraft

landing _- a pre_etemined area of the ocean. ._ps an_ helicopters will

be _ by in the recovery area with pruv£sions to pick up the buoyant

spacecraft 4w_iate_7 after landing. Consideri_ the possibility t_at

the spacecraft c_l_ land in other than the intendml recovery area; numer-

Ons devices, both electr_ic and visual, are auto_tically energize_ or

deployed after impact to ai_ in locating _e spacecraft. Depending upon

the weather, possible damage and the astronaut's ph_ical conditian I .the

ast_atrt m_y either stay in the spacecraft or egress to the lifera__t

_aich is provided as part of the su,-vlwsl equil_aent.

2-16

SECTION III

f

MAJOR STRUCTURALASSEMBLIES

TABLE OF CONTENTS

TITLE PAGE

Introduction; ............................................ 3-3

Spacecraft Forebody,............................... 3-4

Spacecraft Afterbody............ .................. 3-6

Entrance Hatch..., ..... ............................... 3-7

Observation Window _............................. 3-9

Small Pressure Bulkhead ...................... ,. 3-11

Large Pressure Bulkhead ........................ 3-11

Recovery Compartment .......................... 3-13

Antenna Fairing ..................................... .3-14

Destabilizer Flap ..................................... 3-16

Impact Landing System........................... 3-16

Escape Tower ........................ ,................. 3-20

:::_%::iiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiill Pylon-Spacecraft ;Clamp Ring ................ ,3-2 2'_ii_ii!!!ili!!iiiiii!iiiiiiiiii_'_= :_ Missile Adapter. .................................. ....3-22

Spacecraft!-Adapter Clamp Ring ............ 3-25

Retro-Package ...................................... 3-273-i

i

NNELL SEDR 1041

AFTERBODYI

HATCH WINDOW

(EXPLOSIVE

RELEASE) EXPLOSIVE

FOREBODY ARF._ --DOOR

VENT (12)RECOVERY

LARGE PRESSURE--BULKHEAD

ANTENNA

LANDING _NG

SKIRT

GROUND HANDLING"FITTING(2) II

MAIN AND ISMALL PRESSURE RESERVEBULKHEAD CHUTES

DROGUE _CHUTE

FIBERGLASSATTACH RING

'D

NOZZLES

ABLATION

_JMBILICAL IDOOR

FMI 8-86

Figure 3-1 Spacecraft _tructure.

3-2:

ILL MAJOR S_RUCT_RALA_T.VR, S

3-'1. _a_u6-_ION

_ae Pro_ectMercury spacecraft_Figure 3-1; is designe4to cc_tain

an as'_-cuut, dur'Az_ c_b:t'_Pl flight. _he spacecraft also con'_sins re-

eca_ exffIr_ stabillza_i_ an_ other e_uIpmeDtnecessary f_

•_e SlX_ecra/_ Is of s c_tlcz_l sez_i-scnocoqueceastr_ion uti-

11zlagtit--4_ for the primary structure. _e s_ructureis designe_to

protect the internalcabin from excessivehea_ noise an_ meteori_e

penetrati_. Be spacecraftis basleally a c_cal coaflgursti_ e_-

sls_ of a foreb_ _ afterbo_V. _e fore_o_v is the large dlsh

s_ shape structurec-I_-4 the heat shleld. _e afterbc_ consistsOf a

c_tieal :i_-secti_ ettachedto a mall cyl.l,,,,l_ical section. _u_

the orbitalfli@h_i the f_bo_7 is forwardwith respect to the flight

path. Provisionsare Incm'pczate8to permit cabin en_r_,no_--_ aria

esersencyexlt an4 exteriorvlew_.

Prim" te flAg,t, an escepe tower an8 anteanafairing are attache4

to the afterbo_V c_esl see_l.cm, ghe escape tower, _Lesi_ae8 to

ai4 in spaceeraft-_isstle e_er_aey sepsrati_, e_sts of a l_lnn

fr_m_ _o_k equippe_ with rockets. _he antemm fairin_ is a eylt_tcel

shsp_ stru_ttre ec_dnt_ the radio _ reeel_ an4 _am_Lttln_

antenna. _e escape to_er is _ettlsoae88ur_ the launch phase or

8ur_ an escape sequence. During the _ phase the antennafair-

lag is e_ s_ servesto 4eplo__he :aln chwte.

3-3

'___IA.L SEDR 104

3"-2. I_ODY

The forebo_, Figure 3.1, ,_in3_ consists of a 3._'ge_ blunt,, dish

shaped structure that is sup_z_d 1)y the large pressure b-l_ead _M

adjoins the afterbody conle_ section. 'Zae larse pressure b-l_ead

lutor-_1_y separates the forebo_v _ the after_. The forebo_

dish shape_ structure is an ablation heat ahiel_ that is designed to

protect the spacecraft _ extreme the_! conditions durlng re-entry

fli_t. It is also designed to prevent @_age upon _ _pact.

The heat shlel_ is a_ to the heat Shield attach r_ which in

turn is riveted to the co_cal section _m_ n_ti_, _he heat shield

attach ri_ iuco_tes elo_ated holes_ for f_e inst_ll_tton of the

heat shield to the sI_cecre_G and to allow for therme_L expa_lon. The

ablation shie_ is des_ned to ablate twder heati_ conditions add is -_

constructed of fiber@lass to form a smooth contour. A retro_mde pack-

age assa_ly is attached to the heat shield by means of three straps.

The retrograde pac_e is Jettisc___ed from the spacecraft followi_

retrogrede rocket fir_, which _tiates spacecraft re-entr_.

The forebody area, _etween the large pressure b,,lkhead=_ the heat

shlelcl,is vented to atmosphere _ a series of vents located arou3acl

the _eril)hez_" of the spacecrai_ forebode, adjacent to the forebo_ and

aftorbod_ _unctlon. _hree toroi_-1 shaped _ro_en peroxide _-_s and

six reaction control l_ozzles_each cove_l with Min-K heat i_sulatlon_

are located in the fore_ody area. The foreho_y area also houses the

heat shield release l_e_tlc system. A landing i_pact skirt is -I-o

store_ 4, the forebod¥ area. The rubber _regnated fi_er_£ase i_pact

skirt, attached to the heat shield attach r_ and the heat e_leld_ is

designed to absorb high ener_ shock loads e_co_tered duri_ a

__NmtJ,. SEDR 104

land or water; an_ also to stabilize the spacecraft _ an astro-

naut's egress, foll_A_ a landing in the vator. D_ing the lsndAng

phase, the heat shield is released, and extends the f_l_ length of the

impact A_t. Upo_ heat shield ecatact _ith land t air vi_h4_ _he im-

pa_t _ 1o fcT_d Otrt thro_h a series of holes located in the t_act

skirt _ _nich in ttu_ provides a ¢-_-like effect. To prevent

d maage "to .I-_,_ 1A,.ge press_e b-lkhead in the event the heat shield

strikes the spacecrai_ during lan_, the l_e _reaaure b,,_ad in-

corp_ates a re_ed 1_4.-ted fiberglass shield as_. _e

fiberglass -h_eld as_l_ is a_ to the t_s t_ support brack-

ets. Sand_che_ between the fiberglass shiel_ and the large pressure

bnl_,.h,ad, are sec_cmas of hc_teyea,a'a. '_enty-f_r straps fabricated of

stainless steel are located about the periphe_ af the i_act landing

skirt to prevent to_ng _ the _pact _ n_ aur_ h_h h_A-

z_tal verity rater!_4r_s. T_enty-four_ta_-_se steelcablesare

_ated insidethe i_p_t _ hag and altexm,ate_ located in rela-

tlc_ tO the steel straps. _he cables retain _he heat shield tO 'f3ze

spacecraft in the event strap fA_l,,,.e slumld occur. _e a_od_

c_Acal secti_ exterior shingle arrang_ent exten_s beyo.d the large

pressure bulkhead, to the forebo_ heat ,_e]_, and encloses the equip-

merit located be_een the large pressure h-lk_ad and the heat shield.

Locate_ a_acent to the forebody an_ ai_er_od_ _un_ure, and bolted to

the heat -_teld attach ri_ is a fiberglass a_ach ring.

spacecra_t-adal_teriD_tallatien_ the fiberglas attach ri_ a_ the

adapter attach flange are clamped together _ith a segmented el_p ring.

Receptacles for the retro-packa_e_ adap_r, sn_ the el_p ring pnetua'_J.o

3-5

_N_mLL SEDR104

and electrical connectors are locate_ under the forebody shingles ad-

Jacent to _Aberglass attach rt_8. rive spring loaded access doo_s, for

the receptacles are lnoorporate_ in the shim@les.

'We afterbo_ eon:Lcal _-sectto_ ma:Lu_ consists of a presmzz,Xzed

cabin that is supported bet_mea a _1_ pressure ,b-_,ead and the large

pressure bulkhead. _he cabS- tnterto_ _11 is 1_-._1 vtth c_led

_w_es to provide addittoDaA structur_ stre_th and e_ilRent attach

points. The m_d-seetion Is eonstructe_ of a cn_cal_ formed 4_r _

outer tt+_-_mm shell, seam welded together. _he outer skin ls beaded

to form small sealea pressure panels capable of w'J.ths'_,,_4,_Z _ pres-

swine and structural loads. _ze outer e,___al A_. ls re_._'orced with

longitudAnal hat _s. A _!_-_t of thersoflex :Lnsu_'t:Lo_ ls

bonded, in between %he hat _rs, to the outer (beaded) oonteal

skin. Wn-K _-mz_At_on ls also __ over the hat sections and

covered vlth a shimgle _nt. _e sbimg_ _ Is s4_4_

to the shiz_e tns+_l_tica used ca the ree_,_,-erysyst_s e_ut.

q_e forward e_l of the c_cal seetic_ is attached to the fo_ebod_ heat

ehle.l_.. 'J_e ea_ination of the co.ca1 seet_c_ beade_L outer _ctn,

hat section reinfo_cements, themoflex ims-l=tton _-_ extermal shingle

ins_al!atio_ provide the slzaceera_ with adequate hea% noise :_

meteorite protee_Lo_.

Located _n _he bottom of %__ e_z_ca_ seetion, as wXeved_Lur_ngnor-

real flight attit_te, ls a sln_-__ loaded door that enclosed the grow_

checkout umb_tea_ rece3d_.le. The door, _ to _ Sl_u:eemA_

struetttre, a_att_!ly e_oses when the ,m_14ca_ iS discc_me_.

__NNBL_ $EDR 104

T_ro auxiliary hoist fit-tings, attached to left and r_ht side of the

spacecraft, provide ground handling attach points. _ae hoist fifties

are removed prior to launch. Am explosive 4o_, _ml_ the snorkel

door, is provide& in "the spacecraft shing_s, between _he small pres-

sure b,,_h_ad and the oo_ical-c¥11-drical sections Juncture. This door

is e_loded from _he spacecraft during landis. Act_ation of the door

enables cool ._ to be &fawn into the spacecraft _rough the snorkel

valve when the cabin air inlet valve opens.

3--_. EFmANCE HATCH

An entrance hatch I Figu_ 3-2, Is located c_ the rlght side of the

sf+_rbod_rcc_'Lcal se_tlon as viewed ITem the crew :M_er station. En-

trance hatch co,ruction, s4_:r to +_, conical sectlon oonsln_au-tlcn,

consists of an Inne_ and outer (beade4) skin _ _lde_ together and

reinforced with hat str_-_-ers. An explosive charge, mo_ in the

hatch sill, is provided to qulcXl_ release the hatch and enable the

astro=aut to egress rapidly. An explosive charge initiator, located

in the upper aft corset of the hstch, is _ to an internal release

control initiator. Prlc_ to launch, the hatch Is bolted and sealed in-

to position with bolts, m_ _4o corr_a_d, shingles are In_!_,=_ over

the hatch. _e bolts are inserted through the entrance hatch sill,

which incorporates the explosive e%,_Ee, and threaded into the space-

craft sill. A magnesium gasket, wJLth1,1-_a rubber, f_s _he hatch

seal when the hatch is bolted into positi_a. Two hatch shingles are

attached to the hatch stringers, but in no -_.er are they attached to

spacecraft .hln_s. (_h!S enables the hatch to separate cleanly, up-

on ignition of hatch explosive charge.) Follo_ impact, the astronaut

37

"_MCDONNELL : SEDR 104

' INITIATOR

COVER • _ ,PLUNGER

Z RELEASEHANDLESAFETYPIN

EXTERNAL WINDOWRELEASE

ELE !

'E_CtEXPLOSIVE

SHEAR SPRINGSWASHER.

PPERCUSSIONCAP

FIRINGPI

DLg

EXPLOSIVEINITIATOR _)' m-o:rATEDle0°);

/HATCHINTERNALEXPLOSIVEC

HATCHSEAL

THERMOFLEXTHEP,MOFLEX INSULATIONINSULATIOi__

HATCHSILL MIN-K INSULATION

FM18-83;

Figure 3-2 Entrance Hatct_.

3-8

MCDONNELL SEDR 104,

removes the initiator cap from the initiator, and the safety pin from

f the initiator plunger. By depreseing the initiator plunger, the _,I.

tlator's two sprlng-loaded fir_-_-pins strike The explosive charge per-

eussion caps and detonate the eu_losive _b-rEe. _4s action explodes

the hatch from the spacecraft. An exterior hatch release control is

.1.o provided tO enable grouna personnel to explode the hatch in the

event the astronaut is unable to do so. Natch retOntlon aprings, se-

cured by pip pins, are incorporated c_ the inner side of the entrance

hatch to prevent injury to ground persnnnel in the event the initiator

plunger is accidently depresse_. Two pressure valves_ located in the

hatch, enables pressurization and purging of the spacecraft duri_

ground checkout operations.

3-5- OB_VATION WIDOW

An observation window, Figure 3-3, lecate_ on the after_ody conical

section, provides the astronaut with external viewS. _-e window, lo-

cated above the maln instrument panel, consists of an _--Pr and outer

assembly. The inner _ assembly made of three glass panes is sealed

in a tltaz_,m fr_: _nich is attache_ to the cabin wall. Each glass pane

is independently sealea to provide a pressure seal between the panes.

_ae outer window assembly conslsts of a glass pane sealed in = tltani_

free, that is at1_he_ to the spacecraft outer skin. _ae carterwindow

ass,mbly is sealed separately_ from the inner window as_ly, to provide

a complete seal. Be outer win_ow conform- to T_e curvature of _he comical

section. _e obselwatlon _ is equipped with filters_ enabling

astronaut to regulate external light entering _he cabin. A shield provided

39

_NNEJE.. SEDR 104,

' _ _ /FILTERI

LATCHMECHANIS_ _ J

$1=CTION AoA /OUTER WINDOWASSEMBLYGLARE SHIELD

GLASS PANES

IFM}8-PA

.Figure 3-3 Observation Window

3-10

__NNJ[LL SEDR 104

between the inner a-_ outer window assemblies e_m_tes images reflected

from the inner spacecraft structure. The obse_ation window includes a

two pOSition _ror assembly which increases the astronaut's angle of

observation •

3-6,. EN.£T.T, PRF_SURE BULKHF_LD

The small pressure b-_ead iute r__ _y separates the cabin pres-

surized area fr_ the recovery system c_nent _ structumll7

supports the aft conical section. A sealed escape hatch, FIEure 3-4,

tntexmally actuaT_t, is prowlded in the small pressure _,lkhead to

enable the asT_aut's exit following spacecraft landis. The dish-

shape_ escape hatch is eonstructe_ of a beaded a.],a-tnm= skin slx)ty_relded.

to an 4--er akin, that is reinforced _th structural "Z" shaped members.

The hatoh outer flan_d edge f_ts _nto the _,1_ pressure b,,lk_ead sill

and is held in place with a retai_ing ri_. Expelling the re+_r ri_

by raising the hatch handle I wedges the reta_er r__-_- between the _,lk.

head sill =_ the hatch flan_d edge and forces the hatch f_a_e aft to

prowlde a s_AI_ ac_on. The titanimn _--_1 pressure _,_k_ad is seam

welded to the conical secti_ _-er skin and bolted to the conical hat

_r_er flanks.

3-7.

The large pressure _,_k_ead supports the forward end of the conical

section and Inter--_y separates the pressurized cabin from the fore-

bo_7 heat shield. The large pressure b,,Ik_eadIs constructed of a com-

bined 4--er an_ outer ti+_-4_ s_n. The outer skin is beaded =-_ seam

welded to the _ -_. The b-lk_ead is reinforced with hori_

3-]1

NNELJI. SEDR 104

/,/" ,., Y/ / ,....,.,..// / \

.......i i//

RELEASEHANDLE

RETAII_IIN_

HATCH

ANDLESMALL SUPPORTPRESSURE

B]--

ESCAPEHATCHASVIEWFROMASTRONAUT'SSUPPORTCOUCHHATCH CLOSED

RETAINING

RETAINING RETAINING _ HATCH

0 / HATCH RING _ I

_ x---" HATCHSILLj _ _ HATCHSILLI

SMALLPRESSURE SMALLPRESSURE _'RULKHEA__ BULKHEAD

RELEASEHANDLE

HATCHRELEASEDL HATCHCLOSED SPRIN,ASSY i

HATCHRELEASED

SECTIONR-B

FMI841

.Figure 3-4 Escape Hatch,

:3-i2,

"_MOD_ONNIgLL SEDR 104, @

cha--Als Inst-11_ on the outer skin. _he b,,1_head inner skin is

provided with two verticel _h---ele, centrally located en_ spaced,

that furnish s_ructurel sttach point for the astronaut support couch.

Honeycunb shelves are provided on the bulkhead inner skin, ontboard of

the two vertical channels, for equipment insTmllation. _he b-1_head

outer flange ring is bolte_ to the conical section inner akin and the

bulkhead is also bolted to the conical section _--ar attach ring. Vents

are provided in the large pressure bulkhead to enable overboard venting

of the spacecraft bettery vapors and envircemental control system ex-

haust steam.

3.6.

_e spacecraft after_ody, Figure 3-1, basically consists of the

abort cylindrical section and the truncatea cone shaped structure. The

cylindrical sec¢ion is referred to as the spacecraft recovery s_

compartment s_l contains the landing psrachu_s, recovery aids and the

reactic_ control nozzles. _he truncated cone shaped structure, referred

to as the afterbody conical section, encloses the pressurized cabin.

_e recovery cuBpartment is connected to the p_essurized cabin by a

small pressure b,,Ikh_ad, q_e recovery system c_-._.artment is a cylin-

"_.rlcal formed tlt--_ skin utructure_ relnf_ce_ wlth l_it,,a_--1 h-t

struts, and covered with a oo_-,-,.q_a'te_ bery'l"H,,,,, shingle arrangement.

A layer of ther_lex insulation is installed between the hat stringers/

and the external -ht-_les to prevent excessive heating within the com-

partment. The _les are individual panels bolted to the h-t sections

with allowances for T_erm-1 expansion. A set of reaction control ex-

haust nozzles are internslly located every 900, bet_men the compartment

3-13

4#O_O_J_ u $EDR I04

Innm" a_. am'4the e_znsl _ tns_1._ti_. _',,e zecom_ s_'r, em

o_q,_ 11_ez'1or :f.8 _a/.1_ d1_.dm1,tn'_o a le_'t and risb_ sec-

tion. 5he o,cm_arlm_'t left 8eettc_ houses the recovery aids, electrAcal

viring an4 _!-_ing _ throu_ the e_-partme_t. 5he rlS_t se_J.on

of _ ecmpartmm_ houses a ftberg_ss container, structurm?ly al_t4e_

_nto _eo seettcas tha_ contain the mA_ and reserve parachutes. _heo

ematstner can be removed by _he astronau_ _rcm the cabin folJ_rl_

landing, to per:it egress through the recovery e_.art_nt.

_e an_n_a f_ .Ftgttre _-_ is a cy_tea_ shaped _truc_re

_hat houses the p_ch an_ roll horizon scanners_ an_ the main receiwl_

an_ transm_ antenna. 5he antenna_alrln_basic structureis of +

titantu: eonst_uetto_ an_ is covere_ _rAth "Re_e.,_.l" shingles. An et_h%

1rich vAn_o_ as_V is located aroun_ the outer base of the fairing

an4 sets as a dielectric between the _op of the fslrtng and spacecraft.

_ae _ assemblyco_s£stsof a a£_ccne base, _ber_es insulat£o_,

_r glass and teflon e_rips. In line wtth _he three _efl_n str_ps

attached to the antenna fairing _les, are three _ _lber-

glass Ku/des. _h. 1"1berg/ass guides an_ _efloD strips prevent da_Ke to

the a_te_ falrl_K _nen the escape towe_ is _e_Ttisone4. An al,_mm hi-

conies1 hc_n is inter,-: 3y loeate_ at the base of the ant_na fairing.

An eleet_le tnm.:-t_r a_ loekfom, locate4 above the bi-eonteal horn,

a14 in antenna f_ In__,_-tlon. A :o_.I hor1:c_ scanner is loea_e4

at the top of the antenna £aLr_g. A p£'_..h hc_lzon sca,,_r £s located :Lu

the sl_ of the f_, in l£ne vlth the roll hor_s_ so-_v. _he

fairing is atta_e4 to the spacecraft by a mortar gun l_ated in the

3-14

MCDONNELL SEDR 104

RI-CON CAL f

SUPPORT CLIP(TYPICAL6 PLACES) " ELECTRICAL

CONNECTOR

(TYPICAL3 PLACES)

CHUTE

POST

F1.APDIELECTRICWINDOW

TEFLON STRAP

(TYPICAL3 PLACES)

HORIZON ESCAPE/SCANNERS_ PYLON

LOCK FOAM'-'__ REEFINGCUTTERS

INSUU_TION_ _,

DIELECTRICWINDOWJ

• _'"_._,N _--RI-CONICAL HORN BI-CONICALHORN

tFMIS-10

Figure 3-5 Antenna Fairing

3-15

_N_m&J. SEDR 104,

recovery compartment. A steel post located in the center of the fairing

is use_ as a guide vhen the falring is Jettisoned. _ee index pins and

six sUpport cl£psI in _ antenna fair_ lower matln6 flaz_e, align wiTJ2

+-h_-eeholes an_ six brackets in recovery c_ard_ent mating flange. _le

antenna fair4_ also houses the drogue chute. _ree cables retain the

drogue chute risers to the fairing when the chute is deployed.

3-10. DE-STABTr.T_RR FLAP,i

A spring loaded de-s_abillzer flap, Figure 3-5, is attached tO the

top of antenna falrinKs opposite the roll horizon scanner. 5he de-

s_ilizer flap ensures cc_.rectre-entry attitude during abort and re-

entry phases. During launching phase, and UP to the spacecraft-tower

separation, the sprlng loaded de-stabillzer flap is held against the

antenna fairing by means of a nylon cord. _e nylon cord routed _rough

de-s_abilIzlng flap reefiug cutters is severed after the escape tower

Is _ettlaoned, thereby releasing the flap to the outhoe_1 position. When

the spacecraft descends to 10,000 feet altitude, the ante-ha faL-_ng is

aut_natteally _e_ttsonrd from the spacecraft by the firing of the fair-

ing aortar gun.

3-1I. neA

• he _"T.a_ I,,_,_ system, Figure 3-6_ is _estgned to absorb

enerEr shock loads eneoun'l'.ered clu_.ng _; and also to stabilize _e

spacecraft following a landing in water. The Impact system basleall_

consists of a heat .h4eld release mechanlmn, heat -h_eld re_mlxtg straps

(2_), heat -h_elclretention cables (2_), a rubberized cloth _-_-_act skirt

3-16

f{ IWICDONNELL SEDR 104

3-17

__NmLL SEDR 104

an_ a f£bers]_ss sh£eld asse_]_. _he _a_ _-_t t8 8_ed t- +_M

farebod_ area. During the noneal land£ng ._A_, the 10,000 feet baro-

stats ener_zes the 1_- Deploy" Re].ay to eJecl; "the antemm fairit_

which in turn dep]_)ys +_- ma£n parachut;e. (See Fisure 3-7). Ejection

of the entenua fa_"£_ closes the ante=na fs£rl=8 separat_an se_s£n8 sv£tch_

_ch in turn a_ects 2_ V d-o electr£c_ poeer to the Main Inertia Se£tch

zay #z (t me ',,ezve8eco,zlater,theMsln

#1 ener_zes to direct elect_ca], power to the heat sh£e_l release system

llm4t mr£tohes and. e_so to eners£ze the _ Bag Rela_. Eners£z£n8 the

Ba_ Re_ _t_ects 2_ V _-c el_c_-lca_ power to £Sntte "the t_o heat

shield release e_p_osi_e squib valves.

I_nttt_ of the squib v_lves _ 3_000 pet8 nitrogen pressure to

f_oe to the two heat _4eld release me_m_l sm aotuators, q_4s act£_

moves the heat shield from the spacecraft. _4ml_taneous_y w11_ the actu-

at;ton of "the release mee_,,,,:_,M_ the I,-_,,__,',_m 'two _-_t mr£tches close "to

ener_ze the _ Ba8 Ext, ensto_. SJ._a.l. ReXa_r, Eaez_z_ the 8_

(green), Ind.l.cat.l.n_ a safe cc_I11;1o_. T_amnthe actuator plst_ f,,l_y

travels to the open ]_, the aotua_c_ is _ by a sprY8 loaded look

pin. _he _._act _.a_.= bag circuit is de-ener_ze_ _d£e the spacecraft

is In orbit. Plac_n_ +_ _ bag mr£1_h £n the "A_O" position dm'Ln8

spacecraft re-e=tr_ _11_ arm the circuit A_l,'qr1_ _ operst£c_ of "the

_n the event the heat shiel_ meehsntm failed _o aotuate_ and release

the heat sh£el_ the t_o _-_t s_tehes v£11 re_tn open en_ the

Bag WarninS _ _elay _ ener_tze vi_ two se_ads. _zts in turn

d£reets po_er to J_,_-_te the Landing Ba_ Telel_ht (red), £n_£oa__18

II_ICDONItlELL SEDR 104:_

SCHEMATIC DEPICTS TWO EXPLOSIVE VALVES FIRED

MAT[C OPERATION. ISOLATEDSQUIB BUS24

IISW_Tc_GBAG" I

MAINSQUIB

IANTENNA FAIRING BUS 24V D-C

i_,AUT Ov r SEPARATION SENS,NG _._"_F" SWITCH NO. 2 I

"aql ISOLATED J V!MANSQUIB BUS J _ I

.._ EMERGENCY

24vo-c I L ;_;LANDINGBAG

l__ O J ql_ -alRELAY LANDING BAGMAIN SQUIB BUS _

24V D,-C

v

SWITCH RELAY TNO. 1_12 SECONDTIME DELAy

RESERVEDEPLOYMAIN . RELAY NO. 3 ;

STORAGE TANK

_QUIB ANTENNA FAIRING 11 j s_ P.S.l.:BUS r . SEPARATIONSENS,NG , ] I

SWITCH NO.| O C _ ¢ O t

T_ PORT

_EXPLOSIVE

A I_

ijA/_i_N_R RESERVEDEPLOY ......RELAYNO. 4 GROUND

i_ • "HECKOUTEMERGENCY

• MAIN DEPLOYMAIN DEPLOY RELAY CHECK _"RELAy NO. I VALVE

ENERGIZEDAT 10,000 FT. ACTUATORDECEhJT !

LANDING BAG

. L TELELIGHT _ i

I /

' ,ILANDING BAG /WARNING LIGPflRELAY 2 LSECOND

MAIN SQUIB 'lIME DELAY -

BUS 24V D-C ....

LANDINGSKIRT

(24 REQ'D.)

I_ LIMIT

• SHIELDCLOSE UPONACTUATION OF

RELEASEMECHANISM FMIII-11_

Figure 3-7 Imoact Landing Bag Schematic

3:19.

3-20

"_i_HCDONNELL SEDR 104.

PYLON STRUCTURE

(TYPICAL 6 PLACES)

1 ; SPIKE

ANTE Ni_IA FAIRING _*_N ESCAPE RCCKEI"

ROCKET OZZLE (TYPICAL 3 PLACES) PYLON ADAPTERCLAMP RING

PYLON ATTACH

ESCAPEROCKETPYLON

R :K'RECO' ¥C PA T.NT liATTACH. FLANGE

ESCAPETOWER

DESTABILIZING -

ANTENNA FAIRING __R

SCANNER CUTTERS /__ -- "/'_'_'f /_c__ ././ ,

RECEPTACLE

__ (TYPICAL 2 PLACES)

I)ISCONNE _ i _"

R_I/GON AT" ACH "_aRECOVERy COM PARTME NI

ATTACH FLANGE FMI8-12A

Figure 3-8 Escape 'rower

3-21

__mLa. SEDR 104

_he escape tower is fired to propel the spacecrai_aw_ from the

M4esilean_ then the _ettisonrocket is flre_ to separatethe pylxm

fran spacecraft.

3- 3. Za,0Zf-SPaCZCZZAZCZ,

The _m_. rAug eonslstsof three _ =h.=_edse_ents

e_ the pyl_ at_h ring to the recovery s_ e_artaen_ flange.

q_ee explosivebolts, wi_h _;,.Ii_laa provlsio_s,collectthe ring

se_ents in tensing, q_e el-.!,ring is basie-lly_ seinein 4esi_

as the spacecraft-adapterelm_q_ring (I_ 3-10),bu_ eo_siderabl_

smallerin size. _he clamp ring retains the I_ to the spacecra_

untll the els_ ring a_losive bolts are £'_.z,ea _x:J._h in t_-- separates

the elmp ring. An aex.od,_ma_e stability wm_e a_r_..bml to pylon

ring, aid_ in st,abi.l_.zing the spaee_-at_ _ the lauaelz phase. Six

cable s_raps,bolted._o the pyl_ stru_ and elm__ ring stabili_

we_, ai_ in space_-l_l_a separatlo_b_ re_ the el--p_r_

sea,eats of _he pylc_ when the explosivebolts are fire&.

3-I_. MXSSn_

•_e missilea_apter,Figure 3-9, is a slA_ht_V_apere_,e_-a_Aeal

shaped _me _ is deslgae_to mate _he spaeee_ wASh _he A_las

missile. Up_ adaptera_ spaeeerax_ lu_im to the missile,the

adapteris bol_e_ to _ mlssile au_ _he spacecraftis a_ _o the

adapter. _he a_apteris of ,,4.a_nocoque e__ and is _ppr_xl- -_

ma_el_ four feet in hei_t. _e a_ basi_,lly e_sists of an outer

e_,_._i_ate_Lti_ai_ :_- as_l_, rlvete_ aa_ mum welde_ to an inner

port rings, rlve_ bet_mea _he e_ of _he adal_. A steel3.2_

ozZO"<0

_z0 zoo

_or-mz° <g<_ X

IIE_ •

--'N-"

q9

-=< £I

FMIS-I

•Figure 3-9 Atlas Missile Adapter

3-23

_oN_Rr.m. SEDR 104_

ring is riveted to the bottom, 4n, Ar surface of the adapter. _ae

flanged rt_ is pruv_ded vith holes to enable the attachment of the

adapter _o the mlsslle with boZts. Aliment :turks are provided cn

the ring for proper a¢lapter-mtsstle 8_aent. Riveted to "the t_p;

4--er surface of the ag_mter is an almstntm flanged ring. _ adapter

aluminum ring -roteswith the spacecraft forebody fiberglass attach ring;

duri_ spacecraft to adapter inetallatic_ An _t _ on +:h_

a_spter ring BY A_s enables proper _ of spacecraft to a4apter.

top of the -!,-_-_a _ is slotteO at 120° int_s, to proyAde

adequate clearance for the retrograde rocket asseabl:r attach s_s,

when the spacecraft is attached to the adapter. A metal striker

bracket is riveted Inter-ally; every 22001 to the adapter a_._ Waen

the spacecraft is attached to the a_apter; these str4k_r brackets de-

press (open) the spacecraft adapter separati_ se_tz_ switches; locat_t

cn the bottaa of the retroKrade rocket asse:bly attach straps. _he

spacecraft is attache_ to the e_pter by Installing s chevron -h-ped;

se_aented clamp rl_ over the mated flanges of the fc_ebocl7fiberglass

attach ring and the aSapter ,pper ring.

A retainer asseabl_, a_ to the adapter interior akin, is pro-

vided tO _t the retro-pa_ an_ the explosive bolt fr_s

from strlking the Atlas _is_lle adapter L_X tank. 5he retainer ass_ly

is a cup shape_ structv_e, that fits over the retro-packa_e dome, 8n_

is s_ported by three metal straps _-t are _ to the adapter

with ceble asse:blies. A vent port, locate6 In the adapter -_-_ re-

eelves the mlsslle boll-off valve tube ariaenables tJaerelieving of

liquid oz_en fr_ the missile. Opposite the liquid _en boil-off

3-24

WO_Om_mA.L SEDR 104,

port, is an essptar door installation. The door lnstal_ttc_ provides

access to the booster and heat shield area vhtle on the pa_L. A fiber-

glass shield attached above the vent port opening, stresmlAnes the

adapter au_ shields the boil-ofT tube. Two stretch fittings, located

180 ° apart at the t_per section of the adapter, provide a mesnn of s_p-

porting (stretching) the aissile vhile in the vertical position fal-

adapterInstal2ation. Six cable assemblies,attache8to fi_i_s

space8 around the adapter outer co._ate_ skin, are attached to the

cla_ ring _hat attaches the spacecraft to the adapter. _e cables re-

tain the 01-=__ zt_ to the adapter folloving spacecraft-adapter sepa-

ration.

_- 3-15. SPA_CRAVT-ADAI_ZRCLAMP

Be spacecraft'adaptercle_ ring, Figure 3-IO, is proviSed to

attach the spacecraftto the aAapter. _ clap ri_ securesthe space-

craft to the sSapter_b_oughoutthe launchingphase until the ¢'tmap

ri_ ls separated by means of explosive bolts, allowAng the separation

fr_ the adapter. _he cle_p ring consists of three chevr_ ahspe8

seKments; that _ t-at_Ale6, mats with the forebody fiberglass attach

ring aria +_e adapter upper s_part ri_. _ee explosive bolts, vAth

Aual ignitionprovAsions,co--_ctthe three cl_ ri_ segmentsIn

tension. A metal strikerbracket is bolted, every 120°, to the inside

of the clap rl_. When the clmp ri_ is _-etall_, the striker bre,_ts

depress the spacec_ ring separationsensingsvltehes,locatedin outer

periphery of the spacecraftforebody.

_e exterlor of the e_-_p _ Is coveredwith a heat shieldthat

protects the e_q_loslve bolts from emcesstve heatl:_. _ae heat ah_elA

3-25

CLAMpRING

3-26!

*_A_O_Et.L SEDR 104

consists of three fairing asse_lies which are located _ectly overf

the explosive Bolts and three segmented fairing assemblies which cover

the remainder of the spacecraft adapter clamp ring. The falrlng as-

semblies which locate _t,'ec_y" over the explosive bolts are a thr==

piece installation. The top piece is fabricated of aluminmn and the

two bOttOm pieces are made of ti+_-4_. These fairIDg assemblies are

fastened to the clamp ring support fittings. The interior of the fair-

Ing ass_lles is _n--1-ted with thermoflex. The three segmented fair-

i_E assemblies are of a titanium construction whose interior is insulated

with thermoflex. The seKmented f8_ assemblies are Bolted to the

adapter clamp ring. Six cable straps are bolted to the spacecraft

adapter cable fitting° These straps aid in spacecraft-adapter sepa-

ratio, by re_InID 8 the clamp ring to the adapter whe_ the explosive

bolts are fired. An eloctrics_ cable_ c18_ aro,_ the interior of

the adapter; iS co-_cted to each Of the clamp r!n_ explosive bolts, tO

two receptacles in the foreb_ly area and to two receptacles on the launch

vehicle. A pne,-_tic _e is also connected to cae end of the explosive

Bolt and to a quick disconnect in the forebocly.

3-16. RETRO-PACKAGE

The retro packaKe, Figure 3-11, is a _ettisonable dome shaped container

moun_ed to the ablation shield by three retention straps. The package,

constructed of s1,,,,,lm_ alloy contains mountIDg provlsio_s for the posi-

Krade end retroKrede rockets, BF dipole antenna and associated wiring.

3-23

NNELL SEDR 104

RETRC

Figure 3-11 Retro Package

3-28

©"_A_IOi_4r)NNIKLL SEDR 104

_rmoflex insulation is provided on the _nner sides of the retro pack-f

age to protect the rockets .from excessive heat. Jettisoning provisions

are also provided by means of a post mounted in the center of the retro

package c_telning a spring assembly and explosive bolt. Detonation of

the explosive bolt releases the retentio_ straps and the spring assembly

ejects the retro package from the spacecraft.

/

3-29

SECTION IV

ENVIRONMENTAL CONTROLSYSTEM

TABLE OF CONTENTS

TITLE PAGE/p

Description .............................................. 4-3

Cabin Environmental Control ........... ,_..... 4-5

Suit Environmental Control ............ , ........ 4-6

Suit Emergency Control .............................. 4-7

Oxygen Supply .......................................... 4-7

Cooling Circuit ......................................... 4-8

:__:_i: Blood Pressu re Measu ring System ........ 4-9

Operation .......... ...... ................................. 4-12

_::_ System Units l........... ............ , ................... 4-31F _ .

"'::_i_:..... :!i!ii_"

4-i

4-2'

'__;v_Ka.g. SEDR 104

IV. _R_ ¢_ROL S'_

F ¸

DEm TIm

_he environmental control system Figure 4-i_ provides _he cabin and

_he astronaut with a 100 per cent ox_Een envir_ut to furnish the

bre&thlng_ ve_ilatlon an_ presst_izatlon gas requlre_ during _ space-

craft c_blts: fl_ht and ventilation for a 12-hour post-_ phase.

• he _c_ental c_trol system also functions in the following _---_r:

Removes odors_ COS a_l moisture from the astronaut's suit circuit; pro-

vides an "emergency ra_" usage of oxygen an T_e evant of pressure loss

in the sult circuit; malnta_n- cabin and suit T_mperatuze at approxl-

ms_e_7 80°F; provides an emergency flre extln_tlshlng capability an_

,_ operates in _e_htless" or "high g" c_/tions. Sys_ functioning

i_11 be automatlcally co_o11_d _ur_ng .11 phases of flight. In

_v_t the syst_ aut.o-_tlc cc_trola m_ac_io_ manual controls are

l_v£c_ed, to insure syste_ operation.

q_e anvlro_.nen_alcomtrol system is des16ne_ to be operated in el-

ther the suit mode_ cabin mode or emergency mode. _he system suit mode

is nor_-lly utilize_ au_ enables the as_ro_au_ to function in the closed

suit circuit d.urin_ cabin pressurized an_ _w-_ncy (_epressurize_) con-

d_tio_s. In the ev_t one control mode m-l_mctlonS_ the r_._nt._

control mode _11 continue to operate. _ne emergency mode insures

astronaut s_vlval in _e event both the suit and c_bin modes malfunc-

tiom. (me

_e enviro_tal control system pro¥1des a primary and secondary

ox_en suppl_ for both the cabin and suit circuits. Pr_-_y an_ sec-

4-3

_MCDONAIELL SEDR 104

Figure 4-2 Environmental Control System Block Diagram

4-4

--_-_y ox_en syst_a are basically the same, however, the secondary

cx_en regulated pressure is lower then _h* _ oxy_n re_late_

pressnre. A maunal_ controlled cooling cireuit_ for suit and cabin

sys_as_ t8 provl4_ to control suit and cabin _mperature during flight.

_he environmental control system components are located below the astro-

naut's support c_,,h adjacent to the large pressure bu!khea8 end also on

the interior of the -mAll pressure b,,l_h_ e_eeent to the escape hatch.

System manual controls are located on the left and right consoles; sys-

tea instruments on_ warni_ l_ht8 are located on the main instrument

panel.

4-2. CABINE_IR0_mTAL COHTROLp

During normal orbital flight, the enviro_ental control sysW is

operated in both _ cabin and suit mode. Operation in the cabin mode

per_ts the astronaut to open his helmet faceplate. _he prizmry and

secondary c_pn supply furnishes the cabin wl_h preestu_sation,

breathiug, and ventilation gas. _e cabin is equippe_ with auto-

marie ana manual controls for cabin ventilation, decompression, pres-

surization, temperature control, lanaing and p0st-lan_in_ ventilation.

_e cabin is cleared of con_-a_ts and a 100 per cent cx_Een en-

viro_ent i8 made available by purging _he cabin prior to launch. During

orbital fl_ht, cabin pressure 18 aut_-tlcally controlled by a cabin

pressure control valve. The cabin pressure relief valve prevents exces-

sive pressure buildup within the cabin and provides a manual means of

dec_ress_ the cabin in the event of a flre or buildup of toxic con-

t-_anta. Two coolant supply tanks eontainin_ _O pounds and 9 pounds of

4"5

_NtVfI.L SEDR 104 .

water respectively are e_on to both cabin end suit circuit heat ex-

changers _o pro_iae cabin an_ suit cooling. _ae coolant tank ec_taini_

40 pounds of water is also e source of drinking water for the astronaut.

Cabin temperature is controlled by em.,..? !y controlled selector _Xve_

which regulates _he amount of water entering _ cabin heat exchanger,

and in turn provides cabin cooling by means of water evaporation. _he

cabin fan, located oa the inlet side of the heut excha_er, forces cabin

air +.h_-ou_x the exchanger to provide cabin cooling and ventilation. Cabin

air _3_t an_ outflow valves, loca_1 cn the small pressure bulkhead., In'O-

vide ventilation during the landlu6 and po_t-_ phase.

During normal orbital flight, "thecc.,_,,.ono_Een supply furnishes ozy-

gen s:lmultaneously to the suit and cabin enviromnentel control circuits.

If a cabin circuit malfUnctlon, such as cabin decompression, should occur

at a tt.._ when "the astronaut has his faceplate removed, T_e astronaut

should 4-m_dla_ely close his faceplate. Closln_ the faceplate i_itia_es

the suit mode en_ confines _he astronaut to _he close_ suit control

circuit°

While operat_ in the suit mode, _- suit pressure realm-tot controls

the suit pressure to approx_ately _ psia and replenishes oxygen consumed

by the astru_mlt, during no_mal suit control circuit operation. _tit cir-

cuit pressure te utilized as a means of preesur_zin_ the water coolant

$--_e. _e m,'tt-env_ente_ control circuit incorporates e_pressors,

filters, absorbers an_ a _EperatUre control to insure astrc_e_rt'smax-

c_._or_. Sttit circuit temperatttre is colltrolled by means Of' _ter

evapc_atlc_. A water separator utilizes the c_on oxygen supply pressure_

4-8

NNELL SEDR 104

to remove moisture from the suit circuit oxygen supply. A caupressor,

/ located on the upstream side of the suit circuit heat exchanger, forces

the suit circuit oxygen supply throughout the circuit, providing suit

circuit ventilation• During the landing and post-landing phase, at-

mospheric air is drawn in _rough the cabin airiinlet valve to provide

suit circuit ventilation.

4.4. _JIT E_GE_CY 00NTROL

While operating in the suit mode during orbital flight, the suit

emergency control mode automatically activates when suit circuit pres-

sure decreases below 4.0 + •.3 psia pressure. A control handle is pro-I

vided to enable manual selection of the emergency mode. During the

s l-_ding phase, the emergency mode is aut_tically actiwated. _e

environmental system ox_en rate valve and the suit circuit shutoff

valve actuate simultaneously to switch the enviro_sental system fran

the suit mode to the emergency mode. Actuation of these valves may be

either auto-tic or manual.

An 02 _ light, located on the main instx_-B_ntpanel, and a tone

_enerator indicates when the envirc_nental system is operating in the

suit emergency mode. _he 02 Emergency Rate Handle used to activate the

suit emergency control, is located on the right console•

4-5. OXYGES _JPPLY

_he envir_utal system is supplied with ox_en, from pr4_Ary end sec-

ondary bottles. The _ and secondary o_n bottles are _irectly inter-

4-7

_o_la't.J. SEDR 104.

con_cted by a supply line, that forms a ¢_,._,_on c_gen supply to the cabin

pressure control valve, suit pressure re_,_tc_, e_ergency oxygen rate valve,

and the suit circuit water separator. The primary and secondary oxygen sup-

ply lines incorporate shutoff valves, pressure transducers, pressure reducers,

and check valves. The pressure transducers travm,tt c_ygen pressure, present

in the primary and secondary c_ygen bottles I to a dual quantity indicator,

tape recorder, and to a telemetry unit. _he primary oxygen bottle pressure

is reduced to 100 + 10 psig, by a primary c_ygen pressure reducer. Two pri-

mary c_gen pressure reducers are pro¥1ded for redundancy in the event one

pressure reducer fails. The secc_lary oxygen bottle pressure is reduced to

80 paig by a secondary pressure reducer. The primary oxygen supply pressure,

being greater than the secondary oxygen supply reduced pressure, permits the

prt-_ry oxygen supply to be utilized during normal conditions with the secon-

dary oxygen supply in reserve. _he oxygen supply line check valves prevent

+_e total loss of oxygen, in the event either the primary or secondary oXy-

gen pressure s_ply systeas fail.

COOLD

During normal orbital flight, the enviromnental system cooling circuit

furnishes the cabin and the suit circuit with provisions for independently

controlling the cabin and suit circuit temperatures. Water is supplied,

under oxygen pressure_ fran water coolant tanks to the cabin and suit

circuit heat exchangers. The water absorbs heat frnm the cabin and suit

circuit oxygen which causes the water to evaporate.

4-8

"_M_ONNELL SEDR 104

The cooling circuit basically consists of two water tanks, cabin

and suit temperature control valves and heat exchangers. Temperature

control valves are located on the right console.

4-7. .N_00DPI_S_,II_ _A_mIl_ gZS'I_

A semi-automatic, independently controlle_ system is provided to

measure the astronaut's _lood pressure during orbital flight. The Blood

Pressure Measuring System (Figure _-3) activated by the astronaut, records

the blood pressure through transducers and amplifiers which is +_en tele-

metered to tra_Lng stations. _e system essentlall_ consists of an oxy-

gen bottle, controller, pressure regulator, solenoid operated control

valves, occluding cuff and m_crophone.

Prior to installation of the entrance hatch, the oxygen supply (Figure

4-_) manual shut-off valve is opened allowing an oxygen flow through theI

regulator to the Fill Valve. _e re@.,latoris provided to maintain a Blood

Pressure Measuring System differential pressure of 4 _ psi in reference to

Enviromnental Control System suit circuit pressure. Depressing the START

switch locate_ on the main Instx,_nt panel directs electrical power to

activate the Blood Pressure Measuring System for 3.10seconds. Activation

of the system simultaneously opens the Fill valve an_ closes t_ D_ valve

allowlng the astronaut's suit cuff to _-_late. A time delay relay con-

4-9

NNEILIL SEDR 104

TO SUIT

EVIRONMENTALCONTROL

YSTEMSUITCIRCUIT

GAGE

MICROPHONECC BOTTLE

RELIEF

FIXED

ORIFICE_

I

RESTRICTORVALVE

PRESSUREREGULATOR

MANUAL SHUT-OFFVALVE

SUIT HOSE

MANIFOLD

WATER FILLSOLENOIDVALVE

SOLENOIDVALVE

FMI8-151

Figure4-3Blood PressureMeasuring System

4-10

MCDONNELL SEDR 104

FUSEPANEL MAININSTRUMENT

PANEL

J LEGEND j

OXYGEN BOTTLEPRESSURE

+/- "l"O _ I-_:_:!:_:_:::_!_:_OCCLUDING CUFFPRESSU,RE ]/NOTE

\SCHEMATICDEPICTSOPERATIONOF : _.

BLOODPRESSUREMEASURINGSYSTEM ..--

w,+.OCCLOO,NGCUPFPRE:SUR,_E_I._/i/ f 5\ _"*

TOSUIT :

.2 aRC0.ELOW/_, _RECOVERY ,_.

RELAY A,_

ENVIRONMENTALCONTROL

PANEL SYSTEM

HOLD RELAY / tf_'_ t

SUIT

-- BLOODPRESSURE

RESTRICTORVALVE

CONTROLLER RELIEFVALVE

f/

(ENERGIZEDFOR j 110 SEC.)110 SECONDS)FILLVALVE

+ TRANSDUCER FILLFOR5 SEC.

J PRESSUREREGULATOR

MANUALSHUTOFFVALVE

PRESSUREGAGE

/

PACKAGE "D" TRACKINGSTATIONTOTAPERECORDER OXYGEN BOTTLE

1100PSi

FM18-152

Figure 4- 4 Blood Pressure Measuring System Schematic

4-11

_M_ONNIrLL $EDR 104

rained within _ Recovery Relay Panel actuates five seconds after the

switch is depressed removing power to the Fill Valve solenoid. Pres-

sure in the cuff is dissipated +.t,_'ough the orifice on into the ECS suit

circuit in approv_atel_ thirty second_. _ne astronaut's blood pressure

is measured and telemetered by means of a transducer _ the controller re-

cording inflated cuff pressure, and a microphone placed under the cuff sensing

pulse sounds. A timer also contained within the controller _e-ener_lzes an

initiate relay at the end of ii0 seconds_ re_ electrical power to the

system, therefore op_-_-_ the d_. valve allowing system pressure to vent

to the Environmental Control System suit circuit.

A rest_ictor valve provided at the entrance of the suit circuit permits

a pressure flow into the suit circuit an_ a 1_mlted flow in the opposite

direction. Zu the event a Blood Pressure Measuring System llne shoul_ fail,

suit circuit pressure wc_l_ be maintaine_. A relief valve is provided to

dissipate excessive pressure in the event the regulatc_ should fail. If

the astronaut desires to discontinue the Blood Pressure Measuring cycle,

the STOP switch is depressed. Activatin@ the STOP switch energizes an

,interrupt rele_ in the Controller remov_ electrical power from the system

in turn opening the _,_ valve to discharge system pressure.

_e environmental control system is designed to sequentiall_ operate

automatieal_ _ the lau_ch_ or_it_ re-entry and post-la_ phases

_ of the flight. _he mode in _hich the environmental system is operate_

is de_nt _on the existing conditic_ within the cabin and suit cir-

cuit.

4-12

"__ItlNffLL SEDR 104

During the pre-launch phase of operations_ the o_en and water sup-

ply are fully serviced. Refrigerated air is ducted through the spacecraft

hatch to precool the cabin and structure duringl spacecraft pre-flight. The

refrigerated air supply is removed when an external supply of freon cool-

ant is directed to the cabin and suit circuit heat exchangers, +h_ou@h the

,m_ilical, to continue precooling the spacecraft structure ana cabin equip-

ment after the flight hatch is installed. The oxygen supply manual shut-

off valves are opened and the astronaut is connected to the spacecraft

suit circuit by attaching the suit circuit personal leads (flex hoses) to

the astronaut's pressure suit. The suit compressor and cab:In fan are

activated at this time. The suit circuit is purged wlth an external

source of low pressure oxygen applied _h_ou6h the suit circuit purge

valve. Yollowlng the purging operation, a sui_ circuit le-_-ge check

is performed. The spacecraft entrance hatch iS bolted into position and

the cabin is then checked for leakage and purged with o_gen. _he suit

circuit incorporates provisions for obtaining launch purge oxygen samples.

Forty-five seconds prior to launch, the gr'oun_ umbilical plug is

disconnected and freon coolant supply to the spacecraft ceases. During

launch and orbit, the cabin pressure relief valve maintains cabin pres-

sure at appro_m-tely 5.5 differential (cab_--_lent) psi. During space-

craft launch, the suit circuit pressure red,flaVor maintains the suit cir-

cuit pressure approximatel_ equivalent to cabin pressure. _Ihe suit cir-

cuit oxygen is kept free of contaminants by a solids trap and a C_ and

odor absorber. The solids trap removes foreign particles such as food

particles_ nasal excretions, hair, etc. The C02 and odor absorber filters

4-13

_MODONNELL SEDR 104.

odors and C_ from the circulating oxygen. Moisture from the suit

circuit oxygen is removed from the system by a water separator. The

pneumaticall_ activated water separator deposits the moisture into a

condensate tank. Cabin and suit circuit temperatures are controlled

by manually operated metering valves, that re@ulate the water flow rate

from the water coolant tanks to the cabin and suit circuit heat exchangers.

Upon reecho-= altitudes where the saturation temperature of water is lower

than the cabin and suit circuit gas temperature, the cabin and suit cir-

cuit heat exchangers will provide coo1_- S by water evaporation.

When the spacecraft descends to an altitude of aplrro_m-tely 21,000

feet, the snorkel explosive door is eJectea. (Door is located on space-

craft exterior.) At an altitude of appro71mAte]_y17,000 + 3000 feet, the

cabin air inlet and outflow valves open barometrically venting the cabin

to the atmosphere. Operation of the suit circuit compressor draws out-

side air into +he suit circuit thr_,_h the ejected snorkel door opening,

the snorkel valve and the open cabin air inlet valve. _e air, circulat_-_=.=

through the suit circuit, is relieved into the cabin end in turn flows out

+-hroughthe cabin air outflow valve. S4--,Itaneousl_,with the ope-_-_ the

cabin air inlet and outflow valves, the environ_utal system mode of opera-

tion switches to the mnergency mode., but_ the suit compressor continues to " -

operate. Switching tO the emergency mode provides a greater cooling

capacity for the astronaut. An inlet air snorkel valve and an outflow

air diaphra_n flapper ventilation valve located on the unpressurized side

of the small pressure b,,lkhead, prevent water from entering into the cabin

4-14

"_o_Kl_. SEDR 104

in the event the spacecraft submerges after landing in water environ-

_ ment. A veeumn relief valve, located in the flexible ducting between

the cabin air inlet valve and suit circuit_ prevents s vacutm to occur

which may cause the snorkel valve to stay closed. Du_=ing the post-.

landing phase, the astronaut may continue to operate his suit circuit

compressor to provide suit circuit ventilation. _ suit circuit com-

pressor draws atmospheric air into the suit circuit, through the cabin

air inlet valve.

_-9. CABIN ENVIR0_TAL CO_ROL

Operation of the enviromnental control system in the cabin mode,

(Figure _-5), after the spacecraft has entered the orbital flight pav_

permits the astronaut to open his helmet faceplate an_ be exposed to

cabin enviro_nent. -The cabin pressure relief Valve relieves cabin pres-

sure in excess of 5.5 psta. In the event cabin pressure tends to exceed

the 5.5 psta pressure (cabin over ambient)_ the relief valve w_dl open

to relAeve the excessive pressure. When the cabin pressure decays to

5 psla, the cabin pressure control valve will open to maintain approxi-

mately 5 psla cabin pressure. Cabin _-_e-up oxygen flow into the suit

circuit, q_ suit pressure regulator will sense the increase in suit

pressure, and relieve excess gas into the cabin. Routing the cabin

pressure control valve oxygen supply through the suit circuit, provides

a constant purging of the suit circuit. Cabin lpressure control valve

mainteinsoabin ress,,s to5.1.+ p,in.During orbital flisht, cabin gas is circulated throughout the cabin

by the cabin fan, located at the inlet to the cabin heat exchanger, mhe

4-15

NNELL SEDR 104

!

PACKAGE 02 PARTIALPRESSURESENSOR

I

WATERFROMTEMPERATURECONTROLVALVE

HEAT "_"

_,._ j_,EXCHANGER CABIN FAN CABIN FAN

_.!;,,OXYGEN CONTROLVALVE 8 i

.-CTO SUIT BYPASS FAN BUSCIRCUIT1

CABINAIR

II

r-- --J'- - "1

CAB,N //L _

PRESSUEE

RELIEF

VALVE

TO SUITtClRCUIT_jl

CABIN OUTFLOW CABIN AIRVALVE (OPEN INLETVALVEBELOW20s000 FT,)

SMALLpRESSURE VALVEBULKHEAD

FM18-38A

Figure 4-5 Cabin Invironmental Control System

4-16

©_!UO_ONNWA.L SEDR 104,

cabin gas absorbs "the heat generated by the cabin electronic equil_ent

_ and in turn is cooled when the gas passes thr_,_ the cabin heat exchan&_.

Water from the water coolant tanks evaporates in the heat excha_ which

absorbs the heat from the cabin gas. _e ste_n produced then passes over-

board through the _av_e pressure b-_ead stem vent. A cabin te_erattu_

control valve_ located on the rlgh_ console_ tS manually operat, ed by the

astronaut to control oabln temperature by contro_-S coolant water flow

rates.

In the event of a fire or a bUildUp of to_c cC_t_t.--ts_ _thin the

cabln_ the astronaut may manual_ _ecceq_ressthe cabin by aetuatl_ i_e

_SS "T" b-_a1_, located on the _ console. _e decn:presslon

handle is connected to the cabin pressure relief valve vlth a cable. D_r-

I_ decr_.ressloD of the cabIa, the cabin pressure control valve closes

when the cabin pressure decreases to 4.1 psla. Yolloei_ the ext_shing

of the fire, c_ the removal of tozic contaminants, the astronaut may repres-

surise _he cabin by closing the D_C_SS "T" handle and actuating the

3_ESS "T" handle. _he REPRESS "T" handle is connected to the cabin

pressm.e control valve wlth a cable. _he_ _ cabin has been rel_eSsur-

ized to 5.0 psla_ the REPRESS "T" handle _at be manua_._7 _losed. In

_- event of 8 cabin 8ee_resslon, due to a meteorite penetratlc_ or ex-

cessive cabS- leakage, the cabin pressure ccatro1 valve _lll close auto-

_a_icall_ at approxi_te_7 I_. 1 psta and prevent io_en flow to _ cabln.

_ Closing of _ cab:Inpressure control valve reserves the remslnlng ox_sen

supply for the suit envlro==ental control circuit, enablln_ the astronaut

to continue the =lssic_.

4-17

__m/.L SEDR 104

Prior to re-entry, the astronaut should assure that his helot face-

plate is closed. During spacecraft descent, ceb4_ pressure is maintained

at appr_mAtely 5 psia pressure. At 27,000 feet altitude the cabin pres-

sure relief valve opens allowing atmospheric air to enter the cabin and

equalize capsule internal and external pressures within 10-15 _0. When

the spacecraft reaches 17_000 + 3,000 feet altitude, the cabin air inlet

an_ outflow valves open providlng outsl_e alr ventilation for the suit

circuit. Suit circuit air is then vented to the cabin and out through

the cabin outflow valve. If the cabin air _-_et and outflow valves fall

to open at 17,000 + 3,000 feet altltude, the astronaut sho_L1_actuate the

SaO_. pull ring to open the valws. A snorkel valve, provided on the

inlet alde of the cabin air 1-1et valve and a di_hra_ flapper ventilation

valve provided on the outlet side of the cabin air outflow valve, prevent

water from entering _e cabin when the spacecraft lands in the water.

A cabin pressure indicator and cabin temperature indicator are pro-

vided on the m._, _-_r_sent panel. An alternate method of determining

altitude Is incorporated in conjunction with the cabin pressure indicator.

A placard with altitude m-_-_s mounted over the cabin pressure indicator

provides a direct reference to cabin pressure in the event the altimeter

should fail. A partial pressure sensor located below the correlation clock

is utilised to measure the ex_gen content circulating throughout the cabin.

Pressure measured by the sensor is tran-=_tted to an indicator _-_ked

"PARTIAL PRESSURE" located on the main instrument panel.

-1o. c maOT

The suit environmental control circuit_ Figure _-6, is supplied oxygen

from the envtro_Autal system o_gen supp_7, _brough the suit pressure

4-18

_MCDON_IELI. SEDR 104.

regulator and the cabin pressure control valve. During the launch and

re-entry phases, when the astronaut's helmet faceplate is closed, the

suit pressure re_,1_tor utilizes cabin pressure as a reference to control

the suit circuit pressure. While operating in the suit environmental'con-

trol mode, (helmet faceplatc closed), oxygen from the suit pressure regu-

Istor enters the suit circuit and is recirculated through the suit com-

pressor, CO2 and odor absorber, suit heat exchanger, water separator, astro-

naut's pressure suit, and the suit circuit solids trap. The suit pressure

regulator will maintain the suit circuit pressure within 2.5 to 3.5 inches -

walter of cabin pressure.

The suit circuit incorporates two compressors installed parallel to

each other. During normal suit circuit operation the #i suit compressor

circulates throughout the suit circuit. A differential pressure switch

is vented to the inlet and outlet ducting of the _I suit compressor. In

the event the #I suit compressor malfunctions, the differential switch

senses the loss of pressure across the _i suit compressor, and in turn

directs power to operate the _2 suit compressor. A SUIT FAN switch is

provided on the main instrument panel, to enable selection of either

compressor.

Oxyaen flowing from the c_ressors passes through the CO2 and odor

absorber. The absorber is divided into individual sections that contain

activated charcoal and lithium hydroxide r_mov_n_ Odors and carbon diox-

ide from the o_aen. Filters, incorporated in the absorber retains char-

coal and lithiu_ hydroxide dust.

4-20

MODONNELL. SEDR 104

Suit circuit temperature, controlled by a suit heat exchanger, removes

_f

heat fran the suit circuit oxygen flowing through the heat exchanger.

Waterflow to the heat exchanger is contro!1_d by a suit temperature con-

trol valve, located on the right console.

A water separator containing a sponge, collects moisture fr_n the

suit circuit o_gen flowing thro,_h the separator. At timed intervals,

the sponge is pne_natically compressed an_ water contalne_ within the

sponge is transferred into a condensate storage tank. A sponge position

indicator is attached to the piston hous4ng of the water separator. As

the water separator piston is in motion, the "PARTIAL" sponge position

indicator light ill,-,_nates. _oth "PAR_.AL" and "FULL" indicator lights

_ ill,_Inate upon c_letion of piston upward travel. As the piston returns

to its original position, both indicator lights extinguish. A sponge

squeeze switch located on the main instrument panel is provide_ to actuate

the water separator prior to the normal progr_d sequence of operations.

Suit pressure and temperature sensors, located in the suit circuit, trans-

mit suit circuit pressure and temperature to the _JlT ENVIROm_T indicator.

The dual faced SUIT ENVIROI_E_T indicator is located on the main panel. The

content of 002 in the suit circuit is measured by means of a calibrated

partial pressure sensor. Pressure measured by the sensor is transmitted

to an indicator marke_ "PARTIAL PRESSURE" located on the main instrument

panel. An indication of excess C_2 in the suit circuit, detected by t_f

CO2 partial pressure sensor, directs electrical power to ill,_nate the

"002 PRESSURE" warning light and operate a tone generator.

During the pre-launch phase, the suit circuit is purged with oxygen

from an external low pressure source. Suit heat ex_b-_er is a_,o sup-

4-21

_ONNELL SEDR 104

plied with a freon coolant, frcm an external ground supply, to pro-

vide suit circuit cooling. The suit circuit oxygen circ-lates _h_O,_b_

the suit circuit, during the suit mode operation. During spacecraft

flight, the pressure within the suit circuit is autc_atically maintained

at approximately 5 psia by the pressure regulator. During the descant

phase, the 21,000 feet barostats actuate to cause 2_V d-c electrical

power to energize the inlet air door relay. Energizing the inlet air

door relay directs power to ignite an explosive squib, which in turn

ejects the snorkel explosive door. (Door is located on spacecraft exter-

ior. ) On descending to an altitude of 17,000 + 3,000 feet, the cabin air

inlet and outflow valves open barometrically. _he suit compressor draws

atmospheric air into the suit circuit through the ejected snorkel door

opening, the snorkel valve and the open cabin air inlet valve. In the

event the cabin air inlet Rnd outflow valves fail to open, the astronaut

may manually open the valves by actuating the SNORKEL pull ring, located

on the left console. Opening of the cabin air inlet valve automatically

switches the envircmmental system mode of operatic_ to the emergency mode,

but the suit circuit c_..A.ressorcontinues to operate to provide suit cir-

cuit ventilation. Also, opening of the cabin air inlet valve directs

electrical power to close the suit circuit shutoff valve, which in tu_:_

mechanically opens the emergency oxygen rate valve. The emergency air

inlet door relay is energized which in turn directs electrical power to

ignite the snorkel explosive door squib and eject the snorkel explosive

door. (This provision insures the ejection of the snorkel explosive door,

in the event the door fails to eject at 21,000 feet.) Air circulating

4:22

_MCDONNffLL SEDR 104

through the suit circuit is vented through the suit pressure regulator

to the cabin, and in turn is vented out of the spacecraft through the

cabin outflow valve. In the event the spacecraft submerges momentarily

following e water land_nS, the ball float in the cabin air inlet valve

and the diaphra6m flapPer valve in the cabin air outflow valve will seat.

Seating of_the valves (snorkel and flapper), prevents water from entering

into the suit circ_ti_and cabin, through the open cabin air inlet and out-

flow valves. Operatic_ of the suit circuit compressor with the snorkel

valve closed will create a vacuum in the flexible ducting, located between

the cabin air inlet valve and suit circuit. The vacuum relief valve,

located in the flexible ducting, will oPen when the pressure differential

between the cabin and flexible ducting is 10-15 inches of water. Opening

of the vacuum relief valve reduces the vacuum to Permit the air inlet

snorkel valve ball float to unseat if the snorkel valve is above the water

_n_s action in turn allows outside air to enter into the suit circuit for

ventilation. During spacecraft submersion, cabin air enterlng the open

vacuum relief valve provides suit circuit ventilation.

The suit emergency control, Figure 4-7, is provided to insure +._

astronaut's survival in the event the cabin and suit environmental con-

trol circuits m-lfunction. Operation in the emergency mode basically

consists of opening the emergency oxygen rate valve, to supply oxygen at

approximately .05 Ibs/min and closing of the suit circuit shutoff valve.

II1,_uation of the 02 EMERG light an_ the mo_-_ut of the EMERG 02 rate

handle to _ position_ indicates emergency mode of operation.

4-23

©

When operating in the normal mode, (See Figure 4-6), during normal

orbital flight, the emergency oxygen rate valve is closed, the suit cir-

cuit shutoff valve is open, suit compressors are operative, and the suit

circuit pressure regulator is controlling oxygen flow to the suit circuit.

The emergency oxygen rate valve remains closed as long as suit circuit

pressure remains at approximately 5 psia, pressure. In the event the

suit circuit pressure drops to 4.0 + "i paid, the rate valve internal.3

aneroid extends, to offseat a poppet, and allows oxygen from the oxygen

supply to flow through +_-_herate valve and into the suit circuit. _e

extension of the rate valve aneroid, due to low pressure, actuates a

14m4t switch that provides electrical power to energize the suit circuit

shutoff valve solenoid and the suit fan cut-off relay, illuminate the 02

_ERG light, an_ operate a tone generator. Energizing the suit fan cut-

off relay removes the IISV a-c electrical power to operate the suit cir-

cuit compressor. (At an altitude of 17,000 + 3,000 feet, the cabin air

inlet relay will open. Opening of the cabin air inlet relay de-energizes

the suit fan cutoff relay. _he de-energized suit fan cutoff relay routes

power to the _i suit circuit compressor. If the _I suit circuit compressor

fails to operate within 12 seconds, the suit fan selector relay will ener-

gize and allow power to be directed to the suit fen cutoff relay and then

on to the _ suit circuit compressor.) Energizing the shutoff valve

solenoid releases the shutoff valve shaft arm, and mechanically moves

the _ 02 handle, right console, to the _ position. Movement of

4-25

_N_mA.L . SEDR 104

the _ 02 h_dle _echanicall_ actuates the _nergency oxygen rate

valve to the open positi_. With the _rgency oxygen rate valve open

and the suit circuit shutoff valve closed, o_gen from the oxygen supply

flows into the pressure suit and is discharged through the suit pressure

re_,lator relief valve.

Actuating the EMERG 02 b-ndle to the NORM position resets the shut-

off valve to the open position, the emergency oxygen rate valve to the

close position, starts suit compressor operation, extinguishes the 02

light, and in turn switches the suit circuit operation to the suit

norm-i control mode.

_e emergency mode is also automatically selected during spacecraft

!Anding phase, when the spacecraft has descended to an altitude of 17,000

feet. At 17,000 feet the cabin air _nlet valve opens. Opening of the

cabin air inlet valve actuates a 1_m_t switch that provides electrical

power to operate the suit circuit co_ressor and close the shutoff valve,

which in turn mechanlcal_ opens the emergency oxygen ra_e valve. Au

inlet power switch, located on the main instr_aent panel allows operation

in the suit environmental control mode in the event the cabin air inlet

valve prematurely opens (See Figure _-6). Premature Openln@ of the cabin

air inlet valve deactivates the cabin fan and closes the suit circuit

shutoff valve which in turn opens the emergency ox_Een rate valve. The

suit circuit is now operating in the emergency mode. To initiate tran-

sition back to the suit mode, the inlet power switch is placed in the

BY-PASS position. With the inlet power switch in the BY-PASS position,

the cabin fan is activate_ (See Figure _-5) and the suit circuit shutoff

valve is deactivated. _ E_R@ 02 h_la right han_ console, is now

4-26

MODONNfLL SEDR 104

placed in the NOF_ position; placing of the _ERG 02 handle to the NORM

position opens the suit circuit shutoff valve ana closes the emergency

oxygen rate valve. The environmental control system is now operating

in the suit environmental control mode. To prevent snorkel door separa-

tion upon premature opening of the cabin air inlet valve, the emergency

inlet air door relay is intercc_uected to the antenna fairing separation

relay during descent. After opening of tb_ cabin air inlet and outflow

valves, the inlet power switch is placed in the N01_L position.

4-12. OX_G_ SUPPLY

Durin_ the pre-launch phase and prior to installation of the entrance

hatch, primary and secondary oxygen system shutoff valves are manually

opened, by ground crewmen, to activate the oxygen supply. Opening of the

shutoff valves 3 Figure 4-8, provides oxygen to the cabin pressure control

valve, suit pressure regulator, suit e_-_rgencyoxygen rate valve end the

suit circuit water separator solenoid valve.

During operation, when the prim__v_oxygen bottle pressure drops below

approximately 200 psig, due to near depletion of the primary oxygen supply;

the secondary oxygen supply line pressure will override the primary oxygen

pressure and continue to supply the environmental system with oxygen.

Audible en_ visual means ere provide_ on the Main Instrument Panel to warn

the astronaut of a dlm_nlshing oxygen supply. As the secondary 02 supply

decreases to 6500 psi_ the secondary o_gen supply pressure transducer/

activates the "02 QUAI_XTY" telalight and the tone generator. A quantity

indicator gage, located on the main instrument panel_ is provided to inai-

4-27

"_ONNELL SEDR 104

PRESSURESUIT

C,RCO,T, CIRCU,TFLOW FLOW

GROUND TESTSHUT-OFFVALVE 2,4.VD-C

CABIN PRESSURECONTROL VAWE

__ 24V D-C

TO WATER =1SEPARATOR

SUITPRESSUREREGULATOR EMER_

OXYGENWATERSEPARATOR RATEVALVESOLENOID VALVE

PRESSUREREDUCER

MANUALSHUT-OFF REDUCER

PSIG) WARNINGLIGHTSSWITCH DIM

CHECK CHECKVALVE BUS1 CrtX/"J_VALVE 24V

MANUAL DCSHUT-OFF BRIGHTVALVE

REDUCER _ EL_

{7500-100PSIG) SERVICE SERVICE I|'VALVE VALVE

_ou,_ T BLIGHT

SIGNALLIGHTSTEST

SWITCH i BUS

/_24VDC

A

TONE _ JI BUS

_ V0

PRESSURE PRESSURETRANSDUCER TONEGEN_ATORSWIT,_H

_A__ BUS

24VDC

OXYGENSUPPLY

INSTRUMENT QUANTITYNOTEPACKAGE"A" INDICATOR

SCHEMATICDEPICTSOXYGEN SUPPLYACTIVATEDWITH PRIMARYOXYGEN SUPPLYBEING UTILIZED (MAIN PANI_L)AND SECONDARYOXYGEN SUPPLYIN RESERVE.

FMI8-27A

Figure 4-8 Primary and Secondary Oxygen Supply

4-28

"__NNfflA.t, SEDR 104

care remaining oxygen supply. Two transducers, primary and secondary

supply, are provided to enable telemetering of oxygen quantity remaining.

-13. coo o

During pre-launch, cabin and suit circuit cooling, (Figure 4-9) is

achieved by supplying freon (F-II4) through the ,_ilical connector and

into the cabin and suit heat exchangers. _he freon coolant evaporates in

the cabin and suit heat exchangers and is discharged overboard _h_'ough the

environmental system steam vents, located in the 1,_ge pressure bulkhead.

Prior to launching, the freon coolant supply is discont4n_ted. When the

spacecraft reaches appro_-_tely 115,000 feet altitude, cabin and suit

circuit cooling is achieved by water evaporation, that occurs within the

suit and cabin heat exchangers.

Water from the water coolant tanks is supplied through the temperature

control valves, to the suit and cabin heat exchangers. Oxygen, _ the

suit circuit is utilized to pressurize both water coolant tanks. 0xTgen

pressure moving each tank diaphra_a, forces the water supply out of the

tanks at a rate dependent upon the position of the temperature control

valves. _ne temperature control valves control the amount of water entering

the heat exchangers, and in turn controls cabin and suit temperatures.

_-e steam flows out +_ou6h the steam vents, located in the 1-_ge pressure

b,,1_head. A dual faced heat exchanger temperature indicator, and warning

light is provided on the main instrmaent panel to inaicate temperature con-

aitions in the cabin and suit heat exchangers. An excessive amount of

water flowing through the cooling circuit is detected by sensors attached

4-29

_MCDONNELL SEDR 104

PACKAGE "A" • L[GHT

HEAT EXCHANGER TEST EXCESS

SENSOR TEMPERATURE DOME TEMPERATURE SW[TCH HZOSENSOR INDICATOR

/ TELELIGHT24V D-C

TONE _ (MAIN PANEL)GENERATOR

I_ 'll OFF

SWITCH

*_ 24V D-C

BRT

_'ARNINGLIGHT SWITCH

TO PRESSURESUIT

SWITCH NO. 2 SUIT

SENSOR TEMPERATURE j CIRCUITSELECTOR FLOW

WATERCOOLANTTAN KS

CABIN TEMPERATURE SUIT TEMPERATURECONTROL VALVE CONTROL VALVE

ORIFICE

FREON CHECK FREONVALVE INVERTER COOLING CHECK

CABIN HEAl DUCTS VALVE

EXCHANOERii/r SO,THEATDOME ::_ EXCHANGER'

SENSORS ::i CABIN ) _ DOME SENSORS

CIRCUITIFLOW TQ

PRESSURE' HEAT SUIT

OUTLET SENSOR CABIN 115V D-C MAIN STBY MAIN EXCHANGER:. Cr_N _J,L LI1H INVERTER INVERTER INVERTEREXCHANGER:_, =V.A.2SOV.A.'50V.A.

L_,RGE PRESSUREJBULKHEAD CAPSULE (FREON SUPPLIED DURING

,NOTE GROUND OPERATION ONLY)

SCHEMATIC DEPICTS COOLING CIRCUIT OPERATION DUR- _ OXYGEN FLOW

ING NORMAL CAPSULE FLIGHT _i SUIT CIRCUIT FLOW.................. PMIS-14AGB

Figure 4-9 Cooling Circuit

4-30

MCDONNELL. SEDR 104

to the cabin and suit heat exchangers directing electrical power to

F ill_.Inate the "EXCESS _0" warning light and also operate the tone

generator. The astronaut must then position the cabin or suit tem-

perature control valve to a warmer setting to prevent wasting coolan_

and to achieve efficient operation of the heat exchanger.

tt..l_.PRIMARY AIEDSECOI_DARYOXYGEN BOTTLES

The primary and secondary spherical shaped oxygen bottles are

located beneath the astronaut's support couch adjacent to the spacecraft

conical section and large pressure bulkhead. Each bottle has a capacity

of 4 pounds oxygen, stored unaer a 7500 psig pressure at 70°F t_.Terature./

Servicing of the ax_gen bottles is accomplished thr_h a quick disconnect

filler coupling.

4-16. SUIT CIRCUIT PRESSURE REGULATOR

_e suit circuit pressure regulator, Figure _-i0, is provided to regu-

late oxygen pressure to the suit circuit an_ to replenish suit circuit

oxygen consume_ by the astronaut, or lost through leakage. The regulator

is a d_mand type diaphragm operated regulator that controls suit circuit

pressure in reference to cabin pressure. Suit circuit pressure is main-

rained approximately 2.5 - 3.5 inches of water below cabin pressure during

normal system operation, under ideal (no cabin leakage) conditions. Cabin

pressure is sense_ on the upper side of the regulator control diaphragm and

4-31

_ONNELL SEDR 104

//!t

\.

-\

SUIT PRESSUREREGULATOR

CABIN VENT PORT

CONTROL_ _. , j .... "

OXYGEN : I 0 0 0

PORT _ |

RELIEF -/ .DIAPHRAGM

FMI8-25A

Figure4-I0SuitPressureRegulator

4-32

_M_CDOItlNELL SEDR104

suit circuit pressure is sensed on the lower si_e of the diaphragm.

..... _he regulator also contains a resilient type diaphragm +.hAtis use_

tO relieve excessive suit circuit pressures. Two aneroids are pro-

vtdea to shut off cabin vent port of regulator in the event cabin

pressure _ecreases below _.6 + .2 psia. In the event of cabin leak-

age_ not deoreas:Lug below _.0 +_:21pala I the cabin pressure control

valve will open to replenish cabin pressure to 5.i + .2 psia. Make.i

up oxygen from the cabin pressure control valve will flow _hrongh the

suit circuit and OUt t.hro,,_h the suit pressure re_,!Atc_ relief valve

and into the cabin. At this time, suit circuit pressures will exccc:1

cabin pressures aue to pressure differential (suit above cabin) re_,,_ed

to open the suit circuit pressure regulator relief valve.

_ing normal ascent, cabin pressure decreases, and the regulator

relief dia_ relieves WAit circuit pressure to within 2 - 9 inches

H20 above cabin pressure. During normal orbital flight, the control dia-

phra_ will regulate suit circuit pressure in relationship to cabin pres-

sure. An increase in cabin pressure will act on the diaphra_ to unseat

a poppet valve and allow suit circuit pressure to increase to within 2.5 -

3.5 inches of H20 below cabin pressure. In the event cabin pressure de-

creases below _.6 + .2 psia, the aneroids will extend an_ close off cabin

vent port of regulator. Two 60 co/rain bleed ports provide oz_en to pres-

surize the reference ch--_ers ana permit the regulation of suit circuit

pressure to 4.6 + .2 psia. Two anerotds an_ two bleed ports are prov£aed

to insure redundancy in the event either aneroi_ or either bleed port

fails to function. Descent operation of the regulator is the stoneas an

increase in cabin pressure during noa_ml orbital flight.

4-33

_MCDONNELL SEDR 104

4-17. CIRUT

q_e suit circuit shutoff valve, Figure 4-11, is designed to shut off

oxygen flow to the suit environmental circuit accessory components, when-

ever the suit circuit i;s operating in the emergency mo_e. be shutoff

valve, spring loaded to the close position, is latched in the open posi-

tion during normal suit circuit operation. Valve is maintained in the

open position by a solenoid controlled detent pin engaged into the valve

spoon arm. A mlcroswlt,-_,depressed by the valve arm, completes the

solenoid circuit when _ valve is latches open. Opening of either the

emergency o_gen rote walve or the cabin air inlet valve directs an elec-

trical signal to energi:_ the shutoff valve solenoid. Energizing the

solenoid retracts the detent pin and allows the valve spring to rotate

the valve spoon to the ,:loseposition. Closing of the valve, %_,_h an

inter-connectlng l_ka_._. The shutoff valve is mechanically opened by

the EMER02 control hau(tle, locate_ on the right-hand console. _he

shutoff valve is interconnected to the emergency rata valve, so that

when the emergency rata valve closes, the shutoff valve opens.

-18. oxY

_he emergency o_gen rata valve, Figure I_-12,is provided to supply

a re_,IAtad mnount of cc_Een directly into the astronaut's pressure suit,

in the event malfuncti_l occurs in the suit circuit operation. _e rata

valve is designed to OlX_.reteaut_tieally an_ contains provisions for

manual operation, q'ne_mlve, closed _uri_ nc_ml suit circuit operation,

contains an aneroid that senses suit circuit pressure. Whenever suit cir-

4-34

©_MCDONIOIELL SEDR 104

SUIT CIRCUIT SHUTOFF VALVE

/f--

DENT PIN

VALVE SPOON ARM

.ADJUSTMENT

MICROSWITCH (CLOSED POSITION)(NORMALLY CLOSED)

HOUSING

VALVE SPRIN(

.S-

VALVE SPOON

FM18-29

Figure 4-11 Suit Circuit Shutoff Valve

4-35

lUNELL SEDR 104

/_/;;"_L?\/. b_\/ i "_.,<:_k_"k,

•, _ \ l/ If s! /

"-.,_ i !

IEMERGENCY 0 2 RATE VALVE

DIAPHRAGMCHAMBER OXYGEN SUPPLY

TO SUITCIRCUIT

INLETDUCT _1 -,_{iL//dl_-.\'_'.<_-.\\\\\\\\_-k-_-_ /- s_nuAcCONTROL

k./.<_, .---,o,----7___co,,,o,sv,,,_.o,,°--"1_:7.; ; ', L2"

ANEROI_ __

FM18-24

Figure 4-12 Emergency O2Rate Valve

4-36

_M_ODOI_IN|LL SEDR 104

cuit pressure drops below _.0 + .l psia, the aneroid extends to offseat a- .3

_- spring loaded poppet and allow oxygen to enter the diaphragm ch-m_er.

The pressure in the diaphra_ ehAm_er increases and f_11y strokes the

poppet, allowing oxygen to flow into the astronaut's suit at a fixed

flow of .0_9 to .051 #/mln. Simultaneously with the offseating of the

poppet, e control switch is actuated throu_ a lever mechanism, and di-

recta electrical power to close the suit circuit shutoff valve, ili,_I-

hate the 02 EMERG li@ht, and stop suit circuit compressor operation during

orbital flight. Suit circuit shutoff valve is interconnected with emer-

gency oxygen rate valve. _herefore, closing of the shutoff valve actuates

the emergency c_Een rate valve manual control shaft to close off oxygen

flow to valve poppet _nlet. O_gen then flows directly into suit circuitf

through the valve aneroid e_Am_er.

_gency oxygen rate valve may be opened m-nually by selecting

position with EMER3 02 control h_ndle. Whenever the _ 02 cantrol

handle is moved to NORM, the suit circuit shutoff valve opens and emer-

gency oxygen rate valve closes.

1_-19. _ CIRCUIT COMPRESSORS

_he suit circuit enviro.._entalcontrol system utilizes two electric

motor driven, single-stage, centrifugal compressors (See Figure 4-6).

One c_.nressor is a standby compressor used in the event of normal com-

pressor failure. If The normal co,_ressor fails, the standby compressor/f

is activated by a pressure differential switch which directs power to the

standby compressor electrical connections. _he only time the suit com-

pressor is inoperative is during orbital flight when the astronaut is

4-37

_M_NItI|LL SEDR 104

utilizing oxygen from tl_eA-_rgency oxygen rate valve. When supple-

mentary oxygen from the e_ergency oxygen rate valve is being used

below 20,000 feet, the _suitcircuit compressor will continue to operate

to circulate ambient ai:¢to She astronaut.

4-20. C02AND ODOR_ER

The C02 an_ o_or ab;gorber,Figure 4-13, is provided to remove astro-

naut emitted odors and ,-arbondioxide from the suit circuit. The absorber

is basically a ,-_talcannister dlvide_ into two sections. _he inlet sec-

tion contains activated charcoal that r__m_ovesobJectlonal odors from the

suit circuit oxygen. T.ithiumhydroxide, locate(1in the center sections re-

moves carbon dioxide. !_e outlet section is an e_t filter, provided to

retain lithium hydroxide in the cannister. _he charcoal and lithium hy-

droxide granules are ca_resse4 by a spring force. _he useful life of

the C02 and odor absorber is forty-four hours.

4-21. SUIT CIRCUIT _E_T EXCHanGER

The suit circuit heat exchanger (Figure 4-14) is of a plate fin

construction with rect_isr offset fins, double _lwlch, one pass on

the oxygen side and two pass, single sandwich on the water side. The

function of the heat ex,'_er is to cool the gases circulating +_rough-

out the suit circuit. 1_aterfrom the water cooling tanks is routed to

the inlet side of the heat exchanger which contains a high density woven

felt pad. The function of the felt pad is to evenly distribute the water

÷_ough the core of the heat exchanger. As water passes throu@h the felt

padj it comes into contact with the heat tra-afer surfaces on the water

4-38

.m4CDONNELL SEDR ]04

TO SUIT CH_CUIT

HEAT EXCHANGER

CO 2 AND ODO

SPRING

FROM SUIT Ch_CUITCOMPI_SSOR

LITHIUM HYDROXIDE

FMI8-23 A

Figure4-13CO 2and Odor Absorber

4-39

NNELL SEDR 104

/

//

!\\

/

SUIT HEAT EXCHANGER

SECTION SHOWING OPERATION

FMI8-22

Figure 4-14 Suit Heat Exchanger

4-40

MCJDg_NNELL $EDR 104..

aide of the heat exchanger. The water evaporates and the steam is

f vented overboard.

_..22. WATER _ARATOR

_he water separator, Figure _-15, is provided to re_ve condensate

from the suit circuit oxygen. The separator _ontains a sponge that col-

lects liquid frnm the oxygen passing through it. The liquids are squeezed

from the sponge and deposited into a storage tank. Once every 30 minutes,

for a duration of 30 seconcls, the spacecraft progra_r supplies electrical

power to energize the water separator solenoid valve. Energizing the nor-

reallyclosed solenoid valve opens the valve and directs c_ygen from either

the primary or secc_y supply to the pistan stem ana the piston plate

chambers. A sponge squeeze switch, located on the main inset panel,

is provided to permlt actuation at a_y time.

_he piston raises the sponge out of the suit circuit oxygen flow and

compresses the sponge against the separator housing plate. Water squeezed

out of the sponge is forced into the c_densate tR--k. The water separator

solenola valve is de-energizea and the solenoi_ valve closes. Oxygen be-

low the separator pisto_ is vented to cabin through +he separator solenoid

valve. Ox_en above the piston, entrapped by a check valve, forces the

piston down, thus returning the sponge into suit circuit oxygen flow.

During squeez_ operation, suit circuit oxygen flow will not be affected,

as oxygen will continue to flow +_ougb area normally occupied by the sponge./

A sponge position 1_cator is attached to the base of the water separator.

"PARTIAL" and "I_JLL"travel indicator lights used in co, unction with the

4-41

_MODONI_IELL SEDR 104,

-CHECK VALVEI

FROM SUiT

__) C'_:U'T

1TO

CONDENSATE

__ TANK

_l SPONGE

_ CHECK_LVF

MAGNETS_ OXYGENSUPPLY

INDICATORLIGHTSWITCH

NDICATOR

PISTON_ LIGHTSWITCH

WATER SEPARATORiNDICATOR

r-VENT]

SOLENOID=_ j_ /

4 FROMOXYGEN SUPPLY[

WATER SEPARATORSOLENOID VALVE

,FM18-28JA_

]_gure 4-15 Water Separator

4-42

"_ONNma.i. SEDR 104.

position indlcator_ are loea_=a c_ the Main Instrument Panel, Both

"PARTIAL" ana "FULL" indicator lights il1,_-_ate upon completion of

piston upward travel. As the piston returns to its original posltlc_

both indicator lights extinguish.

4-23. SOT.TnSTRAP

The suit circuit solids trap, Figure 4-16, is located in the pilot's

suit oxygen outlet duct. _he trap consists of a _0 m_cron mesh screen

filter which incorporates an integral bypass to insure operation in *_

event the trap would becu_e choked with collected solids.

4-24. CABIN _R_T EXCHANGER

The cabin heat exchanser (Figure 4-17), cools the cabin gas in the

same marine._ as the suit circuit heat exchanger. Internal structure is

the ssme as the suit circuit heat exchanger.

4-25. WATER C00_ TARES

Two water coolant tanks, (Figure 4-18), are provide_ in the environ-

mental control system. _he larger of the two water tanks, located directly

below ¢_e astronaut's couch, contains forty pounds of water. The second

tank containing nine pounds of water is located to the right of the astro-

naut's right knee. Water is displaced from each tank by oxygen from the

suit circuit acting upon the gas side of a rubber bladder which separates

the coolant water from gas. Water is d_rected to two manual control valves

which control the water supply to the suit circuit and cabin heat exchangers.

The larger water tank also provides the astronaut with a source of dr_-k4-_

water.

4-43

_NELt. __.f_.SEDR 104_ .!

PRIMARY FLOW

---- SECONDARY FLOW

1_XYGEN

BY PASS VALVE -

SCREEN FILTER ASSY.

ro SUITCIRCUIT TRAP

FMI8-21

Figure 4-16 Suit Circuit Solids Trap

4-44

IrlIICDONNELI. SEDR 104

CABIN F

INVERTER

COOLINGDUCT

LINE

COOLINGDUCT

EXCHANGER

II i CABIN FAN

_'. , CAPSULE, _'_'VERTICAL !WEBI ELECTRICAL CONNECTOR

FMIS-20

Figure 4-17 Cabin Heat Exchanger and Fan

4-45

_MCDONN£LL SEDR 104

,/

//

!

_TANKBLADDER

NLET--

WATER OUt LE'[

BLADDEF

PRESSURE INLET

TO POSITION UNDERNEATH ABORT HANDLE

(ASTRONAUT DRINKING WATER)

WATER OUTLET

FMI8-19 A

Figure 4-18 Water Tank_

4-46

_ ,_O_NNBtJ. SEDR 104

k,-26. CABINPRES,_JI_C(_J_OL VALVE

_he cabin pressure control valve, Figure 4-19, is provided to maintain

cabin pressure to 5.i + .3 psia. The control valve contains two aneroid_

that sense cabin pressure. Whenever cabin pressure drops below 5.I + .3

psia, the anerolaspartiallyexpand an_ ,reseat the spring loadedmetering

pins, which in turn permit oxygen to flow into the suit circuit. The suit

pressure regulator senses the increase in pressure, and relieves suit cir-

cuit gas to the cabin. Directing oxygen flow through the suit circuit

provides constant purging of suit circuit. When cabin pressure increases

to 5.i + .3 psia the aneroids contract, allowing the metering pins to seat

and shut Of_f t_h_ oxygen flow. In the event of cabin dec_npression, or

+ .2whenever cabin pressure drops below 4.0 . .I psia, the aneroids i_111y ex-

pand and seat against the inlet port. This stops oxygen flow and reserves

the re_aining oxygen supply for the suit circuit. Two sneroids are pro-

vided in the valve to insure operation in the event that one aneroid fails.

A manual control is also provided to enable cabin repressurlzation. Act-

uation of the REPRESS "T" handle offseats a spring loaded poppet in the

valve and allows c_gen to flow directly into the cabin. REPRESS 1_,.

b_n_le Rhould then be pushed in, following cabin repressurization, to

stop repressurization flow.

_;-27. CABXN PRESSURE l_-'7.'rg_ V._Vg

The cabin pressure relief valve, Figure _-20, aut_Atically relieves

cabin pressure relative to _-hient pressure during launch, orbit, re-

entry and landing phases. In the event of a water landing, the valve

4-47

_MCDONNELL !SEDR 104

CABIN PRESSURECONTROL VALVE

TO SUITJ_ CIRCUIT

I FROM OXYGENi SUPPLY

iSPRIN( ro SUITCIRCUIT

FM18,-18

Figure 4-19 Cabin Pressure Control Valve

4-48

MCDONNELL SEDR 104

CABIN PRESSURERELIEFVALVE

AMBIENTSENSING G CALIBRATEDSPRING

$Et, ISINC

_ CHAMBER

METERINGVALVE

CABINAIRFILTER

CHAMBER

ABIN

DIAPHRAGMCHAMBER

CABIN AMBIENTPORT_ CONTROLDiAPHRAM ARMCHAMBER

ORIFICE

)RIFICE

POPPETVALVE- KVALVECONTROLSECTION

z

CARIN _\ DIAPHRAGM

CABIN

AMBIENT ....

POppETVALV VALVE

SCREEN

FM18-17

Figure 4-20 CabinPressure Relief Valve

4-49

M_O_NNE" " SEDR104

incorporates provisions to keep water from entering the cabin. The

valve also features me_s for manually decompressing the cabin. _ae

cabin pressure relief valve consists of a calibrated spring control

section and a poppet valve control section. The calibrated spring

control section incorporates A-_ient and cabin sensing ch-_ers se-

parated by a sensing diaphragm, spring loadea metering valves and cali-

brete_ springs. The p_pet valve conf_ol ch_-_e_ incorporates a manual

control arm, • check valve, poppet stem orifices_ spring loaded poppet

valves, poppet _Am_er _kiaphragms and poppet chambers.

During launch, the cabin pressure relief valve will relieve cabin

pressure to ma_ntaln a ]_ressuredifferential (cabl_._ient) of 5.5 psia.

Cabin gas will be vented, thro,,_ t___poppet stem orifices, into the

poppet valve cb_-_er, q_in gas will also be vented, through the cabin

air filters, into the cabin sensing _ham_er. Ambient gas will be vented,

via the m_ient pox_, _,ttOthe Ambient seuaIDg chamber. _he callbrate_

springs are designed to respond to differential pressures in excess of

appro_mRtely 5-5 psi (cabin/ambient). When the pressure differential

between the cabin sens_,_ chamber ena s_ient sensing ch-_er exceeds

appro_mAtely 5.5 psia (_cabi_lent)_ the calibrate_ spr_s will re-

tract. The metering v_es will then be _ from their seats, a1_z_

differential pressures _ excess of _._ psia to escape %hr_ the _-_ient

port. Due to the -_i_tt port being 1,_ger than the poppet stem orifices,

the dissipation rate of the excessive differential cabin pressure (inside

the poppet valve chsmbers) will exceed the rate of build-up in the poppet

valve _-m_ers. _h_S _11 m_aentarily cause the cabin pressure to be

4-50

_c_l_mll.a.. SEDR 104.

greater than the poppet valve chamber pressure. _he greater cabin pres-

sure will act ag_n-t the cabin disphra_n, unseating the poppet valves.

_e poppet valves will then aid in relieving excessive dii_erential pres-

sure. If the astronaut e_ecutes a manual aeco_resaion of the cabin,

the check valve acts as an exhaust for poppet valve chm_er pressure.

During orbit, the cabin pressure relief valve will prevent cabin

pressure build-up in excess of appro_m_tely 5.5 psia. Cabin pressure

in excess of approY_tely 5._ psia will be exhausted to the outside at-

mosphere. Upon re-entry, when the -u_lent pressure becomes 15 inches of

water greater ÷_-n cabin pressure, the poppet valves will c_-_ce to open

allowing _,_ient pressttveto enter the cabin. Valve relieving operations

will then be s_m_!a_ to +_ose during launch. In the event the spacecraft

makes a vater lan_, the poppet valves w_1 not open until water pressure

exceeds cabin pressure by 15 inches of _ater.

4..28. SIlC_T. _ DIAPHRAGMFLAPP_ VALVES

The cabin inlet a_ snorkel valve and the cabin ontflow diaphra_n

flapper valve act as water check type valves. During the _--_ug an_

post-landi_ phases, (often reaching a pressure altitude of approxi-

mate1_17,000feet) -m_ient air is clrculatea +_ough the valves. In

the event the valve parts vere under water, the valves voul_ seat an_

prevent water _n entering the cabin.

_._. CABIN A_R_ VALVE

_he cabin air inlet valve, Figure _-_1, provides ventilation and

cooling for the suit circuit and cabin _uring landing an_ post-landin_

4-5]

_MCDONNELL SEDR 104

i

// /

/

/

t 7/ / /

CABINAIRIINLETVALVE

LOCKINGSPRING

MANUAL CONTROLARM'-_ SPRING

RELEASESTOP RO SWITCHES

RELEASELINK

VALVEARM(CLOSED

ADJUSTMENT(OPEN)

SMALLPRESSURESPRING BULKHEAD

VALVESPOON

AMBIENT _ .

TO SUIT _J_ '_CIRCUIT v_ _ I

FMI8-16

Figure 4-21 Cabin Air Inlet Valve

4-52

M@DONNRLL SEDR 104

phases. It is a spring loaded close, spoon type valve and is baronetrl-

/ cally contro_d. Prior to launch, t_ valve is manually latched closed

so that one mechan_mn spring loaded detent pin rides on the large dia-

meter of the aneroid plunger (m_--_ allowable p._1 to set detent pin

in five (5) pounds); and the valve arm is engaged by the release llnk,

which is engaged by the spring loaded aneroid loc_ug pin. During launch

the aneroid expands due to decreasing cabin pressure, and forces the

aneroid plunger down. The valve mechanism detent pin then slips off

the plunger large dismeter onto the plunger _11 _ismeter.

During the !A-d, ing phase, when tb_ spacecraft descends to an altitude

of appro_mately 17,000 + S, O00 feet, the aneroid retracts as cabin pres-

sure increases. Retraction of the aneroid moves the aneroid plunger up-/

ward, engaging the detent pin against the plunger larger di_eter, which

in turn compresses the aneroid locking pin spring. This action raises the

locking pin from release link and allows spring londed valve to open. _he

valve arm is attached to valve _hmft and moves with closing thereby dis-

engaslng _ioro-switches. Disengagement of m_cro-switches directs elec-

trical power to close the suit circuit shutoff valve, which in turn opens

the emergency o_en rate valve. A _-,,-_ control arm is provided to en-

able waive opening in the event valve fails to open at specified altitude.

Actuation of the ma_aal control am, me_,_1 cal_, contacts the lock_

pin spring an_ disengages locking pin from release link, allowing valve

S tO open. The valve must be _s_uall_ reset to the closed position. Open-

ing of the valve enables suit compressor to draw ==_ient air into suit cir-

cult to provide sult circuit and cabin ventilation.

4-53

_O_lg/J. SEDR 104.

cabin air _Atlet valve is basically of the seineconstructlo_ and

functions in the s_ne manner as th* cabin air inlet valve.

_-30. yAC_M _.r_ VALW

The vacuum relief v_lve, Figure 4-22, is designea to open at a pressure

differential of I0 to 25 inches of water, to provide suit circuit ventilation

_henever the inlet snor]_elvalve closes (ball float seats). The relief

valve is located in the flexible d_wtlng, between the cabin air inlet valve

and the suit circuit i_Let duct. In the event the spacecraft sub_ges

momentarily, following a water landing, t_ snorkel valves ball floats

will seat (close) an_ p:ceventwater from entering into the suit cireuit

and cabin. The sperati,_ of the suit compressor and the closed air inlet

snorkel valve will crea'_.ea vacuum in the suit circuit air inlet duet

(flexible ducting). Wh,m cabin pressure exceeds the flax duct pressure,

by i0 - 15 inches of wa'_r, the vacuum relief valve wall open. As the

valve opens, cabin presJmre acting c_ the valve poppet surface will be

great enough to hold t_: valve open until the pressure differential (be-

tween cabin and auct) 1,5apprn_mAtel_ two inches of water or less. Sult

circuit ventilation is ]_rovided by the cabin air, entering the opened

vacuum relief valve, w_:never the inlet snorkel valve ball float is seated

(closed). Also, the Ol_mi_ of the relief valve removes the vacuum in the

flex duet to enable the snorkel valve b.ll float to unseat (open) whenever

the snorkel valve is above water.

4-64

MCDONNELL SEDB 104

VACUUM RELIEF VALVE

CFRING L ,_SEAL I ,_--MOUNTING BOLT

x VALVE DUCT

FLEX BLE •DUCT_ _ "

_' ',--i j,,_9T

FMIE,-15

Figure 4-22 Vacuum Relief Valve

4-55

SECTION V

f-/

STABILIZATION CONTROLSYSTEMS

TABLE OF CONTENTS

TITLE PAGEf

Automatic Stabilization

Control System ............................... 5-3

System Operation ........................... 5-12

System Units.. ................................. 5-20

Reaction Control System

_iiiiiiiiiiiiiiii System Description ......................... 5-26

System Operation ........................... 5-30

System Units ................................... 5-38

s Horizon Scanner System

_::::: System Description ......................... 5-41::::iiiii!!!iiiiii_iii_iiiiiiiiiii_i_iiiii

_::iliiii!ii!iiiiiiiiiiiiiiiiiiii_:_: System Operation .......................... 5-4 9

5-1

NNELL SEDR 104

, o _, o /

/

°/I( -<-. ,,R. _o -2-/\", \',/ !_

/ .,'-. ¢ _ }

o zi jt _ / _o>- _ ......0 --!

o _ .

u

-;. \. ? --/

_ ",, \\ " 7

\ "%.<Q..--// 0

_'-

> ">... "--. I, /

FM18-125/

Figure 5-1 A.S.C.S. Component Location

5-2

SEDH 104

V. _ZABILT_7.ATIONCONTROLSYS'_S

5-L GE_ERAL

Stabilization of the spacecraft is accumplished by the Aut_ntlc

Stabilization Control System in con_unctlon with two sub-syst*m-, the

Horizon Scanners --_ the Reactic_ Control System. _-ese systems estab-

lish an_ maintain a stable platform with four basic automatic mo4es;

Damper, Orientation, Attitud_ Hold and Re-entry. In addition, a vi_-!

indication of Few, roll, and pitch attlt_e is provlde_. _e follo_

paragraphs describe the individual systems an_ functions involved.

5-2. AUT_TI c STAB_TZATI_ C_mOL SY_

5"3. SYS_ DESCRIPTION

The Aut_-mtic Stabilization Control System (ASCS) is c_osed of a

Directional Gyro, Vertical Gyro, .05g accelercmeter switch, Rate Gyros

(yaw, roll an_ pitch), and an Amplifier Calibrator Unit. Location of

the individual components within the spacecraft is shown in Figure 5-1.

mhree switches are provided in conjunction with the ASCS. _e SELECT-

NO_ switch, FLY-BY-WIRE - AUX DAMP switch and the GYRO CAGE, _-GYRO

SLA_E switch. With __e _SLECT-NORM switch in the NORMposition, stabili-

zation is acc_nplished in a eumpletely automatic m---er, requiring no

assistance from the astronaut. With the SELECT-NORM switch in the SELECT

position and the FLY-BY-_r_RE-AUXDAMP switch in the FLY-BY-WIRE position,

the automatic feature is disable_ and 24V d-c power is connected to _h_

Fly-By-Wire limit switches on the astronaut's control stick. A F_ _RUST

S_.LECTswitch with YEW & HIGH an_ LOW ORLY provides the astronaut with two

5-s

_OItlNIILI. SEDR 104

•.h_ust selections for ft_l conservation purposes. Stabilization is

acocmpllshed through an electro mechanical arrangement (See Figure 5-9)

by movement of the astronaut's control stick in the desire_ plane. Low

and high thrust actuati¢_ occur at approY_m_tely 30% and 75% of full travel,

for yaw, pitch, or roll. The AUX DAMP position disables both the auto-

matic and fly-by-wire function, permitting rate damping as a singular

feature. _he GYRO switch is s three position switch incorporating e CAGE,

FREEr and NORMAL position. In the CAGE position_ the Attitude gyros are

mechanically caged and the Horizon Scanner slaving function is disabled.

In the _ position_ the Attitude gyros are uncaged; the Horizon Scanner

slaving function remains disabled. _he NORMAL position uncages the attitude

gyros and permits Hariza_ Scanner slaving.

ASCS

_he following paragraphs, 5-5 an(1 5-9, describe the ASCS sequential

operation under normal _ad abort conditions. Figures 5-2, 5-3, end 5-4

are provided for cl-_ity and should be followed closely in conjunction

with the text concerning the various moaes of operation.

5-5. N0mL QUENCn

In Figure 5-2_ the pip'ogressof a normal orbital mission is shown

divided into eight phasellappropriate to the following discussion.

_le ASC8 is in the "]_ady" status prior to separation of the escape

tower, its _T0S are runI_ng and all circuits except the final 12 OUtput •

relays are fully energize_d. Phase (A)_ involving _To slaving to the HO-

5-4

5-8

_c_a/_mtJ. $EDR 104 ,__

rizon Scanner pitch and ro_ outputs _ ascent, is to _-_-_e 8yro

e_rs wh£ch may accumu3Jl_e while the spacecraft ts being boos_d_

Phase (B) starts _..r spacecraft separation when a brief, f_ve-second

sisnal e._--_-,_s the ASCS to provide rate _£n8 to stop a_y tendency to

Phase (C) is lui_a_ at the e_letion of _ve eeecmdJ of rate

damping. The ASCS Is p3_ed in _ _£entat£c_ mode_ spaeecrat_ turn

eWOttU_ (180 ° co_tereloe_£ee Yaw Rotat£_) is aco_3£ah_ an_ the

spacecraft is p£_.hed-dm_ to the retrograde f£r___ anF_ within 30

seconds. Pitch, roll a_t yaw 8_ro slav£_ to the Horizon Se_-,_s is

provided dur£n8 ._ee (C) _ the _ Select .Swlteh ls in the slave

pos2ttc_. Both the Free and Cs_ed positions of _he G_rO Select StrA_h

prevent _yro .slav£n8 to H_riz_ Sea_ers.

In phase (D) _ Sl_,_eraft is in _rb£t. An erb£t pXteh attitude

of -3_ o (_-_ end down) is he3_ so that +_._. elmeeemft is med_ f_ an

£_ediate abort. As in ]_aee (C) at_i%_le 8_ros will slave the horison

8_8m_rs ff Oyro Select .'_£teh ls in _he nczm81 pos:£ti_. _ +--_ oa_ott

._-:e manual e_ta'ol _. f_y-by-wAre eoz_rol _y be utlltzed as desired.

Rate de:ping :e_ be obta_d by placing ASCS:ode eeleet switch into

AUXDAMPposition. Rate gyro run-up is ec_tinue4 thrceshout phase (D).

_nother feature utlllzed in Phs_ (D) is an autmmttc return to the

orlentatlc_ mode. If _he spaceera/_ drifts (fXwla orbit s_£tu4e) beym_

the limits of the x_nCerloek sector svl_hes, aut_stle _e_urn to

o_lentsti_ mode rill occ_ at +15° plt_h, 2 30° _a_ end rol3_

In phase (E) of FA_ 5-2, rate 8_ro r_n-_ Is autm-t_ea_.v asmn_d

by re3J_ ewit-_-Z 10 _Jtutes prim" to retrosra_ attit_e. _he

5-6

t; MCDONNELL SEDR 104

_l:l:)N:lflO:lS _l:l/$VW WO!hl SONVWWO3

IFMI8-126

.1_gm'e5-3_A.S.C.S.MissionProfile

5-7

__;wffa.g. SEDR 104

aaw change em_ one or sl_ +h_ee of the spacecraftattitudesaaintained

by the ASCS by changing the space referenceplane or planes of the sttitude

gFros. To naintain the hey Merence plane or planes, the Horizon Scanner

slsvi_ e_u_nd must be stoE_4 _ placing the gyro mrAteh in the

position. Nee referenceplanes an7 be establishe_by the astronautMLile

the ASCS is in operationby plaei_ the gyro svitch in the I_ position

a_l placl:_ pitch toz_uiq _tch in the W'F _sttlon. Also mmma_ turning

off the ASCS fuel in the axis or axes e._ected,utilizing:aznal controlto

positionthe spacecraft,and the_ cagingand uncagl:_the 87ros. _he ASCS

ms_ then be returneato f.lly euatcmatlcoperstlonin a11 three axes with

the exception of Rorlson Scmmer sl_Lng. To utilise Horizon Scanner slaving,

the spaee_ &ttttu4es wast be vtthtn the observation range of the 8csnners

and the S_o swatch nus¢ be placed in the _NaL position.

_he ASCS receives Tr s_sl ea_ u-_- a spsceeraft in htah torque

retrograde attitude _phaseY). Horlson 8_ slavl_ is 4tsconttnued

at this time, _htrt7 seconds after retrogrsAe attitude ec_Bad, the

retro roeke_s are fLreS. ]ktri_ the perLo_ of ret_ot_e_e rocket f_rL_

the _ ut_izes hL_ torque action to hold the _p_e_rat_ v_thLn one

degree of the l_eal angles. Retro_e rocket _trtng ccmuau4 an_ A5C8

high torque mrltchla_ _.u_ occur siuultane¢_/_. Rocket _lrtnK ls complete4

in 20 seconds and the h_h torque mrAtch/a_ ccnmad is hel_ far 23 seconds.

Upon _letion of zetro paeke_ Jettison,the ASC_ autems¢lee3_

_itches the s_aceeza_ to the _ost-_etro fire. aCttt_4e (_ase O) in pre ....

paratton for re-entry dxa_. The _ returnsto or£entatio_ aode vtth

5-8

MCDONNELL SEDR 104

constant sca--er operation to accuratel_ m4_ the re-entr_ attitude.

FinAlly_ when re-ent_ is sensed by _le .05g accele_r mrltch,

•he elghth and _ phase (H) of the ASCSperfc_ma_e _tarts wlth the

tmmt_ off of the attitude _ro power. _ t_ls perlcd the ASCS

Initiates mad m-4-+_bls a constant roll rate of 10° to ]2 ° per second

to ,,4,_-4_e to-_ha-wn dispersion. Rate 4_p1_ Is provided to stabilize

the re-entry traJec_. ASCSoperationin this phase continues until

main chute depiJ_ment, at _tch t_ all ASCSpower is removed.

Pilot-override previsions permlt lnterrupticas of the "normal" se-

quence by manual o_ f_-by-wtze control ma_pulation add return 1;o the

"nu,=_Ll"ASCSMODE. _ to a ai_4_Icant degree the astronautis the

_J1te]_1£gent"back-up"fO_ the _S. Iq,11 uti]_zatlonof thls rellabl].%ty

a_mentatlcn principle _as led to _ ce_ng and other mrltehtng features

ldLl.Oh axe izl_ tO _e "the spacecrs.'_t ,M_rmlly cont:rollab].e. _ae

fo]_ovtn_ table lists the md.tch and ccm_rol positic_s necessary to

achieve the four basic modes of control a/_er attalnln_ orbit. Variations

of the varlo_s modes can be obtaln_ by further switch m-4pul_tc_.

_" HANDLES

POSITIONS POSITI0_S

CC_TROLMODE _"LF._T-N01_ - FJ_-AUX, L(N & HIGH- AUTO"T" _ "T"DAMP L0Wo_r_

A_Z_MATIC N(_S.L Elther Y_her _ (_ _j'T.T. 01;r_'

FLY-BY-_IRE ,qRT3eCT FJ_ As Needed _ ON PULL OFF

DII_CT (No N(_V,AL Either E_+-_-r PULL C_F PU._ CNDpin)

DIRECT (With _q_._Yf AU][.DAMP Either PU_ _ P'J_ 0N

5-9

NELL SEDR 104.

\\\

\\

// \/ ABORTAFTER STAGING AND BEFOREORBIT INSERTION

// A 5 SEC. PERIOD OF RATE DAMPING AFTER SPACECRAFT SEPARATION./ B ATTITUDE FROGRAMMIr,IG BY ASCS, COUNTERCLOCKWISE YAW MANEUVER,

/ SPACE CRAFT ASSUMES I_=TRGATT TUDE \

/ C RETRO-FIRING SEQUENCE IS tNITIATED (TR), SCANNERS ARE DISENGAGED \

// FROM GYRO% \\t 30 SEC. AFTE_ TR NO. I RETRO ROCKET FIRES \

/ 35 SEC. AFTE.; TR NO. 2 RETRO ROCKET FIRES \40 SEC. AFTER TR NO. 3 RETRO ROCKET FIRES \

l 23 SEC. AFTER NO. I RETRO ROCKET FIRES (I"R+ 53) A.S.C.S. SWITCHED TO•I ORIENTATION MODE HOLDING RETRO ATTITUDE. RETRO ROCKETS MAY BE

\ /J FIRED ANY TIME AFTER 1'R SIGNAL BY ASTRONAUT OR GROUND COMMAND. \/

V D 60 SEC. AFTER NO. 1 EETRO ROCKET FIRES, RETRO PACK IS JETTISONED, \

i

SCANNERS ARE SLAVED TO GYRO'S AND SPACECRAFT ASSUMES RE-ENTRY .05GATTITUDE. RETRO PACK MAY BE JETTISONED MANUALLY BY ASTRONAUT. _,

E RE-ENTRY ATTITUDE HELD UNTIL .05G BUILD UP. \

F AT .05G SCANNERS ARE TURNED OFF AND DISENGAGED FROM GYRO'S. \\RE-ENTRY STABILIT-_TION STEADy ROLL RATE OF 10_ TO 12' PER SRC. IS IN-TROD_ED.

G ANTENNA CAN IS EJECTED AT 10,600 FT. AND MAIN CHUTE IS DEPLOYED.A.S.C.S. TURNED OFF.

/11//

/ \ B 1o,600'/ \/ \

V 'I

G

• iis--__- FMIS=I22A

Figure 5-4, A.S.C.S. Emergency Operation.

5-10

"__NNELL SEDR 104

5-6.

In general, abort sequencing (See Fl_re 5-_) is progr_ to cor-

respon_ to the safest procedures at all times, q_e poss_le abort situa-

tio_s can be diwlded into +h_ee types s nmely (1) short, befcTe l_rer

separatlonwhen ASCS rate damping is recf,,1:',,'ecX;(2) abort after tower sep-

arationbut before +_ trajectoryis truly orbi1_al;and (3) abort from

orbit. _he fo11-vingparagraphs,5-7 +_o,_ 5-9, discuss ASCS sequencing

in each of the abort conditlc_Is.

_-7. ABORT _ TOW_q .qRPARATION

If an abc_t mlssicn is s_'ted during the perloa when the booster en4

sustalnerengines are burnlng, the ASC8 is utillzedfor rate a_T.Ingcn_7

,a_ter _he fo11_lDg external opera_io_8 h_e _een a_ale_Ml.

(1) Booster au_ sustainer engines cUt-off.

(2) Spaoecrsf_separatlo_from adapter.

(3) o-er rocez(_.) Retro rocket separatl_ frm spacecrs_.

(_) Timed arrival at appr_-te peak of trajectory.

(6) Separation of escape tower from space,aft.

Upon o.....-letlo_of _he later operati_n, the ASCS is _-----_-a to pro_lae

rate a,.Ting,using the rate _os _c_ are ccntlnuo,sl_ eaerglze_dur_

l_e normal ascent an_ "abort trajectory" f]/ght. A constma't roll rate of

i0 ° to 12° per second i8 e_loyed, Rate _--T.tng ceases upon _eployment

of _he main chute.

5-11

_O_ON_RLa.. SEDR 104

q_e first operation is en6tue cut-off. _hls is followed i_llately

by spacecraft separatlc_, poslgrade firing, and the normal mission post-

separation sign-_ seque_e to the ASCS. _e effect Is _--_dlate d__.:tng

of any tendency to t_le. After 5 seconds of rate d_ing, the auto-

_mtic sequence ccm._.ds spacecraft turn around amd an attitude angle of 3_

degrees. _hen either tl_ astronaut or ground e_nd must initiate retro-

grade sequenc_. Upon achieving the proper roll_ pitch an_ yaw angles

withinratherwide"per_sslon"bovnd.s(SeeParagraph5-5,Paze5-6),the

ASCS enables rapid-sequ_ice retro rocket firing to proceed.

NOTE

ASCS _-_mlssi_L interlock" dur_ retro fire can be

over-rl_0en at ,_ time by the astrcz_at.

After retrograde operation, the abort missic_ in this case proceeds as

in the normal missio_ po_-retrograde sequence (except for the _ifference

in tra_eetory time an_ distence Intervals.)

5-9. A_mT Fa_ _

Whenever an abort frcm orbit is initiated, the normal automatic or

_ual retr_ operations will appl_. Ho_everl if manuel retrogrs_e

operatlo_s are utilized the pre-re_ro_rade perio_ of gyro slaving to the

Hurlzc_ Scanners ("last look") w_1 be e1_nated.

5-1o. sYs_ OI_tATION

Overall system operat£on is best explaine_ by I_ _-5- The .,_m-

plifier Calibrator receives i_uts from sensors on the left side of the

page an_ _eneraT_s output;;s to Display an_ Reactic_ Control devices on

5-12

IFM18-49

Figure 5-5_ A.S.C.S. Block l:)iagram

5-13

_MC_NNELL. __ SEDR ) 04

=_ li_,_:i8 li_

F_-_

l_igure 5-6, Pit,ch A'_;_Block Diagram

!5-14

I/ICD%ItlNELL SEDR 104 ,,

Figure 5-7 Yaw Axi,_ Block Diagram

5-15

NNELL SEDR. 104:

>_w

-i

FM18-46,

l,'igure5-8tRollAxisBlockDiagram

,%16:

"_WO_NNi/.L SEDR 104

the right. _e four basic operations are alavl_, repeating, mode s_Atch-

F ing and torque seit_Lng. Data flow pertaining to the iadtvid_a! Yaw,

Roll and PAtch _-_els is illustratedin Yi_es 5-6, _-7 and 5-8. In

general,these dAa_ are straightforeard and require no e_lanatlc_.

However, the method utilized in derlvi_ l_tional information is unique

to a degree and warrants the follovA_ discussion.

The pitch _al (vertical_rro) Is precessedec_tinuousl_.

the orbltalphase of T_e normal m£sslon_ so T_at the spaaecraft"local

vertical"referencerevolves360 degrees_m_ng eaQh c_bltal_/_le.

The _rro slaving principles which permit DArectioaal (:raw) lnfoz'm_on

to be derived are as follow: After t-_tial slaving an4 settling of

the roll -,_ pith loops_ the ASCS controls the spacecraft to the e_

pitch a_titude_ an_ to level roll attit:._. _nitial_, after separation

s_l spacecraftturn around, s_ yaw error (as great as 10 _egrees)may

exist d_e to d_ect_--_ drift dur_ boost. Sluee the Roll _*_ of the

vertAesl _ro is the _--er _=_m_al,_ _Isalig_wnt of the spacecraft

causes the Roll _-_ o_tp_t to e_ntain an error component due to _he

constant orbital (pitch) angular ra_e. _us a ccmparlsc_of _he Roll

Horizon S_---_rend vertical g_ro roll indAeati_s will provide an error

signalproducing a roll _al torquing rate. _4_s to_qu_ rate _hieh

Is a direct ftmc_tlc_of yaw erro_ Is use_ to sXave the yaw _i_baX of the

d'_',-e_'ttmml _., ¢,.

s _aotherarea +_t warrants dAseussionis _ha_ of _orque seltchlng,i.e.,

the thrust outlart_ the Reaction ControlSystem in c_uncti_n with the

variousmodes of ASCS operation.

5-17

_NnmAa. SEDR 104

5-10 serves lw in la_zo4aetlea to the to=q_e u-=_tel_lag l_-

Msvlor of _ ABCS. _r aszIIm eoasezwa+,lonof eoat_ol I_=eI, _e 1_-

havior varies 8_eordln8to the ABC8 mode eppropz_steat a gtvea tJne. A

=o-ealle4 "phue-plane" plot of ea_ rate vs. angle is shogn in the

z_A_t corder of F:L_ure 5-10 a_aeemt to a _teal Pi_eh tlle-htstoz7

for tMe "Orbit" ao4e. |,_:rent J_C8 4eslga lx_atts a plus or _ 5.5

degree ose_ll*tlo= aIKm_ the n_ orbital&tti1_:4e,whieh in _ 18

referencedto the Hor1_m 8__----_'sseamed "Horizo_tsl". _he ose_11*tion

is nonsiunsoldalbecause of the dAseant/nuoustorque_n=gzem;plteh rate

is a s_,*_erave, 8a4 _:Lteh aagl.e s sa_tooth,both hsvlns a ehsra_t_zistle

period of 2_0 seconds. Poz_ on _he phase-plane,the =Orblt"mode

osetllatloa ls & Ipmtl_ drift from -_._ degrees _elattve _lteM aag_e to

+_._ 4esrees relative _ite_ (.39.5o to -_8.5 ° 4esrees, refezeaee4 to true

_). _le &r_ lasts for _te_v o_e-_-:f-_ert_t of two ala-

_te=. Irae_ the erro: _es +_.5 4eSzees, a 1¢_ toz_e _Ase ease= the

rate to z_ez_e_, _aeze _ the seem_ h=:_-_"A04 lS s]_mt drlA'ttag

=l_l_r _ zero to .-_-5 d_prees er_-or.

As aaotlu_ eza_le ,Z__ torque_sWZteMtag, 7tsuze 5-10 sMovs the

"_etrosrade-HoZ_"t_rq_= l_e l_ase-plaae,IA,,gzm. Xa t.l_ ca=e _-

torque nozslesare util:_e4 Inst_a4of the 1ov-_orquenossles_hteh vere

adequateto eoatrolthe Kent2e o=blt oseilAstion. A seriesof attl_o_e

repeste=sector s_Atehesan_ rate-sFroplekoFf seeto_ svltehesare

use4 to de_Ine stepllkebouadarle,vlthln the phue-pla_. A tTplesl

e_zto_r l_ shova to llS._mt.'_te t_e motimz rem_tt_ _ a large di_ar-

hence _orquevhJAe In _zis node. b_en the spaeee_ motion reaults in a

plt_h r_te value above "_d=e1-Asht-han4stair st_p, hlgh ne_tive _oz_luei_

5:18

z

ASCS AMP-CAL

NOTEONLY THE YAW MICRO SWITCHES AND AS-

•'_ SOClATED C I RC U IT RY Ai_ SHOWN. ROLLAND PITCH ARE SIMILAR.

T .I" T t[_ SWITCHES SHOWN IN STICK NEUTRAL PO-SITION LOWTORQUESWITCHESCLOSE FIRST.

JJ_ RELAYS DE-ENERGIZED IN FBWPOSITION.

' IHIGHI-

_RCSSOLENOIDICONTRQL _ADvE (TYPICAL)J I RCS THRUST

CHAMBER (TYPICAL)

,FMIS-131

iFigure5-9,A.S.C.8.Fly By WireControl

5-19

_Mo_NNELL SEDR104

applied until I_1espacecraft attains a negative rate and rotates into

the "no-torque" region. The inverse occurs if the retro rocket thrust

eccentricity or other &'Lsturbancesforce the spacecraft into a slt_ation

ea111_ for positive t_tst. _he net effect of the torque-swltching logic

shown is to mR1ntain rapid and reliable control dur_ the important opera-

tlc_ of retrograde fir_.

Other modes of ope_Ltion requiring torque switclLtn8 logic are "Orien-

tation" and "Rate Da_0e3.". During orientation mode bath high and low

torqut_ is utilized to rotate the spacecraft to new preset attitudes.

Both high and low torqu(_is also applied during rate da-_er mode but

rate _rro signals E_e needed as a basis for switching logic. In

this case, torque swltc1_ng bo_daries are horizontal lines on the l_ase-

plane.

2-11. UNITS

5-2.

_he _lifier Callbrator unlt can be "functio_s_F" divl_1 iuto

four sectl_Is. _lese functional secti_Is are slavluS, repeating, mode

swit_ and.torque sw_tc_.

5-13. G R0SLA

_Is sectl_ co_te_s --T.liflersand s_ networks which accep_

roll a_ld pl1_ _n_tlo_ from +_ HGl_l_zon Scanners s_ generate currents

to torquers in the attitade gyros. _hus, upc_ _._._._ from an external

t:L_t_ de_Lce_ the Gyros Roll, Pitch and Yaw 81mbals are ali_aed with

correspon_11_8 _Lreottons in, or perpend_culsr to the orbit plane. (Ref.

Para.

5-20

lifCDONNELL .: _SEDR 104'.

RETROGRADE_=(PITCH AXIS EXAMPLE):

I "5"5° _I0.0 I

/-

8.0_

m'°i j_+5.5°i

Ai.e DEGREESj

ORBIT l

TYPICAL :TIME HISTORY (PITCH)./

:o5o,s_1--_o5o,s_. , _ r---L_ oo_T.o._,,f- PUSLE IN SEC._ _i, _ .65 ...... -i_

I I-'---24OSEC.t"1 *8 o._7 _, o_.

+5._--I _,"_'A' -,_, :-A ._ =0.252 _!'±DI 0._7, !.I

..... l +A +A. _" *e, b.755 .1._-4° I.

- :A e. [)EGRI_ESySEC.. FMI8-55,

Figure 5-10, Torque Logic Phase Plane Diagram.

5-21

__R'LL SEDR 104

rJ_e repeater secticn is a group of servo-mechanisms (four in present

deslgn, including _o f!orpitch angle repeating). Attitude gyro outputs,

which are reeelve_ at _e calAbrator in proporational ar "analog" for_,

are amrplified and used to drive shai_s _nich serve as roll, pitch and ys_

signal sources for bo_ internal (torquing switching) an_ external (display

an_ teleme'_c'y) purposesJ. _e on-ofT reaction control of the spacecraft

mA_es it desirable to _Lse conductive sectors on the shafts of three of the

repeaters. _e secto_ serve as attitude-l_vel references for torque

5-15. MODE_ _CTION

_is section of the calibrator establishes the proper attitude angle

bias, torque swltchi_ status, and interlock signals correspc_-_ to the

ASCS mode c_,_,_n_edby external devices.

NO_

_he sum of a_ such external _evlces is, for _SCS

design purposes a "easter sequencer" whlch coordinates

all automatic functions.

_he mode-swltching sec1_ionuses c_.act, solAd-state switching circuits.

Altho,_h these cireuit_ contain m.,_ytransistors, _iodes, and other elec-

trical ecmponeuts, th_j are of a class _hat is not eritieall_ dependent

upon reference voltage or _e_perature levels.

_e torque svi_h_1_ section contains transistor and diode elrcults

_5-22

"__J/U_i'/.i. SEDR 104

similar to those in the mode-switchi_ section. Torque switching circuits

receive the step-function outputs of the attitude gyro repeaters, plus

_e outputs of the rate 8_ros. The latter (rate) signals come from sector

swltehes replacing T_e usual proportional rate i_ro pickoffs. Us_

these step-wise __-_eatlons of attitude and rate cc_61tions, alo_ with

the _le switchi_ section output 8efining the current phase of the

missic_ "_ecisicns" are m_ which result in energizing of th e alq_o-

pria_e Reaction Con_l Valves.

_'_._eacceleration switch is a hermetically sealed Ins_nt. q_

basic mechan_m ccnslsts of a central_ located mess supported by a can-

tilever spring. _h_ mass is _ by the viscous shear action of the

fluid whleh fit!. the case. Switch actuation is caused by the dlsplae_aent

of the mass element. An Acceleration force of .O_g, in the axis nor._

and in _he 6irection away from the base, is required to close the circuit.

Me_A-_cal stops are _ovAded to restrain the me?_-ntm an_ to protect

e_ainst _ when sub_ecte_ to excessive acceleration.

_he function Of the attitude gyros (vertical and directional) is to

6etermlne attitu6e angles between a set of fixe_ a_s in the moving space-

craft and T_ reference a_es which are fixed in the orbital plane but _ich

are _ with the local vertical. Both attitude gyros are "free" gyro-

scopes with slaving capability. A me-,- Is ineorp_ted for ca_.z_ an_ for

electrlcal signal (syachros) outlnxts which &efine the attltu_e

•5-23.

_MC_NNELL SEDR 104

of the i_ros vA_b respect to Wo sut_J_r l_rl_aalcular axes. _e

sttltude IDTos possess unrestricted nechaatceA t_eedcm in the outer

sz.t.s sad _.+83° (atnAm:) of :eebaaAeal _- in the _--er exts. Zt

is aote4 +_-t the degree of _ treed_ does not aeeesssrtl_ z_'leet

the attlt-_ies l_Lsslble by amlttslly sl;ee_ the s]paeeera_% in oz_l_.

Due to ltaitsttoas in _be Hortson 8_--_r s_t_s anql the repeater section

of the Awplttter r_S.tbzator, asDsal eoat_l of the _ slued be

lsa.tt,_ to _.+3o° 4,, z'oll a4. ]ru _ _d.t_ _.+3o ° of the -1_..5 o :it, eh

attitude. H_mver, _ e_ot];_mt aslftmetton, ezeee41a& these lJ_ts

not pz.e,,_S.tee the success of a alsstoa. Xf t_ese ltmLtM are ezeee4ed,

tt; ls z_c(umesle4 t_lt the _ rurAl;oh be l_la_e4 in the _ lX)S_tton. Xn-

l_t _ _ts are ]A_ volt J_)0 _s st_1.e l,lu_se (_ro ao_r), aaa

26 wlt, I_o e_s (m_o aaa torque aotor).

.zg.'_he Attitude an4 l_te Indicator is mounted, on the upper portlon of

the Natn Inst_t Paz_I. '_he _adlcator pro_s _ ta41_at_ns of

Sl_eecra_ Rate aa_ Attll:_ in "theTmr, Pitch sa4 Boll plaaes. The

attitude iadAeatorssz_:drlve_ _ _he at_l_xde 8)-_os_nohroout, is

(t_ the A_li_ler Ca_Ib_tor). _e &tti1_ laaAeatorsare osll-

brste4 to la41cate_:_e &_tltude_lt_In & _ of + 180° except for

_ew _al_M -_ _ la41_a1_0e, 80°, u4 2T0° in a cloek.lse41reetloa.

_e rate poztloaof.tbe ladleatorIs _rlve_by the alnlat_rerste treas-

a-eers. The range of =:_e Iz_Aeatlonis 0 to + 6°/seeoa4for a11

5-24

VIODONNELI- SEDR 104

n :GYP-OCAGECOMMAND

N GYRO

GAGE • '2' i ATTrlTUDEGYROSLAVE

COMMANDGYROSWiTC. I i NOTSEP.

I-"II

:ASCSMODE SELECTSWITCH

I I ASCS

I .AUX J CALIBRATORDAMP j

SEC 24V DC 1 O I

ASCSSOS ,i ,_- IiFLYBY I

I WIRE I V LOGICDC

I .o_ I

,y-ii _Iio J

S.A_T_• _ I _-- JSELECTI

"J LOGIC AC

I_EFORE

_ R/G STARTI_ il_/G AC PWR

/" AFT_

_1 !! LATTGYRO P,_i1__ _ .RETROCOMD. RELAYIS BY PASSEDFORA_" .l_v j FIRSTFIVEMIN.AFTER

BUS _ CAPSULESEPAR_kTION FMIB-123 ]

Figure 5-11 Power Distribution D_._m'n

5-25

_NNELL SEDR 104

three iaAt_tors. _e :_11 rate inAioat_r has the a&litio_A r_a_tlit7

of _etag exteraaA_ mrA'_ebe_to a _ of 0 to l_°/see. 4,, order to

monitor re-ent_r zoll _ste.

The zate gyros _ez_orm electricalcircuit svltehlngfunctionsat

8_eeltlcx_tes of 8_Lr velooi1_about 8J_8xls 1_ez_adio-1-_to the I_8e

of each unit, re_erzed"_ as the "_.-putaxis". Rate _s are used.in the

_pttch, roll sD_ _ axeJD, :espective_. Bach z_te _ eouststs of a high

81_ rotor,nounl_ In a glm_ rinK, in such a nm_=er that it is

to 3pzeeessabout _e a:Ls on_ (the _t3mt sxls) which is l_dtcular

to the spin axis of the rotor. _he o_ slsna_ are senerate_ by the

notion of _i_rs, attae]_t to the _eA ring, _ across the contacts

of sector n4.tches. X_t ]power req_tre_eats are set by 11_ volts, Ij_X)c_s.

Srm=

_-_. sz_ _x_

The ReactionP..,o_,z_',LBysten is use4 for s_meecra._ Fmr, _iteh an_

•olI control. The 8_st,-.utilizesnltroKen 8u pressure to ez_el h_

gea _erozid_ _ a bA_L_er into the _hz_st elumber ea_t beds. _he

_A_hten_e _t ebm_ _zo_ce t_u,t by deoca_os_n_90%b_osen

_erozi_e (l_j02)._he _._s_en18 dAvld_ Into three dlffe_ent_ortlons.

One _oz_ion is for e_t_mtte eon_ol (ABe), one for nauual control, an_

a reserve fuel mte_ _ be utilise4 dnx_ag the z_-ent_-T phase o_ the nisslon.

_he m11xmatleaTstem 8_S the na_uaA _rs_e_ a_e b_i_:_y f_4=43m. W4__hthe

e_eeptlon ot the neth_ us_t _o _ the t_Aovof Fuel to the thrust

5-26

o \ __", 'o _._

N

zz '¢

FMt8-3A

5-27

_' ;VICDONNELL ]SEDR 104 i

<

z i_o

oz __-0 _

___ -e_

z_0_- __m

U _FMI 8-15_

Figure 5-14ReserveRCS Installation.

5-29

__JLL, SEDR 104

chars. T, the 8n_Ltle system,the flourof fuel to the thrust

ch_ezs is controlledl_ electrlesl_ actuated_solenoi4valves. _he

I_ of Fuel to the _t ehembersof the hanna1 s_rsteuis eontrolAed

aeehaaleal_ actuate! proI_rtlons_ valves.

_he follo_ l_za_ _-2_ I_ 5-26, brle_ 4eserlbethe opera-

tion of the sutcmatic,,Mmual an4 reservesTsteu. Fisure 5-1T sh_ be

follow_ elosel_ in eo_|uaetioa vAth the fo11_ing text.

_he automaticsysl_sacan be divide4Into two _Jor l_S; the pzes-

su_zatton portion end '_tm fuel poz_ion. _e pressurization sphere,lo-

catedvithln the utzommt'l eo_t, is servlcd with nitrogen to a

pressure of 3000 ps£. ]_en the reg-lstorshntoffneedle valve is opened,

the pressurlslng81s is e2Ao_ to flov into the pressurez_tor vhere

theoutputpreuure to ]nu theresu ator,the

pressurizinggas l_Aovs_rouKh a checMvslveand entersthe fuel tank _here

it 8u_ a bladSer ,_nta_ the fuel.

Tuo electricaltrs_dneers are 4--_ed in the pressurisationsysteu.

One of the txansa-cersis locatedupstreemof the resulstor_:ah-l_ needle,

valve and is used to _J_Lie_tethe fuel q-ntity. _he l_ressurizing _ i8

a_owed to ex_md to oe,_ a laaq_er v_me as the fuel is expe/le4

the fuel tuk bla6_er. _ e_A_msi_ resul_s in a &_.ease in l_resmtre

_A_ln the l_zessuriz_ w.r_tea, The _ecreue in _ressure is se_ed _ the

electrical _u_S, cer m_ coavert_ la_ a vel_e which Olm_tes a c_trol

5-30

"__;V _m " SEDR 104

fuel quanti_ 4_ locatedc_ "theastronaut'smain In_mmn_ panel.

- _he ec_ol fuel quan_i_ 4_leatc_ is calibratedto show percent of fuel

z_aalnlng.

_e seeon_electricalt_an_ucer is located_st_e_ of the fuel

'tankand is used to indicate"thepressure on the _el bladder. _e vol_-

age _ this t_sduee_ is 61s_la_ o_ the _02 pressure Indleatc_c_

•he ast_cz_rt'smain _._t panel. _he _ pressure In_ca_c_ iS

calibrated to indicate pressure frem _0 to 700 psi.

A presage sei_ch located in the press_A_izatic_ system, _pstres_ of

the pressure regulator, is used to t!l,_nate a fuel quantity _srning

light c_ the astrc_ts main instrumentpanel. _he pressure s_i_ch is

set to actuateat a pre-_etermln____edlow fuel level.

A pressure re_ef.valve is also incorporated into the pressurizatic_

system and is set to relieve excessivesy_ pressure. _e l_SiCa_

locatic_of the various e_aponentsin the aut_--tlcpressurizatlcnsystem

can be seen in Figure 5-12.

_he fuel portion of _he a_t_ tic systembegins _Ith the half t_rOida_

fuel tank. Locate_ inside the tank is a flexiblebladder ec_taln_ apprc_i-

mtel_ 32 pounds of 1Aquid 90% _02. _e pressur_z_ sas surr_ the

outsi_eof _ bladder forces the fuel out of _he blair through a per-

forate_ transfer tube located insi&e _he bleA__r. _he fuel flows _hro_gh

a checkwalvean_ into the downs%reamllnes.

Located in each axis, yaw, pitch and ro!_, is a manual_7 actuated

shutoffvalve. _hese valves are linke_ to I_,__ _s lo_ate__ the

5-31

_CDONNIL L SEDR104

astz_mt'e left hand e,m_oZe. _ aetuatt-n these nhut_Tvelves, the

fuel suppl_ can be slm_g to. each tadividna_ t_mt axis ia the event

a sole_ld aalf_etion should occur. _e abil/ty to isolate eaah axis

iedirl_-ll.y ttle_ t_e wAtxmatie _rstem to operate aonmll_ on tMe re-

axes, ze_ the astrommt to IN_:k-upaa_, only the aal-

fuaetloniagazis.

DovastreJ=of the m-_,-? shutoff yeS.yess_re the eleetzleal_ eo_trOlled

soleaotd v_ves. D_x_areceiving a stgasl _ the _ or tly-_-_Lre eon-

trol system, the s_ropz_ste solenoid valve ol_ss. _ ea_,:ex.sthe soleaot4

valve a_ l_sses into the .eox-reeiKm&Lagt lr_t, e...l_'bex,wb.ea"e11;.4ee_ses

e_l pzo_ees _Me desired thrust. _ are 1 lb. aad2_ lb. thrust ehm-

bets, provi_z_ low aad ht_ thrust, about each of t_e follmdag szes:

_ar le_, yav right, pt_Ja _ ea_ ptteM _mra. _eze are 1 lb. aa_ 6 lb.

t_st _, pz_rtdAa8 lov aa_ bt_ thrust, _ _e follmrA_ szie:

roll CW aa4 roll C_. _eek valves,loeate__ the aaaual sMntoff

valves a_l the solenoid, valves, _ for t,henml _Io= of _el

4o_astrema of the msm:_ _totf vslves. A relier valve in the tm_ sys-

te_ relievesexeesslvepressure. See Fi_ 5-12 for the l_Tsieal loeatlon

of the automatici_el c_x)l_l_s.

_e aa_ s_rstemI_reeserAsattea ffetea is i_=ttcal to that _e4 la

the e_t_ati¢ s_tem _._ one ezeeptioa. _'ae_ ]_reesavlsatio_s_rstes

eontalasno presnx_ m_t_ a_ no l_el _tlt_ _ li_t.

_e _ porti_:of the aa_ :_te_ beglas_It_ the Ma_f tero_4al

1_e1 t_mM. Loeste4 t_t4e the _ t_ a tlezlble t_s4Ate_ eontsiniag

_-'_II/iCDOItlNELI. SEDR 104

FM1B-129

Figure 5-15/R.C.S. Control Linkage

5-33

_M_DONNELL SEDR ]O_t -

TROLLINKAGE

YAW CONTROL" _ ROLLLINKAGE : _'_'. CONTROL

. 'LINKAGE

YAW

FMI8-124

Figure _5-I6/Three ATI_Hand Controller,

5-34

'_a__mAJ. SEDR104 0

8ppr-Y4u-tely 23._ pounds of liquid 90_ H202. The pressurizing gas sur-

_\ roun_tnK the. outside of the ble___r forces the fuel out of the bladder

throuKha perfaratedtransfer tube loca_l inside the bladder. _he fue_

flows through a checkvslve aria into the _ovnstre-_ lines.

LocaT_l downstre-u of the manual system checkvalye 8n_ upstre-: of

the p_Tporticnalcontrolthrottlevalves_is a mechanicall_actuated

shutoffvslve. 5he shutoffvalve is linkedme_h--_eal_ to a I,,11handle

locate__ the astronaut'sleft console. When the p.l_ handle is p lu_1_

OU_, _ fuel suppl_ tO %he proportic_l c(mtrolT2_rottle valves is shu_

off. From _he mmaual system sh_ofT walve, fuel flows to T_e proportional

e_l throttlevaXves. _he throttlevalves, see FIKure 5-19, are I_-_ed

_ mechanically to "l;he astronaut's hencl controller, see Figure 5-16. _st

o_tputis dlrectl_proportionalt;o hand. c(mt_oller d.l.splaoe=ent. SprtD8

cartridKesloca_e_in the hau_ ecntro11_ _ provide control

"feel"and.return "thehandle 1:oneutral. Shear pins, locatedin l_e

throttle valve bellnrsnk8,are designedto shear with increa_ effort

on the pat_ of _ astronaut. _*- ability1;0 shear the mec_--_cal

c_ each-'_8 prevents the _e_d=8 of one *_,,ot;_.e valve _,-ont(1,t.sabl:L_the

ent.tre systen.

F_ thethrottlevalves,fuelflon *_,,'ou_ 8 _be_ve 8n_enters

the thrust _er. 5he _heckvalvesInet_3_d _ownstre_ of the throttle

valyes require posltl_e pressure for "the fuel to flow. _h4 s requirement

el_m_--_es the erratic thrust *h-t woul_ ocour if +___-fuel doenstrem of

the throttle w_l._e vere _ to _r-_- throushthe thrust eh_ber after

the throttle valve _,,,,_returned to neutral.

&-35

_O_AL. . SEDR 104

A _ thrust of _ lbs. 18 arable on the follovlngaxes:

z_Sht,yew left, p£1;eh_ au_ pitch don. A nsxluuuthrust of

6 Ibs., is availableoa the fe_ axis: _ _ an4 _ tag.

A eheek_ve XA0_._'tedLbetT'een the nm_ shutoffvoAve and the tk_ttle

valves .'l"l_m for therm_, ez_e,usien of i"uel _ 6omw'_ms of 'tMe

_At_F_ VS_Ve. A _lle_ _VS_Ve 4_a_8_e_ _ _ _ fuel 8y8_ relleveB

excessive _xenu_. _ae_l_ysical loa_i_a of the ve_Ao_ e_qxments of the

nmual 8Fetes ee_ be eee_ in Fip_e 5-1S-

_he en_matie 8n4 _he mtma_ sFsten ea_ be interc_meete_ _ a me_ani-

aetu_te_ in_conn_ct va_ve. _he intez_onnee_ valve is ne_umteeA_V

link_ to a _ handle ou the astronaut's le_ console. _ ol_ning the

interconnectvalve, the fuel of either s_s_emm_ _e use_ in the other s_s-

ten.

_he reserve systeu_Ist_ _rlua_ of a _,_el teaM, s_atlaria eon-

sit,orionto the f_el t_ use_ in the m_t_matleen_ nau_al s_a_ens,v_th

a ee_met_ of 15 lbs, of _ _0 2. _he :eserye 1_e1 tank is ec_te_ to

the e_toms_i¢ por_lon of the re_tton control eysteu 8n4 is desired to be

use4 dingus the re-enf_7 _r_ton of _he ntuton.

Zn ozd_r _o utJAtse _e zenerve fuel, it is neeesssr_ to s_ppl_ a

_ressuA_lsiag _8a _o s_xmn4 the resezve f_el bla_r :in a--"_r 81u_3_

to that used in the sure.tie su_ manul fuel tanks. X_essuzlng gss is

aa_e available to the rel_erve fuel b/ad_er _ either the sutmmttc pres-

5-36

-- o I!11II,,, £

<4.' _ _.

_MODON,ftlIILL. SEDR 104-18__

surizatlon system, the mamml pressurization system or both. Pressurizing

gas is ,-,'_.e a,_tle_le by flring a squib valve conneetlng the reserve sye-

tea to the appropriate p_eesurlzation system. Firln6 of the s_uib valves

is acc;-,,.-llshedby astronaut actuation of either of two toggle switches

provided on the left console of the instrument panel. In addition, the

s_ib valves are both fired automatically at antenna fairing separation

d_ring re-entry if they have not been fired previously.

5-z7. U TS

Due to the general nature of the system components, a discussic_ of

each is e_sidere_ unnecessary. However, two items (propellant fuel an_

t_rust ch_ere) d_ werrant brief explanations.

Hydrogen peroxide is a clear, colorless liquid soluble in ,_11 pro-

p_tions in water and most substances which are miscible with water.

_Xrogen peroxide when catalytically decomposed releases water vapor, .

o_gen gas an_ heat. _02 decomposition when properly coutained ena

c_trollea is capable of producing usable thrust. One pou_l of _02

solution (90%) when properly 8.eco_ose_. "will pro¢luce appro_Maste_V 60

c_ic feet of _s. Hyclrogenperoxide (_0_) i_A_ezesat ll.3°F, and boils

at 268°F.

mST

_e +h_Ast cb-m_er ass_lies (See Figure _-18) consist of a stain-

less steel chmaber that contains a distribution disc followed by a catalyst

bed and then a nozzle. _he catalyst bed contains a stack of nickel screen

5-38

z

uZ

.,z, _z -_

o

5

o

|

SEDR 104

,// / _ ..>..

'/! i / h-'._j , j , ,t ! / I f_"-.

, ',, _. ;.' / ;b," / / ""-'\ .......... _____ I ! ,>,......"---'-::':_-_-"_,::"-..i{ / ,1

SEItRATED AP,_V_-_ 1LOCKWlRE

SERRATEDSHAFT

SHRAR PIN

THROTTLE VALVE

FM18-121

Figure5-19 Manual R.C.S.ThrottleValve and BeHcrank

5-40

'_,_N _fkL SEDR 104

vsfers. _he screen gauge resembles ccumon household screen. _e screen

_ is plate8 vith a s_ver-pl_l coat_ that enhances the ¢atalTtic properties

of the nickel. 2he open area between the catal_t _ a_l the r_ht _e

_ssle foz_s a short plemm ch_ber to mooth out the flow ]prior to reachia8

tJ:e nozzle throat.

H_ enters the thrust obaaber _xm mtlon of the soZe_td valve.

_he s___4-1_ss sl_el plate d/sl_lbutes the flow sn4 presents the cstaJ_rst

bed vith a un_om l_ut. Upon enterinK the f_t ste_e of the eata3_t

be4, a vtoleat resctioa tames place. _ gases rush throu_ the

renalader of the catalyst _ results-= in a thrust outlmt, in the right

angle nossle. _e maJort_r of the 4ecoaposltion (a_l aos_ vlolent) takes

place within the first two catalTst cu_s. _erat_es of e_proziaatel_r

1JKX)°Ycan be e_ecte_ in this area. _he resmAa4er of the eatal_t cups

are to 8esure a _:_lete dec_ost_ton _rocess e_l to prevent a_r l_d

_'o_ of ][202 from reach_ ",,henozzle.

m nmau

_e Borisoa Scanner S_s'_u incorporates tvo i&m_ical sca_ia_ units.

_e Ima'l_oseof the Rorlzon Scanner 8_8_zt is to prov£de a ro_ a_t pltch

reference 4arias the orbital ]phase of the norasl atssioa. _ae s?"_'8

pro&uee an _t_t siSaal that slaves the AS_ attitude _ros to the proper

aagle_ ulma _ _ an exteraal_ro_r.

asm:::

Fixate 5-20 is a 1_ of a _orlzoa ScaaaerUalt. a_ mJor oct-

5-41

_NNE_.L SEDR 104

• FM18-57

Figure 5/20 Wide Angle Horizon Scanner

5-42

"_'MCDONNELL S EDR 104

/--

DETECTOR FIEL._ __

OF VIEW CIRCLES

// \ \

/ _ \/ \// P,TCHSENSO'_-- \ I I

"fRAJ[ CTORY

_ \ I "-//

/ \\

0

EARTH

FM18-58

Figure 5-2] Horizon Sensor Scan Pattern

5-43

_NNELL SEDR 104

portents and subassemb_lXes are mounted from the large circular plate and

include the so_ prim as _sa_l_, prim drive system, infrared detector,

eleotrc_os, _ous mrl_hes_ electrical co--Actor an_ cover. The

c_cula_ plate is flange mounCe_ so that t_e soannin8 prim e_nt

l_oJects into the space outside of the vehicle. _e eleotr_4c system is

completely transisto_ize_ and the various functional sections are febrtcste_

c_ separate printed circuit boards. _ee of these printed circuit boards

are enclosed in the shielded housing fastened to the circular plate. For

rapid servicing the four posts with attached boards can be replaced as a

single ,_It, or individual boards can be replaced as required.

5-33. _CXAL FEATURES

_he Horlzan ScA--_.r has a _,_er of special features. It is c_T.act

insize(65132"long x 5 718"e aae .roveri)

(3.02 Ibs). _he scanner is equippea with a centrifugal_7 - activated

shu_r. The ah_ prevents solar radiatic_ from dwelling upon the

detector and resultin_ in probable dsma6e duri_ those periods when the

scanning prism is not rotatln6. _other feature is a special circuit

which can be used to dlsc_mect the error signals from the vehicle reac-

f_iondevices _urin_ those periods when the presence of the sun in the

scan path or the loss of horizon woul_ result in erroneous error signals.

_e final feature of si_ficance is _hat _ a single power source

providln_ ii0 volts_ _00 cycles and 3.2 VA for each se---_ is re_1_ed

to operate the entire sysT_n. _he hi_7 re@_tlated power supply in the

system eliminates f_e need for the bulky, bstteries usuall_ required to

bias the _-frared de_ector.

5-44

'_W_g_NNmLL $EDR 104

_-3_. ,_s_t _cs

_ 0pera_icn of the Horizon Scanners depen_ upon infrared radiation

received from the earth as c_pareH to the essential_ zero radiation

i_m space. _hese _fferences in radiation levels provide a m_Rrp radia-

t£cn discontinuity at the horizon. The Scanner system uses this discontin-

,_Lty for both da_ an_ night vertical reference sensing. When T_e spacecraft

is oriante_ so *_t the earth is present in its scanning path, there _ 11 in

general be _wo points where the scan intersects the earth's horizon (_=

FA_re 5-21). _e sc_-er detects the thermal discontinuity, or ehen_

in radiation level, between the earth and space at the t_o horizon points.

_e Scanner then bisects the included angle from itself to the Horizon

points, c_.,_.eres the at,,eetion of _ bisector with that of a fized refer-

ence in the spscecrel_t and generates linear error signals proportional to

the angle between the bisector an_ the f_ed reference. As previousl_r

stated, these error signals (roll a_l pitch) are use_ to slave the A_S

attitude gyros.

FA_Lre 5-_ shows a sinple block diagram of the H_Azon ScAnner. _ae

folAoei_ discussion entails a brief explanation of the functioning of

each block as relatedto the overall operation.

inhereIs a _ differencein the radAatlonwhich the detectorreceives

as it scans across the bounda_ between space and _e upper a_aosphere

(tropom._ere). _l.s _ is _z.._.-:m,,_. equal to that fr_ black

bodies at 0o_ an_ 200_ respectivel_, an_ the radiance differe_ce is

appr_m_e_v 3.00Sntts/_ - steradian._e lo_atlonofth_sgradient

5-45

_MCDONNELL SEDR 104

is sharply defined, and it is much larger than any others that can be

encountered during the scan cycle.

5-36. CORRECTION FOR REFLECTED SOLAR RADIATION

_harp radiation gradients do exist because of reflected so_-_ radia-

tion. Sttchgradients are found at cloud edges, topographical irregu-

larities o_ the earth's surface and the terminator line between night

and day. _ese radiatlc_ changes can be filtered out so that the horizon

gradient is the only one that is detected by the system. Selective fil-

tering can be accomplished since most of the reflecte_ solar radiatic_

falls in the spectral regioflbetween 0.2 end 2.0 microns_ while the

radiation _tted by the earth and troposphere is at wavelengths longer

than 5 microns. _he filter_ Is accomplished by a ger--_1,-,primn

and field lens in front of the detector. As a filterI germa-_um sharply

cuts off all radiation at wavelen_s sho,_er than 1.8 microns while

tra_-mltting very uniformly radiatic_ fran 1.8 to 20 microns. _he use

of this filter removes over 90 percent of the reflected solar radlatlcn.

Signal clipplng techniques in the electrc=Ics remove any residual effects.

5-37. SCAbbING ARD RADIATION rgTECTION

Details of the scennlng prlm asa_ly can be seen in Figure 5-20.

_, _-_rared detector is fixed to the center of the elreular plate and its

field of view exten_s +_ough the ctrcu 1-_ openin8 in the center of the

scanning assembly. _e detector field of view is 2 ° by 8° and T_e pre-

sence of the scanni_ prism has the effect of deflecti_8 it _5 ° from

the normal. _-us _ apex ansle of the scaunl_ co_e is _0 °. In opera-

5-46

"__NNmL_.. SEDR 104,

¢ion, the drive system rotates the scanning pr_ and the detector field

_-- scans the field of _ew throush the conical pattern aescrlbe_ prmri_sly,

Different _:ounts of radlatlo_ strike the detector during various portions

of the scan cycle, and the a_litude of the detector output changes

accordi_l_. _e detector output signal is processed by the electronics

system and t_P error signal produced is available at the electrical con-

hector.

Closely associated with the prism drive system is the reference

signal _erator. _he output of this generator is s square wave signal

at a frequency of 30 cycles per second. _Is signal is the fixed reference

against which the detector horizon signals are ccmpare_. _e reference

signal is triggered _y the interaction between a magnetic pickup coil

and a semi-circular steel vane. The vane is imbedded in a slot cut into

_he surface of the scan_ prism a6semb_V gear. A pickup is mounted

so that the end of its magnetized core c_s close ¢o the m_rface of

the vane. As the scennins prlm assembly t_A-s, the ends of the vane

pass by the end of the ma_netlse_ pickup coil core, generating the ref-

erence pulse. A subsequent electronic network converts the pulse to a

phase Iocke_ 30 cycle square wave. _he use of this signal will be con-

sidere_ la_er in this section.

_e san shutter consists of a pair of sprin_ loaded nctal slides

which fit into opposed ira--verse slots throush the tube section of

ecennln8 mirror ass_,_l_. When the scennln8 mirror ass_l_ is not

5-47

_NNJ_ SEDR 104

rotating spring tensic_ I_11- the two slides together an_ the detector

field is obstructed. When the scanning mirror is turning, the centrifugal

force c_ the slides is sufficient to open _e shutter.

Y_frare_ radiatlcn from the fiel_ of view strikes the infrare_ detec-

to_ and produces the electrical signal which is processed by the elec-

tronics system. _e infrared detectar is a thermistor bol_ter _rAthits

active element _rse_ in the germa._,_,lens.

_he active element is a rectangular flake of thermistor _-terial and

is coD_ected in a bridge circuit with a s4_I._ ec_atlng flake which

is shielded fr_ radlation. _ two f1-_s are opposlte_ biased and their

Junctic_ is cc_cted to the input of the preamplifier which follows. By

4_w_rslng the active element in the rear surface of the ger_--_,w lens

the overall detectivity can be increase_ by a factc_ of abo_t 3.5 over an

_w-_rsed detect_r having the same field of view. _he m_erial in _he

thermistor flake has a high negative t_ra_e coefflclent _f resist-

ance. _hat is, _hen the temperature of the _-terlal is ralsed_ the flake

resistance decreases. Since the surface of the _her_eto_ flake is

blackened, it abso_os i_i_ radiatic_ and its resistance is decreased.

When the shutter is closed, both flakes in _e _etector brid_e are at

the same t_rature. Since both flakes have the sm_ linear character-

istics, their resistances are the same. Gradual variatlc_s in _ie_t

_rature change the resistances of both flakes by equal mounts and

the voltage of their _unctlon r_-_n- the s_ne. When the shutter opal,,

incoming radiatic_ is focused o_ the active element; the compensating

5-48

'__M_ma..a. SEDR 104,

e_nt is shieldedfrom outsideradiation. _he _Tera%_u-e of the active

_ element is changed2 en_ Its resistancebecomes differentfrom _-t of the

c_ensating element. As a result,there is a voltage change at the

Junction of the two f1--_s and this change is connectedtO the electronics

system. As the sca_ prism turns an_ causes the detector field of view

to cross the ho_:_zo_,there is a sharp cha_ in the radiationlevel strlk-

i_ the detector. _e result of the radiationchangesdur_ a complete

scan cycle is the generationof an apprrm_matesquarevavesignal at a

frequent7of 30 cyclesper second.

The electronicssystem is physlcal_y arrangedso that functicmallyre-

lated parts are locatedclose to each other. _he electronicssystem is

dAvi_ed into et_e ma_cr circuits,locatedc_ individualprlnte_ circuit

boards. In some cases, the requirementsof compact and ecc_._cal cc_-

struettcD have resulted in two or three sub-circuits being located c_ one

board. _hus_ the functiowal_7 related booster amplifier, signal centeri_

circuit a_l phase tnverT_r-l_m4ter are located cn one board which the

block diagram (Figure_.oo) shows as divided by dot-te_ lines. Although

the po_ su_30" _ reference generator circuits are not close_7 related

in func_Ic__hey are buth locatedc_ _-_ same prlnte_ circuitboard.

_e paragraphs_ha_ follow describe She func_lonsof the m-Jot sec-

tlc_s an_ s_-sectlcns of _he electronicss_s_e_. _- _escrIptlcnis

made with z'eference "to the wa_efc_msgeneratedby system operal;l_ a_l

these are shown in _ 5-23. FunctionaldescrIptlc_rill be made at

the level of the ma_r circuits and sub-circuits shown in the block dAa-

grm Fignre 5-22.

5-_

_N_mA.A. $EDR 104

The radiatic_ fa111,_ 5 up(m the detector determines the waveshape of

the detector ouLgut sisal which is to be processed by the electronics

system. _e radiation characteristics are determined by the scanniDg cycle

described previous_4y, an_ are shown as _he first wavef(n'm, 1,'F-l, of Figure

5-23. be wavefc_n shows that earth radiation is higher than space radia-

tion and that there is an abrupt shli_ fraa o_e level to the other as

the detector scans across the horizon, be change in radiation reT,1_es

200 microseconds to take place because the detector is of finite size, and

÷_le t_,_ is re_,4_ed for a ccmplete =h_*t of radiation level across the

entire surface of the detector. Thirty ccs_lete cycles of radiation

change take place in one sec_.

_TF-2 shows the detector output signal which results fron the radlation

changes taking place at the detector. _hls signal res_les the radiation

signal with the exception that t_ -h_t bet-_eenthe two levels takes a

ic_ger time. _he reason for _s is that approv_m-tel_ 2 m_l_econds

is re_,1_ed for _ active detector flake to reach the half-level of its

now stabilized output. _he detector output signal has an s_plitude in

the order of 2 _ l__volts.

5- z. BOOm c acu ms

_e _unctlon of the two thermistor f!-_es is direct-coupled to the

input of the pre-_ler. _e pre-a_pllfier has a voltage gain of 400

at 30 cycles per second. Direct-coupliDg is use_ between pre-a_plifier

stages to provide goo_ low-frequency response an_ to prevent phase _ft.

Negative feedback is used within the pre-amplifier to provide stable gain_

5-50

_VlCDONNELL SEDR 104

_, CENTRIFUGALSUN SHUTTER

SCANNING

PRISM IDETECTOR

li ..

II "0II/ ,..

._ pREAMPLIFER t SUN

PRESENT

MAGNETIC

REFERENCE _ k

PICK-UP _ SP-HLDETECTION VOID SIGNALCIRCUIT OUTPUT

BOOSTER AMP

SIGNALSUPER

REGULATOR CENTER LOSTCIRCUIT

PHASEINVERTERLIMITER

POWERREGULATOR&FILTER

POWER INPUT LIMITED SIGNAL

I10V400 _ A-C OUTPUT

PHASEPOWER DETECTORSUPPLY &

FILTER

PHASE D-C ERROR SIGNALREFERENCE AMPLIFIER OUTPUTGENERATOR

_. REFERENCE SIGNALv OUTPUT

FMI8-59

Figure 5-22 Horizon Scanner Block Diagram

5-51

_OItlIWELL SEDR 104

WFI-RADIATION ON DETECTOR WF7-PHASE INVERTED LIMITED OUTPUT SIGNAL

SPACE / 50-150_ SEC.

C. WF8-1NPUTSTO PHASEDETECTOR

SOURCEVIBRATINGARMNO. 7 AT/ SOURCEWF2-DETECTOROUTPUT ATR801

_ \ LOAD_ LO,A0_.ATRR02_ _ _50% LOAD

WFg-CHOPPER INPUT (AT NO. I CONTACT)WF3-PREAMPLIFIEROUTPUT LOAD SOURC

KI02 l_SOURCE_" LC*ADr_ r----TSOURCE LC*ADWF4-BOOSTER AMPLIFIER OUTPUT (O° HORIZON) _I I k....-----.-._._ 1 2_v.

L_J L_Jt/--___,_v:_Csv.SEC. WF10-CHOPPER OUTPUTS (AT NO. 7 CONTACT)

WF4A-BOOSTER AMPLIFIER OUTPUT LOAD SOURCE 0_.3V

(3soDROPPEDHORIZON) K,0,"_ "Y_.I ""_v'---J='_---T

WF5-SIGNAL CENTERING CIRCUIT OUTPUT

._--)_. sEc._-_'- _WE6-LIMITER AMPLIFIEROUTPUT

_,, sEc._ /÷_ov.INTERNAL SIGNAL WAVEFORMS

a. NO HORIZON a. NORMAL APPROX.

EXACTLY 36MSEC

0 _. _ JITTERMUSTBELESSb. LOW ALTITUDE HORIZON THANSUSECWITH

1) ZErOTILT RESPECTTOLEADINGEDGE

VOLTS, b. MOTOR STOPPED(LOSSOF MAGNETICPICKUPREFERENCEPULSE)

2) PosIt,rE tILt , I l 1

_J I VOLTS c. PARTIAL FAILUREOF SWITCHING TRANSISTOR-0I 1) DEFECTIVE_,.v_ _, _._v,,'.j JL+14VNORMAL; I ; i I

GAINORPARTIALSIGNALLOSS Q3043) INSUFFICIENT t I

I t 1 . 2) DEFECTIVE _3VDC JL .._c. NORMAL SIGNAL DROPPED HORIZON Q3O5

1 I vo,ts.i,..i_.T%_MSE_ J... _ "0 d. TYPICAL LOCK-OUT SIGNAL

d. SUN IN SCAN _-_-_INCI_EASEDWIDTHCAIJ_EDBYSUNPULSE TOGROUNDn HHORIZON ; I VOLTS ............

_-] ,1 ,J /-o _[_ ......... U----LOcK.Out TO.,4vI _ "I NORMALHORIZONDISCONTINUITY

2) SUNINI _L._I,_SIUNpUL_SE I 1-20

SPACEJ I._ "_ J VOLTS e. IMPERFECTSYNCHRONISM

LIMITED SIGNAL OUTPUT AT P-101C LIMITED SIGNAL OUTPUT AT P-IO1A

FMI8-60

Fi_u'e 5-23 Horizon ScarmerWave Forms

5-52

"_MOO_NNmAJ. SEDR 104,

and the RC coupling network in the feedback loop provides a high-frequency

boost to co--sate for the long detector t4._ constant. WF-3 shows +h_

effect of this boost. _ rise time of the waveform has been reauced

to appr_m-tely 350 microseconds at the half-level point. The booster

_nplifier provides an -d_itional voltage gain of 5 to 30 cycles per second.

WF-4 shows the output of the booster a_plifier. The peak-to-peak signal

amplitude is in the order of 5 volts.

5-43. SIGNAL _ .CIR(Y_

In the signal processing considered previously there has been no

particular interest in the voltage level of the average signal. However,

this average signal level is important in system operation. _e reasou

for this is that the error signal --,stbe determined only by the phase

angle between the horizon and the fixed reference in the vehicle, and

amplitude variatians in the signal should have no effect. Amplitude

variations will take place because of ('J_ugesin earth temperature at

different parts of the trajectory or orbit. When these amplitude varia-

tions are camb_ned with the rise-time characteristic of the detector

there is a difference in phase between different portions of the lead-

ing edge and the fixed reference signal. Error signals would also be

affected by amplitude changes due to changes in amplifier gain and supp_

voltage. T.4m_tingcan be used to e14m_nate the amplitude variations

but the 14m4t_ slice must be taken at a point of m_,_m phase varia-

tion. These variations are greatest at the peaks of the wave and least

at the center. Using an RC circuit to couple the signal to the l_m_ter

woul_ balance equal areas of the signal waveform above and below ground.

5-53

_MC_NNELL SEDR 104

Changes in the angle of horlzon depression would _use a shift in the

doc lev=l of the signal. Rence, a slt_nsl centeri_ circuit Is __loyed

before the 11_4ters to assure that the site center sllce is semple for

phase shift under ell conditions. _he slgn_ centering clreutt consists

of two diodes connected back-to-back as d-o restorers. _he dtoAes condnct

on opposite peaks and thus permlt the assootsted ca_¢ttors to chsrp up

to opposlte peak values of the signal. _he tvo levels are then _med

in a resistiwe _tTlder network, and the fdm is s_pled by te_ptng the

dlTlder. An emitter follower eo:ples this signal vhteh is shown in _-5

to the llat_T ¢lreutt.

The s18Dal next enters the first of a pear of oaseaded f_ empll-

flers_ each of which acts u a ll:iter sDA phase inverter. The eapllfler

eoaslsts of s srouaded emitter stage _hlch perforas the phase InTerslon,

mad an w-Itter follower. The feeAbaoE ratlo ls about _0:i emd the o_er-

ell 8e£n of the seotlon Is about 30. The output sWln8 Is i0 vOlts eaoh side

of the fixed lO-volt level. A low outlnatJape4sn_e is maintained 4nrlng the

time _hen the emitter follover is in _utof_ by feedt_ the signal from the

_ollector of the _ eeltter stage ,_t,'eotl_ throut;h & shunt dioAe.

The first sectlon of the fee4back e_pllfler Is lea by the signal center-

tag _ireutt. Xts output eisnal is the "llatted stSaal outlet" eusa shorn in

_F-6. Part o_ this I:IL_II1 ls fed to another lSatteA _l/fter _IbB1_MBtlally

t_ same ms the first, _e_e it _m_tez1_oem& secom4 11sverslomto beemme s

mirror _mal;eof the om_1_t of the flre_ seetlom. _:e Omtl_t of the 11mlter

seetlom is thus the 4msl signal _ in _-8. While e_t1_ers_4P_ esrrles

5-54

_M_NNIILL SEDR 104

the stSnsl _-#on_tion, the presence of the _ st&_l _13 be found

useful in ea-ce].lt_ out umles_-_le rLl_le ccerl_nents In the rect_te_

A 1_t_" of sj._e_rtcsl, ltuLted stSasls enter the 4erector section

(T_-8). Fr_ these the detector dez_Lves s 4-c stSn_ _l_teh is pro_or-

t:20]_L1 tO the phase _e__mce bet_m the z_.tel_mce 11-lee _ t_le m44-

1)o:blt of the two bo_.so_ 2]_tercep_s. The l_8ae sensitive z_t_fter con-

sists of two SPDI' l_Ol-___ze_ z_J_rs, or choppers, dr£ven t_ phase opposition

]_ the ::_tez_ac:e stKua2. _ese are d_stKnst, ed. rlOZ _ 11102 (IG'_). _he

use of _o Cbol_e_s p_des the _2v_q_es of f-_ _ w_ve rectXg£eatXon,

mta_l:r lo_ _21_1e.

TO w_lerstm_t the antto]a of the _h,'OaOq_ reotif£er_ t_ ls esse_t_

to _ the _e]Jttive ]phaa:lJa8 of _ile dr£w _ hor:_]a sXSIla_. S£_aoe the

two _ are driven 180 ° out of phase, the arm of one emmee_ tt_

e_itor to the source while the arm of the other c_=aeets Its c_aeitor

to the load. Swlteh-over takes place when the radla_ sector of the se_

bema c_sses _he vertle&l z_fereaee _k of the sensor and mrll_b_

occurs 180° later. _, whea it is eoaaeeted to the source, the e_itor

receives part of the s_ InLYseaa_ ]partoft he earth latXee. The ce_aeltor

is charge_ _osltlve1_ _"_Ia8 the ewltohe_ in portion of the earth Im_e

_e_tlve3_ a,ri_ the swltche_ In _ortioa of the sky _-3te. Xf the sensor

hori_oa_al is 1_el to the horizon, each e_itor i_ ne_tive_ -ha_ge_t

8_ a_10tlllt e_ml_ tO _he 1x)et_,XTe _ha_e. _el_fo_e_ the iBeX;_ha_ge i8 ZerO,

5-5_

__m/.IM SEDR 104

If the senso_ t_ilts with respec_ to the horizon the s:ount t_at each

eapaeito: eharps positively is not equal to the mount it charges

negatively. _e net charge is, ther_ore, no lc_er zero. _he net

signal st the _ of _he d-e _plt._e_ ls thus positive for posltlve

tilt of the sensor (ew as vieve_ fma the sensor along the seem a_s)

an_ negative fo_ a tilt In _he ¢pposltedirection. WF-9 and WF-10

indicaterespectlve_,v_e voltage c_ each choppersn_ the une_iaed

output.

output of the phase detecto_is o_ine_ an_ filtered in an R-C

netv_rkat the Iz_ut at"the d.e ampli_Aer. _he sl_nal at this point varies

appr_Hte_v 100 _ per degree of tilt au_ +_- _ level is - 0.15

volts. _e a_3ifier i_ut is at hi_ iaqmdance to maintain a low ripple

factor. With a 8ain of apprc_mstely three, _ output of the _mmlifier

is 286 my per de_e tilt of the sensor,reverslngpolarity at zero tllt.

Part of the output is fed back to the M_tter of the iz_ut erase. _e

balanced circuit ccz_tion m_94_4zesthe output drift with temperature

fluctuatic_.

_re are t_o cc_dAtlcnsunder v_eh unuante_ error sl_aalsare

generate_, neme3_, vhen the sen appears in "the scan an_ _hen the hc_izou

is lost. Signals prodnced under these eondi_Icu trigger a logic circuit

_teh indicates by its out_ that the sun Is present or the horizc_ is

lost (hence_he deslgnatlcnS_.WT.CirCUit). _£S O_ can be used to

dAsc_---ct _e _-e error output from the vehicle guidance systea. _he

5-56

"_,__ffLL SEDR 104

effect of sun presence is shown graphic_1]y in the waveforma of I_

_ 5-_3- Be sun pulse introduces an w_y_trical e1_nt into _he signal

tr_j and the horizon _-formation derived fran it is llke_ to be false.

_he presence of the sun's radiati_a is perceived at the detector. _ae

s_ radiation is b,_d_eds of _4_e greater than that of the earth. Be

stars and other bodies produce neE14gible si_Lls. When a sun p,,1.e

occurs, the second stage of the pre-s_plifier puts out a negative p,,1.e

wlth a peak enpl_t_t_eof _ to four volts. _hlS pulse causes the

Void Signal Circuit to produce an output. When a horizon is present

in a nm_al scan a signal of 5 of 6 volts from the signal centering cir-

cuit suffices to keep the void circuit _llfier shutoff. _he absence

of the signal _hen _he horizon is lost has the s_e effect as a sun

l_,!Ae-- it causes the void _xpllfier to conduct with a consequent o_t-

put ou_nt of _ _ into a loa_ of 2000 _= or less.

5J_. PHASg _E SIgnAL C_CUIT

A phase reference si_al is produced by the scanu_ s_ when-

ever it passes *_ot_ its _st point with respect to _he Sensor. Be

reference signal is generated in the scanning system. Xt consists of two

equa_ spaced pulses, c_e positive an_ o_e negative, for each revolu-

tion of _he scanning s_e:_ _ese pulses trigger the bistable _,Itl-

vl_rator+ _ two-level detector section is in sy_o_l_a with the scan

cycle. _ output of _he reference generator under various operating

c_llti_ is shown in Figure _-2S.

5-57

_o_lJ_,. SEDR 104

a,P Y

A]] the power required to operate the sensar is derived from the 110

volt, _00 cps line by a built-ln power supply. Input to the supply is

throu@h the transformer. _e pr_m-ry of this transformer is tapped liEe

an auto-transformer to provide low voltage a-c to operate the scanning

motor. The transformer secondary output is i_.13wave rectified to produce,

-30, +30 and +16 volts d-c with respect to ground. _ae +30 and -30 volt out-

puts are fed to the Regulator. The +16 volts supplies the reference gen-

erator, and void signal circuits. Part of the transformer secondary volt-

age is rectified separately to produce ,m_egulated power for use in the

reference generator and the void signal output current smplifler.

5-50. POWER REGULATOR AND SUPER REGULATOR CIRCUITS

The Regulator circuits convert the outI_Atsof the power supply into

regulated voltages for use in the sensor. Most of the voltages are regu-

lated by cascaded zener diodes which maintain a substantial/y constant

voltage across their terminals by an effect s_m_far to break-down in a

gas discharge regulator. The regulator also contains a sys,aetrlcal

arrangement of transistors connected as emitter followers. Since the

base potential of each transistor is fi_ed by zener action, the output

voltage is accor_ly re_,Inted with reasonably low noise. _xis out-

put is filtered and further regulated in the Super Re_,lator circuit to

provide the highly regulated voltage required by the detector and pre-

amplifier. This voltage is extremely stable and its noise content is

essentially transistor noise. The zener diodes used in these circuits

are 1/4 watt units which regulate within 5%.

5-58

SECTION Vl

SEQUENCE SYSTEM,LAUNCHRETROGRADE

OR ABORT

TABLE OF CONTENTS

TITLE PAGE

Normal Mission Sequence ........................ 6-3

Escape System.......................................... 6-14

.iiiiiiiiiii!iiiiiii!iiii!!ii!iiiiiiiiiii!iiiiiiiiiiiiiiiiiiiiiiiii_

'::iiiiii!ii!iiiiiiilHiiiiiiiiliiiiiiiii

6-1

_MCDONNELI- SEDR 104 @

0 I

×_h"@ @ @ @®

o _ _ _ o

, _ _ _ _ _ _ _-

' i -_ _ _ o _ _' _ 2 _

., _ -_ _ oU

_ _ °_ _ _ z

_ _ _ _ -_ _

- _ ! ._0 -_ _ _._ _.-_o _oo

®®®® ®®®®®® (9@@

® (

Figure6-1 Normal MissionSequence

6-2

___"" $EDR 104 Q

6-2. La_BCB_OUaU STAG_

6-3. mmum,zcm

_t_ launch _ stegtng sequence estsbllshes basic references at

t4_ c_ launch and then reaains inactive until staging. At stsgt_, the

:tsetles's booster engine separates, resulting in the escape tower bolts

being fired after a t_mnt7 second t_ delay. _e eseape rockets are

fired. 4-u_q_ 4atel_ _ tower bolt detonation a_ subsequently the la_a4._

system beeone8 arned.

oPzaAmzox

sequence system is _ntttate4 by tvo 28 V d-e signals from the

_nlle _nlch occur at 2 in____s after l_toff (_= F_ure 6-2). _Ls

is known as +_ zero refereaeeen_ energizesa Tine Zero Lateh_ Relay

in _ No. 3 Launch an_ Orbit Rel_y Bax locatedwAthln the spacecraft.

An aeta'onaut eontrolAe_ back-up sw_tch i8 provi6ed in the e_ _ 28 V

signals fr_ the :lsstle _o not res_h the spacecraft. _:ese see slsnals

Mae _ to the M_--_ Al_tude sensor results in estab:lAshins the

f_...ntion _ _-4,_ l.lftc_f versus the t_e anabcn, t n_r oeeu_. _ Spprc_-/

aate_y 135 seec|xlsalssile sta_ _ ooeur _hereb¥ the wehanleeA

separation_ the booetez engine _ oause the :Lossof spseeere_t poem-

to the Boos'_er _ Separation Sensor _ela_. _ this de-emr_Lsed

teleX'; power wAl_. be appl£ed to the Tower _son 20 Second Time Dele_ -

6-3

NNELL SEDR 104

LANDING SYSTEM(ARMED)TWR.JETT.

WARN LIGHT J DUAL LANDING

IIII I 2,=FT =SYSTEMR G R BAROSWITCHS ARMED

l IN Si RIE_S

B H HMAIN CHUTE 10,_600FT J LANDINGSENSORRELAY SYSTEM DELAyRELAY _ SYSTEM(DE-ENER- ARMRELAy (2SEC. T.D.) BAROSWITCH ARMED

GIZED) -(2 SEC.T.D.) IN SERIES

SRACECRAFT-TOWERDISCONNECT

STAGING

TWR.JETT.

WARN. LIGHT SPACECRAFT .20G THRUST q JETT. RKT. H JETTISON

SEPARATION -_ INTERLOCK FIRE ROCKETDIELAY RELAY RELAY RELAY(1SEC. T.D.)

WARN. LT. RING LIMIT ROCKETRELAy ROCKET

(_SEC. T.D.) SWITCHES FIRERELAy J

t i

I H I IRELAY BOLTS _ BOLTS(20 SEC. T.D) RELAY SQUIBS

tENGI NE BOOSTER

SENSORRELAY ENG.DE-ENERGIZED SEP.

LIFT-OF____ 1

SATELLITECLOCK

J ATLAS J

28 VOLTS AT

TIMEZERORELAY

I FASTRONAUT*STIMEZERO

SWITCH

q ALTITUDE I

_o_ MAXIMUM

[_ USEIFATLASFAILSTO PRODUCELIFT-OFFSIGNAL. SENSOR

[_ LOSSOF 28 VOLT POWER.

_[_ IF ESCAPEROCKETSFAIL ,TO FiREAND THRUSTDECAYSTO ,20G.

[_> TOWERRiNG INTERLOCKRELAYIS ALSO=NERGIZED.

DD'ToWPR RING INTERLOCKMUST BEENERGIZED FOR JET=TISON ROCKETFiRERELAyTO ENERGIZE.

FMI8-121 A

Figure 6-2 Launch Through Staging Block Diagram

6-4

M_._ONNIII,.L SEDR 104

Relay. After 20 seconds, power will be applied through the contacts

of the Tower Jettiso_ 20 Second Time Delay Relay _o energize t h_/-

Tower Separatlc_ Bolts Power Rela_ and the Tower Jettison Warning

Light Relay (2 sec. T.D.). _he Tower Separation Bolts Power Relay is

armed by both +h_ Main and Xsolated DC Squib Bus through the Squib _m

Seiteh. When energized, _h_ Isolated _luib Bus power fires Wo of the

five squibs (2 bolts) and Main Squib Bus pover fires three of the five

squibs (3 bolts. _he Tower Ring Znterlock Relay will also be energized

vhen the Tower Separation Bolts Relay is energized. As the three seg-

mente_ Tower C_-_. Ring separates, the _.h_ee Tower Cl,w_. Ring T._mtt

Switches return to the normal position an_ ,_!nw Isolated and Main Squib

Bus power through their contacts. 'l_e Isolated Squib Bus power energizes

/ both the _rgency Escape Rocket Fire Relay and the Emergency Jettison

Rocket Fire _l_y, _tle the Main Squib Bus power energizes both the

Escape Rocket Fire Rela_ and the Jettison Rocket Fire Relay. As the con-

tacts of the Emergency Jettison and Jettison Rocket Fire Relays are con-

nected in parallel, either relay _ill fire all squibs of the Jettison

Rocket from the two _i_ferent pover sc_rces, m_e _rgency Escape and

Escape Rocket Fire Relays are ecnnecte_ in the iaentieal same _ner and

will fire 811 squibs of the Escape Rocket from both pover sources.

Power to energize the _rgeney Jettison and Jettison Rocket Fire Relay

is route_ through the .2g _ust Relay which is energize_ through the Space-

craft 1 Seco_ _-_ Delay an_ Thrust Cutoff Sensor. _ne .2g sensor plus the

1 Secon_ Time Delay Relay alloys the Tove_ C_a_ D Ring to separate and the Es-

cape Rockets to fire separating the tower i_cm the spacecraft vith the Jetti-

son Rocket unfired. When this is aec.-_llshed_ two electrical disconnects be-

tveen the to_ar au_ the spacecraft are separated and remove power from the6-_

_N_m£.£. SEDR 104.

three Tower Separation Sensor Relays. _aro_h the de-energized No. 1

Tower Separation Se_sc_ Re_, _e green JETT _ 1£ght on the isle-

light panel 111_ntnstes. _mm the to_ an_ the spacecraft separate_

the No. 1 an_ No. 2 Tover Separation Rele_ are de-energize_ s all_

pcver to energise the No. 1 awl No. 2 Ma4, Chute System Arm 2 Seco_t

Time Dele_ Rele_. After 2 seconds de ls_ t the Ma:ln _te Re]_Fs az'm_

the 21,000 Foot Barosvitehes and _he Main Chute Delay 2 Second _mA

Delay Relays. After two seconds, the 10,600 Foot BarosvAtches are armed.

_he power circuit will hold at these _o points m_t_l the spacecraft

descends down through the 21,000 foot range, at which time the landing

se_e is In_tlate_. Refer tO Sectlo_ VII of _s _m,_.

6-5. _ smas_

6-6. z=scazl:_ow

Second _ is initiated by sustA1-_r engine cutof_ at _ch

_he Spacecraft Adapter Bolts are fired, providing accelerattc_ has decayed

to .20g. _e three Posigrade Rockets and the fou_ explosive electrical

disconnects are fired _--_llate_ after the bolts are detonated an_

result in spacecraft separation. Spacecraft separation is sensed and ini-

tiates five seconds o_ rate d_-pIng which Is followe_ by orbit o_iante-

tion in _alch the spacecraft rotates 180o degrees an_ settles into a 34°

crblt attltu_e.

66

• IICDONNELL SEDR 104

<_lllllllllllllllllll _ooE ('----_ o

_ _=_ _ - _o=_ _z _ _ _

_- - _ _== _ •2 = = _ ' "uz

= _

°T;_- _=_ _z ._ o= -_o_

r........................ _, _

, ! T' _

_ z u

2,__ _ (.___o

U

i

F_1_101

_gure 6-3 _o_ S_g Bl_k Dh_

6-7

__m_l. SEDR 104

6-7. OPERATION

At appro_m-te_y 285 seconds after launch, second staging wlll occur

(See Figure 6-3). At this time a 28 volt d-e signal from the missile

rill energize the Suetalner Engine Cutoff Relay. When the thrust d_ops

below .20g, the .20g SwIT_.hin the _ust C_off Sensor closes. Power

is then supplied through the Spacecraft Separation 1 Second Time Dela_

end Sustslner Engine C_toff Relays after the 1 Secon_ Time Delay to

energize the Spacecraft Separation Bolts Power an_ the Spacecraft Sepa-

ration Warning 2 Seccm_lTime Dela_ Relays. Th_oush the energized con-

tacts, power from _he Main an_ Isolated Bus fire the Spacecraft Sepa-

ration Bolts. Also, Main Bus power is su_plled _ough the Warnlng IA_ht

Time Dell7 Relay to _11,_4,._e the red SgP CAPNJLE sequence L_ht on the

Le_t Hand Console. When the tri-se_ente_ Spacecraft-to-Adapter C_--T.

separates, it allows the Spacecraft Adapter Ring v4-tt Switch to

close supplyl_ power to energize the PosiErade Rocket Fire, _or_ency

Pos_rade Rocket Fire ana the Spaeecraft _dapter Disconnect Squib Fire

Releys. _he Main an_ Isolated Busses s, pp_ power _h the ener_zed

contacts of these relays to fire the Posigra_e Rockets and the four

Spacecraft Ad_pter E_losiva Disconnects. _e Posigra_e Rockets create

sufficient thrust to separate _he spacecraft from the adapter. _e

allows the eh,.ee Spacecraft separatlc_ T-4_rlt _t_he8 _h_h 8re atta_

to the retrograde atr_ps to close. Power from the Isolatea Squib Bus

flows thrce_h the closed eontaets and activates the _i Spacecraft Sepa-

ration senacr Relay _nich extl_uishes the red m_ CAP_F_E sequence L_ht

-_ _l_,--_--tes the green _P CAPSULE Sequence L_ht. Power through the

6-8

__N_mgJ. SEDR 104

_l Spaceeroft Separation Sensor Rel_y is applied to the Five Seccwlf_

Time Del_ Dempiz_ Signal Relay. _tivat£o_ of the Dmnping Signal Relay

actuates the Orbit Orientation Relay bringing the spacecraft to a S_ °

(blunt en_ up) orbit attitude.

6..8. RE-_

6.9. nE an OS

In order fc_ the spacecraft to 4roD.act at a desi_ated area, the re-

entry sequence must be initiated appro_-_tely 3000 nau£ical miles

rau_ of the to_chdovn point. _e method of t-_tiat_-_ nocm_ re-entry

sequence is by the clos_n_ of the Retrograde Firing Signal Switch viThin

the Satelli_e Clock. The switch may be actlva_ed by the run-o_t of tlme

pre-set into the clock prior to _ for a calculated re-entry time.

Timing starts at booster liftofT. The ,.4.m may also be pre-set by the

astronmat or by ground c_...,L_-a vhen necessary. _he sequence may be star_

directly by using ground command tran_tters and the Spacecraft

Receiver. _e final method is for the astronaut to m....lly start the

sequence by pressing the Retro Sequence Button. q_e last tvo methods

by-pass the Sate111re Clock. A brief resume of the sequence starts with

the closing of the Retrograde Firin_ Signal S_Itch, _hich energizes the

Retro Sequence Fire 30 Second Time Delay Relay. After the spacecraft has

attained the proper attitude and the *-__ delay has run out, the Three

Retro Rockets will fire 5 seeo_s apart. When the Re'fro Rockets fire

and the Auto Retro _ettlson Switch is in the "A_M" position, the Retro

Rocket Asse_ Jettison 60 Secon_ Time Delay Relay is energlse_ and at

MCOONNmLL $EDR 104

the run-out of the 60 second t_._ delay the Retro Package is Jettisoned.

_he Retro Packa_ separation is sensed and results in the separation of

the three Betro Package Electrical U_ilicals.

6-1o. OPEP,ATIO_

The Satelllte Clock Retro FAre Swltch is armed by _In Squib Bus

power _hro_h the Spacecraft Separation Relay contacts (See Figure 6-4).

With the Retro Delay Switch in the "NORM"position and the Retro FAre

Switch closed by any of the three previous_ mentioned methods, the Retro

Rocket Sequence Indicator Relay is activated _11,m_latID_ the green RE_R0

Indicator Light. With the Retro Delay Switch in the "INST' l_Osition,

power is supplied direct_7 to the contact of the Attitude Permission

Relay No. i by-passing the 30 second delay. _he astronaut may _,,_11y

start the retro sequence by pressing the Retro Sequence Switch on the

left hand console which _1_ energize the _rgency Retro Sequence Relay

and allow the nor_=1 sequence to be fo_1owed. The Retro Interlock Switch

in the ASCS Calibrator closes allowing power to flow through the Emer-

gency Retro Fire No. i Relay and energize the No. i and NO. 2 Attitude

Permission Relays when the spacecraft is in the proper position for retro

rocket firing. The red RETRO ATT Telelight is switched on when the Retro

Rocket Sequence Indicator Relay energizes at the start of the Retro Se-

quence.

Normal_7_ the Attitude Permission Relay extinguishes the red REPRO

A_ Telelight, 111,_-_n_tlngthe green light and energizing the Retro

Signal Latch and the Retro Rocket Fire Relays. Power from the Isolated

S_ulb Bus is now routed throu@h the Retro Rocket Fire Relays to the

6-I0

__NIki SEDR 104

]_tro Rockets in t_.. firing first the Left (No. I) Rocket, after a

".) second time delay the Bottom (No. 2) Rocket an_ 5 _conds later +:h,___

1_Ight (No. 3) Rocket. _ough the Retro Signal Latch Relay: a circuit

_ill be c_leted to energize the Retro Fire Signal Disengage 23 secon_

!_uneDelay Relay. _-e power to the coil of the Retro Fire Signal Dis-

,engage Relay allows the circttlt to be completed to the ASCS Calibrator

resulting in high-torque RCS operation. _-_s high-torque operation

w_1 _ last for 23 seconds, which is 3 seco_Is more than the auration of

total retro rocket firing. Be high-torque mode holds the spacecraft

in the 34° attitude while the rockets are firing. At the en_ of 23

seconds, the Retro Fire Signal Disengage 23 Secon_ Time Delay Relay will

energize remo_ power fron the Retro Fire Signal Relay and thus remov-

ing the h_h-torque signal. With the Attitude Switch in the "AUTO"

positlon_ the astronaut may press the Retro FAre Switch energiz_ the

No. i _rgency Retro Fire Relay AIlowing Isolated Bus power to energize

the No. 2 Emergency Retro Relay, firing the Retro Rockets when T_ space-

craft ass,_e T_e proper attitude. With the Retro Attitude Switch in the

"BY-PASS" position, -ha pressing the Retro Fire Switch which energizes

the Attitude Perm_ssio_ By-Pass Relay, the Retro Rockets will be fired.

regardless of the attitude of the spacecraft. When the Retro Signal Latch

is energized_ Main Squib Bus power is supplied,to energize the Retro Rocket

Assembly Jettison 60 Second T___ Delay Relay and the Retro Fire War_

Light 15 _econd _-- Delay Relay. After the 1_ second time delay has

run ont_ the red FIRE RETRO Telelt_ht is ill,_t-=ted. After the +_ee

_-12

__NNEIkA. SEDR 104

Retro Fire Monitor Relays are energized_ the red FIRE 1_I_0 Teleltght

r_ goes out and the green light is $11,m_n_ted. At _he en_ of l_e 60 sec-

ond time _elay, the Retro Rocket Ass_l_ Jettison 60 Second _-_ Delay

Relay a_ovs pover to energize t_e Retro Rocket Ass_m_l_ Jetttsou Rela_

end the Jettison Retro Warnl_ L_ht 2 Second Time Delay Relay. As _he 2

sectmd t:lme de_ Is exp_-_d, the red _ 1_'_0 TelelXght is 111,-,_na_l.

_he Retro Rocket Assem_]7 Jettison Relay directs Main and Isolated Bus

power to the two squ_s of the Retrc Rocket Ass_z_ly Jettison Bolt.

be bolt rill t_acture and the package _rl_ drop free of the spacecraft_

heine assisted by a coil spring Installed be_een the heat shleld and

Retro Package Assembly. _e dropping of the Retro Package Assembly from

the spacecraft _J.l a_ov the three Retro Rocket Assembly _srsttou Sen-

sore (stn_e pole l_mtt svltches) to return _o their normal poslttou

energtzin8 the Retro Rocket Assembl_ Separatlou Re_. _hls v11_

the Retro Rocket Aseemb_ UmbilXcal Separation Relay to energtze_ firing

the six squlbs of +h_ _2_ree Retro Rocket Packaee _tllcala and _etttsc_

the elactrieal ,_tltesl pl_s _1_ ]_oeec_ls after dropptn8 of the _tro

Package. When the Retro Rocket Assemb_ Umbilical Separation Rela_ Is

activated, it removes power from the red JETT 1_0 Teleltght and i_ _,_-

nares the green light. When the Retro Rocket Assembl_ Separation Rela_

is energized, it activates the Accelercmeter Arm _ Second Time Dela_

Relay. At the end of the 5 second t_ae _elay_ the relay functions sup-

plying a ground for Main Btts power which operates the .05g Relay. _he

energtzing of the No. 1 and No. 2 .05g Retro Sequence Drop_ .05g Jetti-

son Asse_ly Sequence Drop, and .O5g Retro Teleltght Power Drop t_rouEh

6-13

__NNgLL SEDR 104.

the contacts of the .05g Relay removes power from the various relays

and switches involved in the retro sequence as well as extinguishing

the retro telelights.

6-ll. ESCAPE

6-Le. GmmRAnESCZ: XX=' ION

The escape system pr1-_rily consists of a tower assembly designed

to provide a safe means of abort between pre-launch andstaging. By

utilizing the Posi_rade Rocket System, escapes may st_.l] be initiated

after booster staging and throughout sustainer operation until orbit.

The tower assembly consists of a i0 foot, tubular steel structure with a

4 foot Escape Rocket mounted %o its tapered end, A se_ented cls_p ring

with 3 explosives _olts secures the base of the tower to the recovery

compartment upper flange. Attached to the Escape Rocket Nozzle Adapter

Plate is a Jettison RocEet which is used to Jettison the tower assembly

after the Escape Rocket has been fired for an abort; however, under nor-

real launch conditions the Escape Rocket is fired to accomplish tower

separation at time of booster engine separation.

6-13. ESCAPE __ORE LIF_0FF BEFORE _ILICAL DISCONNECT

0nly one gro-nd controlled signal will energize the Mayday Relays.

This signal is a direct hard_line from the blocE hollse Abort Switch to

the MaydAy Relays. The sequence (Ref. Figure 6-5) to energize the May-

day Relays is as follows: The Abort Switch is activated energizing the

50 Micro-Second Time Delay Relay. 28 volts is applied through the 50

6-14

I¥1CDONNELL SEDR 104

F',/

z_N

u >" _.,__Z

v-

_ >_

_ z_ _._ _8

o u_

8: _

.... _i_'"_

FMI 8-149

Figure 6-5 Escape Before Liftoff Before Umbilical Disconnect

6-15

NNiiLL SEDR 104_

Micro-Second T_-_ Delay Relay contacts and through tb_ m_ssile to the

Mayday Relays. In the event the spacecraft must be aborted on the

launch pad and the m_ssile is unable to tran_tt the hardline abort

signal, there is one other method which may be selected. Umbilical

Pins _ and 45 are abort wired and transmit 28 V power from the block

house to the spacecrai_'s Ground Co.w-nd Abort Signal Latching Relay

energizing a na locking in the relay. _rough this energized relay space-

craft 28 V Squib Arm Bus power is transmitted to the pole of the Ground

Test Umbilical Relay; however, power will not continue through this relay

until the relay is de-energized. _e only way the relay may be de-

energized is by ejecting the ,m_ilical. _herefore, if this abort

method is required to be used, it woula be necessary for the block

house conducter to select the Abort Switch (power to pins _ and _5)

and within mi_l_seco_ds thereafter the ,w_ilical is ejected. After the

Mayday Relays are energized, the escape sequence is the same as explained

in paragraph 6-16.

6-1_. ESCAPE BEFORE T_TVTOFFAFTER _3ILICAL DISCONNECT

During countdownj there will be apprn_4mate_ 50 to 90 seconds between

time of spacecrafts unbillcal eject and time zero, which is two inches

liftoff. During this period, the three available methods of abort are:

(1) _-e block house to missile hardline abort signal as explained in the

previous paragraph; (2) Ground c_.!_nd receiver abort signal; (3) Astronaut's

Abort Handle. _hese three methods all result in energizing the Mayday Relays.

6-16

_PN_fl./. SEDR 104

After liftoff, (Time Zero), there ere three methods by which an abort

may be _-_tiated_ _ey are: (1) Ground c_n_d receiver abort signal

an_ (2) Ast_=._-,,tAbort Handle, both of which were possible methods in

the prevlov_ _aph, (3) The Booster Catastrophic Failure Detection

System. _s +.bt_ method has been noneffective in the two previous para-

graphs due to the _i TAme Zero Relay being de-energize_. However, ÷_ _i

Zero Relay is energized two inches after liftoff and completes a

circuit to the Nayday Relays if the Catastrophic Failure Detection Relay

is ae-energlzeclby loss of power fron the missile.

6-16.

When the Mayday Relays are energized, the abort sequence (See Figure 6-6)

will occur as follows: The abort Light on the left hand console will _33,--_-

mate, the Spacecraft Separation Bolts Power Relay is energized and the Space-

craft Separation Warning Light Time Delay Relay is energized. _e Abort

Relay in the MA_--_n Altitude Sensor is energizes after Spacecraft Adapter

separation. _e M-_--_ Altitude Sensor com_utes the time delay required for

the spacecraft to reach a safe d_m-4c pressure before _ettisoning the Escape

Tower. The Spacecraft Separation Bolts Squibs will be fired, releasing the

Spacecraft-/_=pter _ Ring and allowing the three _4_4t switches to re-

turn to their n_nal positions energizing the Emergency Escape Rocket

Fire Relay, the Escape Roe_*t Fire Relay an_ the Spacecraft Adapter Dis-

connect Squib Fire Relay, firing the Escape Rocket and the four Spacecraft

Adapter Explowive Disconnect Squibs. _e Escape Rocket's 56,000 pounds

of _ will _eparate the spacecraft frc_ the missile an_ carry it away

fr_n the sustainer at a mall angle. The Spacecraft Separation Sensor

6-18

MODONNELL SEDR 104

T_tm_t Switches also energize Spacecraft Separaticm Sensor Relays, which

turns on the green _ CAPSULE Teleli@ht 3 and also energizes the Tower

Separation Abort Interlock Latching Relay. The Abort Interlock Relay

energizes the Retro Rocket Assembly Jettisca Relay and fires the two

squibs of the Retro Rocket Assembly Jettisca Bolt. The bolt will

fracture and the package will drop free of the spacecraft, being

assisted by a coil spring installed between the Heat _ield and Retro

Package Assembly for this purpose. When the spacecraft reaches a maxi-

altitude, contacts in the Maximum Altitude Sensor will close and

energize the Tower Separation Bolts Power Relay firing the bolts. As

the three tower bolts are fractured, +_e segmented Tower Clamp

separates allowing the *._ee Tower Ring Limit Switches to return to

their normal position energizing the Emergency Jettison and Jettison

Rocket Fire Relays. _ou@h these relays and their parallel contacts

Main and Isolated Bus power will fire the squibs of _b_ Jettison Rocket.

The tower will be Jettisoned clear of the spacecraft resulting in sepa-

rating the two Tower to Spacecraft Electrical Discon-ects. _e separa-

tion of either disconnect will de-energize the Tower Separation Sensor

Relays energizing the Abort Rate Damping Relay ÷_ro,;_hthe contacts of

the Tower Separation Abort Interlock Relay. _nls relay will send a sig-

nal to the ASCS c-remandingrate damping until time of Main Chute deploy-

ment. De-energizing the Tower Separation Relays will also stert two 2

second timers in the recovery sequence. The first timer will arm the

21,000 Foot Baroswitches and two seconds later the second timer arms the

10,600 Ft. Baroswitches.

6-.19

6-20

_O_O_Bg.L SEDR 104

6-17. ESO:'E ATZONF

The methods of initiating an abort after staging are identical to

the methods named for the escape after liftoff and are: (1) Ground

ccemaandreceiver abort signal; (2) Astronaut Abort Handle; (3) Booster

Catastrophic Failure Detection System. AnY of the three methods _ "1]

energize the Ma_l_y Relays. The sequence which occurs by the energizing

-of these relays is described in the following paragraph.

6,.18. OPE TZON

The signal which energizes ÷_ Mayday Relays also is transmitted

to the missile tO shut down the sustainer engine (See Figure 6-7).

_w0t_h contacts of the energized Mayday Relays_ a power circuit is can-

plated to the ABORT Light on the main instrument panel and the .20g

contacts of the _h_us_ Cutoff Sensor are armed. As thrust decays to .20g,

the contacts close and energize the Spacecraft Separation Bolts Power

Relay firing five Spacecraft Separation Bolts squibs and zeparating the

Spacecraft Adapter Clamp Ring. The sequence following clamp ring sepa-

ration is the s_ as the normal sequence (Refer to Paragraph 6-7). Re-

entry may be accomplished by any of the emergency procedures (i.e., astro-

naut or ground initiated). Refer also to Paragraph 6-9. If the abort is

initiated before the spacecraft has obtained the correct velocity fc_

orbital flight and it is not desired to fire the Retro Rockets, the Retro

/ Package must be Jettisoned manually, it sh_,!d be noted that even if the

spacecraft does not attain orbital velocity, the quickest way for re-

entry is by _a_rgency firing of Retro Rockets.

6-21

SECTION VII

SEQUENCE SYSTEM, LANDINGTHROUGH RECOVERY

TABLE OF CONTENTS

TITLE PAGI

Automatic Sequence Description .............. 7-3

Automatic Sequence Operation ............... 7-4

Emergency Sequence Description ............. 7-7

Emergency Sequence Operation .............. 7-1(

System Components ................................ 7-1_

7-1

JWOOO_NmLL SEDR 104

vii. s imcESYSTmLAmminG m0UGHm covm z

.... 7-m. AOmU TICSEQUm CEm sc oN

_e _a-_4_ end recovery sequence system provides automatic electrical

and mechanical sequencing to land the spececrat_t safely after an ab_ or

normal re-entry_ and to Initiate locating aids for assistance in the sub-

sequent recovery. _e pr_mmry (completely aut_matic) system incorporates

e drogue parachute, used initially to decelerate and stabilize the space-

craft in the inttisl phase of recovery and a main parachute for further

deceleration. Redundant circuits have been incorporated to eliminate the

possibility of stng_e-point failures. The landing Is accomplished utiltz-

Lug a 63-foot-dlsmeter parachute which is deployed at 10,600 feet. In the

event of a main chute failure, a 63-foot-diameter reserve chute may be de-f

ployed by the astronaut's m.anualselection. Both main and reserve chutes

are reefed tO 1_m_t s_ock loads at initial opening. _he reefing line is

severed autcuatically after a pradetermine_ time delay and the chute will

open ful_, lowering the spacecraft at the prescribed l-ridingspeed. A

souna f_ and ranging (SOFAR) b_ is attached to the main chute risers

and is releaser as a function of main chute deployment. When the risers

I_,_Itaut, f_e b_._ is ejected and falls to the ocean ahead of the space-

craft. When the b_._ reaches a depth of 2,_00 feet below sea level, it is

detonated thus provla_-ga means for deter_-_ng the appro_m-te location of

the spacecraft _n_,g area by soun_ fixing an_ ranging stations. After

main chute deployment, the landing impact bag is extended, providing a

cushioning effect for the landing impact. After impact, the ma_n chute

is autc_aticall_ disconnected followed by reserve chute ejection; how-

ever, chute disconnect is delayed as a function of the Rescue Aids Switch:

in autc_atlc (AbvfO),a 10-minute delay is accomplished; in manual (MAN), a

cue-second delay is accc_pllshed. _erefore, if the astronaut desires7-_

m_DO_N/B._. $EDR I04

t_med£at_ chute meparation at 4.Tact_ he must positi_ the Rescue Aids

Switch to the "MAN"position at impact to by-pass the 1D-minute delay (at

any portio= of the lO-_,_te _elay r_.4._._ after :Impact). _e astro-

naut will _ egress no_a]__y taking with him the survival klt which

containsa 1_ee raft and other survivalaids.

7-2. A_TIC ._, OP_

On rover separation, power is removed from the Tower Separation Relays

_he Main Chute SyltemArm 2-Secoz_l _J.neDelay Relays tO be ener-

gized (See FA_n-e 7-i). After the 2-secondtime delay has run out pover

_icws throughthe closed ecuta_tsenergizingthe Main Chute2-Second

Time Delay Relays, and a_ter a 2-second_elay arms the No. 1 10,600 ft.

Baroswltchthroush+h. 10,600 ft. Arm Relay cc_tacts. 5_e No. 1 and No. 2

Baroseitches are _ired in seriesthereby requiring both swatches to be closed

before normal m-tn chute deployment can be accc_lishe_, q_e No. 2 21,000

ft. Baroswltohis arme_ +_oush the closed contactsof the Main _ute Sys-

tea Arm 2-Second Time Delay Relays. Upo_ descentto 21,000 ft., both the

No. 1 and No. 2 21,000 foot Baronltches, which are wired in series,close

_hereby energizing the D_o_e Deploy Rels_, _ the Drogue Chute M_Gar,

deployingthe I_ Parachute. _he Drogue Chute stabilizesan_ decelerates

the spacecraft. At sppr--4:_te_710,600ft., the 10,600 ft. BaromrAt_hes

actuate the _,4. Deploy Relays resutting in the r_oval of the squib ground

cix-euits and _ o_ all four squibs of the Antenna Fairing E_ect_r. Also,

the Main Deploy Warai_ Light 2-Seconcl _,,,_ Dela_ Relay is ae_uate_, a_

at the end of 2-seoc_l del_ the ze(1 Main Deplo_ Telellghtis l_--4--te_.

_he Antenna Fairing Sepeawtic_ Sensor Arm Rela_ are energized _ the

74

__NNMLL SEDR 104

closed cc_ta_ts of the M_n Deploy Relays arming the two Antenna Fairi_

Separatin_ Sensor Swi_es.

_e firing of _A four Antenna Fairing EJectc_ Squibs causes the

Antenna Fairing to separate from the spacecraft. A la_Lrd_ co_nected

from the Aute--a Fairing to the Main Chute_ extracts the Main Chute from

the chute c_ax_nt. The Main Chute opens _.Itla_ in the reefed con-

dition to limit shock loads. Four seconds after the chute is deployed, the

reefing 1t_e is severed by a pyrotechnic c_ge in the reefing lane cutters

alAowing the para_,_te to open _y.

_he separatic_ of the fairing from the spacecraft o!lows the Antenna

Fairing Separatlo_ Sensor Switches 1;o functlcn. _]_coushthe switches,

power is routed to energize the Main Ejector Relay firing the Main Ejector

Bag Squibs. _ _ squibs fire_ _hey generate a gas_ filling the E_ec-

tot Bag at the bottom of the Main Chute compartment aiding the e_ectton of

the chute. At _he same time the Antenna Fairin_ Separation Signal Relays

are ener_Ize_ i1?,--_,atln8the _reen Main Deploy Telelight and re_ovi_

power from the re_ telelight. Power Is also directed through the Autenna

Fairing Separatic_ Sensors to energize the Main Inertia S_rltchArm 12-

Seeo_l Time Delay Relays. After the 12-seco_ time _elay has run out, the

energized contacts allow power to be supplied to energize the ___ding Ba_

Extend and Landing Bag Naming Light 2,-Secon_ Tt_ Delay Relays as well as

to the Inertla Switches. _he closed contacts of Landln_ Bag Extend Relay

fire the squibs of the Landi_ Ba_ Valve releasin_ the heat shiel_1and

extending the impact landing bag. As _ 2-secon_ time delay runs o_t,

7-5

_ONNi_LL SEDR 104 @

the Landing _ Ws_ Light Relay illmminates the red T_ndiD_ Reg

Telelig_ht. Upon heat shield separatlon, the Ianding _g Unlock Sig-

nal T,_m_tSwitches are actuated and through its closed contact_ power

from the Auto I_ Bag Fuse is directed to energize the T_,_

Bag Extend Signal Relay ill_ti_ the green Ta.A_n_ Bag Telelight

and extinguishing the red light. _he force of impact on la_i_

operates the T-ertia Switches which provide power to the coils of the

Impact Relays. Through the closed contacts of the Yzpact Relays, power

is supplied to energize the Post Tal, w14._ _Sr_ Re.B° _,_h the

activated contacts of the Post T_,A_,_ System Relays, power is tr_---

mitred to energize the Impact Signal Relay. Also through the closed

contacts of the Post T_In_ System Relays, the Flashing Recovery

Light circuit is ccmpleted sett_n_ the light in operation. _en the

Impact Signal Relay is energized, the green M_in Deploy and T_nd_,=

Bag Telelights are exttnsulshed and the red Rescue Aide Telelight

is ill-m4-_ted. With the Rescue Aids Switch in "MAN", at the end

of the l-secoDd time delay, the Spacecraft Stabilization Relay is activated

allowing the Main Disconnect and Reserve Disconnect Relays to be energized;

with the switch in "AUTO", this action is delayed I0 minutes. _ough the

energized contacts of Main Disconnect Relays_ the Main Chute Discannect

Squibs are fired, releasing the main chute from the spacecraft. _e Re-

serve Disconnect Relays fire the Reserve Chute Disconnect Squibs releaetDg

the Reserve Chute an_ energizing the Reserve Deploy Relays. The Reserve

Deploy Relays fire the Reserve Chute E_ector Bag Squibs. The Reserve

7-6

"_M_DONNffLL SEDR 104

Chute Ejector I_g Squibs activate the _s generator which has a one-

second delay in ignition time before inflating the ejector bag ex-

pelling the Reserve Chute and the dye _rker. When the Rescue Aids

switch is placed in the "MA_" position or s_ter the 10-minute delay

with the s_tch in "AU_0"_ the Rescue Aids Switch Signal Relay and the

Post Landl_ System Power Drop Hold Relay are energize4, q_e energized

Rescue Aids Switch Signal Relay removes power from the red Rescue Aids

Telelight and tll,_nates the green light. _e Post-I_ADg STstem

Power Drop Hold Relay energizes the Post-Ta-dln_ System Power Dzop 30-

Second Time Delay Relay. At the end of the 30-second t_._ delay the Whip

Antenna Extend Relay is energized firing the Whip Autemm Extend Squibs

activating the gas cartridge exteDdl_ the active element of antenna to

its full length. _hen the Post-EandAng System Re_ys are energize_ on

iml_t and, depending on the position of the Rescue Aids Switch, power is

applied t-_4£ate_ or after a 10-minute time delay to the coil of the

Post Landing System Power Drop Hold I_ .,_-Ito the Post I_d_ System

Drop _0-Second Time l_e3a_r. After the S0-sec_n_ delay, the Post Iand_n_

System Power Drop Relay is e_r_ize_ which removes power flwm the re-

maining cmqnents except the WhipAntenna Extend aelay.

7-3.

_he emergency provisions of the _ system basle-_ ly consist of

-_.ually-operated back-up systems initiated by the astronaut. _e appro-

prlate button, pu11-rin_ and switches are located on the Left Hand Con-

7-7

_ONItlELL SEDR 104

\'\

-ANTENNA FAIRING

I "SOFAR BOMB

HF WHIP ANTENNAi

' PILOT CHUTE LANYARD/ i

IE CHUTE RISER

/

:HUTEHUTE

"" "_ PILOT CHUTE RISER

DEPLOYMENT GUN

/ RESERVECHUTE TO ANTENNA FAIRINGEJECTOR SAG

PILOT CHUTE lANYARDTO DEPLOYMENT

DYE

RESERVEPARACHUTE

PILOT CHUTE RISER

FM18-65

Figure %2 Main and Reserve Parachute System (Sheet 1 of 2)

7-8

_rMCDONNELL SEDI{ 104,

CHUTE

ANTENNA

FAIRING _

SOFAR N3_/

DYE_RKER

FM18-65

Figure 7-2 Main and Reserve Parachute System (Sheet 2 of 2)

7-9

__Nm_t. SEDR 104

sole. The emergency system controls manusJ__-tnittated _eployment of

the Drogue, Main and Reserve Chutes, extension of the LsndJ_g Bag, and

initiation of rescue aids.

7-4-. msms OPZaATIm

On descending to 21,000 ft., if Drogue Chute failure is detected by

lack of opent_ shock and _y a visual cheek through the window, the astro-

naut will depress the I_ogue button (See Figure 7-3). Depressingthe button

allows the Emergency Drogue Deploy Relay to be energized and the Dro@_e

Chute Mortar Squibs to _e fired deploying the Drogue Chute. If the green

Main Deploy Telell_t fails to t"!],,,.t--,t_, failure of the _nt Chute to

deploy may be detected by a lack of opening shock, a visual check and no

decrease in rate of descent. Upon determining that the Main Chute has

not deployed, the astronaut will place the Recovery Arm Switch on the Con-

trol I_I to the .mmml position. If Main Chute Deploy is stl]_ not

sensed, operating the Main Deploy Pull Ring energizes the Emergency Main

Deploy Relay, firing the Antenna Fairing Ejector Squibs, ejecting the

Antenna Fairl_ and deploying the Main Chute through the nor -_1 aut_-_tic

sequence. When the green _4_ Deploy Telelight is ill-m_-ated and the

rate of descent is greater than 32-feet-per-second, the chute is vls,m_ly

checked for damage. If the chute is damaged or did not deploy, actuating

the Reserve Deploy _,11 Ring w_11 energize the l_serve Deploy Relays.

_yugh the energized contacts of the Reserve Deploy Relays, power is

applied to the F,_t. Chute l_sconnect fi_ the squibs disconnect___ the

chute frc_ the spacecraft. At the same time, the Reserve Chute E_ector

Bag Squibs are fired _nerati_ a gas after a 1-second delay and _n_4ati_

the ejector bag which aids in deployiu_ the Reserve Chute.

7-10

MCDONNELL SEDR 104

EMERGENCy _ DROGUE CHUTE

DROGUE DEPLOY MORTAR DROGUERELAy SQUIBS CHUTE

DROGUE CHUTE _41 _L_iL_T_" o_-L

EMERGENCY MAIN ANTENNA FAIRING J_DEPLOY EJECTOR

RELAy SQUIBS

MAIN CHUTE DEPLOYED BYTHE AUTOMATIC SEQUENCE

MAIN CHUTEFALLS TO DEPLOY

RESERVECkfLITEDEPLOY GUN

SQUIBS

PILOT CHUTE

RESERVE MAIN CHUTE

f DEPLOY DISCONNECTRELAYS SQUIBS

RESERVECHUTE

EJECTOR

MAIN CHUTE FAILS _IAG SQUIBS

TO DEPLOY OR IS EJECTOR BAGDAMAGED

• ELECTRICAL SLGNAL Ill

!I_ MECHANICAL

I MOVEMENTGAS INITIATED

EMERGENCY EMERGENCYLANDING BAG LANDING BAGEXTEND RELAY VALVE SQUIBS

LANDING BAG

MAIN CHUTE

DISCONNECT ILANDING BAG SQUIBS

FAILS

RESERVECHUTEDISCONNECT

RESERVE CHUTEDEPLOY GUN

SQUIBS

PILOT CHUTE

I0 MIN. T.D. _ RESERVECHUTEJ EJECTOR BAGSQUIBS

NOTE: RESCUEAIDS SWITCH I

PCSITtONED TO "MANUAL" TO RESCUE AIDS I 30 SECJ .D. EJECTOR BAG

BY-PASS "AUTO" 10-MINUTE DELAy. (10 MIN, T.D. RELAy) WHIP ANTENNASQUIBS

WHIP ANTENNA FMI8-66A

Figure 7-3 Landing and Recovery Emergency System

7-11

ml_OONNBZ.L SEDR 104

Twelve seconds s__er the Main Ch_ is _p_j_ the green

Bag _llght should be t_.md_a1_1. If the light d.oes not cm_ on, pl_e

the Landing Bag S_Ltch in the "MAW"positions enm'Slzi_ the EuergeneT"

Landing _ Extend Relay, f_rJ:S the l_-rgoncy Land_S BsS Valve Squibs,

releas_ the beat shlel_ end _ the impact _ bag. Ten

u_nrtes after _ the Rescue kLds Sw£tch By-Pass Relay is ener_Lzed.

_lhon aetlva'._ the relay by-passes the Rescue A_ds Sw£tch and enar_zes the

rel_m vh£ch mq_l_- po_r to fire the Math Chute D£sco_-et 8qulbs as yell.

as "the squibs for the Reserve, D£seonneetj Deploy Gun, _ the _ector Bag

In the mine a_ner as if the mritchwere place_l in the "MAN"position.

mo m

_e 6rc_w parachute ass,._l.y (See Figure 7-5) eo_slstsof a eon_ea_

ribbo_1-t_ _ogue e_nop_ vitb _1%'£ser, drogue _plo_ beg_

_ro_e mortar, sabot, aria &rogue mortar cover. _e drogue parachute cano-

py 18 a conical ribbon parachute havi_ 8 gores of 2-1nch wlde_ l_O-lb.

tensile strength ribbons on_ 8 tubular n_lon suspension lines of 1,(XX)-lb.

tensile strength each. _ para_-te is constructe_ to a dl_eter of 6.85

feet end per,m-entryreefe_ (restricted)to an efTecttve d_a_eterof 6.0

feet by ,.e--,_ of pocket bands. The ccnst.w_te_ total porosity is 27.9%

and the effectivepc_oelty (_hro_ ree_) Is 36.3_. _he 30-ft.

Integralriser is made frcw three layers of 3,000-1b.tensilestrength

low-elevation hot-stretched Daero_ webbing. _he drogue parachute stabtli-

7-12

,MCDONNELL SEDR 104

1 ANTENNA FAIRING EJECTORGUN 9 SHARKREPELLANT

2 PARACHUTEDISCONNECTS(2) 10 DROGUEMORTAR3 RECOVERyLIGHT 11 WHIPANTENNA4 ANTENNA LANYARD 12 PILOTCHUTEDEPLOYMENTGUN5 BARDSWITCHES(4) 13 PILOTCHUTE6 MAIN CHUTEAND SAG i4 RESERVECHUTEAND BAG

15 SEAMARKER7 EJECTIONBAGS{2) 16 INERTIASWITCH8 GAS GENERATORS(2) 17' SOFARBOMB.

J NOTEVII_V LOOKING INBOARD

LEFTHAND SIDE

FM18-67

Figure 7-4 Landing and Recovery System Installation

7-13

• _

_ONglELI- SEDR 104

FMI8-68

Figure 7-5 Drogue Parachute

7-14

1. "O" RING 5. CA_[RIDGE

2. SABOT 6. CHAMBER

3. INSULATION

4. COVER

Figure 7-6 Drogue Chute Mortar Assembly

R3"IPROTECT'VECAEPLECTR'CALCONN"C'O"_R'"C"AMBER!!ATTACHMET_0B_"T_'N'"OOR_'NOPL0_O0_BiFMI8-74

Figure %7 Main and Reserve Chute Gas Generator

7-15

__ma.a. SEDR 104

zes and decelerates the spaeeera_. _ canopy weighs 2..9 Ibs. wlthout

riser and 5.9 ibs. ine_ the 30-ft. Daero_ r_ser. The _c_e pars-

chute deployaent bag serves a _ual function of (i) protect_ the drogue

parachute _ eJe_ a_ (2) _ means_or order:_ dep1oymnt

of the &ro6ue parachute. _he bq is _A__eactlxred of cotton saracen fab-

ric reinforee_l vith _1_ vebbing aria covered at the upper en_ vAth a

heat insulato_of glass cloth. _he bag is weighte4 at the upper end

vlth a 0.5 lb. lea_ &isc_hlch assistsin strippingthe bag fr_ the canopy

at the c_.__leticnof 14.A and riser stretchout. Inside the bag are

cotton tapes to v_4_h the riser is secured _uring packing in order to pro-

vide orderly riser deployment. _he mouth of the bag is closed vith a

light cott_ cord.

7-7. modus_ _o_ _rDS_SO_

_he _ parachute e_ectio_ mortar is a device for positive Ae-

ploy_nt of the drogue parachute _rAth sufficient ener_ to overe _ l_al

pressure gradAe_ts an_ _avitaticnal forces. _he 4roL_e parachute is

packe_ in a protective bag an_ stove_ in _he molar tube o_.top of a

_ASht_t sabot (See_ 7-6). :he sabot _me_ns as a p_s_onto

e_ect the parachute pack, when pressure_ i_ below by gases &_nera_

frc_ a pyrote-_-_c charge. _ae propellant charge is _-ttial_ fire_ into

a breech eh..-_er of mall volv_e, to produce high pressure _nlch is sub-

sequent_,7 vented through a small orifice sad into the main ,_-._er at rel-

attve_,7 lover pressures. In this M--e_, reaction loads are kept to a

.4.4,_._ since the pressure energy is not e_enAed instan_aneousl_. _he

7-16

"_MO_NNE£_. SEDR 104

pressure se:!4-u quality of the sabot is derived from an "O" ring, in-

stalled in a _ve near the base. Two mall holes are located in _he "O"

x_ groove to ve_t air _ra_ped in the mortar tube u_er_a_h _ sabot c_

instalAaticn. For proper operation_ the "On ring and the inner wall of

_ m_ar tube_ which Is always in contactwith the "0" ring, are _.-

brica_e_ before installatic_. Be dro_w parachute pack is retaine_ in

its et_ posltlcDvAthia _he mortar _e by a _ metal "Rene-_l"cover

which is attached to the upper surface of _e antenna houai_, q_wee cut-

out sectic_s_ provide_ in the sides of the cover, permit routing of the

steel cable risers into the drogue chute can. m_o cover is designed to

constrain the chute in its comp_t a_t negative decelerations and

also to require m_-_m-I forces to break loose from its attaohm,nts at the

time of deploy_nt.. Pressure of _he chute pack causes _he cover "to deflect

in such a ma_r that atte#_t tabs i_,11o_t from _der attachingserev

heads th_ a slotteAhole designedfor this purpose. _he ener_ required

to expel the Aro_ue chute from its compartmentis provided fromhigh pressure

gases, _enera_edby i_nltlon of a pyrote-h-_ccharge. _he cartridgeis

1Oe_0___Ath 66 grains of powder, contained in a propellant can attached

to a steel bo_ _nich hooses the lgni_lon w_J_ anA terminates in an

eleetrlcalconnector. Be i_nltlc_ circuitryeomslats of two separateand

IndlvIAualbridges, either of which is capable of ignitingthe power charge

upo_ applicatic_ of the proper current.

7_. MAINPARA_

_e main parachute assembl_ consists of: main parachute canopy,

riser, deployment be_, and parachute disconnect. _he main parachute

7-17

_ONNELI- SEDR 104

Figure 7-8 Main Parachute and Packing Box

I , STRUCTURE 5. SHEAR PIN i

SHORTING WIRE 6. PISTON3] SQULBCA_RIDGE 7. LEADBUFFER4. BUSHING 8. ARM

FMI8-71

Figure 7-9 Main and Reserve Parachute Disconnect

7-18

At'ICDONNELL SEDR 104

/

I 1. FIRING MECHANISM 4. SHEAR PiN II

Ii

I2. BODY 5. ELECTRICALCARTRIDGE

3. PROJECTILE 6. MA!NCARTRIDGE

Figure 7-10 Pilot Chute Deployment Gun

FMI8-73

Figure %11 Parachute Ejector Bag

7-19

_N_m£.L SEDR 104

canopy ls a 63-foot DRY4"-1 dtmeter rlngsstl type. _he rlz_sall para-

chute ls fabrtcate_ from 2,25- and 1.1-ounce per sT,_e yar4 nylnn para-

chute cloth into _8 gores with _8 suspension l_s o: _:_-poun_ tenslle

strength. _he :-_- parachuteis pa_ke4 in a deploymnt bag -._h:J.ehpro-

vtaem a 1_ sna_ force aria orderly aeplo_en_ (See FA_n_ 7_). _e

bag is :anufa_tur_lfro: cotton sateenfabric,relnfcree4vlth _Icn

vebbing an_ eovere_ a_ the upper end vlth _:erao£1ex enA glmmecloth

insulation. _4de the be_, :i4n_ along its length,is a pair of trans-

verse lockingflaps. _helr funetlcn Is to separatethe canopy fabrle

fr_ possible _t v_Lth the l_-As and to eause full 11he stretch-

cutbeforecanopydeploy.

7-9. P_ DZsc_

Both main and reserve parachutes are att_rh_d to the spacecra_ by

a device designe_ to sustain the parachute loads during descent and to

disc_-_ct _he pe_achute. _e chute is disconnected 10 -_w_es (+ 3. see-

c_) a_ter _act _Ath _ Rescue Aids S_ltch in "_TO" o_ _ 8ecc_ after

positioning the Rescue Aids S_Ateh to "MA_" (a_ter l_pact). _- ass_l_

consistsof _ separatedetailsinst_1_l in a mounting _ure vhlch is

an integralpart of the space_ra_t. _e parachuteriser is _ around

the am _hlch transal_sthe load to the structurethrcushthe plstc_. The

shear pin restrains the piston frc_ a_ _ion te_a4_ _o dAsplace tt.

_hen the chute _iscc_neetsignal Is ec_le_) a squib cartri4geis fired

an_ _ resul_ e_pand£_ gas fc_ces _- pisS;on fca_ard into the arm

recess_ cuttlng _he shear pin :In the process. F.11 d.lsplaee_e_t of

7-20

'_._Hmg.i SEDR 104,

p£stc_ removes par_;;_e load. tranm_ss£c_ to s_unture_ a_ the

_ am to ro_e around, t_e p£vot pin. _he loop of _he parachute riser

slips off the arm end the disconne_ funct£o_ i8 ca_lete. _e lea&

buffer serves to absorb e_-_gy of moving g£st_ en_ prevents rebom_

of _ p£_tc_ back into the _ pos£_£v_.

_e reserve parachute assesb_y consists of: the pllot chute deploy-

gun and _s p£1_t para_ute I reserve parachute canopy_ reserve

parachute deployment bag_ en_ reserve parachute d_sconnect. _ reserve

parachute deployment bag ls s4u_lA_ to the main pare_h_,te deploymen_ bag

with the addition of flaps st the upper ena of the bag to contain the

_ p£1ot chu'r,e, q_e reserve parachute d_sccnnect is Identical v'J.'_

_et used to dlsccanect the m_n parachu_. _he reserve parachute cauop_"

is _entleal w£th "the main pa_-_ute eauop_.

7-11. PILO_ PARACSU_

_e pilot parachute is a fl_; eircular type_ 72 inches in dXe_er

w£th a 30 _. bridle. It is --.ufaetured at 3._-o.nce per square yawl

febrlo In the cauoP7 and 2.2_-ounce fabrlc :in the vanes.

7-12. cruz OTto

step :In T_ae seque__n_e of resez_e p_n'a_hute deplo_zent. Ei%her gas presst_e

or ma elec'brtcal tzqp,_,,e _ cause the gun to fire, thus extmLli_ a 12-

ot_ee ]pz'o_e_.-t_ile Idlt¢31 is at_aclze_ tO _Aze msez_e parachute pilot; chttte.

%21

__i1"_ ' SEDR 104

_he pilot chute Inflates and in turn _,II. out the:reserve

chute, ccmpletlng the sequence. Whether fired electrlea_ or pneu-

matlca_, a c_e-secc_d time delay is provided between receipt of the

end detonatic_ of the maln charge, q_S delay permits the ma4n

parachute (if deployed and damaged) to separate frmt the spacecra__ to

avot_L entanglmnent vAth the reserve parachute to be deployed. _ gun

is basicall_ a tub-la_ body _nlch ccntalns the main firing eartridge

and the pro_ectile assmbl_. _e projectile ase_a_ly is held in place

by a pin which is aheare4 _hen the projectile Is expelled. _e main cart-

rldge, which _nerate8 the gas pressure to eject the projectile, is fired

as follmm: (i) Gas pressure, through +-_,. gas firing :ec_antm (s_pplle_

when RESERVE PULL-RI_ is operate4), drives a fi_ pin into the primer

cap at the base of the ,.a_ cartridge, 4n4tlating a time delay train,

causing a subsequent detonation of the charge. A m_,_m of 750 psi gas

pressure is required fur pnemmatlc operatlcn. (2) An electric i_ulse

is received at the time _ela_ igniter Install_ through the si_e of the

gun. A_ter a c_e-secc_d delay, the igniter fires through the wall of the

main cartridge and _etc_ates it instantaneously. Fi_ characteristics

of the igniter certrid_e are as follows: All Fire Current 2._ stopsper

bridge, A]] Fail C_+_nt 0.5 a_ps per brtd_e, q_ i_nttton elrcutt con-

sists of two indAvi_ual bridges termdnatin_ in a _-pln receptacle. _,_z_e

velocity of the pro_ectlle is 250-300 ft/sec.

7-13.P .mm'm mmm,<

The e_ector bags are inflatable air cells made of lightwelght rubber-

ized n_l_ fabric (See FAgure 7-11). _he design _-_lated _ is that

7-22

_'_sM_C_NNILL $EDR 104

of a cylinder I 11 inches in di_eter an_ appro_ate_7 35 inches in

height. _he _per end of the bag is slanted at f_,11 inflation to pro-

mote Jettison of the psrachute pack overboard after impact.

7-14.

_ts is a device to provide a rapia an_ sufficient volmne of gas

to __a_e the main end reserve parachute e_ector bags (See Figure 7-7).

_he reserve parachute gas generator is sI_I,÷ to that used for the main

parachute except the additional feature of I_ second delay in ignition

time. The generator functions to produce gas by the relatively slow

burning of a solid-powder prope11-_t in the main ch-mher. The gas is

directe_ from the main ch-_er into the ejector bags +_ough a 3/8 inch-

dismeter stainless steel tube. The tube serves also as a heat exchanger to

reduce temperatures to wi1_hintolerable values prior to entry into the

ejector bag. The generator body is eq_Lppe_ with lugs for mounting to

the parachute container with four bolts, Ignitic_ circuit characteristics

are as follows: _I Fire Current 2._ a_ps, All Fail C%trrent0.5 amps.

7-15. DYE _ PACg_T

The d_e marker packet is a post lending recovery aid which performs

_its function by dissolving in waterI thus producing a highly visible yellow-

green patch. Apprn_m-tely 1 pound of fluorescein dye is packed into a

soluble plastic bag_ wh4ch in turn is packed luto an outer al,-.1-umcon-

tainer. The entire packet assembly is ejected overboard, at the time of

reserve chute ejection. _e fluorescein dye farms a spot on the ocean sur-

face which is visible from an airplane 10,600 feet high at a distance of i0

miles on a clear day.

7-23

__mo_,J. SEDR 104

CAUTI_

The dye marker pae_e should be strand

in a day place au_ not be axposed to water.

To aid _n the _sual locatic_ of the spacecraft after 1._, a

fleahi_ l_8ht _s Inuta_.l__.nthe recover7 c_pertment. 2he 2ntensity

of the light is such t2mt it will be _stble in normal darkness for 40

nau_£cal m£1es A_ up to an altitude of J2,000 feet. _he fls_ht.a rate

is appr_m-tely 15 flashesper minute. Poweredby a battery pack 3.0-

cate_ within the space,raft,the l_ht's circuitwall be closed +h_gh

energized,contacts of the Post _ SystemRelays which are actlvaT_d

by the closing of the Inertia Sw2tehes on impa_t follcved by the energizi_

the ImpactRelays. _he llght will operatefor approximately28 hours.

7-17.ww_ A_mA

To provide operation of the _F voice receiver-_rsns_ter and. HF

recovery beacon after _-T.act_ a Whip Antenna £s used, _e active element

is stowed, in a collapsed, c_a_tion in the recovery c_partment end _hen

extended is apprn_mn_e_7 16 fee_ I_. _he an_,_- is exteDdedby a

gas cartridgewhich is activate__hen Sb_ Post-Lsndlz_SystemPowar Drop

30-SecondTiae Delay Rela7 energlzesthe Whip Ante--aExte_ Rely7. _he

Post Lendin_Syste_Power Drop 30-Secon_Time Delay is started._-tel_

u_ impactwith the Rescue Aids S_itchin "MA_" --_ after a lO-mlnute

delay _Ith the switch in "A_TO". While it is extendinga galllagaction

takes place between the se_m,_nts of the active element holding it r_Ld in.

the extended position.

7-24

MCDONNELL SEDR 104

Figure 7-12 Baroswitch

FM18-79

Figure 7-13 Inertia Switch

7-25

_M_NNIILL SEDR 104

7-18. BAROSWXTCHES

_here are two pairs of Baroswitches used in the recovery system

(See Figure 7-12). in these switches, an over-center spring is in-

cluded in the design to mi_4m_ze chatter dur4___ vibration an_ Shock

and to prevent contact oscillation. _e switches are located in the

recovery ccmpar_nent t one pair is set to close at 211000 feet; the

other at 10,600 feet.

_e inertiaswitch is essentiallya spriDgdevice actuatedby mass

(SeeFAzure 7-13). A landingshock of 7.5 _!,,_or :Anus i.l_' s min-

im=n will producemcmantaryclosingof two electricalcontacts,thus

c_leti_ an electrical circuit. _h_s SWitch is used in COD_-nction

with a latching relay which receives an electrical pulse and by latch-

ing into the close_ positionl provides continuot_s electrical continuity.

'l_,e inertia switches used consist of four separate snap-action switches

a_d two separate masses_ all housed in a c,_._,_o_case.

A post-lar_llng recovery aid. SOFAR is an abbreviated form for

"sound fixing _ ranging". This component performs its function when

it detonates by l_dro-static pressure at a predetermined water depth.

Shock waves from the explosion are receivea by sound detection devices

aboard picket ships or shore bases and a positio_ fix on the capsule is

thus made. _he _ range of the Mercury SOFAR Bm_ is 3000 miles.

_he SQFAR Bc_ which is tossed overboard by action of the :_,ainchute

e_ecti_n system is preset to _eto_ate at S_O0 ft. (See Figure 7-i_).

7-26

SqVlCDONAIELL SEDR 104

s

\ I/

//

/

SURFPICE PIN5

FIRING PIN-_

-INTERRUPTER

SHE NP, PIN

OPERJqTJONSURFACE

"f_ DETONF_TtON OF THEMRIN cH,qRGE ISRCCOMPLISHEDINTWO STRGE5:

R. W_TER PRESSURE ON SUP.FRCE ",q'CRERTES R DEIONRTORFORCE SUFFICIENT FO BREF{K SNERR PIN",q"

PEffMITTING THE IHTERRUPTEI_ BLOCK TOMOVE UPWARD ,qG._IN5TTHE 3TOPPING

SHOULDER. WHEN )N TH)3 POSITION_ THE LEAD INPRIMER CHJqRGE IS IN LINE WITH THE FIR-ING- PIN.

B. WBITER PRESSURE ON SURFRCE 'B'CREI_TE,SFOF_CE TO BREAK 5HEflR PIN "B" BHD

DRIVE THE FIRING PIN INTO THE PRIMERCHFIRGE. THE PI_IMER CNFIRGE BL,qST5 IN-

TO THE BOOSTER CHARGE Vl/_ THE LEND

iN ORIFICE_ riND THE BOOSTER CHARGE BOOSTER C,CRUSE3 THE MAIN CH_qR&E TO DETON-ATE. STREklGTH OF SHEBR 'PIN"B" IS PRE-

DETER.MINED FOR DESIRED bETONFC_IOI-IDEPTH. STRENGTH OF 3HE,_R P_N"B" 15

3UCH TH,qT iT WILL SHE,qI_ BT R DEPTHOF _PPROXIM_TELY ONE HFILF THE DEPTH z

REQUIREI) TO SHERR PiN "B". ./

MRIN CHRRGE/

(0.7 LB. HB×) -'f

f

,_Tr,j/, :/. .(- ,//

FMI8-1,54

Figure 7-14 Sofar Bomb Schematic

7-27

SECTION VIII

ESCAPE AND JETTISON ROCKETSYSTEMS

TABLE OF" CONTENTS

TITLE PAGE

System Description .................................. 8-4

Escape Tower ......................................... 8-4

Escape Rocket ............................ ............. 8-4

Jettison Rocket........................................ 8-7

Astronaut Controls ................................ 8-9

_F :::_ System Operation ................................... 8-12

8-1

_ONNELL SEDR 104

_8 o_O

UO,.

O<

_ _ Z

_z_ o_o .Z_

FMI8-50A'I

Figure 8-1 Escape System (Sheet 1 of 2)

8-2

8-3

_i_V_mLa. SEDR 104

YZZZ, ES_.:'Z _ JL_Z_ZSON_ 8T8'_(

_he spacecraft escape qstAm ec=slsts of the exeal_ tower, ese_e

rocket aa_ esealm to_m_ 0ettSson rocket, Zn a(MAtt_, t.hez_ are a_-

trols available to the ss_reuaut to tnl_late an escape sequence _ to

a nanual baek_ of certain events vhieh normal3_ occur by auto-

=-tic 8equenc_ _ an escape mr a _ nisslcn.

8-2. E_

M1e eseape _owe_ is a welA1ed s_eel st_eture sppr_z4--telsy ten

in len_. 5he t_Ner _s attaehedLto the spaeee.va_et reeorer7 ecu_

by a three-se_ e_ flag. _he se_sen_sof the e_ ring are held

toKetherby +_ree explosivebolts. _he _ en_ of the escape _over lwo-

rides a mounting base for the eseape rocket. Mae escape tower 81so pro-

vi_es fc_ _he ro_lug of the elee_riealvArlng neeessax7_o provide ig-

nlti_ of _he esee_e rocket,escape¢owe_ _et_Isonx_ end _he e_-uD_

e_losive bol_s. Fo_ a more _etei_ dAseussicuof the esea_e

str_,l;_e, refer to Se_-_io= 3, Ma,l_" _ Aue_].l.es.

8-3. _SCA_

5he escape rocket ccmis_s of an elee_Ao-:_y actuatedISai_erasses_IF_

s _ - laeh _iSO steel case, rocketnoule asseub_V,phu_n ehmber anl a

sofA4 propellant(see I_ 8-2). 5he length of the escapexx_ket Is 8ppro_i-

na_e_y 70 Inches. 5he a4e_eterof _he rocket ease is 8ppr_us_e_y 15

8-4

,MCDONNELL SEDR 104

IGNITER FLIGHT IEPTACLEHEAD (

I

i FLARE

FOT[IN

RETAININGTUBE

CASE CASE

IGNITION

RING

PROPELLANT

GRAIN ASSEMELY_

IGNITER ASSEMBLyROCKET

JETTISON MIRROR I/4 WAVE

"0" RING_

TOWER MOUNT-ING AND JACKETSTUD

DAVIDSON

ESCAPE ROCKET

FM18-52A

Figure 8-2 Escape Rocket

8-5

_mRnlr&L SEDR 104

_hes. _he weight of the motor prior to _ is app_-Rtel_V

6_0 pounds. ]Vor aero&ymM£cal stabil_t7_ ballast is emd_ to

•opofthe t SMet loft), moor

incorporates three eq--_ly space4 nozzles. _e nozzles are cants4

at 19 degrees _m _l_e of rocket case to cen_l£ne o_ nonle

so as to dlreQt _he ro_x_t blast ou_ an& awq _oa the tower and

spe_e_t_. _e eft _losure of the rocket motor inc_porstes a boss

which provides for the :Lur_13a_ of the Je_£son rocket motor.

_e Je_tisan rocket sot_ boss also provides for _he attar_--nt o_

the thrust _t sl_or. _e Ol_tCal stshtt_ oft he resultant

thrv_ vector is aec_.ltshe8 by the _ _t atrror.

_he escape rocket projpelA_r_ t8 a p_t_e em_e_um per_a_e

form_at£on. _e Un£_ _ates Bureau of _lostves olaosll_les the

propellant as a "Class B _plostve". q_e. propel_nt Is senslt£ve to

_ressure an_ a s_ark or flee :a_ easl_y ignite it. _e l_ellsat

_raln is an tn_zmal bwm_ nine-po£nt star _eh is cast ,_e_l_

into and boa_e_ to the case. With the nine-poin_ port _estsa, the

pose£btllt_y of thzu_ :l_t ls ze&um_. _hls t8 4us to t_e

_._ slAsh-eat betvean the star p_'_s an_ the exhaust n_s. q'_e

n_ resu_taW_ ex£e_ thrust at 70 4e_reesF. is _2,000pounds for

0.78 of a secoa4; it then drops o_T ,-_or:l_ to 5000 _ in the next

0._ of a seec_. _e +___rt _3.1. then _4,,_,,_sh at a re4uce4rate to zero.

•_e tc_l i_ c_ _ motor, at sea level, is sppzoziaate_y _,_00

pcem_-secea_s.

8-6

_N_llfA,t. SEDR 104

_ae escape zeeket igaiter is a Me_ _ a..1 _it vA_ two

_ e_lete_ 4_lent 4_!tiatiea _te_ te eecM _mtt. _

lai_istloasTetemto eachua_ ham Xade_t eXre:ttrl_ eXffer-

eat _stterles.OaeuX_ is e_tesl Xu shoe, ma is a eeatrsl

_rae._Aew.1_r_e_' _ dazstioa._ts uaXt is esseatla_ a alaXs_=re

reekerrotor. Xt iae_rstes a msAi pz_ _ _ieh eaa _e

laiti_e__ ei_er of _ sqai_ss_ _ _o_assims aitA_tte

_lle_e. _ _ first watt is tae _ ualt,e_i_se4, of

aa aa_ plastlet_e f411e_._"A_M& _-e_l.da_ mi_.t,_t'e £a _l.eh

are loest_4 t_o sets _ l_Lvesqu_. A_ oae squib is ee_sble of

_he Jet_Isoaz_-_ Is a qealifle__ retzoeait. q_e rocket

eoulst_ ef an elee_esl/_ se_as_ed_alter,stuporeasesin4a trl-

aossle ssse_T'. _e nessles sre _ st 30 4eszees _ eea_erltae

e_ z_._e_: ease te _l/ae e_ aossle. _=e roeMet nighs _M_.OI_ua4:,

aa:a Xeagehe_ 18 _teaes,a aXmeterof_._Xnehe,,aaaIneaaees600

._Te,m_ ef _t fe_ 3.._5 seeea_ a_ TO,_ees F. at sea Xeve". _he

_mket has _m meeesm_,aX3_ ft.ree. _ -7_ 4eip'ees F _e 17'3 _lelp_esF.

mt X'_t m %eveX,0 wmm.

capabilities. _ uaXt is e/_e,2 _a slm_ewith a h_ he_ m_

r_ t_ la_ the top of the _etti_en z_ket. _e _A_er eo_a_e _t_-

mt_ T Srm,et_-_ _At_ l_Aets_axeaaze_Sa_ea_ a,__aeof

8-7

MCDONNELL SEDR 104

POTTING

IGNITERASSEMBLY JMODEL4004 U.S. FLARE_

SHUNT

IGNITER

GASKET_ _PLUG

RETAININGRING

PROPELLANT GRAIN

"O" ASSEMBLy

!l !!

ELECTRICALDIAGRAM

FMI8-53 A

Figure 8-3_,Jettison Rocketl

8-8_

"__NmAL SEDR 104

fcu: squibs. _he four s_s are .azTa_Ded,4. _ peirs _ _ Ik_l,l,ba_

each. Zaeh _ has i_ elreultz7/_oa a dAfferen__ sou_ae.

as rmt's eem",'ols the escape

of the abet _a_al.; in adaAtl_, thee are tvo Za_tl-rlngsto.p_A,le

aaunalbee_ of e_ic tunc_la_s.

ab_ handle's_z_ tunotlc_is to InAtlatethe abort sequence.

5he ha_ is also _ as a re_ ha_ dux_ ]_meh. Loeat£on of

the ebox_ handle is f_ ef _ 8s1:_naut'ssuZ_ox_eou_h left ax:

rea_;. Fo_ an _ _-_1_tate_abort,the releasebutton loeste_4,

the top of the handAe u,_ be da_resse_, -11a_Au_ the handle to be :orated

cut_oa_. _ _ved 1;o the eb_ (o_boa_) post_ien, an ele_rAc81

mrl4_h is _e_, _hl_h se_s _o 4eI_ _ 8paeeez_-_o-a_

els_ x_ bol_8. _ze escape sequenceis 1_ initiated,provldAn8_h:t

main _ilieal ha8 bee_ dAso_te4. Be_rozeumbiIAeolrelease_

abort hsndle 18 Ino_Ive.

_o l_-zlngs are Io_ on the left ban_ e_m_ole of _ nain ins_-

the sj_eere..et-_p-_ e lm_ _ _ the eseape t_" e_

z_. Z_eate_ ImmeaAa_e17a4_aceat"to 't,he p-_-x_ are _o tele-11_

•111mlas_;e green when the eseape tom" has bee_ _e_tiscned an_ when the

_paeeers_ has separa_e_ _ the booster-adal_er, respectively.

8-9

_MCDONIVELL SED]_ 104

LEFT

SWITCH

I

A6ORT H,6,NDLE- -_

LOCK RELEASE _ /___

SUPPORT ASSY_ LX

MIC ROPHONE , _7_BUTTON R,_

\

",,./\\

"\

BLOCKHOUSEPILOT ABORT LT. 24V DC

(BLOCKHOUSE) POWER

ABORTHANDLE _

LOCKING PIN _ 43 UMBILICAL 93 ;

SIGNALS' TOMAy DAY

NOTE

[_)SEE FIGUREIIi-tS _ I •

ABORT SWITCH _j_ELECTRICAL DIAGRAMGROUND TESTUMB. I_LAy

PM_d-st'A

Figure8-4_Abort Handle

8-10

MCDONNELL, !SEDR 104 '

GAS GENERATOR

:::I TO EXPLOSIVE BOLT

,hPLJLLRINGS j _.v

iL.H. CONSOLE

J"ABORT" LIGHT ILLUMINATES WHENIABOKf SEQUENCE IS INITIATED

I'JETT TOWER" LIGHT ILLUMINATESI GREEN WHEN nEXCAPE TOWER HAS SEPERATEDI FROM SPACECRAFT

/ I"SEPCAPSULE" LIGHT ILLUMINATES GREEN

"_'-_.._ / / J _WHENISPACECRAFT HAS SEPERATED FROM

2_ _ IBOOSTER ADAPTER.,/

TO GAS G_

f_ I EXPLOSIVE BOLT I EXPLOSIVE BOLT

ONE SIDE ELECTRIC SQUIB ACTUATED BOTH SIDES ELECTRIC SQUIB ACTUATEDONE SIDE PRIMER CAP ACTUATED. TYPICAL TWO PLACES ON SPACECRAFT TO

JTYFICAL ONE pLACE ON SPACECRAFT TO BOOSTER ADAPTER CLAMP RING.BOOSTER ADAPTER CLAMP RING TYP$CAL TWO PLACES ON ESCAPE TOWER TOTYPICAL ONE PLACE ON ESCAPE TOWER TO SPACECRAFT CLAMp RING.

SPACECRAFT CLAMP RING

IFM18-143

IFigure 8-5_ Emergency Clamp Ring Controls

18-ii

__mA.A. SEDR 104

8-6. _ et_ATX_

Under norm_ mission conditions: vhe_ the escape syst_ is not

used, the escs_e tower c_ ring is detonated at e_prox_atel_ T +

15_ sees. When the escspe tower clu_ ring separates, the escape

r_ i_tes and carries the escEpe tower clear of the spacecraft.

Under norm_1 Liaslon eonditlons, the escape tower Jettison rocket is

Dot firecl. Nor"rally, the c_ r_,_ bolts are detonated _ auth--tic

sequencing which applies electrical power to the squibs in the e_

bolts. If de_tion of the esee_ tower clamp bolts fails to occur

as the result of autcmetlc sequencing, the astronaut m_y Jettison the

tower nmna_ by pulling the pu11-ring adjacent to the "JEST TOWn"

tele'llght on the instrt_mentpanel. Activating the i_I 1.rlng closes

a toggle swltch and 8pplies an alternate source of electrical power

to the cl_ bolt squibs. ActlvatIDK the l-,11-ri_ also Initlates s

gas generator locate_ behiml the 4-ntawment panel, q_e gas generator

is connected to a _sion cap located in one of the three explosive

bolts, qgte rapid extra.ion of gas fires the explesive boZ% thus

the _ r_-_ to be detonated even with a loss Of electrical

in all the squib circuits.

Under boreal conditions, the spaceeraft-to-ads_ter cllmp rt-_ is

detonated by a_tcmatic sequencing at sustainer e_Ane _t-o_L_ (_,CO).

T, the event that the clsmp ring fails to detonate as the result of

aut-_tic sequenein8, the aetrons_t my detonate the (_1_.. tin 8 -m'_,=_ly\

by I_ the puli-ri_ adjacent to the "SEP CAPSULB" isle-light on the

_--_t panel. _his action initiates a series of events si_ to

those deserlbe_ for the escs_e tower el_ rlng above.

__NNmAJi. SEDR 104

_le spacecra__ electrical system provides for an abort _ t_me

after "the gantry is removed,. Whenan abort is _-_tat_l (See SectJ.cn

6 for variousmethods of 4-4_tatlng _ abort), the spaee_-to-saapter

16 detonated,the escaperocket i_4ted, an_ _he _aeeeraft is pro-

pe_l_l away fron the booster. If the abort Is made off the pad, the

escape rocket will carry the spacecraft I;o an altltuAe of apprn-_u-tel_

2_00 feet. At The peak of the escape tra_ectoryt as 4et;erained by a

alti______ se_or_ the escape _tover _1 _. ring is _Letonated.

escapeW Jettlscnrocket ignited,an_ the escape rover propel_d

eeay from the spacecra_. Two seeon_ after rover _ettlsoning,the

drogue chute is _eployed. Two secondsa_ter drogue ,_te 4epio_ment,

f_ the antennafairing is released. M_e secondsafter antenna falrln_

release,the heat _eld Ii releued, exten_ the la_ i_ .,_,'t.

f_

8-13

SECTION IX

POSIGRADE ROCKET SYSTEM

TABLE OF CONTENTSTITLE PAGE

S\

System Description ................................... 9-3

Posigrade Rocket ..................................... 9-3

Rocket Igniter., .................................... , .... 9-3

System Operation. .................................. :9-5

' -,' i!!!!! iiiiiiiiiiiiiiiiiiiiiiiiiiiiii!!!i!i!iiiiiiiii ;'"% i_iiiiiiiiiii!!i!iiiil[iiiiiiii!i!lli

::_i_!iiii!iiiHilHiiiiiiiiiiH_

9-1

_OItlNELL !SEDR 104

SQUIB

IGNITIO

IGNITER ASSEMBLYMODEL 3004 U.S. FLARE

\

RETROGRADEROCKE]

_ _ Rc_TROGRADE

ROCKET PACKAGE

E_'CT_._L DIAGRAM

FM18-84A

Figure 9-1, Posigrade Rocket System

9-2

_C_O_EI.i. SEDR 104

xx. mere srma

_he 3pesL_rede _t sTs_ea coasis_s pr_ ef the three l_st-

_te x_seJm_s and _e_s _ Xa the :et.-_ X____sge aa_ the

sssee_ w_J_ aeeessm7 to X_tte _e _ st *J_e _ time.

_he _pos_4_le roeket p_ eonsXets of & nozzle usem_l_V en4

ease, a so3Ae prope32ant eadt an elee_iee3A_ 8e_ted Xip_tter. The

;pestmgrade rocket is a ey_Julrical deviee _ _te_f 11t.?

£aehes £a ZeaS_, 2.8 iaehes in _meter a_ weilghi_ qT_zmdatte_

5.21t ]pounds. Th£8 rocket is bmsle_31yam AIDLa8_z_aket w£th m£nor

e_e for laereue_ zelta_X3A_, ael_a_i_ has beea pieea _

me1_eds: first, _ i_ni_ioaof the i_ni_er squibs f_ two &IA_gex_

_es; 8e_, oaly one of the three roeke_e is neeesea_ to aee_a-

_llsh eucoesefalse_aratloa. _e to the vlde te_tare range of the

•oeMets, & te_e_a_Are eea_l s_s_ is mot req_Are_. Posi_ zeeket

_hz_et i_ _16 Pounds + _% at sea level. Firlag time i8 1.01 see.

mma

_e _si_ x_eket igaiter is a hea_ _ouate_tumi% with dnaZ 18nltlon

e_Illtleo. _he i_alter £_ c_lladriealin she_ wi_h & he_-_ head

for _ it In_ the _ of the Ix_ei_ roaket. TI_ unit eonta_Lns

.... ___ _h_ee 8ra_s _ i_nltion_elle_ewhich are i_alte__ either

ef two I_ of squibs. _ I_ has. lad_t elreui_ _ a d_fereat

I_wer s_ee _ a_ one squib is eal_le of i_nit_J_the ImIAelm.

9-3

NglELL :iSEDR 104

÷ .

POSIGRADE ROC KETS_ ""2AND3

TO ISOL --

TO MAIN _ !SQUIB BUS I I

I I

,II,

I_:)SlGRADE ROCKET EMERGENCYFIRERELAy FOSiO_DE-RO_kET

FIRE RELAY

t TO SPACECRAFT-ADAPTER

RING LIMIT SWITCHES

! FM18_85A

'Figure9-2._PosigradeRocket IgnitionSystem.

9-4

'__Hiri._. SEDR 104

_e purpose of the posigrade rockets ls to aeecq_llsh separa_Lon

between the spacecraft an_ booster. Under norm_ zd.sslcm eco_itians;

the posi_ade rockets are act_vat_ by the spaeeeral_-to-booster el_=.a,

ri_ separation, vhieh oeeurs at sustaine_ engine e_-o_. _ posl-

rockets propel "the spaeeersft ava_ from. the booster at a rate of

15 feet per seecm_L. 5he three rockets are _ staultaneotwl_,; how-

ever, should _eo of them fail, the remainingunit _ sueeessf_

cause separation.

_e poslgraderockets are also used to separatethe spaeeerattfra:

the booster in the event an abort ls Initiated aider tower separatica

but pric_ to sustalner en_L_ cut-off.

_5:

SECTION X

RETROGRADE ROCKET SYSTEM

TABLE OF CONTENTS-

TITLE PAGE

System Description ................................. 10-3

System Operation ................................... 10-5

;ffffffiffffffiff!ffffiffffffi_:.::ff:::|_:

=_iiiiiiiiiiiiii_iiiillilliifliHiiiii!!ffi_::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::

::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::

._i_i!iiiiiiiii!iiiiilHii!i!iiiiiiiiiiiiiiiiiiiiiiiiiii!iiiiiiiiiiiii_-f .iiii!!iiiiiiii!iiiiiiiiiiiiiiiiiiiiiiiiiii!iiiiiiiiiiiiiiiiiiiiiiiiiiiii!i!_iL

:::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::

10-1,

NNELL SEDR 104

PYROGENiGNITER

ASSEMBLY

PYROGEN

RETROGRADE!

ROCKET,

POSIGRADEJ

ROCKET

PYROGEN

'SPA'CEI_!TOJALIGN 'RETROROCKETS

TEMP. IGNITERRECEPTACLES!"P,ANSDUCE_

RETROGRADEROCKET,(ROTATED180°)

FMIH_.I

Figure 10-1 Retrograde Rocket System.

10-2

"_,_NNmLL SEDR 104.

X. RL_O_qlB ROCI_ 5X_

_.1. _ ___

_e retrosrade ro_et s_s_em c_ststs prdmr£]7 of the three retro-

Z_.JCe_S;"blitZ' _ t_.1._Ss _ _ assoolat_-_ _ neoessax7

for r_ket tgntt;iou. _e retro-rockets are housed in the _ettiaonable

retrosrade paoka_e _ Ir£th the pos:14_ade rookel;s (See FI4pn_ 10-1)o

lo..2, aoc[_ N0mm_

The retro-rockets are mmmte& in "the re_ro par.kase. _ae m_t_'o

package is held a_Inst the eenter of the heat shtel_ by three retent£on

straps. _he retentt(m s_waps are attached at three equal_ spaced point;8

on the base of the spaoecz_t aria ccn_._e to a ccmn_ po£nt In the center

ot the _ package vhere they are Jo£ne_ l_l_her by an explosive bolt.

seconds fo_ retre_ade f1:1_ s_4_asl, the bolt deflates, the

str_ps are release4 end a ootl. sp_nS e_ects the z'eta'o l_cka_ away

_he8_o_e_L-_(SeeFigure10_). To_e_t the ro_et., _ar_o_r_

fr_ _Loro-mt_or£tes, each _t has s meta_ cover over its exposed

nozzle end. _ae cover ls blown off by _he rooket blast at tAae at 1J4_xt-

Off. _amt_ of the rooket8 is so des_ed as to-d_eet t_e m_

thrust veot_ towards the spacecraft's predeter_d center ot _mvity st

t_e ot f_-ns.

/-

_he retz_pm&e paoka_ is s_pplle_ electr£ca_ power _ three

ele_trtea_ _b_l£cal_ _eh are eq_l_r spaced _ t_e bm of t_e

10-3

NitlELL SEDR 104

BOLT

SPRING

RETROGRADEROCKET I

POSIGRADE ACK./ROCKET 1 RETROTP

;='=, \\

STRAP

RETRO-PACK

UMIT SWITCH

i

•SPACECRAFT;-_

SEPA_TION_LIMIT SWlTC

EXPLOSIVEDISCONNECY

BOOSTER,ADAPTER(_F)

' FMI8-147

Figure 10_2, Retro-PackRetention System

: :10-4

'__NNfLI. SEDR 104.

spaeeers_. _he electrlO_A uabilicals lesve the spacecraft throm41h

explosive aiseomaee_, follow the +hree retro _ retention sta_s

_ mm:_ro _,.kap a.4 +a+Az_ _r. _s' A_mm-

hector temt point is looate_l oa the si_e o¢ the retro Im_mlle _ a3Aows

-11 _ _eM, te _e brok_ _eWeemthe _o_.t at _eh t_ e._

•_ _ _ ,.,a t_ ,a.tt _,,,a.t_ t_ m,ee.__,m-. (See],.m=e:]LO.-3).

_._. _

,a_'n'Imm-_ "tke cmmr-e.1_xl,m_Lam,a. z,e43mmb_--t,reeker t:J.z'+l,__ lure beea

e_l. An att.e_e4 "kml,e_'kmr'e tz,_,a,,,eer maJ.¢m"mz'e'k_z'ook_ 'kulm_-

m._.e,m,_ =eP.zo-_.,m1,__ ,++.o+..z_,,,._e o+_,_o '+. +-No. + _, +,,

a+v,mm+ Ave_le !_m,,t _ zo'ro_ _*o=,_u._ ,,eem,,af_'Jal v,w.

Io-5. _ _mA._C01

1_mrl,o,,e o_' "P.Merekxolz, a_ zoeke+.,,3r,,v.em_ "ko _ .tae s_+oem.,,._

• eemalm_oa 4ar_ml _+ +Jwm_m+ee,_ t, _o+Ittomea _o+._e

_t_.3_,0_ + ,:I.o rol_ or+3rm,. ,Jehe_:I,_. se_l'oe_ ,_t',t_ aot "oq_,,,_o_C_t,

la_ _ the _moee.-.,m_aeeea ",.liea_t_t_e _=At_

the se_ ]iu 1_pm. SI_ _9_eaee_ az_L_e,Moveve_,_Me a_ove

1+i,d_m_ be m_ _. Iei_ e¢ _he x_e_+ _t_l_boemm_

10-5

NOTES

[_ EXPLOSIVE ELECTRICAL DISCONNECT FOR SPACE-

ADAPTER RING AND BOOSTER WIRING. _. ,/'"C'RAFT

CFM18-82A

;Figure 10-3. Retro-Package l_,|ectrJc_ Installation

10-6"

_ODONNArLA. $EDR 104 ,_

.... All three rocket fire relays receive 2_ V d.-e s:l_taneousl,,y;

hmmver, the No. 2 and No. 3 ror..ke'tfire rel, e_ have a five- ancl

ten-_ond t_e delay, resl_ee_I.vel,V. _e left rocket fires first,

five se_ after the left rocket ignites the bottom rocket fires

end five see_xts after _ bott_ rocket _n£tes the right rocket

_xes. ]k_:h retro-roek_ fires fro" a total _ ten seeonde.

_e retro-rockets are f£re_ sequen_ally to awed the Ineffective

resUltS f_ a fs£1n_e of either o_ the _st _wo rockets. Consequent_y_

if the Wo. 1 rocket failed to a degree whleh woul_ disr_t the Betro-

grade Attit:_# Per_l.sslca_ bla.y; the No. 2 _ 'FAre _18_r would

beewle de-e_e_gize4,q_e spaceera_ eouT_ then be reposi_io_ed

the _ a_titu&e_ the No. 2 l_ro FLre Rel_ w£1£ be

re_n_d _ the Retrosrade A_It_le PermissionRel_V. With

and the retro sequence cantJ_uod.. 'Jhe=_,m_sequenceof events voul8.

oeear £f the No. 2 rocket were t;o _..1..

ere CAve_eleli_hCs an the _'s left eouola _t_h

concern the re_e_rade s,j_ea. _e _ cue is _ _ a_l is s

1= _, eJ#J_erbY the =a'_ellA_eelx_ or bY the but'_ a_aee_ _,o

IA_h_. _e l.n,pose e_ the bu_t_ £s _o _i_ia_e re-ea_qVprlo_to _a_-

IA_eclockz_nou_o_ f-4_-reof semi.

10-7

_ON_fELI. 'SEDR 104.

IREASONFORSELECTION41_ _IFROMRETROROCKET

/_ Jk I IFUSEHOLDER

A--O ( PROMEMER.gET+gOJREY_OSEQ._ SEQ. RELAY_ND

RELAY", ii._,_ _

.RETRO -- ;NORM

DELAY_IN + _INST I__ _ .'a _ ...... TOATT'TUDEPERMISSION JFUNCTION.NORM_.__ST IRELAy(BYPASS30 SEC I_FAILUREOF SATELLITE.. . CLOCK TO

...... I _ I_nMEDELAyRELAy)

_i_JT ql'_l_- ---+l tREI+'+ROGRAI_EJ:IRING $1GI_IAL'_'SA'TELLITECLOCK)ITORET_ROROCKET+FRERELAy(30SEC. T.D.)] I10r_URTI.Y RE-ENTRYBEFORECLOCK RUN-T _ I i I IRE[RO RI_SQUIB ARM

k A --" r, t O-F"EME " R IRETROSEQ. IND RELAy

_ 1 . '.RETO "

|_ SEQRELAY[_R. _TROFl_NO.1_

ISOLATEDIBATT.

I,_.:_=:=:___ _;;;:,:m___m:_..............L...__..........h............................................................................................................i!iiiii_ii_!!i!Wimmm!!!mmmmmiiiiiiiiiiiiiiiiROWERFROK.i : . •

"J'o RE[ROFIRED -_AT[ITUDE PER- RETROROCKET'MISSION RELAY j _ND. I_ET-_Y L'GHTS._ j_ _'_

WHEN ENERGIZED. t _ I "POW -- "RoRo_'_,_-rr,_/q_-/qIZ_L.! _ .EROMI_o.,,o.C.H.! Iff' IRET,OROCKET I ti' Vl T YI T_co_o,_.+. ,_O.,TORRELA¥sI " 11 " _l " |

--- t _ " 1 z - " & l _rRo EJ__ ,_k I T-I_L-T1 lWARNING_"-'_ *"--"_ *----_ JFIRERELAyS

,,,,or_rP_'__ ___,_,_1 I I 1 ImG"TRUS_ , ca --,....l_._O)(())(C))lr I _ I TRELAY]],, ]_,_"__I m J'- _' J I/I ' . JJ5SEC._T.D. ]IIOSECtT.D..

: IPOWERPROMRETRO

i II!THE "RE[ROATTITUDE" LIGHT DOES, IT.D. RELAy(15SEC. T,D.) _ _ TONO I, NO 2AND RED,BUTVISUALAIDSINDICATESPACE-

J. '_ ..... -_ .... _ _ __JNO. 3 r_E,. RETRg]_KTFIRERELA', .CRAFTIS IN RETROATTITUDE.

m, \'I_+ I '_I IRELAY............

R _'j_ I ',SOLATED:', EMERRE[RO0"1_" 4'l'_)--_m"_ FROMR_I"RO INTERLOCK ""iV--- I IEATTERY, I IF,RENO+_ +.. IA..REIn:

/I RETRO _ IJ IATT. AUTO; J '7 I TO EMER.K!O. I RE[ROROCKETFIRERELAYJ _' J _---._1 TOEM_mNO.__m ROCHE[F_RERELAY(SSEC.T.Da

+[_[_.im, ...__.4k i v "t TO EMER.NO. 3_O __KET]=J_RERELA.y (10 _EC, "r.D.)I ]+01._+/_._.[R_SIGI_ALILtATCIq'_IELAy - -

IBY-PASS IA'RE"BY-pASSflELAY.

_,,!._..._...,.l ................. _..................... _._ ........ ll:m........... _................I_ff_rffff_ffi._.iffHff.iL_j._ff_ffiiffi_._iffff_F_._s_!C!_!!_ ! _...'.::: _ .'.m..'+mm::,hmmm.m.:.::

_ JTORETROROCKET

[L_PA_['F_N DSEC_--I_Y"QLEJ _j IU/V_ILICALSEPARAT10N ! _ql"JETTISON RETRO"UGHT, LLuMII_TSSIRED.

f _' •

_ [_GREEN LIGHTONLY,_

/" / ISOLATE[)

TO JETTISON J ISWITCH _DIP THE "RE[ROATT." LIGHT IS GREENRETROWARNING hAND THE J"FIRERETRO"I LIGHT ILLU-[LIGH](_RE_Y_. I . MINATESREDTHE "RETROATT"SWITCH

SHOULD BE LEFTIN THE _AUTO" PO-.. / JE[TISON BOLT SITION AND THE "FIP_ RE[RO"BUTTON "

DEPRESSED.CIRCUITRY WILL PASSTHROUGHENERGIZEDATTITUDE PER-MISSION _LAY BUTWILL BY-PASSTHE

'q_-TE i30 SEC. T.D, SEQ. FIRERELAy.MEI_GEm,+:Y _Li<_HI'_, DI+A_E_"_TRO ROCKET ......_SEMBLY

'_s6_Ter" _eT_SO_RELAY

FigureI0-4_NetzotocketOver-rideFiring System Schem_t_ic

.10-8

AwoDoJvivae4.1. SEDR 104

_ _ "t,ele:tl_t8 :in *_- _rH_;z'e4e eec_aenoe m _0

A_ttu_e SrJ.*,ehed_8_ to t,hei_ A_LT.L:ILSh_shoulA _ in wA17mm,

.t,_ retro..roekets _ f_e. V£th the Retro A_t_.tuAe SylPh in the

"_A_ w pooi*J.on, the _)e_et,. elm be _ _L_aoqxtthe spaee-

m-a_ be_ in the _troi_'ade .at_tude,

_he _M_O A__ _eleltsht SAlmdma_s red _ben the spaoe_t is

not _ retro_e _*_ae _ _._te= ween _ re_rosr_

O_l_=_lJ_r the three RJ_O _ _e_:L4_ht= 4_,m,4-,_i;e4 _I_LIL_A-=_Iy

u es_..h _d;_-o.._ vos se_t_*3 ly _ ]b_a'_enoe has shown that

three _ _ _s.3a3._'l_ have been 4tseb)_l.

three _rl=o-_s _,_re not ll_tt_t mL_ 1,5 seoon4sa_er the f_e eli;=

-.'-'_ is sent to the NO. 1 _tro-rocket.

If the _tO _. _ele)A4ht JA3:_nates teA, the sst_ons_ -._t

the _ stttt_ In m_er to d=tez_=e _t_the spse_ is in the

oo:reotz_Srede stt_tuOe. Drthe _zaeec_ is+fore4 robe *nthe

•eo=Teet att_LtuAe, tbsn the _ shomlAl_sltt_ the+Ret_o AttltmOm

Swltch to the _AS8 _ poslticn en_ also Imsh the FIB R]_mObuttm.

10-9:

M_C_NNR_L SEDR 104

• en. seooals late_ the _ KilO _]_elel£_t._o_l_ _11..4e_e

]kn_', if theastw_ _el_z_ea that the spaoeoret% was not

the e_teot attt____e, the Reao_c= Coatwol Sys_e=_o_ld be _.loye_

In o_ler to oo_Tectl_ posltt_ t_e__m_rat_ _- the re,rotate atti_te

(See _e_tm 5). _ the eo_eot _ a'_tt_te is a_ue_, the

A_. blelAg_t sho-_ i11._--te t_:een.

TelelJ_ht i11-_es z_1, the buttc_ a_aeent to the _ .1_0 Tele-

I_I_ sho_ be 1_ le=_Aa8the_ A_ltu_e Swl_=hin the "A_'_O"

posi1_Lm.

_he 1_Ltthtele1_t is the _. _ Teleli_ht.__= telell_t

_1_ _--_e sreea60 secondsattarthe No. _ :elwo-z_ is iSmi_e4.

Xa the evea_ this _ t_-_,-te= _, the e_L_s_t b,_t_ shout4 be

dsF=es_e4 to _ en altezaa_e s_z_e o_ ]_owe: to t_e re_o-_

;}eriCson bolt. Zt the z_1_ _-_ be _}e_Is_sedby the a_o-

astleer ove_ as_, itrillbe e_eete4so_ttm _ z_-e_t_r

•hen the extzemehea_ ene_ _ __ 4etcaate the e_los£ve ,bolt o_

_ Z"@'t_._ B_,t'8_ll t;0 =,l:e_ _ e¢I,1 _ _o eject, the ]_.ke_.

lo-8.X_eatedm the _ haa4 e_ole m "t_ strAtebu _.eJa e_ol ]_owe:

to the relwo-:oe]_ISaA1_m s_tbs =aa to _ zstzogra_ _acksge o_'t_.sm

W'-.Lththe swAteh:l,nthe "At]M)"_md.t_Lm_ Is n_pllea to the

•10-10

"_IeODONNELL SEDR 104

RETRO ROCKETJETTISON ARM SWITCH

FUSEPANEL SWITCH

° EMERRETRO TO EMER.RETROROCKETASSYJETT. RELAY & RETROROCKET

I _D J SW SE ASSYJETT.RELAYARM _FI_ _ RETRORKT. ASSY. JETT. RELAY

OU_ _ RETRORKT. ASSY. UtvWILICALSEP.RELAy8

LH CONSOLE, _ RETRORKT.ASSY. UMBILICALSEP.RELAY

MAINitSQUIB : _ RETRORKT.ASSY. UMBIUCALSEP.RELAYBUS

RETRO ROCKET SQUIB ARM SWITCH

[_IlB TORELAyRETROROCKETSQUIBARM,

/-- FUSE PANEL SWITCH _i_0 _ _ #3 RETRORKT. FIRERELAYISOLtSQUIB

-7SQUIBiBUS !

t2 RETRORKT. FIRERELAY'

u,0J L.HCONSOLE' RI RETRORKT. FIRERELAY

; _ IPlRETRORKT. FIRERELAY

/

: _ 12 RETRORKT. FIRERELAyNOTES

_> MAIN SQUIB BUSPOWERSUPPLIEDTHROUGHRETROROCKETSQUIBARM RE-LAYWHEN SWITCHIS IN "AUTO" AND RELAYENERGIZED. : _ 13 RETRORKT. FIRERELAY

[_ ISOL SQUIB BUSPOWERSUPPLIEDTHROUGH RETROROCKETSQUIBARM RE-TO RETRGROCKETSQUIEARM

LAY WHENSWITCHIS IN "AUTO" AND RELAYENERGIZED. [_-- RELAY

;FM18_-114B

Figure 10-5 Retrorocket Arm Switches

10-11

_NNIrLL. SEDR 104

Boek_ 7ire Re]._" eon_.ets _aen "theRe'_:ol_oeketS(l_t.b_ Rela_-is

merstse¢. _r ]_la_ag _ mrlto.h in the "IiMI" ]positle: ];_:_er is 8ul)-

r_l _:eet_" _ _e P_tro aoeket r_re ReZ,O, _,rm:t, _

,_._, lm_,,_ t_ene_-o_ _,ib Amn._. (See7_oz. ZO-_).

_e ReCz_Ik)eXet_ettisoaArm B1rAtebha8 An wj_ ]_Itlon 8a_ an

"OWJ_l_sttloa. Wt_ the mrl_ in the "GFF"Ix_itto=, no lx_er is

mmtlsble ta fJze t_e ex_ostve bolt _ holds the re_o-l_Jm_e to

the sl_'eoza_t sa_ no power is mmllsble to f/ze the 41_ots

• "r.hethee mb:D,_,,J.',,,_ t;o 'the z.e'_'ro..]paeke_.]_r ]p.l.ae:l._"the

wetzo _ AssaYer Jettison _ redthe _ ]kzeket Ass_l_ Ua-

_.t._ _-_._ _,_ (see_ _-_).

_)-s. _m__

30 se(_aaS pz-Ja_t_ t_e _ _r t_e _ seq_moe. _e_

11_ _ _ is__ea _ _re.aaeammd aaa_e_Atas_o_he

resetof z__ _ae _ the _1_e eleek.

• 10-12

SECTION Xl

ELECTRICAL POWER ANDINTERIOR, LIGHTING

SYSTEMS

TABLE OF CONTENTS

TITLE, PAGE,

Electrical Power Svstem

System Description....................... :11-3

System Operation, ..........,.................. 1i-4

System Units .... ............. ............•...... .i1-11

Interior Lighting

iSystem Description/.;_ ................... ,,;11-16

.: -::.

_11:1

iz

_ _o

50

i-_oJ

i -

i_ O:

f_ .<:

'_:M]87_0_]_

Figure 11-L Electrical Power Supply System

11-2,

_NNmmJ. SEDR 104

XI. _._ICAL _ ANDI_G_ SYS_MS

11-1. _._'_RIC_L POWERSYS_4

_he spacecraftpower su_l_ consistsof +_ree, 3000 WH main bat-

teries,two, 3000 WH standby bstteriesand one, 1500 WH isolated

battery. The standby batteries have paralAeled taps brought out at

6, 12 aria18 volts to power the apaeecraft6 V ste_y, 12 V standby

and 18 V stan4bybusses. The Isolate_battery also has taps brought

out at 6 V an4 18 V to power the spacecraft6 V isolated en4 18 V

isolatedbusses. ExternalA-e l_rer is supplleA+-_oughfuses or

diodes in the spacecraftprior to launch (See Figure 11-1 aria11-2).

_ An rater is use_ to indicate batter7 c_Awnt _nen the batteries are

in use. A d-e vol_m_f_eris utilized to read individualbattery volt-

ages as yell as the main auA isolate_2_ V bus voltege. Main and Iso-

lated 24 V bus voltagemay be read on the 4-e voltmetervhen the main

bus is povereA frc_ externalpower or the battery po_r.

A-e electricalloads are supplle__hrongh fuses vlth +_ ex-

ception of vital oontn'ol elreults which incorporate a soli_ eonAuetor

in place of a fuse. Some of the _'c circuitsutilisetwo fuses in a

s_Atch,i_se arrangement. A three position, center OFF seitch, pr.ov!_es

nc_al operation in the No. 1 positi_ or a rapi_ eeitchover to the No.

2 position for e_er&_mcy use. Sc_e of the more !-T._rtant_.-c c:l.z'cu:l.te

are provided _Ath a solia coo£uctor in the emergency or No. 2 pos2tion

of the followh_ ct.rcu.'l.ts:

(a) z,,..rS. Oapsule Saparat_.on Control.

(b) TowerSeparation Control.

11-3

_NNl£2a SEDR 104

(e) Sm_s. Mathc_ _.

(a) _tro. Jeff. c_rol.

(e) _tro _ control.

(f) _ve _ute _.

(h) Retro_.

(_) _. c_a_.

Z-e power £J produced by 'tvo ns:J.n hxwa-ters end cue stan_y _Lnvert_.

Mae two _ _ are rate_ 8tI15 voltsj _00 eTeles. One m_Lu In-

wn_r has a capacity of 250 VA_ the other _ta/nverter _.s rste_

at 150 VA. _he s_n_b¥ inverter has a eapaelty at 2.50 YA at II_ volts,

In tim /nv_-t, ez_.

1.1.-3. _82SM 0u__2zcsI

_-_. _c ecma_.cm.n_.

_ae spaeeers_ _ 2_ volt d-e power m_l)_r eom_lm of thr_,

3000 wad-hour bstter_s. _ m_Ln batteries are eemmet,_ 2n I)az'_l_l,_.

to each other by en _-01_ _Lteh an each battery. Each battery con-

tains 8n _ _Lo_ _n the _o_tt_w _ 88 _r_tton _atast

_ s _e_._ ca" 6£_asrKe_ "nst_0_y. The m_Lubatteries

feed the _Lu bus _w_l_ _nen the /nd_rl_a_ B_f t O]J-_ s_tehe8 are

_u the _ portion.

_',ter. far the na_n_O w :tnvert_ eno.'the ha'in ].5OVA_r.

11-4:

_'MCDONNELL SEDR i0_

BUS -- A ATT J

IA I

RELAYPANEL TEST 1NO. 2 UMbILICAl

24VMAIN RELAY JPRE-IMPACT+ 1064. i • J

24V MAINI -

_ER_S_r_ m_-U_CT!_- :A I'BEVY,ANaLNO.,I I -- --

' . [L,CO, 'L I _BE_YPANELNO._ RElYII_'EC0'TS_EE,",! I li _,_, 1, _.,_._A, i I I

I r-,, _l I I• I Ii ii

SQUIB _ .O_G- I

_E_.Y ; ISQUIBARM

t swl_c. II BELAYIL

54 _T _

87 8US r

[ PANEL " O OFF921 I

90 BUS STBYEATTSW

,m I _ NO_106 I O STBY

I ISOL_

UMBILICAL I 'qJ_----'J i -- NORM

DISCONNECT ! _ • O EMER

AUDIO BUSSW-

NORM: C_ OFF

] I AMMETEROBYPASSI

SWITCH :

TDC VOLTS:

BUS

il-5

MODO_KmI_. SEDR 104,

Two stnn_ ba_es, of :3000watt-hccwsespaeltyeach, l_*ovi4e

ata_ power a_' lower tap voltagezequize_s for ecmsualeatlcas

equilx_ and vaz_ liSh_8dla ope_a_Icn.._be s_¥.battez_s

__ _cx_e, reverse euzme_ _'oteet1_m, on aaAposlt£ve volt_e

ouches. _-0_ mrAte__sare loeatea on eachbs'_'ter'_'to prov'£dea

to ae_ _e ekvolt c_A_c_.

:18vol_ a..e Y,othe vs_.oms sTs_4n busses. _-Ao_ to :tsua_, "c2_ese

e_.r_tts axe en_'gt_ __ pom_ _ the usbt_tesJ, a_

extezaal power fuses l_ca_.ed in _he spaeeera_. Standby batter_" 2_

volt _-e e_p_Leatlcnis oout_o1_-4by _he S_f _Y, _-O]? svi_h

_ _on_ the s_4a_O_ybatteriesao not .e,w--__uthe --_ bus.

Xn the O_ position,the stan_y 2_ V_-e bus is eoleete_ _Izeet_Vto

the,mAabus. X_theman battez?_sae_late_,rhea_bes_ bat-

_wies _ en_-_Ly.e *_he_as:_ bus. Xf the I_n batteries are not

A X_0 wa_l:.hem. Isola_e_battery is _-_.,813_ _o pz_A_e e_rgen_

•"_ud.t.obus and sq'_,b _ voltaps sad to s_p_V _ne7 voltages to

other elx_uitsin the event the _in an_ stsn_ 7 b_s are deplate_.

_ae isolatedbatte_ also lneoa'pca'ates reverse ¢m-re_t proteett_a and

is ecemee_d to the isolated bus throt_a an _-01_ switch. Zsola_d

battery taps _3,y 6 and 18 volts A-e _rouKh sel_-ecmd:aln_ dlcde8,

to the 6 an_ 18 volt tsolate_ busses. _he 2_ volt isolate_battery

111-6

"_'t_ONItlELL SEDR 104

output is available through the ARM position of the SO/fIBswitch and

F _ through the _RER position of the AUDIO BUS switch to the associated

busses, q_e isolated 24 volt d-c output may also be connected in

parallel with the 24 volt output of the standby batteries throush the

STDBY position of the ISOL-_/RY switch.

External d-c power is supplied thro,,_hthe umbilical cable to space-

craft circuitry. Th_S power is used for pre-launch operations in order

tO conve_v_ the spacecraft battery supply. Normally 6, 12, 18 and 24

volts d-c are supplied through seven inputs. External power voltages

of 6, 12 and 18 volts are fed through fuses in the spacecraft to the

6, 12 and 18 volt busses. The 24 V external power is routed through

diodes in the spacecraft, to the 24 V busses. 0nly four external power

supplies are used to supply the 6, 12, 18 and 24 volt requirements, q_e

d-c _._,_teris used, with the _-w_ter switch in t_. NORM position to

indicate d-c current from the batteries in the circuit.

11-5. A-C POWER AND CONTROL

11-6. MAIN I_ERTERS

Main 115 volt, _00 cycle a-c power is supplied by two inverters of

150 volt-amperes and 250 volt-amperes each. _he a-c load is divided into

two groups ne=ely the ASCS a-c bus and the FANS a-c bus. The 250 VA

inverter supplies the ASCS a-e bus an_ the 150 VA inverter supplies

f_ the FANS a-c bus. _e cabin fluorescent lights are energized from the FANS

bus. The main d-e bus powers the 150 VA (fans bus) inverter through a line

11-7

_'%b-.=.o~~E-.. SEDR 104

S,AN,Y/MA'"I 1INVERTER INVERTERINVERTER 150VA 250VA250 VA (FANS) CS)

_.N,'STRUME"TPANELq L_ J G/ _, _ JG_ _ %q7

'ILl tl 1'STBY J J POWERSYSTEMCONTROL

l RELAyPANELNO. IIFANS BUS

,VOLTS

SELECT_,_ 12'/24IISWITCHvDcJJ _ i_A • I BUS

' LTc ' !V (AUTO)_ I1"

12O

25A ASCSBUS

C_0 11 RELAY

STBYOFF _ ANO_O7I I •

I BUS l I25A I ,li.

AscsAc.0s, i ---[¢.SWITCH I

--O1 2 I FAN BUS

O_ J RELAYSTBY J 100KOFF I D

NORM6 I I i .i.O_ I

LJ ' I iFANS AC BUS J < NDBY

SWITCH I _ T ,NV.POWERI , RELAY

L.- J lo_

24V De ........ -- (HATCHMAIN BUS DISCONNECT)

_ I I|SVACI MAIN STBY& MAIN I FANSBUS250 VA 150VA

J INV FILTER INV FILTER IL

FM]8-119A

Figure 11-3 A-C Power Control Schematic

11-8

oo

"_

_o_

-_

o

"all_l+

,OV

dWI

__-,,.,+

-,,....

t/"r

[1:

_':_35O

C÷

S(IW

"$]a--

I

L)V

dW

Ii

I•_

_o,-I

"J3XZ

l_

|I>-

o_o'-

I

'03SO

_+

"t,_ll"Oa_ll

--I

"L,L_.I'o

aJ3_--

iI"N

IWE

M_"U

Z--I

"NW

_Ol-aJ.--

]

"NIW

_-_1-

[

"gllo

_-ml--

i4F

"_I

f--

I--•e,o

r-'_-

I4"

II--

oo

,z_r"

ann

--I

II

I

-".,_.a,,

_I

II

I=

I8

"all_•xaw

s-I

II

I'._o

_+-,_s,v_

-I

,I,_

,e'I

"allL

+"daS"dV

_--

I"N

IW_;+

'dis"dV

3--

I

"d_$"dV

3JI

"aNl"

NO

NN

VI

"d_S"_ML

--I

°x

Io

'NIW

9-°1--

!

5'N

IW_-°z-I

I"N

IW_-°

1--

•,_

.._

_>:

ON

'H_I'M

SO

JJ'V_)

0_

i__

__

0Z

0_

__>

__

0__

__

_0_

__

ii

,.z.8

_,_

__S

-

_tvtvmi.L SEDR 104

_Ltter eireuit, en_ a 25 _ere fuse. _3w 2.50 VA _rter (ASCS_us) 2s

._-o powered _ *h- --J- A-e bus _hrcugh a 14.. f!lter enA 25 empere

:_.se. _he &-e power is controlled through _ _ posttion of the ASCS

,_CBUS_ enA FANS AC BUS s_tehes on the _ _nt panel. _he

_tmts of _ FANS a_l ASCS _tverters feed the solenoiAsaf the fans bus

:rel_ ena the ASCSbus ro1_. _eJe ener_=ed rela_ feed the

oc_p_ thro._ the eloseA een_aets of the rele_ to peter the FAWS ona

Ascsbsses.

Stan4by 115 V_ _0 cycle a-e power Is sullied by one 250 volt

aq_re stan4by Inverter. _ stsn4by inverter rill suppl_ a-e power

to etther_ or both_ ASCS and FAILSa_ busses by selecting the ST£RI_

posltlon on _-_,_respective _ AC BUS c_ FANS AC BUS switch loceted

on the _.4. _t panel.

In the event of fa_._e of either the 250 VA _r 150 VA main In-

wn-ters the respectivefan bus relay or ASCS bus rel_ wlll be de-

_. _s action wlll aut---ttc-_y energize the standby iu_-ter

rela_ whl_h in turn will app,7 d-e power from the filter to the st--_y

lnmrter. _he a-c outTut fr_ the standby inverter is then directed

through c_tacts tn the de_nersized ASCS _ _s bus r-_-ys to their

respective busses. A wernln_ li_latc_athe main Instrumentpanel inAi-

ceres _hen the stan_y inverter is switched tn_o o_era_£on _y reason of

fa_ure of e,th_ of the _ inverte_. (See _ 11-3).

11-8. l_3Um _13UTIOS

11-10

"_,_N_IiA. SEDR 104

1.1.-'9. D-C P0ma DX_0N

IF-- D-c power Is taken from three separate battery groups, neaely +.h-

main bat%ery, standby battery and isolated bsttery. Various sub-busses

which operate fro: "r.hese sou:ees and the bus separation method are as

follmm:

(a) Main _-¢ bus directly to the main battmz'le8.

(b) Math 24 v sauib bus _hro_h SCgIB _tah fr_ main bus.

(e) Main retro squib bus fr_ main bus through main retro squib

power drop relay.

(_) ASCS w._. 21_ V bus from u-_u bus %hrou_ sepamtlc_ relay.

(e) Pre-_wT_actplus 10 _nute frommLtnbUs through_-p.actrelay.

(f) Standby a-e bus direatly to s_nxlby battery.

(g) Isolat_l _-c bus directS7 to isolate_ battery.

(h) Isolate_ 2_, V squib bus _hrough SQ_JD3mrlteh from isolated bus.

(1) I8oi retro Squlb bUS fr_. main squib bus through lsolated retro

squib power _rop relay.

(_) Audio bus from main bus ar Isolated bus through AUDIO BUS switch.

(k) _ 6, 12 and 18 volt busses dlzeetly to taps on _an_y

batt_nT.

(1) Isolated 6 au_ 18 Tolt busses _etl.7 to taps on isolated

bat_ezT.

_ _I-,i0. S'_ UNITS

ii-ii. _S

Each eabln battery conslsts of series co-_ct_l silver-sine re-

chargeable cells hawln_ a n_-al potential rating of 2_ volts end a

I]-II

_t

NNELL SEDR 104

1. TOTALACTUALAND INDICATEDPOWERAND HEATDISSIPATIONLOAD 12,589.BWATT-HOURE.(MAIN BATTERIESSUPPLY7,553.8 WATT-HRS.AND STANDBYBATTERIESSUPPLY5,035.9 WATT-HRS.).

2. STANDByBATTERIESAREPARALLELEDWITHMAIN BATTERIESTHROUGHOUTENTIREMISSION. I Li:GEND J

3. PEAKSTO SHOW SQUIBFIRING SEQUENCEONLY. "JMAIN BATTERIES J JI STANDBY BATTERES ......ACTUAL WATTS

0 100 200 300 400 500 600 700 800 900 1000 11OO 1200

I I I I I I [ I I I I I I

| '.194.6 508.4 WATERSEPARATOR30 SEC./30 MIN,

| J643.6 EROGRAMMER"A" 50 MIL-_SEC./17.5 SEC.

T0 " 30 MIN. L'I _-

PRE-LAUN CH : 211.3 J$28.2 : TELEMETRYPWRSUPPLYAND XMIT - CONT. (PILOTACTION)

HR- T0 - 18MIN. t! t I , UHFT/l_AND BOOSTAMP. - ST'BY (PILOTACTION)214.3 535.7 "_"-I TAPERECORDAND LO LEVELCOMMUTATOR-ON

_r0- 12 MIN. "_237.S 1593.7 _ C BAND BEACON- CONT. (PILOTACTION,L /

TO 6 MIN.-596.3 IC EAND BEACON- INTERROGATE

i

1238.5 614.0 -- UHFTRANSMIT

' • O .._^ tHORIZON SCANNERS- ON

UMB. DISC(To)BECO _ 245_3t 245.9 614.7LAUNCH TOWERSEPARATION _ ,_ TOWBt SEPARATIONBOLTS

.I HR. : _- ':SCAPERCCKET

,q_ : 253.1 650.6 - UHFTRANSMIT! .7

SPACECRAFTSEPARATION--I-- 1696.3_ _ :SPACECRAFTADAPTERBOLTSI 278,5 POSIGRADEROCKET& UMBDISC.SPACECRAFT SEP,+5 SEC. /

|276.7 691.7 HF DIPOLEANT EXTENDSPACECRAFTSEP+ IOSEC. i_

j 278.0 695.0SPACECRAFTSEP+ 30SEC

| 276.7 691.8 ( ANG RATEIND-OFFORBIT-ATTITUDE"|---J 1_5553.5 • _ TAPERECORDAND LO LEVELCOMMUTATOR-OFF

SEPARATIoNSPACECRAFTI _P 612.0- REACTIONCONTROL (ASCS)

L.+S MiN. i

i 221.4 57! .1 - UHFTRANSMIT

- C BANDBEACON- INTERROGATE

SPACE---_" ........ _ .c - ASCS- OFF (PILOTACTION)CRAFT I 297.6

TAPERECORDAND 60 SEC/10MIN+I HR : 119.0 " 336.9 Z CAL - 15 SEC. ONCE EVERYHR. LO LEVELCOMMUTATORORBIT o 334.3RCAL.- 15SEC.28HRS. I

C BAND BEACON- GND. COMD.SPACETELEMETRY- GND. COMD. |(PILOT ACTION)CRAFT

[ UHF- OFF & HF T,/R- ST'BYSEP.

+3 ORBITS 1220.7

_2_07.4- BLOOD PRESSURE(PILOTACTION)

j_J 251,2- HF TRANSMIT1377.4- EROGRA/,M_',I_"A"

88.3 _] 242.3- WATERSEPARATOR/

L.s_ 279.3p REACTION CONTROL(F.B.W.)229.3- ROLLHORIZON SCANNERHEATER

229.3 - PITCHHORIZON SCANNERHEATER

241.7- DATA_60.0 - Z CAL. - 15 SEC. ONCE EVERYHR. _ rAPERECORDAND 60SEC/10MIN.

i_ 255.5 - R CAL. - 15SEC. |J I LO LEVELCOMMUTATOR229.3 YAW OPTICALREF(PILOTACTION)

| 220,7

-f- _.......i j- ,A_CS-ON(PILOTACT,ON)4 HOURASTRO

I 190.5"SLEEP" _ 534.6_ REACTION CONTROL(ASCS)PERIO0+ .......: : ASCS - OFF (PILOTACTION)

FMI8-14,5-1

Figure 11-_ D-C Watt-Hour Loading (Sheet 1 of 2)

11-12

MCDONNELL SEDR 104

ACTUAL WATTS0 100 200 300 400 500 600 700 800 900 1000 1100 1200

lJ--I ' IT2' ' ]{ . . . . I I j20.7

T88.3 , TELEMETRY- ON

_'] 1"_8"7_°SEC'),.3 "cBANDBEACON-ON/_116.8- z CAL.- 15SEC.

ORBIT 1119.5 314.2 - R CAL - 15 SEC. 6 MIN/GND. COMD.

28 HRS. : • c BAND BEACON INTERROGATE

TELEMETRY - OFF

r'J88.3 J220.5 _ C BAND BEACON - OFF 7 [ TELEMETRy - CONT. (PILOT ACTION)

TR-3 ORBITS --"Ii 106.0 '--I ( HF- OFF & UHF T/R & BOOST- AMP-ST'BY (PILOT126S (ACTION)

TR'2 ORBITS --t"i119.0 J2;7.6 C BAND REACON - CONT. (PILOTACTION)T R- 45 MIN,

J_°.5 'ASCS - ON (PILOT ACTION)221 _4 L _TR - I0 MIN. 1--_ ANG RATE INDICATOR - ON

231.4 f;]578'5TRO5EC 2,1R 5 I:Es:;;:::H::2TR "I I -

I 238.2 J 595.5 RETRO ROCKETS (3 PEAKS AT 5 SEC. INTBVALS)TR+ 30SEC. L-I

,:,z_3.2 _..'2

T + 90 SEC. I'll " ' HORIZON SCANNER - ON. RE*_O ASSY. BOLTR_TRO JETT. 660.5

264.2 RETRO UMB. DISC,RETROJETT + 30 SEC- Lt- =¢ 'ASCS SLAVING- ON

TR+ 20SEC : 274.0 1 4'9

RE-ENTRY ST'BY BATTERIES- ! MAIN BATTERIES= 706.5 - WATER SEPARATOR

.5HRS.7o2.9-UHE_NSMIT

: I_'1"9-EROGBA,,_ER"A-: [..

.05G r .... .I -- ASCS SLAV1NG. ATT. GYROS AND HOR. SCAN-OFFt204.7 J511.7DROGUE MORTAR

21K' I 207.3518.3

17K' _ _CABIN FAN - OFF'208.0 526.0 ANT FAIR SEP AND MAIN CHUTE ( AND. RATE IND-OPF,

10K' -- f-J • _ ASCS RATE GYKOS-OFFASCS A-C BUS-OFF (PILOT ACTION)

'II 196.6 l_

: 193.5 .7

10K' + 12 SEC. --_ - LANDING BAG491.6

10K + 150 SEC p _-I _ 'REACTION CONTROL (H 2 02 JETT) - OFF

1163.4 1408.5.J.

IMPACT : 144.4 [360.9RESCUE AIDS

_'_ ,MAIN AND RESERVECHUTE DISC (RES AIDS _" I SEC.)l151.3 _ RESERVEEJECT AND DEPLOY (RES. AIDS + I SEC)

139.7: _,_ .3

RESCUE AIDS r I 3: ,WHIP ANTENNA+ 30 SEC.

-_ _x,2 SQUIB ARM SWITCH-OFF (PILOT ACTION)

.... : 136.6 S _ C BAND BEACON AND TELEMETRY-OFFiMPAC1 J213.3 ( TAPE RECORD AND LO LEVEL COMMUTATOR-OFF+ I0 MIN.

J 370.0- PROGRAMMER A/

POST _ 85.3 _ 243.8 - HF TRANSMITPERIOD12 HRS. 235.oWATERSEPERATOR

I1 _n81.7 |J204.3 INTERIOR UGHTS - OFF (el LOT ACTION)

FM18-14,:_2

Figure 11-5 D-C Watt-Hour Loading (Sheet 2 of 2)

11-13

NNELL SEDR 104OFF

-IIl'

7

I[_EAGLE PICHER MA_L028-1, MAC 45-79707-15 {1500 WH)

I[_EAGLE FICHER MAR4027-B, MAC 45-79707-21 (3000 WH)i[_EAGLE FICHER MAR4028-A, MAC 45-79707-19 (150OWH)

_[_EAGLE PICHER MAR4028-fi_ MDE4587020-5 (1500WH)

, • . • •

: T-24V 6V 12V . 18V J18V 24VI

f F G . D E C B_

CONSTRUCTIONTYPICAL 1500WHOR 3000 WH8ATI'ERy

FILLER__

HOLE

PLUG-_

MANIFOLDSCREW PLUG

OQ O RELIEF

_ ELECTRICAL

NOTES

[_ MAY BE INSTALLED IN SPACECRAFTFOR GROUND TESTSOR FLIGHT.

[_ MAy BE INSTALLED IN SPACECRAFTFOR GROUND TESTS.

[_> DO NOT INSTALL IN SPACECRAFT.MAYtBE ACTIVATED ANDIUSED FOR _vO _POWER,SYSTEMS TESTS_ GROUND

AND BATTERY CHARGER TESTS.

VENT UNE

CONNECTOR

24V ON-OFF SWITCH'

OFF

[_EAGLE PICHER MAR 4027C_ MAC 45-79707-17 (3000 WH)[_EAGLE PICHER MAR 4027-1, MAC 45-79707-13 {3000,WH)[_EAGLE PICHER MAR 4027A, MAC 45-79707-17 {3000 WH)

_- _1_ [_> EAGLE PICHER MAR 3027C, MDE4587¢Z0-3 (3000 WH)

-24V 24V 24V

f _, 't FM18-3,_,

Figure 11-6 Typical Battery Assembly

11-14

__NNi/.J. SEDR 104

_',_,m capacity ra%ing of 3000 vatt-hours for the three main batteries,

3000 watt-hours for the _wo stan&y bat_eries an_ 1500 watt-hours for the

isolated battery. Each battery t8 equippe_ with 8 pressure relief valve

desXgned to ma£utA4- £nternal preseure from 5.5 to l_t.9 p82. _he pres-

sure x_lief valve XS moun_ed external to the battery ease. _e battery

ewlteh i8 _ _he poml_£ve 2_t volt CaLtput.

The battery electrolyte consists of a 40 percent solution of reagent

grwle potamsium hydroxide and distilled water and is used to activate the

dry charge4 ba_x_y in£tial_y. After the first dAeeharge cycle, the

ba_ter]r may be reeharged by a constant current battery charger. The

batteries fin_tsh power for all electrical equilment in the spacecraft;

therefore, proper servicing and aLalntenanceis of extreme impca-tance.

_e ba_4r£es are desigl_d for five e m_.2ete cycles of discharge an8

charge; however, for highest reliability, traits shoul8 not exceed four

eyeles or an aetivate_ life of 60 days prior to flight. For the internal

wiring of the batteries see Figure 11.6.

_he d-c "to a-c inverter8 installed in _he spacecraft are of a

solid e_ate design cepable of operating continuously at i_,_ rated

power output in a _ient a_osphere of 160°F. or at 80°F. at _ psia

100_ OX_Ke_. _nverter8 are eoolec_ by the use of heat 8_nk8 and baffles.

5he output is 32_ volts a-e + _%, single phase to ground, with a fre-

quency of _00 cycles + 2. _ and essenti832y 8£nuso£dal in _avefor_.

11-15

Md_OONNmLA. $EDR104

Z.'L-Z3._-C _ 0-_0

The a-e mm___er is located on the main Ins_nt panel an_ provides

the astronaut with an in_icstion of total current drain f_cm all bat-

teries (.seeFigure ll-l). The basic _r movement has a 50 millivolt

sensitivity. A shunt of suitable resistance is connected across the

input of the meter provi4ing a low resistance path to ground with the

proper voltage drop at _0 amperes for a meter movement to full scale

deflection.

11-1_. _c vo_ o-_ v_

A _-e vol_nster, and selector switch, are located on the main

Ixurt1_m___t panel (see Fig_we ll-l). Ap1_csctmatebattery cm_dltion

can be detez,m1,_dby placing _he D-C VOLTS switch to the appropriate

positions and rea_LDg the In_/vi_ual battex7 vol_es. Main and isolated

voltages may also be determiDed by placing the D-C VOLTS switch to the

e_propriate M or I position.

ll-_. A-C

An a-c voltmeter an_ a flve pOsltlon seleotor switch are mounted

on the main In_ panel. The five posi_lans of the a-e voltmeter

mrA_eh are 250 VA, 150 VA, Stay, ASCS ariaFANS. (See FAgusreIi-i).

ll-_. _u_ TTO_n_

11-17. S_ST_ _S_PTIO_

Interior 1Aghtiz_ for the spaeecra_t consists of "two fluo_seont

eabln lights, and a sez'les of warning telellghta. See Figure 11-7 for

11-16

19C_D(PNNELL SEDR 104

I ' I, ' j (_I t J Ss /

',,_ MAIN INSTRUMENT PANEL

,\I

--. MAININSTRUMENTPANEL

FMI8..32 A

Figm'e 11-7 Interior Lights and Warning Lights System

11-17

NNELL SEDR 104

11-18

'__NNJ£J. $EDR 104

_catton a_l arransm_t of cabin lights and tele_hts.

11-18. CABINFLOODL_S

TWofluorescent cabin flood l_hts are soont_ on brackets to the

r_ght aria left aria above the astronaut. Power for the cabin lights is

supplie_ fr_ +__ 119 V a-c inverter fans bus auA controlled by a three

positio_ s_teh loea_e4 on the left ec_eole. _he switch positio_s are

markeA BOTH, 13' 0BLY e_l OFF. The cabin flood lights are of high actinic

value; espeelallysuitable for ca_aerau_. _he lights produce little

heat and have a low Tattage cons,m_tion of 7 watts each (see Figure 11-7).

f_/

11-19

S£CTION XIIf-

COMMUNICATION SYSTEM

TABLE OF CONTENTS

TITLE PAGE

System Description .................................. 12-5

System Operation ....................................... 12-10

System Units ........... . ................................ 12-30

12-1

IVNELL SEDR 104

$ / t

/ _ _

/

I

III

=

III

U

_z

N_

U

I

\

\

_ - , , -""_ _-_ _

Z

i!k _ _ F/_18-I04

Figure 12-1. Communications Sequence

12-2

12-3

Aq_mLL $EDR 104

8 8

i

8_

If 'i

12-4

__NNmi_. SEDR104

sren

The ss_onmt is pro_te_ vtth voice e_esttons t_h_t the

entirealssloa (see Table 12-1). A _ headset _ s__ eon-

t_4_ vtthtn the utzoaant's heluet, ope_ste thzoush the Sa4to eentz_l

eircultsto the seleete4volee e_eatians set (see F_4ure 12-2). A

s_aeee_ intezl_ system Is av_41able_rior to _illeal ease

dlseoaneet.

receptlonis &vai_le t_ the _ Voiee _tlon set

4arlag launch and orbit. HF voice trammm_sionms,y be +used,+,_sly after/f

spacecraftseparationby astronautselectionof the Z_ posltlon of the

sviteh. Th_ _ set is dAsabled at antennafalrlag separateaa£

re-emergizedupon la_. The _ Voloe _eatloM set px_vldes re-

eeptloaca4 transmission,du_ the post land_ ._1-e of the mission,

_1-o.

reception is ava4_*_e t_t the entiremission by the

Voice Co--cations se_ a_ its _ Booster_zTllfier. Traasmissioas

over this set aa_ be mute _hen the _MPposition of the TBAI_MIT switch

is selected by the sstrommt.

_e selectedtransmittermay be energizedby operatlonOf a _-_-

+z_ nlteh, or by a voice operated re_ _e_ the VOX mrAteh is in the

ON _osltlon by speak_ into the z_lero_. _e _ trausmltter_

si_ml. _hls antc_atlefeatureI_ be ove_Ti_len_ the astro_t.

12-5

NNELL SEDR 104

FMI8-102A

Figure 12-3 Command Receivers System

12-6

_ _--_'_NmA_. SEDR 104,

A spaaecreftto llfe raft extensioncable is pre_ to a_aw the

astro_sutuse of spaeeerl_ttra_tter-reeeivers 1_aileeL_mi4e the

ane_ aaaater_ attheeaaeZa _ lestext,mmlm__b_Le, _e

_eeee_ en_ of the exteMioa,esl_e _ :]m_I_L .wt_ a _ _Leh Zlt,

the ut_t's m_Lt _eo_eet. Wlth _e _ Switchin the

position,_ o_L _ _tton is pz_vt_e_. With the _ sw_h

_he ¢_msn_ _elver pz_v_em an mers_z_r Sz_m_ 8tstton-to-_?aee-

e_.vol_e ._mm_Leattons _ _h_ the autu_ untt_ s_aee-

h_aet. Power for die volee emmm_testtons sys1_ £e Sure,Led

thro_ fuses _te_ iu the _eations _ _unle&tlens AS_ Fuse

wozae

A set of Reeeiver-_eeoder_and s_.tAlary decoder m_its is used for

reception ana deeod_ of _una _aad ,_As. _hese st_aa_-are

for the purpose of a_tiv_ti_g various _ontrol circuits.

Power for the Comaand Receivers is s_ppl£e_ th_Oa _e fuses

located in the Cm_ations an_ _he Cem_mteations A_ Fuse Holders

(see _'_ure _.-_.

_-._.

A Tele_et_ Transmitter is px_ywided for _z_ie&tlDg _--tr_en_tion

iu_orm_tion to the _ stations. Zn_tion is picked up throughout

the spaneera_ in the form of voltage_ _ voltage _ivi_er circuits.

12-7

'_ONN£L t SEDR 104

12-8

__N_EI_. SEDR 104

These voltages esuse VCO frequeneles to cha_e, to su1_l_r suitable in-

puts tO the Telmtry Transmitter. (Refer to the T--truaentation

Section. XIV of this mamutl). A trans_tter havi_ a power output of

2.0 watts is usA_ for transmission of telemetry information. The

operation of the transmitter is controlle_ by the T_TR_ sw_ch

on the Main Te-tru_ent Panel. It's _hree selections are ORRD COMDs OFF,

and 00_. _he Ix_wer output of the telemetry transmitter is fe_ to either

the Main or the UHF Descent Recovery Antenna. Power for the system is

obtained frcu fuses locate_ in the Instrumentation Fuse Holders (see Figure

aaa

ac0ns

The beanons provided in the spacecraft to aid trackt_ byf

stations are C-Ban_ and S-Band beacons, a t_F Recovery Beacon and an

auxil4A', 7 _ Bes_on energized at anten_ fairing separation, and an

XF Recovery Bea_an_ energize_ upon landis. These besnons provide sig-

nals c_tlble vlth _ection finding equi_ent use4 by the reeove_,

crees. _he _Y Voice _'.;,----_tions tra-m4tter is keyed at anteana

fairIDg separation to provide an additional signal for _1_ectioa finders.

A flashing strobe liSht is lustalled for visual location of the spaee-

crsf_ after landAng. (See Section VII of this manual).

Spacecraft power for the beanons system is supp]Liedth_ fuses

loeatea in the C,_..,anlc&tions aria ASCS 1_ase Wolaez.s. (See Figure 12-_

aaa

12..6.

_he voice _atlons, telenetry and beae_ receivers and

_m4tters, wAth their various frequencies and tTpes of out'pUts

12-9

__Nmg./. SEDR 104•

require an antenna _stea _rAth vide ee_bilities. _aerefoze, five

anteanasare used to fuAfillthe entire mlsslenrequlremmtsA Amain

_ieone aucemm=a = ae_ .._=_e-_ _ Aut_m_._ u,.earot the

m,_Ior 1_o_ion of the albion. _ z_-e_zT, +.he Bteoae aatens .ut

_e Jett_oaea to -_ov man lm_iutel ae_lo_mrC. _,e _ _le i. •

Jettisone4with the retro l_e. To zvA_laee.the UBF l_etion, a• . • . .

bicone separation° Ul_n lsnd_, an HF ReeoverF _ Antenna an_ an Aux.

out the entire mission, C- ad S-Baa_ snte_as are provid_ for operation

of the radar beae_as. Antemm _w_tehinKsndm_til_exi_ are performed

==t,-,.ti_,y _ the_ =_=i_._ (see_='e= _-6=,d _-z3). _=rer

_.acea on Use_e_ _w,_ s_A_-_e _eae_. (see T_m=e_.-_)

_-9. .a_:_ Cmm_A,= _ i i i r iiii i'_.. . .. .

HF._ _ reoelver out_ are route# to the controlI_, _hls

ln'_rv'ides one _lmM_ e_tzol for _ m_,d.l.oand, one 'volume eontzolfor

7

Of ecm_ aa£:volee_"s:J.KI_I.8 1_ & iC_ pass filter,aa_ a_pllfleatlon

of zem_].ting voice 8n_lx) is _ in the m_l.o ee_er. (Bee Figure 12-7)..

12-10

_/

/WO_OJwvmAJ,. SEDR 104.

Cn_4CsC.tcn Imd.l.osiSw_lJ f_nB the vo_ _,_-_ controls_ the 2nter-

s,,_o fron the pscl.-4;o-the-p21ot She. 81_,wmtones are sut_lAe8 to

the tape recca_er re_Ay and the two headset m_llflers in the _o

center. "ae hea4set _2ifiers serve to smplAfy the audio signals and.

fee_ them tothe indAvidual earlgwnes in the astranaut's helmt. _he

_e-enerKi_l post_ten of the tape recorder rela_ _pplies al_h fo_

receiver e-a',o 'to _he main 'tape recorder.

Z.xtto from +_J_._microphones _.s re& to two separate mieroph_e a_li-

fiefs in the audio center. _aeoe two mplXfiers serve t;o m_p.Ltfy micro-

ph_e o_tp_t to a level s_Aetent to s_P_V -,_,,_ _t_ circuits of _be

voice trans_tters, ghe nieropheue _pAAfAer output is also fed to the

energized by use of the Push-'_-Talk switch o_, 'the abort, handle. _ar.by

+-_-VOX circuit _hen the VOXswitch on the _t panel is in the

.'rnAaSNI"_poelt_cn. A_ter _.,Taot, .h. astrmaut -_.aAseonnee_ his ,uAt

ec_unleaticns em,_t_r an_ attach a _-he_am_-PTT mrlteh

asu_b_V to the suit ccmmm:tea't£_ ec_ctc_. _s mlerophone-headset

asseub_7Is fit_e4vlth a 27 foot vaterproofelectricalieab_eand is

used after egressto providethe astranautvlth tvo ray e_eatlo_s

c_ the spacecraft_ and _ e_eatlcu systems.

IF

12-11. HF _C_2ZC_S

5he HF voice eommnieattcaw set is an _ reeeiver-tranm_ter unit.

12-12

MCDONNELL ' !SEDR 104

A&"_

! U.H.F. DESCENTANDRECOVERYANTENNA

__ _ ACTIVEELEMENT

/ " F ACTIVE ELEMENTI -ACTIVE ELEMENT

i _!'--ACTIVE ELEMENT _ / ["I

" / [ IIII

r -''"NO / / ..... X I MAIN BICONICAL_c

I H.F. RECOVERY WHIP ANTENNA,

{clANDS-BANDANTENNA/_ ___"_\ 1.... _ _---,_,_ ,_.

(TYPICAL3 ,LACES.) /__ ACT,VEELEMENTJ

_ (TYPICALOPPOSITESLOE) " FM18-116A

:Figure12-6.AntermaS_m Utilization

:12-13

12-14

12:15

_NNEg.L. $EDR 104

Power from the _ PreoYjpaet 2_ volt _-e bus is fe_ aireet_ to

the reaeiw m_,.ica of the set. Mac trans_Ltter is fed 2_ yolts throu_

'_D' positlan of the _SKIT n_teh a_ the cloud contacts of

_arat.l.m _r, after _o,mrs_mc,a_m. ._m_Co_ 'to_ tz'ans-

a l._tez" V.c_icm of the m l.t _Ls_ the ml.erolg_m m_-'2er in the au_l.o

center. _he tr----_tteris keyea e_ther autma_leall_ _ the V0X

e_t _ _ _7 the utrmaut's use of _ xwh-to-_k _teh.

(_ n_ _-8).antenna ec_e'_1.en _rea the set :l.s b_ou_ _i,,,, .,.h.,,_ po_t_m

IF _ SZLICT m_teh locs_ bel_ the i_h_Ju_ co.sole. _e

_RCT mr£_ if_lizes kJaree positions s DIPOLE (orbit _Iv)_ BIOOHE

e_d _P. MWsO t_ sw_eh po82tio_s _,vv_ opt/mt_ anteing* opera_0_.

o_bit. Au_Lo outlmt from the ree_wer_ _eln_uK li_eto_e dur_ trsns-

ai.s_I.cn is routed to _ HIP_ol_e control _n the eantrol panel.

12-12. _MF V0I_ _SII_IICAT_IS

_e _F voice e_--_4eat2_ met is an N/_eee_ver-traum_t_r ,m_t

des_ned to operate m a frequeney of _ra_atel_ 299 Me. _he trenw_tter

mrbput _s ineroas_ by a Npmmte _F booster _]£fier.

v •

_MCDONIIIELL SEDR 104'

12-17'

_RNM;.I. SEDR 104

posl_to_ _ _he _ wl_ _ _o_the z_ee_ver Ne_i_

theset..(See_ _-9). Power_orthe._tt_r seet_ o_*__.

iS also taken _ _ _ _OSi_vtoD of the 'J_/MA_'Y svtt, eh. At

bieone an_.e,_a Jepsz_i_ the bie_e _-psz_i_ z_ eon_aets asmme

a eont/w.c_ _ _ _ m' p=pous, r _tO _ tO the

the ,_,_4_oeem_r. _he _'anud.tte_" Is e_er_J.se_ ei+_-_' autnm'_I.eA!_y

or maaual_ by the _. :It v£:Ll.be ener_.sed, au_eBtle-,,y at

bieo_e sepez_ti_ _o prov£de a IIHF'_ f_ _e_i_ _ equip-

the eeutr_l, lumel to the R/Y pos£tt_.

coax 8_A_eh,a_ _tiple_or, a_ _he e_a s_i_eh to ei_he_ the

_ts_s_ voiceo't_++"e..ea+x,'e+t_',_ _ "P_ _w"aoae causes *.hebo_s_

pu_ is _ boo_e_ by _b_ _l.t_z to 2 n_s. _he booster iS _o

mU__b_e _er zaas4_, _ m_ttpzex_ ou_pu_£s eo_e_ t_.

t_e e_ezu_ m_h '_0 et'k_r _ main bte_e _ _he _ rueue e_mua'

JlmsOAoou.'k_tt :Px'oa _ reeeiver, lae_xllz_ s:Lcte'kcm.eflm"l:_ _aumlssi_,

is _ _o _ _' volume e_rol la the c_nt.x'ol l_seL.

12-18

...._. 0 I_ _ 0 -- _ Z Z,..,

m z +z I_-_, _" I/_I-_I I',__

ZFMle-II tA

:Figure 12-10. Command Receivers Data Flow

!12-19

NNELL :_SEDR 104

TELEMETRY BICONE

SWITCH FUSE A m PRE- ANTENNA

t IMPACT

BUS MATININSTRUMENT PANEL24V •

ANTENNA SWITCH

D-C (SWITCHES TO NO. 2

ANTENNA FAIRING

-- -- JETTISON)

ORND I'

COMD 1 b )CONTOFF 1

TEL 2SWITCH

2•1[,_ EECOVERY 1

"_ KEY _ ANTENNA

• i

TELEMETRYCOMMAND

(ENERGIZED TELEMETRY POWER TELEMETRY _TRAN SMITTER MULTIPLEXERBYGROUND SUPPLYCOMMAND) i

B-:-200V --! 2FILAMENT DVOLTAGE

GROUND 5

I 24V D_INSTRUMENTATION

i

GROUND TEST

,.GROUND TEST GROUND _ 1/2 SEC.TEST TIME

UMBILICAL SWITCH _ DELAyRELAY NO. 3 RELAY

PM18-112

Figure 12-11. Telemetry System Data Flow

12-20

• Li L/.

_c.elv_e.._.ecd_' unt_ eom,_._r_sof an IM reee_.ver. _he z_elve_

s_nal asy be ,.__;,]-_e4 with s mztmm _ _Lx e_ s _oss_le' _ sudlo

_ea_les _hleh _ IaA:Lv'J.A,,a! e_'l_'ol re_. (Bee 1,_. 32-3.0).

m3.1,Telou4 cresol eh,,__ L _ea _la are 1='orlae4 _,, _ reee_L,rer-

_o_r,vlth an -aa4+J.one]._ svallable In th_ --_11a_ 4eel. Cca-

ehsanel aesa=ets arenotcU.se3.oae. eason:.

pae_ voice e_es'l:t_s _ be Ms4 _'m _ U,=mA st,at;tomto

s_a_eeza_ _h "the e_ reeetwr, l_-e_.ve_"_s are s_e4

_b_oUi_ a _11_ a_ _m_L_ler 1_ the a_l.o eeatez, etxcutts t;o .the astz'o-

| t s I_. P .Oi.Oi.Oi.Oi.Oi.Oi_"_| _ C_ila_ i_ tli _t_ _ _ ._t"

).8 vo)._ A-e bus. _ pover e_-'eults are roa_4. _ seet._.onsof

Ante_A t_U_ is _ _e bte_ae o_ _ _eseua snta_,m-thz_h tha

_ms svL_ an8 _ nu_t/_leze_ _o i_the _ece£ver.

M_e te_ t_It_er set Is an IM t.-_m1_e_ o_e=at1_ ca s

12-21

_, 2,/,, 6=-- <:>-_: ";._z _==_=-

" Figure 12-12. Beacon System Data Flow

'12-22

WCI_ON_mLL SEDR 104

Before _n_illeal drop, _h. telemetry tranmttter and its power

/__ supply receive 04 VOltS d-c t_on the Ymtn PTe-£mpact bus throt_h the

e_er81zed Ground Test Umbilical Relay t nczmaZ_ open contacts. _h_ S

re]J_'s soZenold ts energ£zed +_,_h-'Ott_the ,__l]_cal until the ,m_i14caZ

To sllence _he _4 tra_4tter, the astronaut may place _he telemetry

svlteh In the OFF position whleh w111 prevent 2It V d-c power from reachln8

the transmitter. PZaclng the telemetry mrltch in the ground c_and

posltlcm enables a signal from the 8round to energtze the telemetry

o.,_;_-_,,d relay vb.l.e.h will app.1_"power to the tranm_tter. _he elgnal

ls programmed to la_t _ mlnutes an_ then it is removed shuttt_ off the

telemetry _ans_tter. The tr_4tter wlZ1 r_,In off until c_=mnded

agaln by _round c.-._-.-_._-e CONT posl_£c_1Of _e _.w_3_/ switch

appZies a_ttnuo_s power _o the _ +_-_-_ter.

Code_ Ins_taticn Inf_raatlon is m_pliea fro: the lns_w*utati_

Ps_mSe _", aua usea to frequency _;:_,te _he tr_tter. (See _he

_u_a_1oa Se_tlon XIV of thls :_usl).

BY power output Is re4 to the _ :nl%Iplezer where It is routed

throush the entm_- svlteh to +_-_e,_-In"oiccme or _Y recovery antenna.

32-17. C-B_ BF_C_

• he C-Bsn_ beaccm is a transponder _tt cc_lstln8 of 8 receiver and

tra-_4_ter operat£u8 on a frequency of epprcnclaa_e3_ 5_00 to _900 MC.

_he beaccet ls _¢mbZe p,,l_ed and ls compectlble wlth modlfled FPS-16 r _a:-.

Upc= ground c_ad_ throush the eo_an_ receiver, or by astronaut selection

1_23

_O_NffLL SEDR 104

of the CONTpositiou of the C-Ban_ beacc_ switch, the beacc_ receiver is

energised. Interrogation by ground radar will then result in a eodea

repl_ fron the beacc_ transmitter. Xnput power is from the main pre-

i_act 24 volt d-c bus through the beacon relay conl;ro].l--_l by the

comm=_d receiver, or, for continuottsoperation_ throt_ _ C-Band

beacon swltch. An OFF position of the C-Ban_ beacon switch is also

provided. (See Figure 32-3.2).

_e C-Band beacon antenna connection is %broach the C-Band power

divider to the _ C- and S-Ban_ Beacon antennas. A phase shifter

is used between the C-Ban_ Power Divider and one C-Bend Antenna %o

prevent nulls in the raalation pattern.

12-18. S-_:._BN-_C05

_he S-Ban_ beacon Is a transporter ,m_t co_slstlng of a receiver

aml transmitter. (_:= Figure ]2-]2). _he unit operates on a frequency

of approxtmate_V 2700 to 2900 MC and Is double _,_l,,,ed to reduos possi-

bilities of unauthorized Interrogation. _his unit is ¢ospatible with

ground based Verlo_t Radars and operates at a positive acceptance

tolerate of + 0.5 mlcro-second_ sn_ a positive re_ectlon %olermace of

+_1.8 _toro-mconds.

Power @£rcu£te, interrogation and repl_ are the s_e as the C-Ben_

kacon, e=ph

Beacon antenna connection is thro_h the S-Band Power Divider to

three "C" and "S" Ban_ Beacon antennas.

12-24

_IIICDONNELL SEDR 104.

_z z_

12-25

_MCDONItlELL SEDR 104

m,/m,TWo recovery beacons are eomb,-_t lnto o_e unit. One beacon operates

c_ hlsh frequency, whlle the other operates c_ ultra high frequency. Both

are energized to provlde radlo signals for recovery direction flnder equip-

Be HF recovery beacon operates on a frequency of apprn_m-tely 8 MC

wlth a tone modulated output. It is powered by the 12 volt standby bus

throush the t:pact relay end 18 energized upon landis. The RF power out-

put ls fed through the rescue dtplexer _o the elevate4 HF Recovery Antenna.

Be _ recovery beacon operates on a frequency of approxlmate_7 243 MC

wl_h pulse modulation. It ls powerea by _ 6 volt isolated bus t_lTC.,dh t_e

antenna letting separation relay. _ht8 circuit is energtze_ when _ antenna

fatrtn8 ls Je_ttsc_. _he RF power output ls fed throush the aDten-a multl-

ple=er an_ the anT_m-n switch tO the UgF rescue antenna.

12-20. _In_.T_ RES_JE

_he Aux. Rescue Beacon operstes on a frequency of appr-_m-_el_ _43 MC

with pulse mo_balatlon. It Is powered by the 6 volt standby bus throush the

Ant_--- Fairl_ Separatlon Relay. _hese cireulte are ener_zed at antenna

fairing separation. _he RF power is radlated frnm the Aux. Rescue Beacon

_. (See ns_ 2-12).

12-2L AWTmNAS

12-26

WOOONNILL $EDR 104

A bico_eal antenn8 28 used for pre-launch_ launch; orbit a_ 4n_tie2

re-entry phases of "the_S8__.1_8__tS_____eantenna fairing and is located over "the open end of tim recovery system

cce_artmemt of 'the c_lind_cel spacecra_ a_eterbody. _ bico_cal

8ntenna serves 'the HF n,_ UHFvotoe receiver-transmt_ter8 s the c.--_,n_

receivers, anti the telemetry trsns_Ltter8. _ ac_lve elemnt of the

bioc_cal antenna f_s the upper portion o_ the antemm fa_r_ag _htle

•the lover p_c_ of the fairing a_l the spacecra_ bod_ fm the groun_

plane for "the ente_nA, (See _ 12-13).

F- A _ _ 28 used fca" the _ _Aee of re-entry; landing

rescue. It; 2s a compact antenna located, cm the open eu:rtace of

meovez7 syateus c_m_-_ent. The antenna £8 folded _en the m_;emm

fS_T_ '_B :l.nfft._11*iL _ 8eCOolld8 8_ th_ f_ t8 ,_0'i_tt8C8_

the UHF recovery antenna is erected an_ serves the t_F voice receiver.

tra-m._t_ers,the UHF portion of the recoverybeacon, the _:--andre-

ceivers,and the tele_etr_transmitter. (See Figure 12-6).

12_._. MAIN BICCffEBF D_I_OLBAHD _F RECOV_ _ F_

_he variousradio systa_ are ec_ to the blc_ne antenna,the

_F dipole or the U_F recoveryante--ain the follo_ runner: (See

12-27

_MCDONNIILL SEDR 104

(I) 'me HF voice receiver-tr_--m_tter antenna leads are ccmnected

to the HF _ SBLECT _ coaxial switch which _nen placed

in the fo3.3.o___-_ positions feeds the antenna systems as fo!_s:

(a) _ position, HF recovery ante--- thro_h the recovery di-

p]_xer.

(b) BICUNE position, the bicone antenna through the main m_lti-

ple_er and the antenna sw_tch.

(c) DIPOLE (ORBIT O_LY) position_ ¢o _ HF dipole ant_ma on

the recto package.

(2) _ O_ recelver-tren_qtter antenna lead is connected _ the

main w,1_Iple_er, _o the antenna nltch whose outputs feeds the

blcene antenna un%il an%4_m_ separatlm. After antenna sepa-

ration the descent anteDna is f_l.

(3) _e c_l receiver antenna lead is ecanected to the antenna

multIple_er.

(_) _ Lov frequent7 tel_._ry transmitter feeds d_recltT to the

antenna mtltip]_er.

m_he ant_"- _,_tiple_er enables aimcltaneous or i_I:Lv_Aual operation

of the ra&to system- using one antenna. EfTective_y this is a raalo f_e-

_Cy _unction box v_tch allows several receivers an_ tr--_tters ¢o

operate slmultaneously _hout Interference with each other.

cc_nectlon ¢o the antenna is e_h 1;he ente-na sw_tch to elthe_ _ae

12-28

W_iI.L SEDR 104

_iconlcal antenna, or the t_F rescue an$_-_na. _e antenna swi_.h is

_ operated by the antenna fairing separation relay to cause the autnmatlc

_ht_t t_Cm _ main am_ezms to the U_ rescqze antemm t_c_ antemm

Jettlsm Figure

An antem_ Is provldml to permit _ radAo tra_eslcn and receptlo_

a1_er ]_z_. q_, and_nna t8 a telescoping _ip an_zma vhloh is auto-

matelal_ extended by a pyrote_ c after _mpact. Once extended, the

antenna is uses for t_e HF voice recelver-tra_m_tter and the HF portion

of the recovery beacon.

_he HF recovery beacc_ fee_s through the recovery dlplexer. _e HF

r_ voice receiver-transmitter is fed through _ position of the ma_ ANT

and then into the zeeovery diplexer to the HF _aip ante---. _he

dAple_r _ e_,,ltaneous or in_tvid,m_: operation over a single lead

12_._. C AND S B_D A_Z_AS

m_ee C- a_l S-Bau_ antenna units are installed in _he spacecraft

structure f_r +_e C- a_ S-Ba_ beacons. _he_e ,,,_tsare equal_ spaced

about t_e ctrcm_erenee of the ec_lcal secttc_. _ach az_enna unit con-

sists of one helix as a _-Ban_ antenna a_4 _ he_Y as an S..Bm_ _tenna.

_tenna lea_s from the C-Ban_ m_ S-Ban_ beac_ are _oute_ through

r _ i_vid_el pca_r dividers tO the three assoclate_ he1_- onte--as. (See

12-29

_ONNBCA. SEDR104,

An HF Dipole antenna is used while in an orbit conditlon. _he

dipole ante--- consists of two unitsj one attached to either side of

the retro package. _he active e_ts co_Islstof tubular bery11'h,,_.

copper ribbons. _e ribbons are rolled in a flat condition prior to

orbit. Upon reaching orbit, a squib is fire_ on the dipole antennas

aasa_lies, to release the active elements and allow them to unroll and

become tubular in an extended cc_Ition (See Figure 12-13).

12-z9.

12-3o.A io

_e audio center provides transistorized audio s_pliflers, a voice

operated rela_ (VOX), an audio filter, tape recorder control circ,xltry

and transmitter control circuitry. (See Figure 12-7). All components

are contained in a light weight, foem encapm, l_ted --_t.

Two fixed gain headset _plifiers are used to bring audio signals

ep to headset level and feed the headsets separately. Two fixed gain

smplifiers are provide_l to increase the dy,=_c microphone outputs to

a level suitable to be used with the various transmitters.

A low pass filtar, with a cutoff f_ frequencies above 3000 cps,

filters the audio supplied fr_ the c_ receivers. Outputs from

the filter is fed to a variable gain_ command audio amplifier.

_e "voice operated relay" is a translsturIzed s_pllfier with separate

a_ustable threshol_ level and release time controls. _e amplifier

12-30

©"_,mqCJ_NNEI,,L SEDR 104

owrates a relay to provide a grounding circuit for tranm-ttter keying.

_his --tt parallels the external PTT switch.

_he auaio center fur__a_s a circuit to appl7 the keying grom_

potential to _e transmitters. Each circuit is protecte_ from the

rest by a diode.

A relay is installe_ in the audio center for suppling pover an_

aud£o signals to the tape recorder. In the de-energized conditl_, the

relay closes s circuit to the tape recorder input, thus audio received

by the spacecraft is recorded whenever _nRtrumentation pro_cmas tape

recorder operation.

When the microphone svitch or VOX is operated, the tape recorder

relay is energised if VOX operation of tape recorder is selected. One

set of closed relay contacts nov c__ple_s the recorder power circuit

indepen_ent of instrumentation l_c_raw_nS, _nile a second set of

contacts routes signal from the microphone amplifiers to the recorder

The circuits in the audio center operate directl_ from the space-

craft 24 VOlt d-c i_puts with no further re_tlatton or voltage increase.

The audio control panel pruv£des controls and circuits for the audio

signals of the variotts spacecraft receivers (see Fi_tre 12-7).

The HF and I_Y circuits are routed through individual T-pads to

vol_ne controls. _e _F circuit has a single vol_ne control, the stone

is true of the _F circuit, _htle separate vol,m- control is provided

12-31

_NItI|LL SEDR 104

for the cm--_ a,_o circuit. F£xed l_uts are used for the alarm

tone and groun_ tnterphone circuits.

_he panel also contains a mrl_ch override f_ the impact keTlng

feature used with the _HF tram_tters, mzt _TInK butt_ on the panel

to _nt_,_ ___e tel_etry B+ s,ppl_ to provide ezer_ keyl_. (P_fer

:12-32. HF VOI(_ _vr,_-_

_he _ volce _t £s _- _ receiver-tr_ttter de8_ as a mall,

The receiver sectionof the --It 18 a translstca_r_d.i,_t_me

circuit using a crystal filter,crT_al diode deteeta_ an_ elaH B audio

emp!tt_er. _he final au_to amp]J_er i8 use_ for sift(me du_ lw_-a-

a£ssic_8.

_e tr_--._ttermetlon of the un£t ut_ vaomm tube s_s fo_

the crystal ¢ontro11_ oscl]._atc_, driver an_ power m_.llf£er. _ae

power mpl£f£er m_ be mod_]_l_l up t_ _0_ by a tw--_tstm_LNd _eoh

empl_£er aml motivator. __q___seau_l.o ert,_8 are alao _meclteL- e_le-

tone. Tr_-_t_ter output i8 _ watts. _ae _m_ i8 powered by spacecraft,

21_volts d-_; Power is route_ _ an exte__-_ mr£'r_.h_ contacts

+_" __ _ a_ _ _ _ r _t_ _

power, rela_ operati_a and a t_an_istar_ poee_ea_verter. •

12_32

"__NmLL SEDR 104

D-e voltage i8 also _ from the receiver RF stqes. Autenna

swAtchtng is acec_llahe4 by 8 solt4 state circuit ihich block= the

•:m_.ver _ trensaJ.ssJ.oa.

vtxl,ee _eelvar-t,r_m,ma,t.tt,_r ecaas:l.st,s of an _ reee:l:ver-'taem_s-

:ttter designed as a malls 11gbtwet_ ,s,_t operating near 297 Me.

_..,_-._tt;er _ i8 .5 va_. 51m traasmAtter _ is boosted oy

a flnal boo_e_ _IACAer.

_e receives aectloa of the _t is a translst_ised sul_0_ete_dyae

elrcalt_ a crystal coatrolle_local oscillator,c_ fA1t_r _

crystal _Alcde4erector, _he audio sexton o_ the re_elver also serves

as _e speeeh _llfler, modulator_:d px_ldes s14etc_e fc_ the trans-

:i_te:. _he transalttersectlc_of the ,,-_tutilises a _-ystaleon-

trolle4 o_l_-tcr, trl_ler ea_ p_nr _m_iAfler. _he RF se_tlc_uses

vacu=n tubes _hile the mo4.ulatlcu clrcultsare transistorised.

Spacecraftpover, 2_ volts _t-e,Is m_iAed to tbe.se_, m_s vol_a_e

is applAed to th_ _e_etver_ a_Ao circuits en_ back _h.rou_ am external

trl_s_Lt seitch to an internal po_er ec_e_er. _s transistorized

converter supplAesB+ vo_e to "the transmitter RF se_ttou. _b_ems-

_Ltter fil_ent voltap is also a_lle4 bT the externeA transit s_Atch

ca' the bteone se_a_'a'tlas, ml.a_ _ bieone separaticm,

SWAtehln__ receiver to transaitter operationis aee_,_.l,t.abed

__e_ _ potentialis appliedto a s_itehingrela_ and a blo_

circuit. _ _1_ _z_t4es sn_ m_l,.power eo'uve_c,ex" mr£teh_.

bloek:L_ eireult z_oves reee£ver voltage,

_mNJ_L. SEDR 104

A booster smq_r Is usea prior to _ to increase the . 5 'ntt

ou'_ut of the _ tr-,,_t'-t_n" to 2.0 w4_ts'. _he higher power is also

available after lsn_ng.

_snaz _ to the _,oos'_ is route_+.h__uSha aoubzepo_, exe_

throw coaxialrelay. _en the relay is de-ener_zed, the Signal is route_

_e_k.

•_e eo_ receiver-decoderis a transistc_-izedunit cc_slstingof

an FM Receiver an_ a decoder unit to operate control e_reuits.

Cs__ng..-.e_-_o).

receiver se_tic_ of the ,m_t is a _ual eonversic_ st_he_

circuit. _he first local oscillator Is crystal con_n_lled a_l uses two

stakes of f_equeney _ttpl£eatton. Two stages o_ _m14_£eation are used

for the" f_rst IF, 78 MC s_na_ _e sec_ loea_ ose_Uator ts also

crystal ccntzolle_ _ wAth the first XF _ glv_ a resultant secon_

IF of.lO. 7_ MC. Outputi_o_ the IY strip 18 +.-_o_h • li_Iterto the _18-

"cz_uator. _;;_o mm_l_flers boost the 41se__m_-to: output for_he corn-

voice_,-,--_e_ .u_ a_oaor_-,_ver._ae_ver tn_m-neupp_es_e

ten _eeoderchannelsin _e aet.

_e In&i_i&ml deceder _--*la each provide filters f_ $_elr _pecli_lc

e_ frequency an_ e_la_ers to operatea _o_ble pole,_ouble +_row

re1_r for ee_h_,,.,.,.,-I..5_ tenrel_'_ _huesakeavat_b_eno_a1_

aria normal_ _ ebntaeta for extea_aL eoutrol e_at_; operatteu.

•12_q4

S_eeraft po_, 18volts_-e,is _ to pawer_he set. A

_ _ioae elx_t, vA_In the _.It, is _ for voltap regui_ion.

auxili_ _e_oaer operates vi_ _e recelver-_eeod_r _mLt, al-

•he deeoder _s_nels _ the e_IAa_ deco4er are laentleal to the

decoder -_m_is of _he reeelver-_eeo_er, _i_ the exeeptioa of the

e_ fze_a_lesat _MA_ they_era_e.

_he _;elamtoe_" l_3_er _lles pne_a_e vol_age _ _il:,be "be3.e_et,.-_

e_a_ _tc4ss. 81u_eers_ X_,r, 2_ volt, _L-e,£s all,ted to a _-aus-

_.

A i_1! _ave, ex,j_ _io_e reeti_Aer iS _ Ca_ one oeeo_, .YAth

voltap _e_,_-ti_,to _ovlde200volts_-c.

.m4m

_ of apize_,,-_.v 2.0 n+..tsat ap_ox_a_e:_v _ _C. a_hetraao_e.er £s.

an I/( ua_ u,_ WO _m_s _a _rme_ta_m circuits, wo" st_us_

are epp_L to a_Lr_ step sS4pa_ m_Aer-ioola_o_ c_-_Lt. _ 1_'.

• 12-35

_MODOItlNItLL SEDR104

portions of the transmitter consist of a triode quarts line oscillator

into a pentode buffer stage feeding a triode power smplifier. The VCO

signals are fed to the oscillator stage. Filament and B+ are obtained

from a separate power supply. Spacecraft 24 volts d-c is the telemetry

pr_,_y power supply.

_e C-Band transponder is a pressurized superheterodyne receiver

and pulse modulated, 400 watt peak output tran_itter, operating in the

frequency range of 5_O0 to 5900 MC (See Figure 12-12). With the exception

of the _gnetrcn an_ local osc_l_=tor, the ,,_t is trs_sistarizea. _e

receiver consists of a pre-selector, local oscillato_, _00 MC IF _nplifier

strip, pulse c'Lete_or, p,,_-e--T.lifierand decoder. Resonant cavities are

used for the pre-selector and local oscillator.

The tran_,_tter section accepts decoder outputs andpulse mod,,Intes

the transmitter out-put.

The unit contains a power supply for converting spacecraft 24 volts d-c

input to filtered 2_ volts d-c and regulated, 115 and 150 volts d-c out-

puts. Antenna sharing is through an internal diplexer.

32-. S-m D

The S-Band transponder is a pressurized superheterodyne receiver and

pulse moa,,1-tea;lO00 watt peak output transmitter operating in the fre-

quency range of 2700 to 2900 MC. (See Figures 1,?.-32).

12-36

_ _O_N_. SEDR 104

Receiver and transmitter circuits ere _he same as "those used in the

C-Ban_ beacon wlth the exceptlc_ of the pre-selector, local osc_11_tcr

an_ trAn_tter which are designed for S-Band frequencies.

_e recovery beacc_ cnm_ines an HF_ to_e m_lulated_ 8.36_ MC trans-

mitter an_ a UHF_ pulse modulated_ 243 MC traumnitter into one .m.11_

foam encapsulate_ _mit. (See Fi_tre 12-12). _e _F section of "the

beacc_ is a c_e tube circuit wlth a p,,lp.e codi_ network. _heHF

sectlc_ of "thebeacc_ is a "transistorizedcrystal oscillatc_ _ "two

stage power mw_l_fler vlth t_e mo_ulatic_ supplied from a power con-

Verter. _e beacc_ utilizes 6 exu_12 volts d-c _m the spaceereft

power syste_ _e _F secttc_ is energize& by e_plying "the 6 volt _-c

to a transistcrize_ power cc_verter. A i_,11wave, crystal diode elf-

cult is used to rectify the power converter ou_ which is applied to

the UHF stage. ApplFin_ 12 volts _-c e_ergizes the _F sectic_ of the

beacon. No power converter is re_-_recl f_ the 12 volt !,,!_t.

Modulation f_r the _' section is provide_ by ro_tlz_ the 12 volt

s_pl_ tO _he power e_lifier sta_es throt_h a secon_._y _ of the

power converter.

12-_. At_Vv_Y _F RESCUE BEACC_AND AFf_NA

_he Aux. U_F Rescue Beacon, consists of a pulse m_lula_d trans-f_

mi_ter and power supp_V which is enclose_ in a foam encapsulated case.

(See _ 12-12). The unit _s c_ecte_ to the 6 volt standby bus

an_ has an output of 91 watts. The on_enna is moonted in the recovery

c_mpa_nt add is self erectlc_.

12-37

_MOOONNELL SEDR104

antenna multiplexer allows reeeptlcn end tr_nm_ssion of the

many spacecraft frequencies over one l_e to _ _Icone or U_F recovery

antenna. _he unlt consists of a n_er of filters a_=Aen6edso that all

spacecraft frequencies between 15 and 450 MC can be multiplexed on the

single feed iane. Each input channel is provlded 60 db of isolation.

_e recovery diple_er n-It is used for the _F voice recelver-tr----

mltter and HF section of the recovery beacon. One low pass and one

pass filter is used to diplex approximately 15 MC on one feed l_-e to the

HF recovery antenna.

RF mrAtehing is ace_wp1Aahed with motor driven SPDT swatches.

_pllcatlon of spacecraft 2_ volts d-e through external circuits drives

the svltch to the appropriate RF position and opens the power circuit

for that position. The manual HF A_ select switch is hand positioned

to the DIPOLE - BICCBE c_ Ww_P position.

12-_6. BICO_E

_he spacecrai_ ls electrically divided in two sections. (See Figure,

_-6). _e antenna fai_Ing structure at the Junction of t_ese sections

resembles a discone antenna. _Is Junction is center fed by a coaxial

cable from the c_mmwlcatlons sets. At frequencies between _ and 450

MC the a_enna fsi_In_ _ts _Ike discon_ ante_a, A lower frequency

of 15 MC causes the u_It to resemble an "off center fed" dipole_ between

the upper end lower _ts.

12-38

_' _C_NNBA_t. SEDR 104-

_us the bicc_e antennamay serve alI spacecrafti_requencleaswlth

_he excelTtlo_of C- and S-Bands,a_ receptlcnend transmission

wlthln 14m4ts of the spacecre2_system.

_'_7. BI00HE ISOLATOR

An isolato_ is proviaed to shield electrical wires _hat pass +.h_.ough

_he blccne antennafairing structure. _2e Isolatoris formed into a tube

_ch is eurve_ to a'l1_ mount:l.ngbeneath T-heperiphery of the ante_-a

fairing.

12-._he _Y Dipole Antenna is extended to 13 feet, 8 inches after an orbital

f .... conditionis reache_. Selectionof this antennafor _F use is s_hlevedby

•the astronautthroughthe use of the HF AHT _LECT switch locatedto "the

rlShtof theastronaut.(SeeFAsure12-6)

12-_-9. trm_zm_'_ _ rmoo_mm_

Be U_F descent and recovery antennatakes over the D_F functions

of the bic_ antennawhen the antennafairingis _ettisc_ed. (See

Figure 12-6). _e U_F descentand recoveryantenna is a fan shaped,

verticallypola_izedmc_opole locatedc_ the top of the recovery ccm-

part_ent°

Upc_ landing, impact circuitsinitiate a sequencefor the HF

recoveryantenna. (SeeFigure 12-6). _'_eelevated antenna acts as a

vertical_vpolarizedm_nopole for BY frequencies.

12.-39

_O_NNmLL SEDR 104

iz-51.9-Am) AW m AS

• h_ee antenna --_ts serve the C- and S-Ban_ beacons. (see

Figure 12-6). Each ,m_t consists of a C- and a S-Ben_ radiator.

Each _dlatar is a eavt_ moemted,helix antemna.

12-52. Nn_xARy UHF _e_E BEACONA_NA

A spring-tape type antenna is vertical_ mounted in the recovery

compar_J_t an_ is connected by coa_l cable a_ec%_ ¢o the auxiliary

_F rescue beacon inside the spacecraft. _lth the btcc_e entenna In-

stalled, _he tape antenna Is held in a bent position an_ _on bicale

separatic_ the an_n-a sprlngs into operating positio_.

12-.40

SECTION Xlll

NAVIGATIONAL AIDS

TABLE OF CONTENTS

TITLE PAGE

General ................................................. 13-3

Navigational Aid Kit ............................. 13-3

Satellite Clock ........................................ 13-3

Altimeter ................................................... 13-4N_4__:':_'__::::: ::_ Longitudinal Accelerometer 13-5_IilH_IHIHIH_ ...................

...iiiiiiiiiiiHiiii'iHii_._ii!iiiii_Attitude-Rate Indicator 13-5_iiiiii_ili_iiffiffi_iiiiii_;;;;i;i_ ..........................

__:_:_:_:_:_"-__ Navigational Reticle .............................. 13-6::::::::::::::::::::::::::::::::::::::::::::::::::

"ff.:ff:":''"L:ffL:.::._:.:L:'.:'_ffff_ffffff!_ff_:_::::::::::::::::::::::::::::::::::::::::::::::::::::::

:::::::::::::::::::::::::::::::::::::::::::::::::::::

:_i_iiii_ii_ii!iiiiiiiiiiiiiiiii_iiii_iiiiiiiffi_iiffffiNff-___..:!!!!!iiiiiiiiiiiiiii_iii_i_!i!i!iii!igiiiiiiiiii_i!!!_:f-N.-='_.:::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::.'._{_!ii{:H:_:i.:iffi:'i{:HL:{-:'ff-:_'H''''"::'!ffffff_ff:Z:_.

/_, ::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::, ._i_{_Siiff-[ii:iiH{{iHHiff'ff:ff:'H!!'!{_'!_'ff":_":":'.:"_":""-::ff_..:!i.:{{iHi!i'ii:i{'i{iiff_"ff_i"HH-_'ff:'!'!{"L:"L:L:.:":.ff.:ffffffffffffffff_.

' iii'!! iiii!i!iiiiiiiiiiiiiiiiiiiiiiiiiiiii!iilWiiiiiiiiiiii ':"::_:. iiii_iiiigi!!iiiiiiiiiiiiiiiigi!g!!_g

iiiiiiii!i313-1

_ONNELL SEDR 104

(TYP.)

_ETIME RESET

SATELLITE CLOCK

/1

=%LNAVIGATIONAL

AID Kl'f _

_ PENCILHOLDER

BINDER ASSEMBLY

FM18-54 A

Figure 13-] Navigational Aid Kit and Satellite Clock

13-2

'_ _'_;Nmi_.. SEDR I04

13-i.

Imr_atlau_ a1_s Vhleh are x-_ct_ to o_ts_ al_ttw_j ec_wNs

w1_,1_y an_ _ _ are prc_r1_ to aCt_Lu 8wL ,.*4?taln the

a_"_tu_ th_c_h each _ of *_ _-_h_.

_-_. __AL A_ I_

_e nav_a_cml ect4 klt ecmslsts af a neopx-_m_eoa_ n71xm ease_

_w_ s b_le= asse_r; ew_ Is nount_ _ the nsln 4n,r_me_

(see _ 13-].). _ b4_-r 8ssmbl]r ecuststs c_ a mmb_ c_ h_Sex

ear_s, l_me_ ho_a-_"t =_'b-.,Jea_ 1_meJ-_ sn_ _ (2) _i_ z_,_m_xton

s_d_s. Mw I_ _ ea_s are us_ to _ note ear_s_ cheek

•tsts t _ esz_ _ navJ4_tlcms_ _s as x_q_.x-_ _ the sl_ac_-

c_'s_t Etsslcm. _,' 1_ne11 ho_ _s _bz_ea_ _ neoprene eoa_

an_ Is sewn _o the ease. _te _-_s_ 3_twxL_ls seemed, to the _

ass,=._y by roans of a _m z_,_ntla_ s]_, A uean_ _a x_t_nt_ca

seemms _ b_u" 8sse_y to the _ eoa'l_l n_'lm earn.

2he =_¢,el"_Jtee:t.oe.kls _ e.l.ee'l=.o-me,,t,=,rlea.l.-t:tm.'L_¢1_'tee ].oeate_l.m

the _ rJ_bt o_ _gw =stn hurla¢_ l_z_L _ sate].l.tte eZoek _,,,t_=tes

s]_h_ _ve= watch, _ =un=utl._ wou_ watch ls h=eate_t _n _ tWJperZet=t-

hewd.eoz_w_ of the sste_ltte clock. 2_IW3_(M L_ _W _0

8_1 _ _ is _ts_le_4 _ 4J41fltsl 4rm eouxd_s. _he _ eoun_,s

h_Leate _ _,, _ _, sn_t _. _he _ e_ts aow ht c_ step

13-3

_Hm=.=. SEDR 104

teleM_ht. _ t,_1.e.14_ht is _ate4 in ___ _ r_ht-ha_ eox-=_

_)= _ is _t_Lstea te_ see_,, _r1_ to x_,ro_a_ t_,w..

M_ sste]31te e]_J¢ is au__-=tleally stazd_4 by 28 1;'D-C pmm_at 1t1%=

o_. _0-1_ thls not oecv_, a mrLtehlsbele4 _ Z_O is prov14e4

s_eve =ha _a_=t to _h. _ to _ the a=-_-_ to ene_l_Lzet_e

eZoe.k(sat mamLmmal._ta_ ssaso_). '_= :_zoi_-sa=t_Je _ n_,=_T

hsma_ _.atea _a the :Lower=d_ht act'the __!4+.e e:Loek_e _:l_y set

through the e,_-,,_ x.eeelvex-s. _ -_tes _¢to: to _etz_aa= ttw,

the satellite e3_ck t=_l_Lts s stsnal to the _.to start h_u_

seamers ol_wat/n_ ec_hmmwZ.V and.sssuzesrate Syro o_erat_o_ In _re-

_rs_lm _ _ se_aace. Whenret_c_ _Lme is obtatne4_ a set .

of eoutaet _tnts v_th/n the eloek e_e, tntt_attng the _ =e-

the eabi= t'J.oo_lAKhts.

z3--_.. _,T_T'.._

_e sZtlaete_ ls a l_:essuz'e sens:t_l._e @s_leeloeate_ o= the 1owe:

le_ of the m_tn _t _el (see Seettm ZZ _or _-___tloea¢lm).

5he s_lLttuetez'i_l.eates the external presm_.re (in ]pcxm_s]per s_uaz'e

_h a_so::l=te]_.&) _ the s,l.t,t"l;c_(t= _,houast_ of feet) abovesea

13-4

___fm. • . SEDR 104

level c_ the spaeeersft. Mae statle systm _s the ataosldmr'..e

presma'e n_es_ for the a1_. l_ Is a sh_terevolnti_ _,

cat, rater _a 0 t.o 100,000 f4_t, vlth a _r at I0_000 f_r_ (_WI)

aceelercmet.er lh_e.h 18 1oeat._1 o_ _ u_mr ls_ of "the

_,rumen_ _ (see 8e_icu rr fc_" _ lae_toc_) _ss _3.f-e_

un_Lta_L is housed Ins he,nm_ien!"ty sealed e_elosvze. 2he seee_

is 4estsne4 to tn41este aeeeJ_-a_ton in _he range -9 to 0 _o 21 g _lts

(1 S _"J_ is e_,-_ to an seeele=at_an of 32.2 feet Per see_ 1_ _ea_).

Attached to the face of +..___+aeeelercmeter are three pointers. One

ln_lea_es lnstan_eous aeee_ezatlc_. _ _ two polnt_s are

1_d_,ers. _e _oz7 _t_ _eeo_4s _ost_lve seeeXa=s_tc_ _

other aeac_ potnte= ln41eates negative acee_zstton. _he since7 lx_zb_s

Incorporate a ratehe_ device _nleh maintain a deflection unit _he¥ saw

reset I_ aeaus of a reset knob .,,_.r_,his _oes_4 _n the lov_ left head

oc0mar of the aeee_.

Attltu_.e-Ra'te _g_I.eatcn' Is a "dn'ee wcLs _ .ratesad at'_d.tu_

hs_Lea_ wj_c_n locate4 s_prax_wte_y at _he top e_ter of the m_Ln

__ _enel (see Section IZ for exact location). _e syst_ _Le_tes

r- p:P_h_), z'o___ _ yaw angles am1 _ ra_es. The u_L_ is a ecm_t_e

az_mlim_t eemd.s'c_ c_ a x_te l_alesto_ s:otma _.eh am post"btcme4s

roll a'_,d._;u_e Incllea_mr) a _ at_.tude In6£eatoa" sndt a p_eh a%'f_L_e

13-5

__Imt J. SEDR 104

Indicator (see 8eet:Lcn XI). Mae rate lndlestcr dlsplsys three pointers.

_e ra_e of _ _ _ieh is flat lhlte in color is parallel to

the po£n_w at _he z_LZ att_ae £n_oat_w. _ z'st_ _ :raw po£n_r

which £s yellow ._a eo.l._ ls po:tn't_, tawax'ds the _.- attltu4e ln_Leato_.

q_e rate of pith l_M_ter _aleh is pink :Ln colo: ls _ towar4s the

pltch attltu4e tn41cat_. _he system ecmpcmm_saz_ c_lete_y lnt.er-

_able so _ _a41._e of one c_caent shal_ not necessitate :e-

callb_atlca or :epla_xt of the ent/ze systea. Mae attitude-rate

ln41cstor is aetlva_ by pitch =a_e, _ rate and yaw rate _ans4_ers.

Bach t_ is i4entlealan4 eonsls_sof a g_-oseope,ampli_er an_ a

de_t_. _hese eau_eats fun_ti_utcsetherto pz_xtueea 4-e _

,_ _,=_:eaal _othe_ rateof chenseof a_7_ae.

13-7. wavma_c_ n:zcrz

_he navlKatienz_ele is a devlee_hlch d_s _hea the space-

crs_ is at t_e eozreet aa_e to= z_wo _J_e. I_ is locate1 at _he rear

to the _ _ t_e _'s _,,_ (see _ 13-_). _e na_-

Sat£m _le is aomt_l _ a 180o_ (frm _ to rlSht), this

allows the _ to be poslttou4 so nat _,o block _he vle_ to the

ast_'s _ _ s_111 be secesslble. 5_e ins_ _hen it is

In £_s vlewble posS.tA_ncontainsa t/nted red l_htln_ systea o_ suffl-

four (_) flues are vertleal. Maefourth _,,- _aleh is hm_J.soatal is the

line _aleh ls ze_dA_4 _o be t_ to the esz_r,hI_ _o z_z_ l_e.

_e _A_ht_ ,_sta _ auta,e_ea_ _ _'_,henthe_stnuna_ _8

_t_tr_sve4l_e_en. _w S=eadaS3A_ n,_be dAumaby t_euseoZa po_-

1_-6

rt_ICDONNELL SEDR 104'

ELECTRICALCONNECTOR

WINDOW

RETICLE

NORMAL ATTITUDE/ \

(RETROGRADE ANGLE)/

PITCH ATTITUDE YAW ATTITUDE ROLL ATTITUDE

(PITCH UP) (YAW LEFT) (ROLL LEFT)

f_

(PITCH DOWN) (YAW RIGHT) (ROLL RIGHT)

: FMIS-14&

Figure 13-2 Navigational Reticle

13-7

_WNm- • SEDR 104

o14 l'_1.ter. _he 1_.ite:" Is ol_zate4 by :o_at_Lag the c_s14e o_

_i,,,rtmm_t _Lch _ W_7 the 11Sht intensJ.t_'.

13-8

SECT/ON XIV

INSTRUMENTATION SYSTEMS

TABLE OF CONTENTS

TITLE PAGE

System Description .................................. 14-5

System Operation ..................................... 14-5

System Monitoring .................................. .14-6

System Instrumentation Control ............... 14-30

Instrumentation Recording ....................... 14-33

System Units ........................................... .14-36

iiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiili

14-1

>-

i ..i m_

FM18-140-I

Figure 14-1 Instrumentation Component Location-LeftSide (SheetI of 3)

14-2

14-3

_MCDONNELL SEDR 104

/

FM18-140 3

Figm'e 14-1 Instrument Component Location (Sheet 3 of 3)

14-4

"_/_NNffLL SEDR 104.

F

mmmmmmmm ,z.

The _--_entstton sys_ consists of the _Jor c_ents shown

on Figure I_-I. These eo:ponents coupled wlth various tz_--_cers and

other plcln_ devlees provlSe a means of monlt0r1_ the physlcsl condl-

tlon and reactions of _e astronaut as well ss spaeeez_ft eondlt_ns

sad systems ope_tlonsl pe_ozmsnce. This dsts so obtained Is applled

_ur1_s vol1_e eont_olled subeaZTler osellla_rs which mo_nlates the

Low-Frequency Telemetry Tz_nsmltter and rsdlates %o ground ststlons for

enalysts and ew_uatton; this s_e data is also recorded on a tape re-

corder in _he spacecraft for subsequent stu_7 and interpretation.

A portable 16 mill_meter cram is provided for the sstz_ut to

record on film _ar_us events of interest during the mission. Prowlsions

are also provlde_ for automatic pro_:_ed control over so_e components

not intended for eont_mous operation.

1_-2. S_ST_ 0PERA_0_

The _--trumen_t:h_n system is auto_t$c and eemi-au_/m-_tc in opera-

tion £r_ the time power is e_plled to the spacecraft until 10 minutes

after landia_ _paet, ho_ev=r_ certain components may be controlled or

interro_tted &ar_ fl_ht by either the astronaut or _ e---_._. The

t--tru_en_tion system is di_ed into _k_ee LToups_ n_ely, monitorl_,

f control and reeordi_. These three groups are treated _tvi_,*_ly in

14-5

_MCDONNELL SEDR 104

Instrtmentatton monitoring consists of sempllng values of pressures,

temperatures, conditions and operations of various u_ts and functions

throughout the spacecraft. (See Figure 1_-6). These samples are con-

vetted into signals composed of voltages proportional to the te_erature,

pressure and conditions being measured. The proportional voltages are

calibrated within c_n _=ximm and mini_m ranges to provide zero and

f-!l scale reading. Instrumentation monitor_-_ is sub-divided into two

areas nemely, High Level and Low Level. A description of each is provided

in the following p_phs.

(o- v

High level input signals are chmmele_ into the c_tator (elec-

tronic switching device) which is located in instrumentation pac_=ze A.

The coNmutator continuously samples its input channels, combining the

si_ o_-1 voltage l_,l-es into a pulse train from the c_tator. This l_u!se

train (PAN) is e_plied to a 10.5 _C voltage controlled subcarrier oscillator

where the changi_ voltage of the pulse train varies the frequency of the

osc_ll-tor. The output of the 10.5 _ voltage controlled osc411=tor and

other oscillators are e_plied to an isolation smplifier which has outputs

for the ta_e recorder, telemetry transmitter and hard line. The High Level

C_,tator output s_ls are also converted to pulse duration sisal= (PDN)

and recorde_ on the spacecraft on-board t_pe recorder.

14-6

©_'t,foJr_ltlNIfLL SEDR 104

_-_. Low_ (-:_.v to ÷_ _)

_ Low level _astr_entation monitor_ performs a temperature survey

of various structural and spacecraft components. The low level c.--,-,tator

output signals are converted to pulse duration (PIN) s_s for reeordi_

on the on-board t_e recorder, only. The low level PAN may be monitored

_rt-_ ground tests by actuation of the Temperature Survey Switch to TEST.

_his pulse train is applied to a 10.5 K_ voltage controlled subcarrier oscil-

lator where the cha_ voltaEe of the pulse train varies the frequency of

_e osc411Ator. The output of the 10.5 EC voltage controlled oscillator

and other oscillators are e_plted to an isolation amplifier which provides

telmetr_ traus_tter and hard line outputs.

Figure 1_-2 is a block diagram show_ the parameters of the instru-

mentation that Is monitored with a brief exp_mation of each parameter

glveninparasraphsX_-6thr_,_I_-_8.

_-6. __ '_.'_m_XCA_

Spacecraft electrical power syste_ I-=trumenf_tion consists of moni-

torln8 the circuit illustr_ted on Figure.i_-2.

•_-7. _oo_s MO_ITOR

ASCS bus 1,1,5 Wit a-c is attema_ted_ rectified and filtered prior to

be4-= e_plied to the e.'=,.,-t_toras a zero to three volt d-c s_al. The

Fan bus 115 volt a-c is s_plied through a 115 to 6.3 volt stepdmm tra---

for_er in _n-_t_tlon packase A. The se_omd--vy Otttl_ItSare attentu_ted,

14-7

_OXtAtiZg.#- SEDR 104,

BICONE DESCENTANTENNA ANTENNA

[AN,E,NASWJT

J EKG(-)LEFTSIDE

_o L,3KcvcoI _.--i,.CONTROL

,IBLOOD PRESS.

RELAy

I EKG (+)

LOWERCHEST J I.TKC VCO]

J EKG (-)UPPERCHEST

I_s°_I i _olLO. CW. & RATE

I '.°'°_c°_--1 ._J ] vco RELAY

THRUSTERPOWER _ J 5.4KCSOLENOID J_

ASCSPffCH L t t UMBILICAlLO-UP, LO-ON .40KC VCO RECEPTACLE

& RATE

A_SYAWJ I--_'cvc°lLO-LEFT-RT

RESPIRATION } ] 1'3KC VCO I '

, a,._+ I '°"'¢v°°I. . jTEMP

HiGH LEVEL TEST SURVEY

LFCOMMUTATOR SWITCH TAPERECORDER

PAM PAM _

÷ • .

° -°" [_

FM18-O7A

Figure 14-2 Monitoring Instrumentation Block Diagram

14-8

"_,'_mNKLL SEDR 104,

rect4.t_ed sml f_J.tered prier 1;o being =pp].te4 to the ecsw=-tst_ as a

zero I;o three volt 4.-e s_uLI.. A three vo:}.1;slW_I. (t',,_1 =,ca]e) re-

presents 130 volts for each bus.

D-e current emplt_lSe is sensed by the sh_ for the 4-etrument

panel s_eter. _hts shunt is in the negative lead to growl ot all

spacecraft batteries and senses total battery current. _e volt_e

across the shunt is 50 _11_vo11;s _aen 50 ._z_es are _, and pro-

pertio,atel_ less fc_ lesser currents. _ s voltage is applied 1;o a d-c

mpltfier in package A which amplifies it to a zero _o three vo11; lewd.

A _ Ir011;]_1 (_111 Bea]_) _rese_11;B _ 8m_)el*e8battery eunwnt.

J

_he omtput Of +_e aap1_ler Is app]aea1;othe ecmntator.

14-9. D-C _r.q, an_

_he 2_ volt main bus d-c u--_tor ctrcui1; is atteanated prior to

bet_ applAe4 to the c;;--_ator in the A paeka_. A three volt signal

(_,11 scale) represents 30 vol1;s bus vo].tap.

1_.10. DIS_ME_J_0g _ SUPP_.re_

Y_str_aenta1;icnpower s_pl£es-lnstr_ma_sta1;Ic_consist8 of the _-

1;or ctrcut1;s for the _o 3 volt 4-c re_ea_mces, zero reference, aria 7 V

stes. (ee

_he 3 volt _-_ reference pove_ s_pl_ fro.,,4 a),,,s excltatlon_c_ .1

pote_tometer type _s_enta1;ion pteksps. _aere are two 3 volt d_

14-9

_N_arLL SEDR 104

power suppl£es located in paek_es A au_ C respec_vely. Each supply

Is zener d/ode regulate_. _he 3 volt 8-c e_ltatton voltage require-

ments are aiTtded between the two separate s_plies with the power sup-

P/_r in package A furnlahi_ a reference f.rl scale stsnal.

1/_.1o. Z_O VOLTImF_EICg

_e zero reliance s_snel ls s_l gr_l and is _ to both

of the above mnti_ed power supplies. _!s a_l is also applied to

_e 7 volt _00 cps power s_pl_ th:rntshes exctta'_t_ for _he i_,_t

brld_ circuits uttlize_ w_th the res_nce e_-_t _li_ers ..a _her-

ml_tc_ signal cc_d£ttoners. Power supp_7 outpu_ is attenuated I rectif_ed

filtere_ %0 a zero to three _olt level _his zero to three volt s_-

hal Is applleA to the c_,,,'tator. A three volt stsns_ (fUll scale) re-

presents a 10 volt output level, _e po_r sappl_ Is a trenststorized

power i_verte_which operatesoff2_. vOICeS8-0 1;0 provide_ 7 _olt

cps outputen_ Is locatedin packa6eA.

Cal£brattcn ON_-_nta_%c_ conslsts of a circu_ _%ch m_£_ors

presence of T_e full scale an_ zero scale e,_4brat_n ecmmnd, s_nals.

_hts slgnal is present _hen 'the CALIBRREI_ switch in the telemetry tra_ler

is placed,to I_JLLSCALE or ZERO position. When the f.'il scale callbrste

eomumd Is present,2_ _olts _-e Is appliedto an attenuatorIn package

14-10

'__NNmLL SEDR 104

C. _e c_put of the attenuatar (2.25 volta d-c n_-_l ) is applie_ to

the e.--,,.;_tor. When "the zero scale calibrate c,_,--_d Is presen¢_ 2_

volts _-e Is app1£ed tO a dAfferent _ point ca1 "the seine attenuator

network. _e c_ut of the attemmtoz (.75 volts d_, n--4--_ ) is applied

to the c.--_.._,tat;(xe. '_us s an upper scale signal indAcstes presence of the

f.11 scale e-_brate eommn_ aria a q..rter-scale signal inaleates presence

of the zero scale e-31brate c._J_a. _ese c_ sl_aals energise relays

_hich apP,7 calAbrate signals to _-_cus other lnstr_entati_ ,_--_*ls.

_e R au_ Z _.ltbra_e function may be initAate_ by the progre_ c_ fr_

a ground statlc_ +_'c._ the em_ reeeivers_].e in ocbit.

i_-15. ST.4TZCP]mSS_l_

S_atlepressure Instrmnentatlc_ec_s£stsof a potentlomter type trens-

_ucer which is operatedby st_tlepressure. _e potentlo_eteris excited

with 3 volts _-c f_ _ Instr_atlon power st_pl_ locatedin the C

penka_e. Wiper voltageoutput is InverseS7proportionalto staticpres-

sure. A three volt signal (_,1_ scale) is representativeof 0 psla.

CCS 0L

control syst_ _tio_ consists of circuitry

• hi_h a_itors priaa_ ana _e_lary _ _pl_ press_es, _it _-_t

air pressure_ cabin pressure_te_perature_CO2 partialpressure_02

partialpressure an_ e_er_ency02 rate.

I_-17. _ O2 PAREIALPRESSURE

02 partial pressure is sensed by a trausduner in the cabin. _he

signals are _plAfied aria _ttea "to a press.re g_e on the lnstru-

14-II

_NNm.L SEDR 104

_-nt panel _e stc_als are also al_L1e_ to the e_ator in

A _o_re _ are eo_ve._._ to P_ aria FIM stpals. _ P_ steals are

te_ to _'oun_ an_ the HM _ sze reecaxlea ca the spacecraft

tspe recorder.

i

C02 partlal pressure is sensed by a transducer in the envlr_n+_L

eoD_rol system's sutt c_utt. _ stgna/s are _pllfle4 and tran_4tted

tO a pressure _ on the 4-_ment panel _he s_n-1- are also sppl1_

to the e_._ta_r in package A where they are cc_d to PAg an_ PIM

st_aals. _he PA_ st_sls are telme_re4 to ground and the I_ s_als

are reeoa'de_ an the spacecraft tape recorder.

./

Priory a_ _eon_7 _ s_p_ pressures are s_ by pressure

aetusted dual potentioaeters In the __a_ area. One potent_mter

operates a panel tn_tcat_r vhlle the other wiper picks oft a value for

tnstr_entati_. Wt_er voltage output ls linearly proportions1 _o pres-

sure. Exei_atlc_is _pplle__ _he 3 volt _-_ _st_umen_at1_ power

supply. _he zero _o 3 volts vlper output represents a pressure ra_e of

zero _o 9,3_ psl wlth 0 to 125_ meter IndlcatAo=s. Outputs fraa the prl-

mary and secondary _ supply pressure _r_n_ducers are applle_ to "_e

e_al;or.

_kttt _ air pressure __atlon consists o_ a potenttcmeter

type transducer vhleh is pressure actual. _ae potentlcmeter ls exc1_ed

14-12

©"_a_CE_O_mZL.L SEDR 104

with 3 volts _-c fro: the lus_c_entati_ power supply in package A.

Wiper voltqe output 18 1_-earl_propoz_lonslto pressuze. _e zero

to three volt (_n_ stele) output representss folded ta_ms4u_erout-

put with a presmuce raE_e of 15 psl= 0V s 7.5 psi : 3V an_ 0 psi = OV

applie4to the c-_-ta_or.

I_L CASIW_SSmS

Cabin pressux_ _-_ntatlon eonslsts of a potentlcme_er %TPe pres-

sDI_ _SDBd_e_ ::!.11_5+-_11_.:I.D,package C. _ potenti_aeter is e_ite&

wASh 3 volts a-e fZ_ the _--trmnentatl_ pov_r s_ply in packa_ C.

Wiper vol_e ou%put is linearl_propca_lonalto cabin pressure. _:e

zero t,o three volt (f.1_ seele) out'put, _ the wlpe_" repre_en_,s e folde¢l

_er _ with a pr_ss_ r_e of 15 psi = OV, 7.5 psi = 3V,

aud 0 psi = OV applie_l to _ c,---,_tor.

1_,.-_. CABIN

Cabin taperature Instr_entation e_ists o_ a t_mperature_sln_

probe mounted _ _he ba_k of the _ instrumentpanel. Transdvnerre-

sistancevariesprop_In--_ ly with temperatureana is part of a brld6e

input circuitto an mpllfie: in packageA. _e zero to three volt

(full scale) outputfr-- the mplifier is representativeof a t_werat_e

ren_e of _0 to 200°F. _he output frc_ the mplAfler 888o_la_e_wi%h the

%rsns_u_eris spplledto t_e e--_ta_or.If

_3. _ 02_

Emez_enc_ 02 _ ios_z_aen_atlon _sls_s of a mrA_h 8u_ua_e_ by

_e ox_sn esarL_ac_ rate valve. Upoa closure of th£s sw£_ch _o mar-

pncy, 2_V d-c is provi_e_to an attenuator_hich steps 8o_n +_s voltageI_3

NNMLL SEDR 104

to 3 volts. This c_t is _en applied to the c_.,_tor.

Cabin heat exchanger gas temperature tnRtrumentation consists of

a thermistor type transducer. Thermistor resistance varies inversely

proportional with te_Dersture and is part of a bridge input circuit to

an _lifier in package C. The zero to three Volt (f._l scale) OUtlmt

from the amplifier is representative of a temperature ra_e of 30 to

lOO°F. The output from the e_plifier associated with the transducer

is al_plied to the _:.--..;,tator and the temperature indicator on the m=tn

_nRtrument panel.

Cabin heat exchanger dome t_m.erature tnstz_zentation consists of

a thermistor type transducer. Therm1_tor resistance varies inversely

proportional with temperature =_4 is part of a bridge input circuit to

an _slifier in package C. The zero to three volt (full scale) output

from the _lifier is representative of a temperature range of _0 to

lO0°F. The output from the amplifler associated with the transdncer

is a_plied to the co_._utator and a coc_it meter. If excessive A_e

temperature is present, an mzdio tone will be heard by the astror_t alo_

with a warning light.

Suit heat exchanger aome temperature 4n-trmnentation consists of

a thermistor type transducer. Therm_.tor resistance v_ries inversely

proportional with temperature and is part of a bridge i_put circuit to an

14-14

MCDONNELL SEDR 104

amplifier in package C. The zero to three volt (full scale) output

s fr_ the sm_lifier is representative of a temperature range of _0

to IO0°F. The output from the amplifier associated with the trans-

ducer is applied to the commutator and a cock,it meter. If excessive

dome temperature is present, an audio tone will be heard by the astro-

naut along with a warning light.

l_-e7. _%CTION CORTROLSYSTEM

Reaction control syste_ _natrumentation consists of monitors for

aut_natic and ma_zml reaction control _pply pressure and astronaut

hand control position. High pressure 4n=trumentation is monitored on

the high level com_Atator while the low pressure is monitored on the

indicator located on the main t n-trument panel.

Horizon scanner t-,trmzentation monitors for the pitch and roll

horizon sc_,-er outputs and ignore signals for each of these outputs.

The horizon scarmer system utilized two identical 4-frared scanni_

units to provide pitch and roll reference signals. The horizon scan-

ners are on continuously_ fr_ launch until re-entry at which time the

scanners are de-activated by the O.05g relay, but duri_ the orbital

phase the reference signals are applied to the ASCS attitude gyros only

upon cc_mnd fr_z the pro_-._.r. (Refer to Table 1_-1). The signals

/_ that are a_plled to the gyros are monitored by I.-trumentatlon. The

pitch an_ roll signals range between + i0 volts d-c. These signals are

_pplied to a biased attenuator card to provide a zero to 2.68 volt out-

14-15

_NArmL4. SEDR 104

put wl_.eh Is eoupXeclto sea.ate _i,,m._ls of .h. commutator. _le

s_ls represent an ou_A)utr.mse of + 35o.

Oeeasltmmlly a 8emmet swee_a across _:e sun. W_ee the seminars

are infrared d_rlees, mmeptz_ of the sun tnta'oduees errc_ voltage.

]prewm't u_.3.:Lza't:Lcuof this voltage,the sc_er supp3.1es an :Lgnc_e

to the ASCS. _u "isnore" s_n81 is m_ltore_L as an _-c/'f

type of _tsnal by Instrumentation. P£tch _ and roll _nore _Zn,,:-

sre applied to the e_...-,'.ator also. A _ sceOLestsnsl represents

presence of the pitch l_ncze slKnal an_ f._l scale level Indicates

presence of the ro31 _nore s:LKnal. Each :£Knoze81Kn81 is montto:re_

mon:J.t_" spacecrai_pl_;ch_roll 8_ yaw a4_;i_:_e8.Each a4_i_u_e18

rea_ _ of a sy_.hroactuate41_mtl_net_r. _e s_.bros are _zlve_

by t3_e mzt_le s_ab_l_ control. _ _-_Ita_imlfor _he po-

_ent_-_te_ rs is l_mlshe_ by _ t3_ee vol_ A-e _-_rmm_atlcn power

sut_l_ In the C psck_e. SIKna_ voltage vsrles _ 8 _ttp_e 8_

function v£th spacecra._ att4tude. Plteh an4 roll stsnals cover a

rause of +130o _o -190o. Ysv si_O=_s cover a tense o_ +70 to -_0o.

Each of the attitude stKnsls is app3£ed to channel: _ the c._._*_t_.

ACter retrosrade assmb_y _ett*son end _ of a O.O_s rel_

the potentim_ter-posltlonlnK sy_os become lnoperat_Lve.

A_tt_Ae rate T__atlc_ ut_e_ signals fro_ rate _yros. _e

gyros are part c_ the attitude rate *n_Lea_n_ systeL A zero to three14-16

__NNIr._. SEDR 104

volt signal level represents a race level of decreasi_ 40o per

second ¢o increasing _0o per senc_. Pitch, roll and _ rates

are assisne_ ¢o Selm_te vol_e ec_t_le4 oscill_s (Pitch

Rate and Pitch lov solenoi_s .l_) KC VC0, Roll Ra_e and Roll lov

so_mo£_ .73 VCO and Ya Rate and Yaw 1or solenold_.56 KC VCO)

i_-31. REACTIC_ COBOL SYS_ SOTRWOIDS

•:e zeactlcn canta'olsystem soleno___@ controlthe thrust Jets

used for Slmceers_ stabil_.attc_l in fl_. _ese solmaoids can

be ener£ized mmmal_ or sutc-.t_cal_. When a solenoid is enar-

sized (_._ solenol_s..ly),2_ volts 8-c is appliedthrough an

st_enuatorin package C to the c.-.-_._or. _4s on-ofT els_al Is

presented to 4--trumentattcn ef_eult_ f_m the ASCS syste_

High pressure maniT_r c___ts fur reactlan c_1_rol s_7 pres-

sures are bsslcally 1_.DtlCal in opez_tlc_. A hel_-m source of approx-

Ima_e1_ 2_770 psl for _nt_--_Io end appr_m-_e_7 2,830 psi for manual

Is utilizedto expel b_dro_en peroxide _ a bladder. As h_

peroxLde is ex_e_l_ the ccaflnedvolume of the helium increasesand

hellt_ pressure decreases. A pres_ potentlame_er senses 1_s change

in pressure. _he po_-,_e_ is exci1_ witch _hree vol_s f_ _

_,-trumentatlo_power suppl_locatedIn both the A end C packe_es.

Wiper ou%_ vol_e ls applied to the e.,._._atorsad thro_ an atten-

uator t;0 an. _ca_o_. TTansducerrange is 600 "to 3,_00 pal. A pressure

of 2,770 psi for aut__attc --_ 2_8_) psi for manual provides a readi_ of

14-17

_MCDONNELL. SEDR 104

10_ on the panel indicator. Hydrogen peroxide is exhausted at a_proxi-

mately 1,580 psi for auto,tic and 1,960 psi for mamma hellm_ pressure.

Indicator readix_ _t this pressure is s_proxlmately 0_. Low pressure

is monitored on the low side of the re&_tlatorwith a tr=_-dncer range

of _00 to 700 psi.

i_-33. HARD CORTROL

Astronaut hand control position is monitored by three potentiometers.

The wipers of these potentiometers are driven by linkage to the hand con-

trol. Three volts from the _--trumentation power supply located in the C

package is utilized to excite the potentiomaeters. Zero to T_ee volt sig-

nal level represents + 13° hand control movement in the roll and pitch planes

and + i0O movement in the yaw plane. Wiper output is _pplie_ to the com-

mutator.

SPACECRA

An acceler_neter 4nRtslled in package C pi_¥1de zero to three volt d-c

outputs proportional to acceleration along the l_ngitu_4-=1 (Nz) axis of

the spacecraft. The acceleraneter output is linear with a zero acceleration

provid_ a 1.5 volt d-c signal. The longitu_4_1 axis aceeler_neter covers

a range of + 30g to provide zero to three volt output signals. These zero

to three volt signals are applied to the _,tator.

1-35..r STeUCTUmL

High level c_mAtated structural te_erature 4n-trumentation consists

of monitor circuits for the ablation shield.

14-18

_ONNI[LL SEDR 104

14-36. ABLATIO_ _m_n _TU_S

/_ _he ablation shield "temperaturesare m_/tored through the tele-

metry sys_m. Two _ransducers are embedded in the inner face of the

-h_eld. _e transducers have a t_aperature ranse frcm -55 to 2,000°F.

with a ...I.AI resistance of I00 ohms at 70oF. Input power of 7 V d-c

_O0 cps applied 1;othe 1_ransdnnersis a%_en,,-ted1;oa value dependent

upon the transducer resistance. Transducer resisSmnce varies pro-

porti_l_y with _rature and is part of a bridge input circuit to

an amplifier in package A where _h_ voltage is converted and smplifie_

to a zero to 3 V _-c signal and applie_ to the telemetry c_,.-,,_tatur.

1_-37. LOWLEVELCO_UTA_ STRU_ __RES

/ Temperatures monitored on the low level c.mB_._ta_r use tJ_mocouples

with reference Junctic_ thermistors in the first available disconnect.

Attenuator olrmllts if needed are local;e(1in the low level cnm-,1;ator.

Refer to Figures iI_-Ian_ 11_-3.

Various structural temperatures are monitored by the astronaut

through the use of _rature _leetur switches _d a temperature

iud£cat_r loca_e_ _ the main _n-_n_ent panel. _-_tsto_ trans-

ducer resistance varies inversely proportional w£th temperature and

is part of a bridge :t-_ut elreu.it t;o an ea_l.t£ie_ in package A where

_ the voltage £s converted --d m_n_ele_l tO a zero _o i00 mlero-_mp sig-

nal an_ sppl£ed _o 1;hel_e_al_re indicator. (Refer to Figure iI_-I_).

14-19

_MCDONNELL SEDR 104

FULLSCALEREFERENCE(+ 15 MV INPUT) FROM J[.._INTERNAL

ZEROREFERENCE{-5 MV INPUT) SOURCE

(__ 180_'FCONICAL SECTIONSHINGLE,ATHEATSHIELD Zll1.5, LX, BY 4.3 TC"I (_ (DIFF,)CONICAL SECTIONSHINGLEAT HEATSHIELD Z109.1 • RX, TY 2 TC"3 1800°F

CONICAL SECTIONSHINGLEAT HEATSHIELD Z108, RX2, BY TC"2 (_[ 45-79012-123J 1800°F

CONICAL SECTIONSHINGLEAT HEATSHIELD Zlll .3, LX2• TY TC"4 (__ J C_ (DIFF)1800eF

THERMISTORREFERENCEAT PLUG1851A (LARGEPRESS.BLK'HU.DISC.) GB34P91 _ C_ 50"150°F

THERMISTORREFERENCEAT PLUG848 CT (SMALLPRESS.ELK'HD. DISC.) _ _ 50-150°F

SPARE (_

SPARE _)

CONICAL SECTIONSHINGLE ZI48, LX, BY2 TC"5 (__ 180(_F

CONICAL SECTIONSHINGLE Z154, IX, BY2 TC"6 (__ C_ (DIFF.)1800OF

CONICALSEaloNSHINGLE z154,_, BY TC'7 (__ laOOOFCONICAL SECTIONSHINGLE ZI57, RX2, TY TC"9 (__ (_) (DIFF)18000F

6O0_F

CYLINDRicAL SECTIONSHINGLE ZI78, IX, BY2 TC'10 (__ [ _ (DIFF)CYLINDRiCALSECTIONSHINGLE ZI78, P.X,TY2 TC"12 __ 6{]0°F

CYLINDRICALSECTIONSHINGLE ZI78, RX2, BY TC"II (_J_-'_'_ 6D0°F

CYUNDRICALS_,ONSH'NGLE Zl_,_, TY TC"'3(__ J (!D 600"F(D'FE)INLETBNUT, AUTO.YAW LEFTSOLENOID Z173, RX, TY1.5 TC"19 _ (_) 250°F MAXIMUM

INLETg NUT, AUTO. PITCHUPSOLENOID ZI73, RXI.S, BY TC"20 (_ 45-79012-65 (_) 250°F MAXIMUM

INLETRNUT, AUTO. YAW RIGHTSOLENOID Z173, IXr BYI.5 TC'21 (_) 45-79012-65 (_) 250°F MAXIMUM

INLETg NUT, AUTO. PITCH,DOWNSOLENOID Z173, IX1.5 TY TC"22 (__ _ (_) 250"FMAXIMUM

SPARE i (_

SPARE _ (_

THERMISTORREFERSqCEAT PLUG3(]04. (ANTENNA FAIRING DISC.) _ , _ (_ 20-15_'E

CONICALSECTIONSHINGLE ZI_.S, _, TY2 TC"R (_)_ AT{_ff_--J (_) IS_F MAXIMUM

MAN. LOW ROLLCCWTHRUSTER Z115, RX, RYI .I TC"15 (_)_ _ (_ 1500"FMAXIMUMi

SHINGLEOVERMAN. LOWROLLCCWTHRUSTER' Z110, RX, BY2 TC"16 (__ _ (_ 18(]O°FMAXIMUM

AUTO. LOWROLLCWTHRUSTER "ZI14, IX, BY2.5 TC"17 (_)_ _ (_ 1500°FMAXIMUM

SHINGLEOVER AUTO LOW ROLLCW THRUSTER ZI11.5, LX, BY2 TC"18 (_ 45--79012-121 _ (_ 180_F MAXIMUM

ANTENNA CANISTER Z202, LX2, I'Y TC"14 (_ 45-79012-15 _ (_) 2000°FMAXIMUM

ANTENNA CANISTER Z21_r RX2, BY TC"23 (__ _ (_ 2[X)0*FMAXIMUM

ANTENNA CANISTER Z2(_, LX, BY2 TC"24 (__ _ (_) 2000°F MAXIMUM

ANTENNA CANISTER 7200, RX, TY2 TC"25 _ _ (_ 2000°F MAXtMUM

TEMP. SURVEY I

TESTSWITCH NORM

TO45-88243-19 VCO _I _ I PAMHIGH LEVELO PAM •

TEST

TOTRACK4, TAPERECORDER] PDM DIFI" i

NOTES

_ REFERENCEJUNCTION, CH. 5(1851A)REFERENCEJUNCTION, CH. 6 (848 CT) LOW LEVELCOMMUTATOR-

(_,_) REFERENCEJUNCTION, CH. 19 (30GA)KEYER-RECORDAMPLIFIER

45-88128-301

CR-CN ARE45-79012-65,-87

CR-ALARE 45.-79012-15,-121,-123

ONLY END T.C. ASS;YSSHOWNFM18-141

Figure 14-3 Low Level Commutated Structural Temperatures

14-20

"M_'DDONNELL SEDR 104

f

i II I

BRIDGE _j- _ 1NEIWORK

I J TEMPERATUREI J INDICATOR

' __1 ICOMMON 1 Ii

: / I ®DOWN : _LL

'o _, &"" , _)_'_

0 >INVERTERTEMP4 MAIN

15OVA

I

I @°"150 VA

I

FM1_142

Figure 1A.-A.Metered Structural Temperatures

14-21

_MO_NNliLL SEDR 104.

Aercmedical instruaentation consists of monitor circuits for electro-

caz_1_gra3)h (_)_ respiration si_lsp bo_ temperature and blood pres-

sure.

The blood pressure syst_n consists of (1) an occluding cuff 3 (2) a

pulse sensor, (3) differential trans&Acer, (_) pressure source3 and

(5) a controller system. The occludi_ cuff is attached to the astronaut's

arm. A transdneer which measures the at_ferential pressure _etween the

cuff and the spacecraft cabin pressure is located in the controller system.

The pulse sensor is a _ tra_-d_cer (microphone) attached t,-ide the

suit. _he pressure source is a separate oxygen bottle containing suffi-

cient ox_en to provide the desired _ercmedieal t-_ora_tion &Aring the

mission, ql'he system measures the astronaut's blood pressure, COnverts

the pressure to a corresponding electrical signal which is then applied

through a blood pressure relay to the 2.3 K_ voltage controlled oscil_ator

and traus_tted by the telemetry tra-_ttter. This signal is also recorded

on the tepe recorder.

The blood pressure syatea may be put Into operation by the astronaut

ac_,_ti_ a STA_ switch on the instrument panel. Upon actuation, a 2_ V

d-e pulse of five seconds &,_ation, causes the system to pressurize to _._

psi differential pressure fr_n the pressure source. After pressurizing,

the syste_ bleeds off at a linear rate to 0.75 psi in approximately 22 sec-

onds. The output signal fr_n the pulse sensor is routed throush the pressure

14-22

suit disconnect ,=a _4 with the differential pressure signal in a/

s_per_postns m-_er. _hts combined s_ml _s rou_e_ thro_h a relay

and relay contacts to a 2.3 KC VCO local1 in D package, an_ then to

the telemetry tran_ttter. Direct_ng the signal through the relay is

necessary in m__er to share the S. 3 KC VCO with +_ _D st_ls.

_e first sppearance of T_e bl/p Indicates systol£c pressure wl_h

a _ peak _T.li_,,0e of 150 mv while the last oeeurence of the

blip s_4paal in_ea_es d£astolic pressure with a m_.4,.,_ peak mz_l.ttude

of 150 my. _e _-_--_ pulse pressure is 1 volt peak.

Upon eomplett_ of the cyele_ the system will r_-in at rest (below

_/4 psi pressure). Each measurement is men,,-lly 4-1tiered by t_e

astn_mut_ if he does not use the STOP buttcn_ a !__n second timer will

rim out _ will $_l_n au$_-tleal.1_y onnw_nce to measure _. A l£ght

on the panel indicates when the system is opera___.

Electrocardiograph signals ere obtaine_ from four transducers

attached to the astr_aut's right end left side_ and _ the upper ana

,lower chest. _he outputs fr_ the transducers are applied to two _pl£-

fiefs in D paoka_ (left an_ rtgh% slde paired to c_e amplifier and Upper

and lower chest pair_l _o the other). Signals _ the _plifters are

t_en diree_d _o a 2.3 KC and 1.7 KC volts_e controlled osclliat_r, which

/_ in turn appl_ their outputs to the tel_try tr-n--_ter. The 2.3 KC VCO

_put s_nals are divided between the as_ronau_'s _D and bloo_ pressure

outputs.

14-23

_mmlLJ. SEDR 104

The _t_ts breath4_ rate is momitore_ t_ The tel_etry

system. Two _ type probes are attached to the sides of the astronauts

chest. An impedance pneumo_q_h senses a capacitance change between

the two probes as the astronmat breathes. This signal mo_,lates a 50

_C carrier wave. The changing output volt_e of the pneumogr_ph varies

the bias of a trausistor in an in-line amplifier. The a_lifler sig-

nal is then s_plted to a 1.3 _C VC0. A potenttcmeter in the pneumo-

graph provides an adjustment for sensitivity.

14-_3. ASTRONAUTBODYTm_ERATU_

Bod_ t_erature is sensed by a rectal temperature probe. The probe

is a thermistor element which is utilized as one leg of a bridge circuit,

which forms the input to a d-c smplifier. The output of the 8mplifier is

spplied to the telemetry c_tator. The zero to 3 V d-c output represents

a temperature range of 95° to 108°F. The s=plifier is R and Z calibrated

by either _ command or the progre_aer.

-,_-_. _ s_ _v_..L __,__,,J_

North1 launch sequence 4--trtmentation consists of monitor circuits

for tower release, spacecraft sepa_tion_ retro_ade attitude command,

retrograde fire and retrograde rocket assembly Jettison. These si_ls

are ,11 on-off type functions and each is applied to the c_utator.

The satellite clock utilizes potenti_eters to provide electrical

signals representative of elapsed time fr_n I_Auch and retrograde time.

These potenti_eters are excited with three volts fr_ the instr_entation

14-24

___m/.g. SEDR 104

power supply located within the A package. The outputs for each type

of time are divided in signals representative of 0 to 10 seconds, 0

1;O 1 m4nute, O to iO mlnutes_ 0 to 1 hour, O to iO hours and 0 to 60

hours. Wiper output iS l£nearly proportio--1 frcl zero to _h_eee volts

for each time span. Wiper outputs are e_plled to the co._,_tator. Instru-

mentation monitors ELAPSED TIME from LAUNCH and also EVENT TIME of retro-

grade. Elapsed time from launch is the lengthof time spacecraft has been

in motion. Prior to liftoff, el_sed time will be zero. Instrumentation

recording _eviees also will indicate zero time. Output signals for

el_sed time therefore are d_ectly proportional to time. As time im-

creases_ so will output voltage; for exemple, elapsed time recorded by

clock is i0 hearts, 5 m_w, tes end i0 seconds. Output signals IrI'll then

be as shown below:

S.aq'W'.T.T_ CLOCK OUTPUTS FOR 10 HOURS,5 MDmTES, 10 SEC'0_q_, _ LAUNCH

TIME POTERTICM_TERS SIGNAL

O - 60 Hours 21.26_ .638 Volts

0 - 10 Hours O_ 0 Volts

o - 1 Hour O_ o Volts

0 - i0 Minutes 55.3_ 1.66 Volts

0 - 1 M4m, te 21.3_ .638 Volts

O - iO Seconds O_ O Volts

f Event ttme of retrograde is preset prior to llft ofT. After rotro-

t_me has been set, t--trmnentatton w_l recelve this time si_!

cent_n-ously throu_out the m_ssion. Event time of retrograde can be

14-25

_MCDONNELL SEDR 104

cha_ed at a_y time during the mission by either the astronaut or by

ground c_,_-4. When retrograde time is changed dnring the mission,

_n-tr_mentation w_11 receive this cha_e also. Si_1 output voltage

is proportio_ to retrograde time. For e_le, if retrograde is set

to c n_enee at 20 hours, 10 m_m,tes and lO seconds, _n-trumentation will

be receiv4_ the signal voltage outputs as shown belov:

SA_.T._ _ OUTPUTS FOR RETR0-FXF_ AT 20 HOURS,i0 MI_ AHD lO S_

TD_ FOTm_fXC_RS SI_

_za__s _ _A_. _ _ VOL_S0 - 60 Hours _0.4% 1.213 Volts

0 - 10 Hours 0% 0 Volts

o - i Hour 21.3% .638Volt.

0 - 10 M_m,tes 0% 0 Volts

0 - 1 Minute 91.3% .638 Volts

0 - i0 Seconds 0% 0 Volts

l_-46.TOWEaS_AaATTO_

When the tower separates from the spaceoraft, the No. 3 tower separate

sensor rela_ de-energizes and e_plies 2.4 + 0.3 volts d-c to the c_._._,tator.

This signal is present for the remainder of the mission.

14-47.SPAC_ _Ae_Im

When the spacecraft separates from the booster, a limit switch closes

and causes the No. i spacecraft separation sensor relay to energize. While

this rela_ is energized a 2.4 + 0.3 volt d-c signal is applied to the c;-..-,._-

tator. This relay r_.-1-s energized for the _r of the mission.

14-26

__NNmie. SEDR 104

14-48. _0mU_E A_

_he ret_ade attitude e_ signal nc__-l_y occurs vhen the

rel_osrede clock runs out. Xt may also be caused by ground co_n_

or by operation of a _ypass swlteh on the instrument panel.

signal r_ma_s present until the _etrogrede rocket asse_ly is Jettl-

sc_ed (spproximste_ 90 seconds). Signal level is appro_:tel_ 2.4

+ 0.3 volts. N_,_J.ly open contacts of the retrograde attitude com-

mand rel_ in retrograde rel_ bo_ No. 2 closes to route the signal

to the c_.._..dtator.

During e mission t the spacecraft may be out of range of a monitc_ing

ground station dm_Ang retrograde rocket fire. To provide the grcuna

ststicn vith s_ idea when retro-rocket fire took place, a solid state

timing device is provided. Upon closure of the No. 2 retro-rocket

•u_nAtor relay_ a ste_ signal is appl£ed tO the timing device. Outputs

for each type o£ time are divided into signals representative of 0 to 10

secollcls, 0 tO i ,R_-_te, 0 to lO mt-uteS, and 0 tO 1 hour. Xns_w_tation

will contlnnous_ monlto_ these time slgnals until i0 -_-utes after im-

pact.

• _e retrograde rocket fire occurs at five second interval=. _he

/-_ first fire occurs thirty secc_ls after receptic_ of retrograde clock

runout if the retrogrede interlock is closed in the ASCS.

14-27

__Na,m ,L SEDR 104

_he retrograde rocket assembl_ Jettison s_nsl occurs 60 seec_1_

after the _nitia_ion of the retrograde fire signal _e signal is

routed through ncrssl_ open ecntaets of the retrograde rocket assem-

bl_ separation sensor relay in retrograde _ box No. 1. _-!s relay

is energiz_l by limit switches _eh close when the retrograde assembly

is blastea away fr_ the spacecraft. _e relay r_a_ns energize_ until

the O.05g relay drops out. (_e O.OSg relay de-ener_zes at 10,000

feet. ) A a-e signal of appr_-tely 2._ + 0.3 volts is applied Through

n_11y open eon*.aets of +_s refer to the ¢.-.-m,tator.

Emergenny escape sequence 4-_-trumentatlonconsists of m_2day abc_t

end _cwer escape rocket fire signal momi_ars.

14-52. MAYDAY

_e Msyday signal is produced by the me_tsy alarm re_. _s relay

is energized by any abort si_pael. With __e relay energ£zed, 2._ _+0.3

volts d-e is applle_ to the e_fcatc_. Once _-_late_, _ signal

is present for the remainder of the _4eslcm. _he m-ydey alarm relay is

in launch and orbit relY7 box No. _.

1_-_3. AS_0_'S ABC_ _r_TCH

Instnmentation is provided to monitor an abort signal _l_t_

fr_ the astronaut's ABOP_ Handle; T_is signal is applie_ to T_e e_.--_,-

tarot.

14-28

The tower escape rocket signal is obtained from the emergency

escape rocket fire rels_ in isnnch and orbit relay box No. 2. This

rel_v rm_._.= ene_gized until orbit attitude is atts_ned.

Landing system instrmaentation consists of monitor circuits for

chute deploy and Jettison and release of the antenna fairing. These

signals are _ppro_watel_ 2._ + 0.3 volts and are s_plied to the co_-

tator. Main and reserve chute deploy signals are obtained fr_n toggle

switches in the chute c_artment. Lanyards fr_ the chutes operate

these switches when the chutes deploy. The main chute Jettison signal

is obtained _h','OU_ a limit switch in the chute o;.,,_.a_:_-ent.The antenna

falr_ release signal comes fr_n the antemna fair_ separation relay

in the co_-,,_mie_,tionsrelay _ox. This relay is energized through a

limit switch. _I landing system signals r_Ain on until impact.

zb,..56, o.o:50 J,x

• -_trumentation of O.05g relay operation consists of an on-off type

signal which indicates whether the relay is energized or de-energized.

The relay ,my be energized by operation of the O.05g sensor or _y the

eozzz_d reeeiver. When the relay is energized, a d-e signal is applied

to the e_tator.

f

14-29

_MO_NNELL SEDR 104

Droguee_ute0_p_t ismonitoredby a 2.4+ 0.3voltslg._1

controlled by the drogue chute sensor, +-_ough a set of cc_tac_s cn

the antenna separatio_ relay an_ is applie_ to the c_-tator.

1_-58. LA_n_ _S

•he I,._ bag opera, on is mmLitc_ed by a voltage signal 8ppl_ed

to the c_ator +._-_ugh two sets of tmloek signal 11m_t switches.

1_-59. IN_ATIOU CO_ROL SYST_

14-60. HIGH LEVEL CODI_

The signals applied to the e----,tator are sampled once every 0.80

seconds. C_or outputs are square wave pulses with m_D.litudebe-

%_een -i and +3 volts. _hese pulses are applied tO voltage controlled

oscillators and pulse durati_ modulatlc_ converters.

(a) _e frequencies of the volte_e controlled oscillator is varied

between 10.5 K_ + 6-3/4% by the o_-_.tated pulse _pl£tude sig-

nals. _hls fre_,_encyb-_ oorrespona- to IRIG _---_I 12. The

frequency modulated outputs of the i0._ KC voltage cun_rolled

oscillator is applied to an isolation ampl_£er.

(b) _>._.._._atc_ p.l_ mpl_tude modulatic_ signals are also appl£e_

tO a p-_-_ dt_ration mo_-ln_;i_l coD_ex_r. _le _onvel_ re-

shapes the pulse emplltuae wave-shapes _o obtn_- pulse duratio_

wave _ralns. _ese wave trains are then applied to the _ape re-

corder.

14-30

_ONNELL SEDR 104

(c) Amplifier aercmedical signals are coupled to a 1.3 KC, L7 KC

/ and 2.3 KC voltage controlled oscillators. A zero to i_,11 scale

sl_al causes a a_rlatlml in center frequency of + 6-3/4%. 9he

frequency ban_- of the oscillators correspond tO ]:RIG_--_is 51

6 and 7. _he oscillator outputs are applied to an £solatlcn ampli-

flat.

(d) AttenuaTed ASCS rate signals are coupled to a ._0 KC, .56 KC

an_ .73 KC voltage controlled oscillator. A zero to i_,11 scale

si_p_l causes a deviation in center frequency of + 6-3/4%. _e

frequency bands of the oscillators cow,respond to IRIG _A--els

i_ 2 and 3. _he oscillator otttputsare applied to the isolation

-_,_er.

(e) _e c.....;.,_!tatea outputs, aer_cal slgnals and ASCS rate sl_lals

ere cmm_ined. _he IsO]atl_ amplifier al-o aeeepts a si_l from

the e__--I_anting oscillator Which serves as a reference durl_

data evaluation to indicate fluctuations in tape speed. _e

composite signal from the Isolation amplifier is applied to the

tape reeorder_ the ground test ,-._illcal and telemetry transmitter.

COD SO

_he st_ applied to +-_- e,-,;_._-tstor ere sampled once every 0.30

seconds. C,_,.-_.._,ator outputs are aq,,_-re wave p,l-es with amplitude be-

tween -5 my and 15 my. _ese PAMp-l-as are applied to a 10.5 KC voltage

controlled oscillator upon closure of the Temperature Survey Switch to

14-31

_NNm/.L SEDR 104

q_STj and also to a pulse _urat£on mo_ulat£on converter for _ape

reeordi_. _ converter reshapes the pulse _Tl£tu&e _ave to

obtain a l_lae duration wave train. _aile the £nstrumentat£c_ sys-

tem is in the low l_v_l mo__e (Temperature S_vu_ - S_ttch _o _T)_

h_h level c.._,_ated inputs are _ from the 10.5 KC V00.

i62. usslo

Ground _esting an_ control of the _nstrmnen_a_ion systez Is pro-

vl_ed +_ough 1;he _iliQal receptacle. NmEadiating checks can be

performedto ev-l-ate systezopemtlc_. Radiatlngchecks are per-

fm_ed through the telemetry _. Refer to Section XII for further

infc0_ation regarding _elemetry.

1_-63. I_S_SM_TATION C0_0L

_e instr_entat_on syste_ controls an_ _s (see Table 11_1)

power tO Its own mad other sysT_ns equ_ne_t by mee_s of tootle relays

sn_ pro_er. (See Fi_tre i_-5).

(a) _e va%er extractorin the envlr_n_l control_st_ is A!-o

prc6r_._l at regular Int_v-_- dm_n_ the =tss£on.

(I)) Calibration volta_es_R-callbratefur _-_ read:i_s end Z-

calibrate for _-_ read:t_s_ are suppl£e_ per_od£cal_ _o

the monitori_ _m_tatton circu_ts. _s £s done prior

tO Isam_h s_l by _rcamd c_-._ or pro6x _..._ at In_er_-1-

_urlng orbi_•

14-32

_ _O_NNml_t. SEDR 104.

14-6_. INSTRI_IERTATIONRECORDING (See Figure i_-5)

Recordi_ ¢--trumentation consists of a tape recorder and a port-

able 16 m_lllmeter camera.

14-65. TAPE RECO_

A lOW power, lightweight tape recorder provides seven channels for

data recording. Voice co.=_ni_ations, high level c_tator pulse _,_-

ation modulation sig--1- and VC0's are e_plied to tracks 3, 5 and 6,

respectively. Low level co, rotator pulse duration signals are applied

to track _. Stick position VC0's are recorded on track 2. The _pe

recorder operates contimaously fran umbilical separation to spacecraft

separation plus five minutes and fr_ TR-30 seconds to impact plus 10

minutes. During orbit, the tape recorder is on 1 minute every 10 min-

utes with a total of 30 seconds every 1 hour allowed for zero and full

scale calibration. The astronaut is provided with a CONTINUOUS- OFF -

PROGRAMMED switch on the _,_in i_trmzent p_nel which allows ._ml as

well as _utc_tic control of the tape recorder. A VOX switch located

on the main instrument panel when placed to RECORD will allow the astro-

nauts conversation to be recorded. A record_-_ indicator light is lo-

cated on the center of the main 4--trt_ent panel when the recorder is

operating so that the astron_t may record voice at these times if he

desires.

A l_ht weight portable 16 millimeter cmnera is provided for the

astronauts use &ar_ the mission. The camera operates at a single speed

of 6 frames per second. Dur_-_ non use, the camera is stowed along with

14-33

_M_DONNELL SEDR 104

i

i +p 0

M'

_g_o.

!

_ °

14-34

"4'

.;CDONNELL SEDR 104

_Aw_OUT RECORDER

LA c (

INSTRUMENTATION _ I

RECORD NO. 2

TIMER HATCHINSTRUMENTATION & DISCONNECT

COMMUNICATIONSRELAY PANEL

CAMERA AND :TAPE RECORD

RELAY

ER 24V

_ =-_. . . ,_ _ PROGRAMMED

C_MERA AND _ _'_

TJkPEON-OFF 4, I _Hc I_llSWITCH _ v n

: "- TO RETRO

TAPE RECORDER COMMAND - g VOX RECORDON-LIGHT _ RELAy

GROUND TEST NO. 2 TAPE RECORD SW. CONTROL

MODE "_

OPERATION

UMBILICAL AND RF

CONNECTOR SILENCE RELAY

1 I ,v

(REMOVABLESECTION)

WARNINGLIGHTS

GROUND TEST TC_

bWBILICALRELAy

I"-" INSTRUMENTATION _ I--_--CONTROL PANEL

• m m m PRE-RETRORECORD RELAY

MAININSTRUMENT

PANELm m i FM18-99 A

Figure 14-5 Tape Recorder ControlCircuit

14-35

__NAIrit.Z. SEDR I04

6 magazines of f_Im (each magazine cont_n_ approximately 120 ft. of f_1_)

in the perso-al effects container on the main In_trument panel.

3._.-67. srm,m um_s

1_.-_.

Potenticmeter type tr=-=dncers are connected across Instrumentation

3 volt 8-c power. The wiper is activated by the action to be measured.

Wiper voltage is then proportional to the action.

i_-69. COI_OL STXCK MOTXON POTEHTXOMETERS

Control stick motion is translated into rotary potentiometer move-

ment. One potenti_eter is provided for each axis of motion.

z_-T0._ CLOCK_z_m_m_s

The satellite clock (refer to Section XXXX) utilized potentiometers

to indicate ele_sed time from launch and time to retroKr&de outputs for

0-IO seconds, O-i minute_ O-IO minutes, O-i hour, O-lO hours and 0-60

hours.

I_-TI._mALAWD_C SUPPLYHm_Im m_mBz P0_zm_cHmzRs

Heli_ _ly pressures actuate the wiper of _ potenti_eter trans-

@Acer to a resistance position proportlonal to the pressure.

x_-Tz.A_ POmm_XSBmERS

The ASCS calibrator (refer to Section V) provides synchro actuation

of potenticmeters for pitch_ roll and ya_r. Each wiper output is then

proportional to the spacecraft attitude for that axis.

14-36

_M_L_. SEDR 104

Eaeh oz_m _o%_le pressure a_uates a dual potentloaetez %r_r.

A low reslstsnee 14-ear element is used to operate a panel indicator while

a higher resistance 11near element ls used fc_ lnstawmentattc_. Wiper

voltage c_tputs are propcrtlcaal to applled oz_en pressure.

S TICP SSm AND TZOmmRS

Each pressure _ansducer ls used to provide a folded linear output

propo:tlcaal to the applled pressure. Pressure ranges are 0-15 psla

for static pressure an_ 0-15 psla for suit pressure.

i_-_. RESPIRATICR RATE PICZDPS

Resptratlc_ ra_ is sensed by "two, one-half Inch o_,-_e stainless

steel wlze screens. _hese electrodes are a_.ae.hed wlth sllve_ ae_l 4._L

a4hestve to the as_uts body. _11 connecting irlree leadl:_ to "the

astronauts suit _tsccnnec_ c_mplete the clrcult.

i_-I_. RESISTANCE w_T _a_S_UC_RS

Resistance e_s are used "tO measure _zpera%_tres. _he resistance

of the element varles prOportionall_ to its t_T.erature. Mountl_ of

the el_nt depeD_ oD _ appltcatio_. Stick-on surface tw_erature

elements are _.1_ l_htwet_ht ,_ts. Other eleme_s are mounte_ as an

integral part of "the spaceeref_ struc_m_e. _ followl_ list tadlcates

p_ the purpose and _ma_e temperature an_ resistance ran6es for each

transducer.

14-37

_MCDONNffLL SEDR 104

(a) Ablation Heat Shield Temperature: -55 ° to SO00°F

(b) Suit Tn_et Temperature: 35° to IO0°F -249 to 300 Oh,.R

(c) Cabin Air Temperature: _0° to 200°F -232 to 316 ohm.

1_-77.Bo_ _ T_m_r_

The body temperature transdncer is a rectal t_nperature pickup which

consists of a thermistor imbedded in sealing c_md at the end of a

flexible wire lead.

lb,-78. _-C_ mUST

The shunt resistance used for the 4n-trument panel _eter also sup-

plies voltage for instrumentation. This shunt is discussed in Section

XX of this mamm]..

1_-79.EL_TROCAR_0GRA_PICKUPS

Cardiac activity is sensed by four, one-half inch square, sta_nl=ess

steel wire screens. These electrodes are attached with adhesive to the

emtronaut's body, .c_,=11 connectln8 wires leading to the astronaut's suit

disconnect, complete the circuit.

z_.-8o, ox_m PAm'XAL_

The 02 Partial Pressure trausdhacers are used to oonvert 02 partial

presuures to a sl_nA1 coupatible with high level telemetry. The voltage

range of 0-3 V f-c output is representative of 0-6 psi oxygen partial

pressure.

14-81._U_ _CO_

A low power, l_hCwe_sht tape recorder is used in the spacecraft to

mak-e available 7 channels of recorded data. At the present time channel

14-38

"_Mo_mmz.I. $EDR 104

asei_mnents are as fol_s: Track 3, voice e_uications; Track 5,

_ e_e_,tator PIM; Track 6_ "qUO'S_ Trace 4, 10W level c--m,tator PI_ t

Track 2, stick position VCO's. Tape speed is 1-7/8 Ips. Tape capacity

is 6,250 feet of _ inch wide _lar base tape. The tape transport con-

sists of a capstan _Lrive,supply reel and take-up reel mechanism. A d-e

motor is used, through reduction gearing, for capstan drive. A limit

switch is provld_l to inte_pt recorder power should the tape break.

Record _lifiers are incorporated in the unit for Channels 2, 3 and 6.

ChA_nel 5 is fe_ by an _lifier ineerporlted in the _-,,,,tatorlocated

in instrumentation package A. C_I _ is fed by an _lifier incorpo-

rated in the low level e_-.-...,tator.

l.-82, z:z , 'mawm o c

The C package incorporates units of various functions into one compact

panel allowing co_venlenee of mounting and of maki_ electrical connections.

These various sub-units are discussed in the following paragraphs.

1_-83. CABIN PRESSURE _

Cabin pressure actuates the wiper of a 10,000 ohm potenttsmeter

located in the C pankage. Three volts d-e from the C pack_e is s_plied

across the potenticmeter. Wiper output volta_ is then proportio-=l to

the cabin pressure.

co,were

The _--trumentation package utilizes a unique method of construction

and mounting of the transistorized empliflers, power supplies, attenuators

and monitors. P_Ch unit consists of the necessary cce_onent parts mounted

14-39

_N_ar_. SEDR 104

cn a prtnt_ ctrcult_ dielectric card w£th prtn_ed connector co_taets

at the bottoa far plug-in tn_rtion. _e card is then covered t with

the exeeptt_ of ba_ connector contacts and side aounttns edges, w£th

a *.ht, layer of epox_ resin, q_g coatl_ is used to provlde molsture

protection, to insure opel'at;J.on in a i00_ coq_e_n a_nosphere and to im-

prove mecba_4eal xd_ldt_ of e_ponents. _hese Converter Cards are pack-

age mounted t-bo_es providing side ra£1s_ base contact receptacles and

In_nt_d elre_Lt ln_zrcczmections.

D-c m r Za

An _l_Ter located in the Z package is used to bring the cl-e current

shunt voltage up to a maximum of 3 volts d-c. _ae _lXfier feeds the c_-

rotator. _he mp]£fier Is trA--istortzed and card mouute4.

]._.._, ]L_:b_L.q_(_[ _ _J_T.TRI_JL_O_ _ __qw_AT(]_ CARD

Resl_tar8 are mortared _ the card for attemt_tlcn of 2_ volt _-e volt-

ages to proportional_ol_es cc_patlblewi_h _he e_-tator.

Reststors_ capacitors and etreult tsol_tln_ crystal diodes are used

to attenuate reaction control solenot_ w_e ene_lztn_ volts_es_ e_-_

receiver st_a_ strength and emergency 02 rate l_£or to application to

the commutator. Each atten_atcz elreuitO_%l_t_ a _=_ of 3 _OltS _-C_

ls spplted to the e_-_,_atc_.

14-40

"___J"_ SEDR104

_ _e horiz_ scanner _pllfter card provides circuitry for processin8

the scA_er roll an_ pitch 8:I.8_1s s 1"o].].artS.pitch i_ore signals prior

to being applied to the en---.tator. Duri_ launch and orbit, the scanners

are operating continuously; however_ during _'bit the signals spplied to

the ASCS and "the e,.,.,._ator are timed by the progrm_er loca_.d on _ae

pedestal.

_e progrm_r emlta1-- switch co.acts which operate control c_:u:l.ts

for specific intervals. The progr_r is mounte_ forward near the center

of the main ins_nt panel.

•ae progrem_r useA for orbitalmissions consistsof two sections.

When power is applAed I;o the programmr_ electronic cc_trol_d timers

c_tinuously operate the followA_ ccQtacts:

C_EACTS CLOWn

i. Water extraction 30 Secct_Ls 1 per 30 .rt--+_es

2. F-_I Scale CaIAbrate 15 Seconds i per 60 minutes

3. Zero Calib. 15 See_ds 1 per 60 _,tes

_. Tape 1 Minute 1 per 10 m4-,r_es

5. Horizon Scanner 8.5 Minutes 1 per 30 -4-._es

14-41

_MCDONNliLL SEDR 104

z -gz. B-

The B Section of the prosr_mer is energized +-__ouKh the c.-_;._-,aza

receiver-decoders au_ the electronic timers to provide full scale and

zero calibrate signal, as follows:

CO.tOTS CLOSED

SECTION DURATION

1. 1_,_ 1 Scale Calibrate 15 Seconds On Co_ud

2. Zero Calibrate 15 Seconds On Cc_mnd

3- Telemetry 6 M_w,tes On C.--..,-_,_

14-92. _i_m_)_ON PA_ A

The A _ackage also incorporates units of various functions into one

panel. These sub-units are discussed in the followi_ paragraphs.

I_-93. CABI_ AIR TEMPERATURE TRARSIX;C_m_

A platinum resistance wire is used to measure cabin air temperature.

Temperature chan_es from 40° to 200°F cause the element to change resis-

tance from 236 to 316 oh-. The resistance element forms a part of an

amplifier circuit. A transducer is used in con_unctlon with an _.._li-

fier to supply signal to the cv,_tator.

A filament transformer is used to step down 115 volts 400 cps space-

craft power to 6.3 volts for use in package A

14-95. COF_ERTER

The _--trumen_ation package A also utilises the Converter Card princi-

ple for e_plifiers and power supplies.

14-42

• CDONNIELL SEDR 104

_ The same type 8mplifier is used for heat shield, suit inlet _tr

and cabin =4_ temperature trsnsdneer signals. Each amplifier is of

dual o_--nel desi_ in order to acccmodate two transducers. Seven volts,

a-c is supplied from the resistance element power supply. This volt-

age is applied across a bridge circuit in each amplifier. The trans-

ducer associated with each bridge circuit causes the voltage in the

circuit to vary proportlonal ly to the transducer temperature. This

voltage change _ppears across a transfo_ner and is rectified, us_n_ cry-

stal diodes, to a _ output of 3 volts d-c. The output from the

an_lifler is supplied to the com,,tator. Two relays on each card e_pli-

fier allow i_,_Iscale and zero calibration of each o_-_el. Calibration

resistors are also provided for each channel.

Resis+_m_e element enplifier circuits require 7 volts, a-c. S_ace-

craft power, 21_.volts d-c, is _pplied to a transistorized l_wer inverter.

The i_verter, using zener diode-transistor voltage regulation and tran-

sistor switching, supplies a 7 volt a-c output which is monitored by an

attenuator, rectifier circuit. The monitor output, a mAw1._m 3 volts

d-e, is applied to the ¢.-_..,tator.

_-_ A transistorized d-e e_plifier is used to increase the output of

the temperature transducer to a maximum 3 volt d-c level prior to appli-

cation to the eo_A1_tor. This amplifier is the seinet_pe as that used

for the d-e current sigDal a_llflcatiou.

14_3

_i_4_IOINELL. SEDR 104

14-_. SIGNAL COnDItION AND D-C SL_PLY CARD

_4s Converter Card provides four functions in the instrumentation

system. Filsment transformer o_tput is applied to a monitor circuit.

•h_s circuit attenuates and rectifies to provide a m._.. 3 volt _-c

signal IndleaT_LngTzansfc_mer operation. Spacecraft power_ 2_ volts

d-c, is applie_ to an attenuator circuit _hich provides a 3 volt a-c

output for the monitoring circuit. _h_s 3 volt output is then applied

to the c_--m_at(E as a monitor of _ m.4_ 2_- volt d-c bus voltage. _le

s_nal condlti_ an_ d-c power supply card also provides meter _ttemmtor

resistors which 11m_t current flOW in the panel indicator circuits. These

circuits involve the primary end seconclary ox_p_n supply pressures, an_

the mau.,_-!fuel supply pressures.

14-100. _I_94UTATOR-_-RECORD .q4FLIFrm_

A unit is provlde_ in the A packa@_ fur e--,-.,_atlngtransducer data

and supplylz_ PDM and PAM ontputs. _he c..-,,;rtatorportion of the unit

is a 90 x i_ solid state device which samples sequentlal_7, 88 channels.

of signal input information. _ae ontput produced is a pulse maplitude

modulated signal wave train. Each 0 to 3 volts (1-e input to the c_--_,_,-

tater is sampled i_ times per secoa_lper IRIG standards. The PAM wave

train output is fe_ throush a buffer stage to a P_FEM converter. _he

output is T_en applie_ to a record amp14_ler _hich pro(luces a signal

capable of directly drtvi_ the recorder heed in the spacecraft tape re-

corder. The PAM output is fed +._ce_h a gati_ circuit which introduces a

master pulse add negative pedestal pulses to operate autc_atlc dec_...-._tion

'_#_'L_LL SEDR 104

equil_ent in the ground statics. A power s_p_ is incorporated in

•the unit %o provide 'the positiwe e_t negst£ve vOltages required in %he

eirc_%s.

1_-:_1. IN--ON PA_ D

The pr4m-_y i_ncticu of the D package is to c_vert spacecraft infor-

matic_ t;o signals capable of modulati_ _ telemetry tr-,m_tter. T_--

dueers az_ mapl_t"iers are .1.o cc_ta_ in "the package %o c_lete space-

craft information circuits.

_e Z -_ s acceler_ter is mounted in the D paeke_e an_ used, to

determ4-e -thesta%Ic lo_%udlnal, aeceleratlcm of "thespacecraft. _he

accelerometer --_t gi_es a d-c output vhtch is applied to 3 channels of

Two mplifiers are use_ for the _ transducer inputs. Each a_li-

f_er increases the transducer o_put to a 3 volt peak to peak s_al.

OSn.T

_he D package s_plies sub-carrier osc_l-tors _o allow c_e ehe_nel

of lnst_me_tattc_ data. _he fo_ paragraphs _escribe +;_ sub-

carrier oscillators.

1_-i_5. CC_P_SATI_ O_._C_ CARD

Daring playback of a tape, the recorded signal from this osc_l_tca-

is mon.i_ca'e_l"to _e'tec,'t changes in tape recorder sr,cc:1.. A freq.ue_cy

1445

_NNE_. SEDR 104

indicates a chenge in speed. _he oscillator is of module c_-

structi_ and operates at 3000 cps. Output level is adjustable.

1_-106. VOLTAGEC0F_OT.T._ OSC_.T.A_C_(V.C.O.) CARDS

Instr_entation data voltages are applte_ to the sub-carrier oscilla-

tors caust_ osc_:ll_tor frequency shift proportional to the input an_li-

rude. The transistorized oscillator consists of a free runuin6 multi-

vibrator anA fllter. _he osctllatc_ functions and frequencies are given

below:

I. _gh and (Lov Level co_._utatcetest ,_y) - 10.5 KO VCO

and Blood Pressure - 2.3 KC VCO

3. Upper Chest (Cnmm) BZD and Lower Chest

(+)_ - 1.7xcvco

_. Respiratlo_ Rate - i. 3 KC VCO

_. Solenoi_ F_/Uucti_ Detector - 5.4 KC V_O

6. ASCS Roll Rate _A Low Solenoi_ - .73 KC VCO

7. ASCS Pitch P_e and Low Solenoid - ._0 KC VCO

8. _s Yav_ate_ L_,Soleno*a - .56KCVC0

i_-_07._ _eLnu_ CARD_ Sm_L_

Spacecraft power, 2_, volts A-c, is ccnverte_ to 6 volt _-c for use

by _ sub-ca_ier oscillators. A _t_ circuit e_r_lnes +,he sub-ca._,_ier

oscillator outputs. SollA state o_,__o_ts for these ctrcults are con-

btned _ cae Converter Car4.

14.-46

IifCDOAINELL SEDR 104

+3V D-C

SATELLITECLOCK O lSTATICPRESSURE(ALTITUDE) ._.SPACECRAFTATTITUDE(PITCH,ROLLYAW)PRIMAI_Y02SUPPLYPRESSURECONTROL STICKPOSITIONS(ROLL, PITCHeYAW)CABIN AIR PRESSURE O

COMMON

SUllr INLETAIR TEMPERATURE

THESMOCOUPLE,y LOW LEVELCOMM.TH_MOCOUPLE, CR J_"

co, .o.2.4V BUS

COMMUTATORPOINTS

(TYPICAL)

FM18-I(X)A

Figure 14-6 Typical Commutator Signal Sources

14-47

__mz.z. SEDR104

TAN_ 1_-2 IN_0N (Xle(0TATORPOINT

(xIoa o-3 vo s.)

PARAMETER _.

_r_'fRICALPOWER SYSTEM

Maln 24 V D.C. _

D.C. Csrrent 3_

ASCSA.O. _

Fans A.C. Bus 33

8ee_ Power _y 19

XN_ATI(M POWERSUPI_._..q

3 V D.O. Reference 1

0 V (Zero)Reference 2, 72

7 v, _0o C_S 3

_ATIC PRESSURE

C_7.7_RATIONC_ 64

E_VIR_ C017_0LSYS._W

Suit Y-_t Pressure 8

Pr4_-_'702 Pressure 9

Cabin Heat ExchangerGas Temperature 7_

Cabin T=_erature 10

Cabin Heat _c_r Dome Temperat,re 20

Suit Inlet Air T_.perature Ii

Suit Heat Exch_r Dume Temperature 21

Seeonaary02 Su_p_ Pressure 12

1_A.8

'__Nmm_[. SEDR 104

,,, , , ,, , , J ,

P_

Cabin Pressure 82

Cabin 02 PartlalPrese_re 6

_argency 02 Rate 68

SuAt C02 PartialPressure

REACTXON COJ_ROLSTS_EM

Reacti_ ControlSUppI_

Reac_i_ ControlSupply

Stick Control Positi_s

Ro11 23, _8, 80

Yaw 25, 50, 83

Pitch 24, 8l

z A_, (_t_J_al) ].6, 38, 61

_C'2URAL T_=_aiTRE

Heat m_4elcl (Center) 75

I_at Shiela.(_ge) 76

A_QMEDICAL DATA

Bo_ Temperature 4

1.7 & 2.3 KC VCO

Respirati_ 1.3 KC VCO

14_9

_NRMg.I. SEDR 104

P_ CHAlm_.. , i i i i i

o.o_ _r.a 87

HC_TT_ON

Ro3.l _are 8_

_teh :_ore 85

_ltoh Outl_o 88

Plto_ (_scs) 1_

ao_ (Ascs) 17

x_ (Asos) 18

_RA_

P'£'tr..h .1,0 ice V(X)

Rol.X •73 _ VCO

Yav . _6 KO VCO

a.P. Pi_ca _ 65

H.P. P_.tch Dotm

H.P. Roll + 69

ILP.Roll. 70

H.P. Yaw - 78

H.P. Yaw+ 79

14-50

'__N_ir/.L. SEDR 104

i, , , , , ,

PARAMETER OB._ImL

10 _eon_s 28, 59

K_z_es 30

z _ 3z

3.0 Hours

60 Hours 67

3.0 8eeo_s _1

1 Mlnute

10 PtXnu_s _3

60Hours 63

Towe_ Separation h6

S_aeecra_ 9eparati_ _7

Retz'o At_itmle Coe_. h8

l_ro Rkt. Asoy. JeSt. 53

:10 _eca1_

10 M_u_es _2

1Hou_14-51

__arLL SEDR I04

P_ _.,i

_,f. v_tase _,pse_ _,,,,- s_ _ _'_o

Rocket _ _'7

P£1ot _q_or'_ 71

MaWrD_" 60

Escape Rocket _ 49

I_'osue (_ute I)eploy 5_.

Antenna Release _5

Chute Dep]._ _6

ReserveChuteDeploy 73

RetroFireNo. 1 35

Re'_o _ No. 2 36

RetroFireNo.3 37

_m_ RE_NER

S_4_._1StretCh 7

14-52