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AS-206 S-IV-B RESTART
ALTERNATEMISSION
L/V OPERATIONALFLIGHTTRAJECTORY
(PAGES) _
OR TMX OR AD NUMBER)
CONTRACTNAS8-4016
• SCHEDULEII, VEHICLE'_"::::::::::SYSTEMS INTEGRATION
!iiiiiiiiiiiiiiiiiil
-iiiiiiiiiiiiii!ii
:::::::::::::::: SPACE DIVISION
,:.:.:.:.:.:.:.:
BB-3.1.3-10-MO3
(TN-AP-67-264)
PART III
(T_U)
(CATEGORY)
CHRYSLERCORPORATION
https://ntrs.nasa.gov/search.jsp?R=19680007324 2018-07-08T17:06:58+00:00Z
BB-S. 1.3-I0-M03
(TN-AP-67-26A)PART III
AS-206 S.IVB RESTART ALTERNATE MISSION L/V OPERATIONAL FLIGHT TRAJECTORY
September 15, 1967
by
AEROSPACE PHYSICS BRANCH
CHRYSLER CORPORATION SPACE DIVISION
PREPARED BY: T. B. PEDERSON AND B. B. BARRETT
• • c tock, S_pervlsar
Preflight Trajectory Unit
APPROVED:
_.S..S. A. Zoba_, Managing Engineer
Preflight & Range Safety Group
R. D. Taylor, Mknaging Engineer
Vehicle Performance Group
': - _ <_ .<"_/_"_R H_ Ross, CHie_/Eug-ineer '
.,>" Aerospace Physics Branch
FOR_gQRD
Thls report documents the AS-206 S-IVB Restart Alternate Mission _V
Operational FiAght Trajectory. The analysis and documentati_ were perforuod
by the Aeroepace Pb_ics Branch, Chryaler Corporation Space DivisiQn, within
the scope of NAS 8-_016, Modification KSFC i, Amendment 38, MCRR No. 103,
BB Itm 3.1.3-IO-MO3, Part Ill.
AcknowledgeRents are nade to the personnel of Marshall Space FIAght
Center, R-AERO-FK, for their assistance and cooperation.
i
,TABLE OF CCl_TS
Page
FOR_gORD ................................................................... . i
TABLE OF CONTENTS .......................................................... £i
LIST OF TABI_ ............................................................. iv
LIST OF ILLUSTRATIONS ...................................................... vi
SUMMARY e e e e e ¢ o • o e • • • • $ • • • • • • • e • e • e e • e e e • • • • • • • • • • • • • • • e • e • • v e e e • e • • • • e • • e e $
1.0 INTRODUCTION ..........................................................
2.0 MISSION DESCRIPTION ...................................................
2.1 Mission Objectives ...............................................
2.2 Mission Ground Rules and Cormtraints .............................
3.0 IAUNCH VEHICLE AND _NVIRON_ DESCRIPTION ............................
3.1 Configuration ....................................................
3.2 Mass Characteristics .............................................
3.3 Aerodynamic Properties ...........................................
3._ Propulsi_ Systems ...............................................
3.5 Environment Description ..........................................
A.O GUIDANCE AND CONTROL ..................................................
&.l Guldance .........................................................
&.2 Control Systems ..................................................
5.0 L_CH VEHICLE TRAJECTCRY .............................................
DEFINITIONS AND SYMBOLS .................................................... ix
1
3
5
5
5
5
5
6
?
?
8
?
5.1 _Boost Phase ...................................................... 9
5.1.1 S-IB Stage Powered Flight ................................. 9
5-i. 2 S-IVB Stage First Burn .................................... i0
ii
,TABLEOF CC_T_TS (Cont'd)
5.2
6.0
APPENDIX A.
APPENDIX B.
APP_DIX C.
DISTRIBUTICN
Orbital Flight Phase
5.2.1
5.2.2
5.2.3
i
• e • ee • e. e • • . • • • • • • • • • • • . • • • e e • e • • e e . • e e . e e e e e
First Orbital Coast Period ................................
S-IVB Stage Second Burn ...................................
Second Orbital Coast Period ...............................
5.3 Spent S-IB Stage Trajectory ......................................
5. A Tracking Summary .................................................
5.5 Launch Vehicle Propulsion Performance Characteristics ............
5.6 S-IB Stage Engine Out Performance Capability .....................
REFERENCES ............................................................
"LAUNCH VEHICLE CHARACTERISTICS AND FLIGHT _IR_" .......
"GUIDANCE PRESETTINGS" ........................................
"TRAJECTORY LISTINGS, ENGLISH UNITS" ...........................
eeeeeeee eeeeeeeeeeeeeeeeeeemeeeeeeeeee .eeeeeee eeeoeeeeeeeee,eee
Page
io
Io
io
11
11
II
ii
]2
12
99
17_
iii
LIST OFTABLES
Table
1
2
3
5
6
7
8
9
iO
ii
12
Description
Flight Sequence of Events ................................... 1A
Launch Vehicle Trajectory Summary ........................... 17
S-IB Stage End Conditions of Flight ......................... 18
S-IVB Stage End Conditions of Flight, First Burn ............ 19
First Orbital Coast Phase End Conditions of Flight ........... 21
S-IVB Stage End Conditions of Flight, Second Burn ........... 22
Trajectory Listing, Metric Units: S-IB Stage Flight Data ... 23
Trajectory Listing, Metric Units: S-IVB Stage First Burn,First Orbital Coast and S-IVB Stage Second Burn Data ........ 28
Trajectory Listing, Metric Units: Second Orbital Coast Data. 53
Trajectory Listing, Metric Units: S-IB Stage Re-entry Data.. 62
Tracking and Telemetry Sta. Coordinates: Launch Phase ...... 66
Tracking and Telemetry Sta. Coordinates: Orbital Phase ..... 67
Appendix A: "Launch Vehicle Characteristics and Flight Environment"
IA
2A
3A
5A
6A
7A
8A
Vehicle Weight Breakdown .................................... 1OO
Launch Vehicle Propulsion Performance Characteristics ....... 102
S-IB Stage Mass Characteristics ............................. 103
S-IVB Stage First Burn, First Orbital Coast and S-IVB StageSecond Burn Mass Characteristics ............................ 10&
S-IB Stage Aerodynamic Characteristics ...................... 109
S-IB Stage Propulsion Characteristics ....................... 110
S-IVB Stage First Burn, First Orbital Coast and S-IVB Stage
Second Burn Propulsion Characteristics ...................... lll
Orbital Vent Sequence and Impulse History ................... 116
iY
Table
Appendix B:
IB
2B
3B
Appendix C:
IC
2C
3C
_c
LIST OF TABLES (Cont'd)
Description Page
"Guidance Presettings"
S-IB Stage Steering Program ................................. 125
S-IB Pitch Attitude Command ................................. 126
IGM Presettings ............................................. 127
"Launch Vehicle Trajectory Listings, English Units"
S-IB Stage Flight Data ...................................... 131
S-IVB Stage First Burn, First Orbital Coast and S-IVB Stage
Second Burn Data ............................................ 136
Second Orbital Coast Data ................................... 161
S-IB Stage Re-entry Data .................................... 170
v
.LIST OFILLUSTRATICNS
Fizure Description
1
2
3
7
8
9
iO
II
12
IA
15
16
17
Altitude vs. Flight Time:
Altitude vs. Ground Range:
Velocity vs. Flight Time:
Boost Flight Data
Boost Flight Data
Boost Flight Data
eeeeee.eeeBe
eeeee.eeeee
eeeeeeseeeee
Space Fixed Path Angle vs. Flight Time:
Boost Flight Data .......................................
Earth Fixed Path Angle vs. Flight Time:
Boost Flight Data .......................................
Pitch Attitude Steering Command History:
S-IB Stage Flight Data ..................................
Vehicle Pitch Attitude Rate History:
S-IB Stage Flight Data ..................................
Pitch Attitude Error History:
S-IB Stage Flight Data ..................................
Pitch Angle of Attack History:
S-IB Stage Flight Data ...................................
Dynamic Pressure History: S-IB Stage Flight Data ........
Longitudinal Acceleration History:
S-IB Stage Flight Data ...................................
Pitch Attitude Steering Command History:
S-IVB Stage Flight Data, First Burn ......................
Yaw Attitude Steering Cmmnand History:
S-IVB Stage Flight Data, First Burn ......................
LcmgitudinalAcceleratien History:
S-IVB Stage Flight Data, First Burn ......................
VehicleAttitude Rate History:
S-IVBStage Flight Data, First Burn ......................
Attitude Error History:
S-IVB Stage Flight Data, First Burn ......................
Angle of Attack History:
S-IVB Stage Flight Data, First Burn ......................
68
69
70
71
72
73
7_
75
76
77
78
79
80
81
82
83
8_
vi
LIST OF ILLUSTRATIONS (Cont'd)
Figure
18
19
2O
21
22
23
2&
25
26
27
28
29
30
31
Appendix A:
IA
2A
3A
AA
5A
6A
Description Page
Dynamic Pressure History:
S-IVB Stage Flight Data, First Bum ........................... 85
Altitude History: First Orbital Coast Phase ................... 86
Space Fixed Velocity History:
First Orbital Coast Phase ..................................... 87
Pitch Attitude History-
First Orbital Coast Phase ..................................... 88
Altitude History:
S-IVB Stage Flight Data, Second Burn .......................... 89
Space Fixed Velocity History:
S-IVB Stage Flight Data, Second Burn .......................... 90
Space Fixed Path Angle History:S-IVB Stage Flight Data, Second Burn .......................... 91
Pitch Attitude History:
S-IVB Stage Flight Data, Second Burn .......................... 92
Altitude History: Second Orbital Coast Phase .................. 93
Space Fixed Velocity History:Second Orbital Coast Data ..................................... 9_
Pitch Attitude History:Second Orbital Coast Data ..................................... 95
Tracking Summary: Launch Phase ............................... 96
Tracking and Telemetry Sumnary: Orbital Phase ................ 97
H-I Engine Out Performance Capability ......................... 98
"Launch Vehicle Characteristics and Flight Environment"
Vehicle Profile ............................................... 117
H-I Engine Thrust Decay ....................................... 118
J-2 Engine Thrust Buildup, First Burn ......................... 119
J-2 Engine Thrust Dec_v, First Burn ........................... 120
J-2 Engine Thrust Buildup, Second Burn ........................ 121
J-2 Engine Thrust Decay, Second Burn .......................... 122
vii
LIST OF ILLUSTRATIONS (Cont'd)
Figure
7A
Description Pa_e
Mean Headwind/Tailwind Profile 123oooeeoooQoeeeoeoeoooeoooooooeooo
viii
DEFINITIONSANDSYMBOLS
Aerodynamic Heating Indicator
Aerodynamic Load Indicator
Altitude
Angle of Attack, Pitch
Attitude Error
Axial Force
Central Range Angle
Descending Node Argument
Dynamic Pressure
Earth Fixed Positic_
Earth Fixed Cross Range
f qVr dt q --dynamic pressure_/2--_t I Vr = relative velocity
a t = total angle of attack
Product of dynamic pressure and angle of attack.
Vehicle altitude above the referenced ellip-
soid measured along the geocentric positionvector.
Angle between the pitch plane component of the
relative velocity vector and the longitudinal
axis of the vehicle, measured positive nose up.
Difference between the vehicle attitude (Pitch,
Yaw and Roll Eulerian Angles) and the vehicleattitude command.
Component of the resultant aerodynamic forcealong the vehicle longitudinal axis (X axis
of PASCS 8a), measured positive toward thetall of the vehicle.
Angle between instantaneous space fixed
position vector and space fixed positionvector at Guidance Reference Release.
Angle measured in the equatorial plane between
the orbit descending node and the space fixedlaunch meridian defined at Guidance Reference
Release.
Cc_onent of the resultant aerodynamic force
along the relative velocity rectory, ama-
suredpositive opposite to the velocity vector.
x (Density) x (Relative Velocity) 2
Position vector components in an earth-fixed
pad-centered plumbline coordinate system.The Xe axis is coincident with the reference
ellipsoid normal, positive upward. The Ze
axis is parallel to the earth-fixed aiming
azimuth and is poeitive downrange. The Ye
axis completes a right handed system. (PASCS i0)
Ye cce_onent of PASCS i0 position vector.
ix
B
DEFIMITIONS AND STMBOLS (Cont'd)
Earth Fixed Flight Path
Angle
Earth FJ_ed Velocity
Earth Fixed VelocityMapitude
Aslmuth
Geocentric Declination
Geodetic Latitude
Gr_nd _ange
Inclination
Longitude
L0_Itudinal Acceleration
Mach M_ber
,Angle between the earth fixed velocity vector
and the earth fixed geocentric position vector
(PASCS ii), measured positive downrange fromthe position vector.
Velocity vector components in PASCS 10.
_e 2 . 2 . 2+ Ye + Ze
Angle defining orientation of the space
fixed coordinate system downrange axis, Zs,
at Guidance Reference Release, measuredpositive east of north in plane normal to
the space fixed Xs axis at Guidance Ref-erence Release.
Angle between the geocentric radius vector
and the true equatorial plane, measured
positive north of the equator.
Angle between the reference ellipsoidnormal through the point of interest and
the true equatorial plane, measured pool-tire north of the equator.
Surface distance from launch site to the sub
vehicle point, positive east (0° - 180°).
Angle between the inetantaneou| flight planeand the equatorial plane.
Angle between the Greenwich meridian plane
and the projection of the geocentric poei-
tion vector in the equatorial plane, measuredpoeitlve east cf Greenwich.
That part of the total measurable acceleration
directed along the longitudinal axis of thevehicle.
(Relative Velocity) (Local Speed of Sound)
X
DEFINITION3 AND ST_BOL5 (Cont'd)
_+
o,
X S
Launch Meridia.
1 N|
I
Z$
Xm : (-_r)l ((_Y_ (_P)2 Xs
Xm
XM X I _ r
x' xs
" ,,,,,,7_,,, • _ -z,Zm
Pitch Yaw Rol I
xl
DEFINITI_S AND SYMBOLS (Cont 'd)
Mass
Normal Force
Pitch, Yaw, Roll
Radius
Range
Relative Velocity
Space Fixed Position
Space Fixed Cross Range
Space Fixed Flight Path Angle
Space Fixed Velocity
Space Fixed Velocity
Magnitude
Time
Thrust
Weight
Mass of the vehicle.
Component of the resultant aerodynamic force
normal to the vehicle X axis, and in the X-Z
plane (PASCS 8a), measured positive towardPosition I.
Eulerian angleBof vehicle attitude measured
with respect to the space fixed coordinate
system. Vehicle attitude is defined by the
ordered rotation of pitch, yaw, and roll,respectively. (See illustration)
J Xs + ys 2 + Zs2
Surface distance from launch site to the sub
vehicle point, positive east (O° - 180°).
Velocity relative to the atmosphere (includeswind velocity).
Position vector components in a spaced fixed,
earth centered, plumbline coordinate systemdefined at Guidance Reference Release. The
Xs axis is parallel to the reference ellip-
soid normal which passes through the launchsite. The Zs axis is parallel to, and posi-tive in the same direction as the earth-fixed
firing azimuth. The Ys axis completes the
right handed system. This is Project Apollo
Standard Coordinate System !3. (PASCS 13.)
Ys co._onent of PASCS 13 position vector.
Angle between the space fixed velocity vectorand the radius vector (PASCS 13), measured
positive downrange from radius vector.
Velocity vector components in PASCS 13.
Instantaneous flight time referenced tofirst motion.
Total effective thrust magnitude.
J FTX + +FTy 2 FTZ 2
Weight of vehicle in pounds.
xii
SUMMARY
This report documents the AS-206 S-IVB Restart Alternate Mission _/V
Operaticmal Flight Trajectory. Trajectory data are tabulated for allphases of f_ for which the Saturn IB Launch Vehicle has a func-tional requirement. A cce_rehensive summary of the launch vehiclecharacteristics and flight environment is also presented.
The predicted S-IB, S-IVB stage first burn (_dance Cutoff Signal) and
S-IVB stap second burn (Depletion Cutoff Signal)end conditlcr_ aresummarized below:
Guidance
Cutoff SienalDepletion
Flight Time (sec) 143.217 508.122 ii,&67.962
Altitude (m) 67,566. 190,872. 216,168.
Space Fixed
Velocity (_sec) 2,598.6& 7,783.58 lO,A13 •55
Space Fixed
Path AnKle (deg) 63.820 90.007 87.187
Range (m) 73,984. i,A85,602. -315,701.
The nominal weight in orbit is predicted to be 67,675 pounds, of _hich31,167 pounds is useable S-IVB stage propellant. Under nce_%al flowratecriteria, this propellant is depleted 76.962 seconds after the S-IVB stage
restart signal is received. This includes a "full burn" period, 90_ thrust
level to propellant depletion, of 6_.A62 seconds.
S-IVB stage restart occurs after an orbital coast phase of approximatelytwo revolutions (10,875 seconds). During this period a local horisontalvehicle attitude is maintained and the Constant Vent System (CV$) is open.
The S-IVB stage restart sequence is Time Base 5 (T_5) dependent. TB5 is
established by navigational sighting ef the Guaym_ tracking station duringthe second revolution. The vehicle inertial attitude cc_Bmd is frozen
30 seccm_ prior to second ignition and held until 30 sec_da after pro-pellant depletion. For the balance of the lifetime of the batteries, alocal horizontal attitude il maintained.
-1-
The S-IVB stage Flight Performance reserve for this mission is approximately
1,200 pounds. Therefore, the predicted useable propellant available at or-
bit insertion may deviate by 1,200 pounds. This corresponds to a second
burn time deviation of approximately 2.5 seconds.
An H-I engine out performance evaluation has been conducted for this mission.
Analysis of the results reveals that the most severe case, engine failure at
liftoff, would decrease S-IVB stage second burn time capability by approxi-
mately eight seconds. The controllability of this vehicle with H-1 enginefailure will be determined at a later date.
-2-
.SECTION 1
/NTRODUCTION
The AS-206 S-IVB Restart Alternate Mission L/V Operational Flight Trajectory
is presented in this document. By definition, the Launch Vehicle OperationalTrajectory includes all phases of flight for which the S-IB stage and theS-IVB/IU stage have functional requirements.
In addition, comprehensive sulaaries of vehicle data, sub-systems character-
istics, and the guidance and control modes are presented herein.
SECTION2
MISSIONDESCRIPTION
2.1 MISSION 0BJECT!V_ES: The basic purpose of the Apollo Saturn 206 S-IVBRestart Alternate Mission is to place the S-IVB stage into orbit and test
its restart capability, simulating the AS-5OI mission profile. In the event
S-IVB restart problems occur in the early Saturn V flights, this missionwill be flown to help correct or solve the problems. The primary objective
of the SA-206 Launch Vehicle is to insert the S-IVB/IU/Payload configuration
into a near earth i00 nautical mile circular orbit. The payload consists of
a Spacecraft LM Adapter (SLA) and a 25 ° Nose Cone (NC #2). (See Reference I)
In the event of an S-IB engine premature shutdown, the desired orbit may be
attained by using the remaining seven S-IB engines and S-IVB burn to orbit.The effects of S-IB engine premature shutdown on mission capability are
shown in Figure 31.
2.2 MISSION GROUND RULES AND CONSTRAINTS: The following mission criteria,vehicle constraints, and trajectory constraints have been imposed on this
trajectory:
i) launch from AFETR Pad 37 B.
2) Pad oriented launch azimuth of 90 degrees east-of-north.
3) Flight azimuth of 72 degrees east-of-north.
_) S-IB stage tilt program defined in Table IB.
5) S-IVB cutoff conditions for i00 nautical mile circularorbit insertion.
6) Commanded pitch and yaw attitude rate limit of one degree
per second.
7) Average mean head/tailwlnd for December through April.
8) NC/SIA remains attached to the S-IVB/IU for restart.
9) First S-IVB burn Engine Mixture Ratio (EMR) 5.5:1.
i0) Second S-IVB burn EMR _.5:1 for 13 seconds, then closed loop
Propellant Utilization (PU) to depletion.
n)
i2)
Simulate as cloee_T as possible the AS-501 profile, restartenvironment and restart sequence.
Open loop guidance during S-IVB second burn with propellantdepletion cutoff.
-4-
SECTIC_3
IAUNCHVEHICLEANDENVIRONMenTDESCRIPTION
3.1 CONFIGURATION: The SA-206 Saturn IB Launch Vehicle consists of a S-IB
first stage, a S-IVB second stage, an instrument unit, and a payload. For
this mission the payload consists of a Spacecraft LM Adapter and a 25 ° Nose
Cone. There will be no spacecraft or LM. An outboard profile of the complete
configuration is shown in Figure IA, Appendix A.
3.2 MASS CHARACTERISTICS: The SA-206 vehicle mass characteristics are de-
fined in Reference 2_ Table IA presents a vehicle weight breakdown of the
launch vehicle. These data are consistent with Reference 2 and the trajec-
tory presented herein. Tables 3A, and _A present a time history of the
vehicle mass and the associated center of gravity and moment of inertia
data for the S-IB stage and the two S-IVB burns, respectively.
3.3 AERODYNAMIC PROPERTIES: Powered Flight aerodynamic data for the S-IB
stage and S-IVB stage first burn were obtained from Reference 3. Flight
time histories of the S-iB stage aerodynamic data are presented in Table 5A.
Orbital drag data was extracted from Reference A and was used for the orbital
coast phaseaand the S-IVB stage second burn.
3.6 PROPULSION SYSTEMS: The S-IB stage is powered by eight H-I engines
which have a nominally rated sea level thrust of 205,000 pounds each. The
predicted nominal thrust magnitude history for each H-I engine, including
thrust decay and the associated turbine engine thrust, were obtained from
Reference 5. The thrust magnitude time history for each H-I engine is de-lineated in Table 6A. Figure 2A depicts the thrust decay histories.
The S-IVB stage is powered by a single J-2 engine which has a rated vacuum
thrust of 200,000 pounds at a nominal mixture ratio of 5:1. However, a
5.5:1 engine mixture ratio is maintained during the first S-IVB stage burn
which results in a relatively high thrust level throughout this flight per-
iod. The predicted nominal first burn J-2 engine thrust history from the
90% thrust level time point to the time of the guidance cutoff signal was
obtained from Reference 6. The thrust buildup and thrust decay historieswere obtained from Reference 7. Table 7A presents a stmmmry of the first
burn J-2 engine thrust history. The J-2 thrust buildup and decay histories
for the first burn are depicted in Figures 3A and _A.
The predicted nominal J-2 engine second burn thrust history from the 90%
thrust level to propellant depletion was obtained from Reference 8. The
thrust buildup and thrust decay histories were obtained from Reference 7.
Table 7A presents a summary of the J-2 engine thrust history. The J-2
thrust buildup and decay histories for the second burn are depicted inFigures 5A and 6A.
-5-
Four solid propellant retro-motors (TE-M-29) mounted on the S-IB/S-IVB inter-stage provide thrust to decelerate the S-IB stage after separation. The retro-motors are rated at a nominal thrust level of 36,720 pounds each (Reference 9 ).
Three solid propellant ullage motors mounted on the S-IVB stage aft skirt pro-
vide a positive acceleration for the S-IVB stage to settle propellants for J-_-_engine start. The ullage motors rated thrust is 3,A60 pounds each (Refm
erence lO).
The S-IVB Stage A_xiliary Propulsion System (APS) consists of two modules.
Each module contains three 150 pound thrust (vacuum) hypergollc rocket engines.
This system provides roll control during both J-2 burn phase% and pitch, yaw
and roll control during orbital coast phase.
3.5 ENVIRONMENT DESCRIPTION: The 1963 Patrick Reference Atmosphere model de-
fines the atmospheric properties incorporated in the trajectory simulation.
The earth mmdel and potential function are those of the Fischer Earth Model.The wind profile is an average of the December through April mean headwlnd/
tailwind profiles defined in Reference ll. It is depicted in Figure 7A.
-6-
SECTION&
GCblTROI, AND GU_C_;
The Saturn IB inertial guidance system performs navigation evaluations, issues
c41screte commands, initiates guidance and control functions, and issues steering
ccmm_nds to guide the launch vehicle to the prespecified targeting conditions.
These ftmctions are accomplished by the AS-206 Flight Program which is
stored in the Launch Vehicle Digital Computer (LVDC). Inputs to the LVDC for
navigation and steering co_and evaluations are the predetermined constants
for the different guidance modes and the inertial velocity increments sensed
by the stabilized platform accelerometers.
&.l GUIDANCE: Guidance of the AS-206 Launch Vehicle into orbit and throughout
the orbital phases of active attitude control is divided into three distinct
phases: (i) Pre-IGM; (2) IGM; and (3) Orbital.
The Pre-IGM phase guidance provides pitch, yaw and roll vehicle attitude com-mands as a function of the time from liftoff to the time of IGH initiation.
The S-IB stage pitch program polynomials for this mission are delineated in
Appendix B, Table IB. Also included in Table IB is a time history of the yaw
and roll attitude conm_nds. A history of the pitch attitude steering conmand
generated by the pol_nomials is given in Table 2B.
In the Iterative Guidance Mode (IGM) phase for this mission, a one-stage three-
dimensional formulation of the IGH equations and logic provides active guid-
dance of the S-IVB stage in pitch and yaw from the time of IGM initiation, TB3
+ 17.0 seconds, to J-2 cutoff. The commanded roll attitude is zero. The IGM
equations and logic progra,ned for the LVDC Flight Program are defined in
Reference 12. The IGM presettings for the mission are given in Appendix B,Table 3B.
The orbital guic_nce mode provides pitch, yaw and roll attitude commands for
the planned maneuvers during the orbital coast phase and second J-2 burn phase
of the mission. The planned maneuvers for this mission consist of :
l) At 10 to 20 seconds after insertion, maneuver into local horizontal
plane, nose leading, fin 1 down and hold this local attitude until30 seconds prior to second ignition_
2) At 30 seconds prior to second ignition, freeze the current vehicle
inertial attitude for the entire second burn period;
3) 30 seconds after second J-2 cutoff, the local horizontal, nose
leading, f_n, i down attitude is reattained and held _hroughoutthe mission lifetime. (See Reference i)
-7-
_.2 CGNTROL SYSTEMS : Pitch, yaw and roll attitude control are maintained by
the four swivelable H-1 engines during the S-IB stage of powered flight. The
control law, gains, and network characteristics for the S-IB stage control
system are defined in Reference 13.
The J-2 engine provides pitch and yaw attitude control throughout both S-IVB
stages of powered flight. Roll attitude control is maintained by the AuxiliaryPropulsion System (APS). The control law, gains and network characteristics
of the S-IVB stage control systemm are defined in Reference 13.
Pitch, yaw and roll attitude control are provided by the APS during orbital
coast phases.
-8-
SECTION5
lAUNCH VEHICLE TRAJECTORY
The nominal sequence of events for the AS-206 S-IVB Restart Alternate Mission
_V Operational Flight Trajectory is summarized in Table 1. It was derived
from References IA and 15.
Table 2 provides a summary of trajectory parameters at pertinent events fromliftoff to loss of attitude control. Convenient summaries of the end condi-
tions of flight for the S-IB, S-IVB first burn, first orbital coast and S-IVB
second burn phases of flight are presented in Tables 3, A, 5 and 6, respec-
tively. Tabulated listings of the trajectory,in metric units,are presented
in Tables 7 -iO. Corresponding tabular listings, in English units, are
given in Appendix C. Graphical displays of the ascent trajectory are shownin Figures I through 5.
The associated data tapes required for distribution by MSFC, R-AERO-F, areidentified as follows :
Trajectory Listing (Printout Tape):
CCSD/Slidell Reel No. 8800
MSFC Copy Reel No. IOA53 j
Data Tape (B-7 Tape):
CCSD/Slidell Reel No. 5&_l
MSFC Copy Reel No. O153
5.1 BOOST PHASE: The trajectory boost phase consists of the S-IB stage
powered flight and the S-IVB stage first burn. The phase begins at GuidanceReference Release (GRR) and ends at Orbit Insertion (O1).
5.1.1 S-IB Sta_e Powered Flight: Tabulated listings of trajectoryparameters for this stage are presented in Table 7. It is initiated
at Guidance Reference Release (GRR), which is ass_ed to be 5 secondsprior to launch (first motion). The time of umbilical disconnect and
the corresponding establishment of Time Base One (TBI) is assumed to
be 0.2 seconds after first motion. This stage ends at S-IB/S-IVB
physical separation, which is assumed to be 1.379 seconds after Out-board Engine Cutoff signal (OECO).
A time history of the S-IB stage pitch attitude steering cc_nd is
depicted in Figure 6. Figures 7 and 8 present summaries of the re-
suiting vehicle pitch attitude rate and attitude error. A summary
of the pitch plane angle of attack is presented in Figure 9. Figure
I0 presents a summary of the dynamic pressure history. The longitudi-nal acceleration history is depicted in Figure 11.
-9-
In order to establish a more realistic nominal trajectory prediction,a constant thrust bias equal to + 0.7 per cent of the vehicle sealevel longitudinal thrust has been included in the S-IB stage tra-jectory. This action is an attempt to minimize the effects of anapparent systematic shift in the ground to flight test performancelevel.
5.1.2 S-IVB StaRe First Burn: Tabulated listings of this segment of
the boost trajectory are presented in Table 8. The segment begins atS-IB/S-IVB stage separation and ends at orbit insertion. Orbit inser-
tion is defined to be at Guidance Cutoff Signal (GCS) plus 10 seconds.
GCS occurs when the space fixed velocity magnitude equals a prespeci-fled value of 7783.58 m/sec. This phase of the trajectory includes
the ullage rocket burns, J-2 engine thrust buildup, mainstage burn
with ullage case Jettisoning, J-2 thrust decay and ullage venting.
The pitch and yaw attitude angle steering commands during this S-IVB
powered flight phase are depicted in Figures 12 and 13. The accelera-
tion history is depicted in Figure 14. Trajectory parameters pertinent
to an analysis of the trajectory from S-IB/S-IVB separation to the timeof active control are depicted in Figures 15 - 18.
It should be noted that the vehicle pitch attitude error history, pre-
sented in Table 8, shows larger excursion than observed in previous
flight predictions. This is primarily due to vehicle center of gravity
misalignment caused by the S-IVB stage restart hard, re installation.
When misalignment is sensed,_ the attitude commands to the control sys-tam are biased by the LVDC steering misalignment control logic so thatthe desired vehicle attitude is maintained.
5.2 ORBITAL FLIGHT PHASE: The orbital flight phase is initiated at orbitinsertion and terminates at loss of S-IVB/Payload attitude control. This
phase consists of an orbit coast period of approximately two orbits, a sec-ond S-IVB stage burn and a final coast period.
5.2.1 First Orbital Coast Period: The first orbital coast period isinitiated at orbit insertion and is terminated at Time Base Five (TBS)
plus ASO seconds (J-2 engine start signal). TB5 is established by the
LVDC as a result of navigational sighting of Guaymas on the second
revolution. Guaymas sighting time is defined as the time at which thevehicle enters the cone described by a 5° elevation angle generated
from Guaymas. Tabulated listings of the trajectory for this period
are included in Table 8. Histories of altitude, velocity and pitch
attitude for this period are displayed in Figures 19 through 21.
5.2.2 S-IVB Stage Second Burn: The S-IVB stage second burn is
initiated at TB5 + _50 seconds with an eight second fuel lead through
the thrust chamber prior to ignition. Ignition occurs at TB5 +A58
-1o-
seconds and the 90%thrust l_.wl is attainted 2.5 seconds later. ThePropellant Utilization (PU) valve is held _ a hard over position pro-riding a A.5:l engine mixture ratio until 13 seconds after engine start
at which time closed loop PU control begins. This burn is terminated
by depletion of useable propellants. The nominal amount of useable
mainstage propellant on board for the second burn is 31,167 lbs. Under
predicted flowrates, this amount is depleted 7_.962 seconds after therestart signal is received or 6A._62 seconds al_ter the 90% thrust level
is attained. The Flight Performance Reserve (FPR) for this mission is
approximately 1,2OO lbs. Therefore, the nominal useable propellant for
the second J-2 burn may deviate by this amount producing a correspondingchange in burn time of approximately 2.5 seconds. Tabulated listing of
the trajectory from second burn engine start to lO seconds after J-2
engine depletion shutdown are included in Table 8. Histories of alti-
tude, velocity, flight path angle, and vehicle pitch attitude duringthis period of the trajectory are presented in Figures 22 through 25.
Du_-Lng this burn, open loop guidance is used. Therefore, the vehicle
attitude commands are not biased by the LVDC steering misalignment logic
to compensate for vehicle center of gravity displacements. Thus, the
displacement caused by the S-IVB restart package installation produces
vehicle attitude errors which are not corrected by the guidance scheme.
5.2.3 Second Orbital Coast Period: Table 9 presents tabulated listings
of trajectory parameters for the second orbital coast period of the
Launch Vehicle Trajectory. This period extends from J-2 engine deple-
tion shutdown plus lO seconds to loss of S-IVB/Payload attitude control.
Histories of altitude, velocity and pitch attitude for this period aredisplayed in Figures 26 through 28.
5.3 SPENT S-IB STAGE TRAJECTORY: The re-entry trajectory for the spent
S-IB stage is summmrlzed in Table 10. This phase of the S-IB stage tra-Jectory is initiated at S-IB/S-IVB separation and includes the retro-rocketburns.
5.A TRACKING SUMMARY: Radar and telemetry coverage during ascent and orbit
are provided by the stations listed in Tables ll and 12. Summaries of the
tracking and telemetry coverage for each station are presented in Figures29 and 30.
5.5 .LAUNCH VE_ICLE PROPULSION PERFORMANCE CHARACTERISTICS: The predicted
S-IB and S-IVB stage performance characteristics are presented in Table 2A.
These data are time averages of the detailed vehicle performance data re-ferenced herein.
5.6 S-IB STAGE _GINE OUT PERFORMANCE CAPABILITY: Free a performance stand-
point, the effect of an S-IB stage engine failure may be offset by utilizing
the seven remaining H-I engines and the S-IVB stage engine to attain the
specified orbit. The effect of an S-IB stage engine failure on available
second burn propellants is depicted in Figure 31 as a function of enginefailure time. These data indicate that for an otherwise nominal flight an
engine out at liftoff would only reduce the nominal S-IVB stage second burn
tlme by approximately 8 seconds.
-ii-
SECflC_ 6
REFERENCES
le
e
•
_o
e
e
•
e
e
fOe
lle
"Minutes of Backup _S-206 S-IVB Restart Mission", I-I/IB-E-335-67,
6 June 1967; "AS-206 S-IVB Restart Alternate Mission Flight Program
Definition", R-ASTR._NG-56-67, 17 July 1967.
"Preliminary Predicted Mass Characteristics, Saturn IB Vehicle AS-
206, Part IXI, Depletion Cutoff", BB-3.8.0-!-MO3, 31 July 1967.
"Summary of Saturn IB/LEM, AS-206 Static Aerodynamics", TN-AP-66-150Volume l, 20 December 1966.
"Study of Drag Coefficients For Unusual Vehicle Configurations" AprilProgress Report, IMSC/HREC A782759.
S-IB Stage Propulsion Prediction, CCSD B5 Reel No. 6755. (B6 Reel No.9351/8_9)
S-IVB Stage Propulsion Prediction, CCSD Reel No. 10028.125 )
(_FC Reel
"Thrust Increase Envelope, Test No. 313-O9A, Engine SNJ-2OA6";
Saturn IB J-2 Engine Characteristics", R-P&VE-PPE-66-M-90, 11 May 1966.
S-IVB Stage Propulsion Prediction, CCSD Reel No. 2072. (_FC Reel No. 10)
"Data for use in S-IB-03 and Sub Vehicle Specifications and Future Se-
paration Studies", MBFC, R-P&VE-PFE-66-M-82, 21 June 1966.
"S-IVB Ullage Rocket Typical Thrust Versus Time (Vacuum 70°F) '',R-P&VE-PPS-65-M-65, Figure 16, 5 May 1965.
"Cape Kennedy Wind Component Statistics 0-60 km Altitude For 72 Degree
Flight Azimuth For Monthl_ and Annual Reference Periods", R-AERO-Y-90-66,23 March 1966; "Latest Wind Estimates Fran 80 _n to 200 _n Altitude Re-
gion at Mid-Latitudes", NASA TMX-5306_, 16 June 196_.
"LVDC Equation Defining Document for the AS-2OT/AS-20@ FliBht Programs",MBFC No. III-_-_23-9, November 1966.
-12-
°.
_CES (Cont Vd)
_o
_e
15.
"Control Gains and Shaping Networks for Saturn AS-206, S-IB and S-IVB
Stages", R-ASTR-F-66-162, 6 September 1966 as revised by Reference 14.
R-AERO-FMR letter, "AS-206 S-IVB Restart Alternate Mission OperationalTrajectory Data", 21 Ju_y 1967.
"Saturn IB Restart Mission Flight Sequence "pDrawing Number IOM30766,26 June 1967.
-13-
TABLE 1
AS-2O6 S-IVB RESTART ALTERNATE MISSIGN I/V OPERATIONAL FLIGHT TRAJECTORY
FLIGHT SF_L_CE OF EgU_S
NGMIK%L FLIGHT TIME PROGRAM
- 0:0:05.0 - 5_00 ---
- 0:0:03.1 - 3.10 ---
0:0:00.0 O.O0 ---
0:0:00.2 0.20 (0.0) I
0:0:I0.2 10.20 (i0.0) I
0:1:00.2 60.20 (60.0) 1
0:1:11.0 71.00 ---
0:1:35.2 95.20 (95.0) 1
0:2:00.2 120.20 (120.O) 1
O:2:12.3 132.25 (132.1) 1
0:2:12.3 132.30 (132.1) 1
Guidance Reference Release (GRR).
Initiate S-IB Mainstage Ignition
Sequence.
First Motion.
Lift-off Signal; Initiate Time Base i.
Initiate Pitch and Roll Maneuvers.
Control Gain Switch Point.
Maximum Dynamic Pressure.
Control Gain Switch Point.
Control Gain Switch Point.
Tilt Arrest.
Emable S-IB Propellant Level Sensors.
O:2:15.8 135.8& (0.0) 2
0:2:18.8 138.8& (3.0) 2
o:2:m.e (0.0)3
0:2:23.1 I_3 .l& (1.3) 3
0:2:23.2 1_ .22 ---
(z.J.) 3
Level Sensor Activation;Initiate Time Base 2.
Inboard Engine Cutoff (IF.DO).
Outboard _ins cutoff (OECO);Initiate Time Base 3.
Separation Signal.
S-IB/S-IVB Physical Separation;Control Gain Switch Point.
-14-
TABLZ 1 (Ccnt'd)
AS-206 S-IVB RESTART ALTERNATE MISSION I/V OPERATIONAL FLIGHT TRAJECTORY
FLIGHT SEQI_CE OF EVENTS
FLIGHT
0:2:24.5 IA4.5& (2.7) 3
0:2:26.9 ]46.89 ....
0:2:27_9 147.9& ----
0:2:30.5 150.5& (8.7) 3
0:2:35.1 155.14 (13.3) 3
0:2:38.8 158.8& (17.0) 3
0:4:A7.9 287.9A (]&6.10) 3
0:8:28.1 508.12 ---
0:8:28.3 508.32 (0.0) A
0:8:38.1 518.12 ----
0:8:50.0 530.00 ( 21.88)_
3:2:23.0 i09&3. O0 (0.00) 5
3:8:53.0 11333.00 (390.00) 5
3:8:5&.2 11334.20 (391.20) 5
3:9:23.0 11363.00 (A20.OO) 5
3:9:53.0 11393.00 (&50.O0) 5
3:9:56.0 11396.00 (A53.00) 5
3 :i0:01.0 11401.00 (A58.00) 5
3 :i0:03.5 11403.50 ----
3 :lO:o6.0 11406.00 (463.00) 5
J-2 Engine Start Command.
Ullage Burn Out.
90% J-2 Thrust Level.
Command PU System Activation.
Jettison Ullage Rocket Motors.
Cummand Active Guidance Initiation.
Control Gain Switch Point.
Guidance Cutoff Signal (GCS).
Initiate Time Base &; Begin CVS LH2
Vent. (Reflects an approximate 0.2
second systems delay)
Orbit Insertion.
Begin Local Horizontal Attitude Hold.
Second Guaymas Sighting; Initiate TimeBase 5.
Begin Helium Ullage Vent Through CVS.
End LH2 Vent.
Inertial Attitude Freeze.
J-2 Start Ccmnand; Begin Fuel Lead.
End Helium Vent.
J-2 Ignltian.
90% Thrust Level.
Command PU System Activation.
-15-
TABLE 1 (Contld)
AS-206 S-IVB RESTART ALTERNATE MISSIC_ L/V OPERATIONAL FLIGHT TRAJECTORY
FLIGHT SEQUENCE OF EVENTS
FUGn P o mM
3:11:08.0 1/467.96 (0.00) 6
3:11:08.2 I/A68.16 ( 0.20) 6
3 :ll:08.& 1/468.36 (O.&O) 6
3:11:18.0 1/477.96 (10.00) 6
3:11:38.0 ii&97.96 (30.00) 6
3:13:08.0 11587.96 (120.00) 6
7:38: 3&O 27518.00 ---
EVENT
Propellant Depletion Cutoff; Ini-tiate Time Base 6.
Begin LH2 Vent.
Begin LaX Vent.
End LOX Vent.
Begin Local Horizontal Attitude Hold.
End I_2 Vent.
Loss of Attitude Control.
-16-
I
I
TABLE 3
AS-206 S-IVB RESTART ALTERNATE MISSION L/V OPERATIONAL FLIGHT TRAJECTORYS-IB STAGE END CONDITIONS OF FLIGHT
Flight Time (t): OECO + 1.379 seconds
(R)-Altitude:
Space Fixed Velocity (V):
Space Fixed Path Angle ( 0 ):
Space Fixed Flight Azimuth (AZI):
Earth Fixed Flight Azimuth (AZE):
Geocentric Declination ( 8 ):
Geodetic Latitude ( _ ):Longitude(_ ): (Po6.East)
i_3. 217 (sec)
6hh0820. (m)
67566. (m)
2598.6A (m/'s)
63.820 (deg)
75 ._.01 (deg)72.322 (deg)
28.576 (deg)28.736 (deg)
-79.8h5 (deg)
SPACE FIXED POSITION AND VELOCITY COMPONENTS
Xs = 6_39A61. (m)
Ys = 35_61. (m)
zs = 127_61. (m)Xs = 1099.5h (m/s)
_s = ns.5o (m/s)_e = _ 51.5s (m/s)
VEHICLE ATTITUDE AND ATTITUDE RATE
Pitch Attitude Angle (_p):
Yaw Attitude Angle (Roll Attitude Angle ( _R ):Pitch Rate ( _p_:YawRate ( BY):
Roll Rate ( @_):
-6o.896-0.069-0.002-0. Ol.1.
0.001-O.O02
(deg)(deg)(deg)(dee/s)(de_s)(deg/s)
-18-
TABLE
AS-206 S-IVB RESTARTALTERNATEMISSIONL/V OPERATIONAL FLIGHT TRAJECTORY
S-IVB STAGE _l_D CONDITIONS OF FLIGHT, FIRST BURN
Flight Time (t): GCSRadius (R):
Altitude:
Space Fixed Velocity (V):
Space Fixed Flight Path Angle ( _ ):
Space Fixed Flight Azimuth (AZI):
Earth Fixed Flight Azimuth (AZE):
Geocentric Declination ( 8 ):
Geodetic Latitude ( _ ):
Longitude ( _ ): (Pos. East)
Inclination (i) :
Descending Node Argument ( _ ):
508.122 (sec)
6563322. (m)
190872. (m)
7783.58 (m/s)
90.007 (deg)
83.815 (deg)
83.&72 (deg)
31.068 (deg)
31.233 (deg)
-65.489 (deg)
31.617 (deg)
119.079 (deg)
SPACE FIXED POSITION AND VELOCITY COMPONENTS
Xs = 6335504. (m)
Ys = 123660. (m)
Zs = 1709766. (m)
is = -2033.62 (m/s)
YS = /_.15.91 (m/s)
Zs = 7501.70 (m/s)
VEHICLE ATTITUDE ANGI/_
Pitch Attitude Angle ( _p ) = -97.136 (deg)
Yaw Attitude Angle ( _y ) = 2.813 (deg)
Roll Attitude Angle ( _R ) = -0.803 (deg)
OSCULATING CONIC PARAMETERS
*Perigee Altitude = 153.31 (km)
*Apogee Altitude = 185.18 (km)
Eccentricity = 0.0024
Se_i-MaJorAxls = 6547.41 (km)
True Anomaly = 182.96 (deg)
Period = 87.87 (mln)
* Referenced to Equatorial Radius (6378.16 km)
-19-
TABLE& (Cont'd)
AS-206 S-IVB RESTARTALTERNATEMISSIONL/V OPEK_TIONALFLIGHTTRAJECTORYS-IVB STAGE_D CONDITIONSOF FLIGHT, FIRST BURN
Flight Time (t): Orbit Insertion
Radius (R) :Altitude :
Space Fixed Velocity (V):
Space Fixed Flight Path Angle ( 8 ):
Space Fixed Flight Azimuth (AZI):
Earth Fixed Flight Azimuth (AZE):
Geocentric Declination ( 8 ):
Geodetic Latitude ( 4, ):
Longitude ( A ): (Pos. East)
Inclination (i) :
Descending Node Argummnt ( _ ):
518.122 (sec)
6563325. (m)190898. (m)
7793.03 (m/s)
89.999 (deg)
8A.223 (deg)
83.903 (deg)
31.138 (deg)
31.30A (deg)
-6&.7Al (deg)31.617 (deg)
119.080 (deg)
SPACE FIXED POSITION AND VELOCITY COMPONENTS
Xs = 631A711. (m)
Ys = 12781A. (m)Zs = 178&7&7. (m)
Xs = --212A.15 (m/s)
= (m/s)is = 7&86.A8 (m/s)
VEHICLE ATTITUDE ANGLES
Pitch Attitude Angle (_p ) =
Naw Attitude Angle ( 4¥ ) =
Roll Attitude Angle (_a) =
-97.3202.660
-.692
(deg)(deg)(deg)
OSCULATING CONIC PARAMETERS
*Perigee Altitude = 18A.98
*Apogee A_titude = 185.26
Eccentricity = 0.OO00Semi-Major Axis = 6563.28
True Anomaly = 108.33Period = 88.19
* Referenced to Equatorial Radius (6378.16 kin)
(km)(kin)
(kin)(deg)(rain)
-20-
TABLE 5
AS-206 S-IVB RESTART ALTERNATE MISSION L/V GPERATIONAL FLIGHT TRAJECTORYFIRST ORBITAL COAST PHASE END CONDITIONS OF FLIGHT
Flight Time (t): Second J-2 Start Command
Radius (R):Altitude:
Space Fixed Velocity (V):
Space Fixed Flight Path Angle ( 8 ):
Space Fixed Flight Azimuth (AZI):
Earth Fixed Flight Azimuth (AZE):Geocentric Declination ( 8 ):Geodetic Latitude ( _ ):
Longitude ( _ ): (Pes. East)
Inclination (i) :
Descending Node Argument ( @ ):
11393.0 (sec)6587268. (m)
21_A3 • (m)7780.88 (m/s}
90.015 (deg)95.7_3 (deg)
96.062 (deg)
31.1_A _detl31.309 (deg)
-89.088 (deg)31.617 (deg)
118.095 (deg)
SPACE FIXED POSITION AND VELOCITY COMPONENTS
Xs = 9_712SI. (m)
Ys = 2396A0. {mmtZs = 36606&3.
is = -&33&.85 (m/s)
_a = _5.78 (m/s)_.s = 6_s.12 (m/s)
VEHICLE ATTITUDE ANGLES
Pitch Attitude Angle ( Sp ) =
Yaw Attitude Angle ( _y ) =
Roll Attitude Angle ( $. ) =
-121.861
3.133
-i .978
(deg)
(deg)
(deg)
OSCULATING COMIC PARAMETERS
*Perigee Altitude =
*Apogee Altitude =Eccentricity =
Semi-Major Axis =
True Anomaly =Period =
208.71216.28
0.o0066590.66
333.587
88.75
* Referenced to Equatorial Radius (6378.16 kin)
(kin)(km)
(k,,)(deg)(rain)
-21-
TABLE 6
AS-206 S-IVB RE_T._T ALTERNATE MISSION L/V OPERATIC_AL FLIGHT TRAJECTORY
S-IVB STAGE END CONDITIONS OF FLIGHT, SECOND BURN
Flight Time (t) : Depletion Cutoff
Radius (R):Altitude:
Space Fixed Velocity (V):
Space Fixed Flight Path Angle ( 0 ):
Space Fixed Flight Azimuth (AZI):
Earth Fixed Flight Azimuth (AZE):Geocentric Declination ( 3 ):
Geodetic Latitude ( _ ):
Longitude ( A ): (Pos. East)
Inclination (i):
Descending Node Argument ( _ ):
11_67.962 (sec)658SSlS. (m)216168. (m)10_13.55 (m/s)
89.189 (deg)97.762 (deg)98.083 (deg)30.A60 (deg)30.623 (deg)-82.770 (deg)31.3_I (deg)
120.679 (deg)
SPACE FIXED POSITION AND _OCITY C_4P_S
za = _7s_2. (m)Ys = 266808. (m)Zs = AI8936A. (m)
is = -6518.51 (m/s)
ts = 272.23 (_s)
Zs = 8116.&6 (m/s)
VEHICLE ATTITUDE ANGLES
Pitch Attitude Angle ( Sp )
Yaw Attitude Angle ( _y )
Roll Attitude Angle ( _R )
= -127.583
= -1.977= -2.A31
(deg)(deg)(deg)
OSCULATING CONIC pARAMETERS
*Perigee Altitude =
*Apogee Altitude =
Eccentricity =
Semi-Major Axis =
True Anomaly =Period =
_9.16 (_=)5o55o.12 (km)
0.7926
31757.80 (_.)1.835 (deg)
938.72 (rain)
* Referenced to Equatorial Radius (6378.16 kin)
-22-
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Table 11
AS-206 S-IVB RESTART ALTERNATE MISSION L/V OPERATIONAL FLIGHT TRAJECTORITRACKING AND TELEMETRI STATION COORDINATES= LAUNCH PHASE
STATION
Telemetry
ODETICLATITUDE(l)(DEOS _SNO .)
Z,O.GITUDE(I)(VETOESEAST)
ALTITUDE ABOVE(l)ELLn SOZD
Cape Tel & 28.&63713 - 80.653029 0.00 (3)MILA-CIF 28.5&2366 - 80.6%3533 0.OO (3)Grand Bahama 26.62851_ -78.299_ 0.OO (3)
Grand Turk 21.&&6016 - 71.I_7500 O.OO (3)Bermuda 32.3&8102 - 6&. 653800 18 .OO
Antigua 17.137333 - 61.77_955 AI.20
Insertion Ship 22.0 - _&.O 0.00 (3)
C-Band Radar
MILA 28. &2A862 - 80.66_0& 12.O2
Patti ck 28.226553 - 80.599293 15.51
Grand Bahama 26.615778 - 78.3_7833 13.98
Grand Turk 21.&62890 - 71.13211& 28.00
Bermuda 32.3&8103 - 6&. 653801 2&. 31
Antigua 17 .I&AO32 - 61.792859 &9.37
Insertion Ship 22.0 - &A.O 0.OO (3)
GLOTRAC
GLOTRAC I 28.A13386 - 80.592263 10.95
Atlantic 3&. 881507 - 76.353_O_ 2.92
Bassett Cove 26.614552 - 78.323580 16.15
Grand Turk 21._33765 - 71.I&5032 21.OO
Bermuda 32.25&&88 - 6&.838675 87.09
ODOP
Transmitter (2) 28.&AA373 - 80.579973 5.14(1.3.l.7)
Notes:
1. All coordinates arc _._ferenced to Fischer Ellipsoid of 1960.2. ODOP tracks the S-IB stage duz_ng powered flight and after separation from the
S-IVB until loss of track at an elevation of zero degrees.3. An altitude of zero meters is assumed whenever a value for the actual station
altitude is not available.
-66-
Table 12
AS-206 S-IVB RESTART ALTERNATE MISSION L/V OPERATIONAL FLIGHT TRAJECTOEY
TRACKING AND TELEMETRY STATION COOP_INATES: ORBITAL PHASE
STATION
Telemetry
GEODETIC LATITUDE(l)
( DEGI=_ES NORTH)
L ITUDE(1) ALTITUDE ABOVE(1)
ELLIPSOID (METERS}
Cape Tel & 28.&63713 - 80.653029 O.OO (2)MILA-CIF 28.5&2366 - 80.6&3533 O.OO (2)
Grand Bahama 26.62851& - 78.29q:AiA 0.00 (2)
Grand Turk 21.&46016 - 71.iI_75OO O.OO (2)
Bermuda 32.3&8102 6i.653_60 18.00
Anti[ua 17.137333 - 61.77&955 &1.20Insertion Ship 22.0 - &h.O O.OO (2)
Canary 27.7&2797 - 15.598103 35.00
Ascension - 7.97A31_ - I&.392221 29.98Tanana rive -19.018056 A7.3OU4/_ 1375. OO
Carnarvon -2A. 8973 56 113.716067 6&. OO
Hawaii 22.125267 -159.667691 1/42. OO
Ship A 28.0 -138.O O.OO (2)
Guaymas 27.958&O6 -ii0.720792 18.00
Corpus Christi 27.655&OO - 97.380256 iO.OO
C-Band Radar
MILA 28. h2&862 - 80.66_/,O& 12.O2
Patrick 28.226553 - 80.599293 15.51
Grand Bahama 26.615778 - 78.3&7833 13.98
Grand Turk ZI.&62890 - 71.13211& 28.00
Be rmuda 32.3&8103 - 6&. 653801 2A. 31
Antigua 17 .I&4032 - 61.792859 &9.37
Insertion Ship 22.0 - &&.O O.OO
Canary 27.7&4861 - 15.602OOO 36.00Ascension - 7.95151& - l&.K12606 152.&3
Pretoria -25.9&3731 28.358&90 1622.&O
Tananarive -19. O180 56 &7.30&AA4 137 5.OO
Carna x-lon -2_. 897&O3 113.716078 62. OO
Woome ra -30.819728 -13 6.83 6989 151 •00
Hawaii 22.12209 2 -i 59.665383 ll&O. OO
Ship A 28.0 -138.0 O.OO
Point Arguello 3&. 582903 -120.561150 6&6.OOWhite Sands 32.358222 -IO6.36956& 1232.OO
(2)
(2)
Notes:
i. All coordinates are referenced to Fischer Ellipsoid of 1960.
2. A station altitude of lero is assumed when the actual value is unavailable.
-67-
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F_e 5
AS-206 S-I_ RESTART AL_TE MXSSICI_ _/_ OPERATIClIAL FLIGHT. ?RAJECT_YFARTH _ FI_GHT PATH _I_ VS FLIGHT TD_E: BOOST FLIGHT DATA
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-72-
Pi_re 6
AS-306 S-IVB RESTART ALTERNATE MISSICN _/Y OPERATICHAL FLIGHT TRAJECTCRYPITCH ATTITUDE STEERING CCI_AND HISTORY: S-IB STAGE FLIGHT DATA
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AS-_K)6 S-IVB RESTART A_TE MY_ESION Z/V OPERATIONAL FLIGHT TRAJECTORY
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AS-_6 3-1_B RESTART A_TE MISSIGN I/V OPERATIG_L FLIDHT TRAJECTORY
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AS-206 S-IVB RESTART ALTERNATE MISSION _V OPERATIONAL FLIGHT TRAJECTORY
H-1 _GINE OUT PERFORMANCE CAPABILITY
PAYLOAD
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APP_D/.X A: "lAUNCH VEHICLE CHARACTERISTICS AND FLIGHT _VIR(X_MENT"
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TABLE IA
AS-206 S-IVB RESTART ALTERNATE MISSION _V OPERATIC_AL FLIGHT TRAJECTORYv_IcLE WEIGHT__m
(Poem)
Nose Co_e
SIA Ring
Spacecraft IM AdapterInstrument Unit
S-IVB Stage, Dry
S-IVB Stage Residuals
Vehicle at End of LaX Vent, Second Burn
LGX Venting
S-IVB Thrust Decay Propellant
Vehicle at Propellant Depletion Cutoff
S-IVB Propellant Cons_ed
APS Propellant Cons_ed
Vehicle at "90% Thrust", Second Burn
S-IVB GN2 Start Tank
S-IVB Buildup Propellant ConsumedPropellant Lead
Ullage Control Helium ExpendedVehicle at J-2 Restart Command
Ullage Control Helium ExpendedLGX Vented
Fuel Vented
Vehicle at Orbit Insertion
S-IVB Thrust Decay Propellant Consumed
Vehicle at S-IVB Cutoff, First Burn
S-IVB Propellant Consmned
S-IVB APS Propellant Consumed
Ullage Cases
S-IVB "90% Thrust" Weight
S-IVB GH2 Start Tank
S-IVB Buildup Propellant Ccns_ed
Ullage Propellant Consumed
S-IVB Stage Weight at Separation
1,055
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5,222
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30,8182
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67,871
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TABLE1A (Cont'd)
AS-206 S-IVB RESTARTALTERNATEMISSION_V OPERATIONALFLIGHTTRAJECTORYVEHICLEWEIGHTBREAKDOWN
(POUNDS)
S-IVB Detonation PackageUllage Propellant ConsumedS-IVB Aft FrameHardwareS-IB/S-IVB InterstageS-IB Dry WeightS-IB Residuals and ReservesS-IVB Frost ConsumedS-IB Frost ConsumedS-IB Seal Purge ConsumedS-IB Fuel Additive ConsumedS-IB Gearbox Lubricant ConsumedInboard Engine Thrust Decay Prpt ConsumedOutboard Engine Thrust Decay Prpt Consumed
To SeparationS-IB Mainstage Propellant Consumed
Vehicle Liftoff Weight
51331
6,667
8_,365
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1,000627
712
2,183
1,670
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TABLE 2A
AS-206 S-IVB RESTART ALT_TE MISSION L/V OPERATIONAL FLIGHT TRAJECTORY
IAUNCM V_ICLE PROPULSIGM PERFORMANCE CHARACTERISTICS
S-IB STAGE
Average Longitudinal Sea Level Thrust (lbs)
H-IEng£n.e Turbine
Engine #i 203914. 6&6.Engine #2 2031A8. 651.Engine #3 203232. 640.Engine #A 203367. 688.Engine #5 205745• 648.Engine #6 207935. 6_.Engine #7 205058. 649.Engine #8 20443I. 6AI.
20_560.
203799.
203872.
204055.
206393.
208579.
2057O7.
20_o72.
Total Average Sea Level Thrust (F): 1,6A2,037.
Flight Time Interval:
W : [Wt (t =0) - Wt
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Isp = F_
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* Waux: Frost
Seal PurgeFuel Additive
Total
S-IVB STAGE
First Burn Flight Time Interval:
Second Burn Flight Time Interval:
- 508.12 seconds
- 11467.96 seconds
AVERAGE VALUES
First Burn
Thrust Level
Second Burn
Thrust Level
Vacuum Thrust (Ibs)
Flowrat e (ib/sec)
Specific Impulse (sec)
229,916. 204,60&.
5&5.A6 479.85
&21.51 &26.39
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6 ibs
27 ibs
i133 Ibs
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Table 8A
AS-206 S-IVB RESTART ALTERNATE MISSIGN _/V OPERATIONAL FLIGHT TRAJECTORY
ORBITAL VENT SEQUENCE AND IMPULSE HISTORY
FLIGHT TIME (HR: MIN: SEC)
sta
0:8:28
EFFECTIVE IMPULSE
(Ib - sec)
3:8:53
3:11:08
3:11:08
3: 8: 5& LH2 Vent (CVS) 120000.
3:9:56 Helium Ullage Vent 2250.
Through CVS
3:13:08 IR2 Vent O.
3:11:18 Lax Vent 3600.
-116-
' -206 S-ZVB RESTART ALTERNATE MINION I/V OPERATI(RAL FLIGHT TRAJECTORYVEHICLE PROFILE
21.778" SPHERICAL RADIUS
t
NOSE CONE
t TELEMETRY
$LA
8" 58'.
RANGE SAFt
ANTENNA
HORIZON
HELIUM
TUNNEL
25"
STA
2034.859
HINGE COVER
STA1781.30
TELEMETRY ANTENNA _STA 169Q.8.59
INSTRUMENTATION UNITJ
S TUNNEL
STA
2170.57O
STA
1662.859
ULLAGE
RETRO ROCKEt
COMMA NO AN
260"
PROPULSIONUNITS
GIM8A[
STA1086. 157
STA
935.3O4
TELEMETRY ANTENNA
S-IVi STAGE
ONE (I) 200K THRUSTJ-2 ENGINE
STA
962.
I-IJ |tielEIGNT III) 2MK THRUST
14-1 ENGINES
GIMIIALSTA
IO0.O00
STA- 1.0(X)
-117-
Fii_ure 2A
AS-206 S-IVB RESTART ALTERNATE MISSION 14_ OPEIIATIONAL FLIGHT TRAJECTC_Y
H-I _IGINE THRUST DECAY
SOOlO0.
TNE
U
T
N
NI
TUD
E
* StSlSGC,.
6
&6-814 rESTART
i
i
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-118-
Figure 3A
AS-206 S-IVB RESTART ALTEmlATE KKSSIGN _/_ OFERATICRAL FLIGHT TRAJECTORY
J-2 _GINE THRUST BUILDt_, FIRST BUR_
N
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AS-2D6 S-IVB RESTART ALTERNATE MISSION _/V OPERATICfiAL FLIGHT TRAJECTORY
J-2 _GINE THRU3T DECAY, FIRST BUHN, _:_
J.
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- 1 2.0-
Figure 5A
AS-206 S-IYB RESTART ALTERNATE _STOH L/V (I_J_A?IOHALFLIGHT T_JECTO_J-2 _QI)O_ T_ST BUILDUP, SECOND BURN
FL|i_NT T| NI[4,4,SrcokDs
-121-
Figure 6A.
AS-206 S-IVB RESTART ALTEI_ATE MISSION L/V OPERATIONAL FLIGHT TRAJECTORY
• J-2 ENGINE THRUST DECAY, SECOND BURN
SGOGGG
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• -122-
l_p_e 7A
AS-206 $-IVB RESTART ALTERNATE MIS3ION _V OPERATIONAL FI_GHT TRAJECTORY
MEAN HEA_WJ_qD/TAILM_D PROFILEDEmmm - APRIL A_
8160OO
TiTU
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-_23-
APP_DIX B : "GU_T3_.NCE PIU_E'r'r_Nc, S t,
-I_4-
,Table IB
AS-206 S-IVB RESTART ALTERNATE MISSION L/V OPERATIONAL FLIGHT TRAJECTORYS-IB STAGE STEERING PROGRAM
For the time segment t - TI -<i0:Xy = O.Xz = O.
Xx = -0.314159 rad. (-18. degrees)
For the time segment i0< t - TI -_&3.:
Xy = AO + AlxT + A2xT 2 + A3X_
AO = .6A6A96 x lO-1 radians
A1 = -.5666A6 x 10-2 radians/second
A2 = -.801710 x i0-_ radians/second 2
A3 = °518111 x 10-6 radians/second3
×x = ×z = O.
For the time segment _3. < t - TI -<87.:
×y = BO + BIxT + B2xT2 + B3xT3
BO = .3_9258 x lO° radians
B1 = -.239a_8 x i0-1 radians/second
B2 = .291350 x 10-3 radians/seconds 2
B3 = -.179669 x 10-5 radians/second3
×x = ×z = O.
For the time segment 87. < t - TI _ 132.:
×y = CO + CIxT + C2xT 2 + C3x_
CO = .350808 x iO1 radians
C1 = -.108421 x i0° radians/second 2C2 = .937385 x 10-3 radians/second_
C3 = -.28626A x 10-5 radians/second _
×x = ×z = O.
For the time segment t - TI > 132.:
Xy = -1.O614721 radians
×x = ×z = O.
NOTE:
My:
T ___-
t:
TI:
Pitch attitude angle measured negative downrange frominertial vertical
t - TI + 1.803 G/4DTtime from GRR
time of liftoff (Time Base i), approximately 0.2 secondsafter first motion
1.803 GMDT: Bias to account for system delays.
-125-
Table 2]3
AS-206 S-IVB RESTART ALTerNATE MISSION E/V OPERATIONAL FLIGHT TRAJECTORYS-IB STAGE PITCH ATTITUDE CO_AND
FLIGHT _ :*PITCH ATTITUDE FLIGHT
_ fS_) CO_.AN.D,_ × c (DE(}) T_I_ (SEC)
O O..OOOO10 o.oooo12 -0.9692
-1.836316 -2.725918 -3.64132O -h.58OO
-5.5_O624 --6.522626 -7.5236
28 -8.5424
30 -9.578132 -10.62_34 -11.692836 -12.769538 -13.856840 -24.9533
42 -16.0581&A -17.1393
._6 -18.098548 -19.O697
50 -X_.027252 -_.975754 -21.920056 -22.8653
58 -23.816160 -24.7781
62 -25.75566& -26.7533
66 -27.7774
68 -28.83167O -_.9206
72 -31.0512
74 -32.2266
76 -33.451478 -34.7331
80 -36.0742
82m,86889O92949698
loo102lOh106108110112
116118120122
124126128130232132.25
IGM Initiation
* PITCH ATTITUDE
C_O_ND, X___)_
-37.4792-38.9564-40.5076
-41.7484-42.8309-43.8408
-44.7857-h5.6708--46.5065
-47.3OO5
-hS.0590
-48.791_-49.5053
-50.2081
-50.9081-51.6128
-52.3306
-53.0690
-53.8353-54.6392
-55.4868
-56.3856
-57.3464
-58.3741
-59.4762
-60.6646
-60.8179
-60.8179
* Xc is related to the Xy of Table IB by the following equation:
Xc = (t - TTTD) .X[i - X_(i - i) +Xy (i 1), whereC_DT
t = time from GRR (FLIGHT TIME +5 seconds)
TTTD = t of last Xy evaluation
Xyi = Xy evaluated at T
Xy (i- z) eval.ated at (z- 1 Gm T)CaMDT = LVDC casputation cycle = 0.75 seconds
-126-
o"
Table 3B
AS-206 S-IVB RESTART ALTERNATE MISSION L/V OPERATIONAL FLIGHT TRAJECTORYIGN PRESETTINGS
LVDC
SYMBOL
_n
Tli
T_
T 3
Vex&
Vex3
VT
XVT
YVT
ZVT
XVT
YVT
ZVT
ee
XVGT
e•
YVGT
_e
ZVGT
INITIAL
'VALUE UNIT_____S
17. sec
0.0 sec
3h9.5 sec
h73.0 sec
0.00 m/ssc
A132.00 m/sec
7783. 577 m/sec
6563365.0.0. mmm 1
O. _sec 1
O. m/sec l
7783.577 m/sec )
-9.256 m/sec _
O. m/sec 2
O. m/sec 2
DESCRIPTION
Time from time base 3 to initiate IGM guidance
Time to go for first IGM stage
Time to go for second IGM stage
Average value of m/m at initiation of second IGM
stage
Average exhaust velocity (go x Isp) for ist IGM
stage phase of flight
Average exhaust velocity (go x Isp) for 2nd IGM
stage phase of flight
Guidance Cutoff Signal (GCS) criteria. Terminal
velocity for IGM equations
Desired terminal position vector components inIGM coordinate system
Desired cutoff velocity components in IGM coordi-
nate system
Terminal gravitation vector components in IGMcoordinate system
-127-
"4
Table 3B(Cont 'd)
AS-206 S-IVB RESTART ALTERNATE MISSION L/V OPERATIONAL FLIGHT TRAJECTORYIGM PRESETTINGS
LVDC
SYMBCL
E
TRI
TR2
TR3
T2
ATN@_
INITIAL
VALUE UNITS
15. sec
3 • sec
1.8 N/D
Oe
Oe
200. sec
O. sec
R-ASTR sec
I. N/D
- .&26665Ol
+ .A951A778
+ .903o5328
-.A182953&
+.998381&3
-.56717968-.9OAAOO02
-.27976999
- .&2576733
N/A
Oe
API
AP2
AP3AP_AP5AP6
APTAP8
AP9
FLAG
E+OO TM
E-OI
E+00
E-02
E+00
E-OI
E+00
E-OI
E+OO,
sec
N/D
DESCRIPTIONS
Value of T3i to initiate IGM _V guidance
Value of T3i to freeze IGM (_)
Mission dependent constant multiplier for
terminal range angle equation
Mission dependent constants for N3 and
N& equations
Time to initiate thrust misalignmentcorrection
Terminal steering time argument
Nominal computation cycle length
ICM staging flag (Burn switch)
Transformation matrix from navigation
coordinate system to the (XA, Y&, Z_)
coordinate systemAz = 72.
@L = 28.531856
@N = I19.05&8
i = 31.61&3
Time from time base 3 to sample F/M
for IGM staging (Approximately 70 sec.
prior to nominal IGM staging)
Number of F/M decreases required for
IGM staging criteria
-128-
Table 3B(Cont 'd)
AS-206 S-IVB RESTAKT ALTERNATE MISSION L/V OPERATIONAL FLIGHT TRAJECTORYIGM PRESETTINGS
LVDC
SYMBOL
ACC
i0
AO
A1
PCO
T I0
CO
M02
M1
M3
ARTAU3
M03
M1
F1
F2
INITIAL
VALUE
N/A
NIA
N/A
N/A
N/A
N/A
N/A
N/A
N/A
N/A
1.O
120039.A
229'708.
20A6o&.
2850.81
UNITS
m/sec 2
sec
sec
N/D
sec
sec
sec
kg
kg/sec
kg/sec
N/O
kg
Ibs •
lbs.
k_/sec
DESCRIPTION
F/M comparison tolerance for IGM
staging
Constants for updating second stage
time-to-go for perturbed EMR shift time
Backup time for IGM staging
Constants for artificial T3 mode
Artificial T3 mode flag
Mass at J-2 start command minus mass to
be Jettisoned
Mass at first motion
S-IB average sea level longitudinal thrust,from first motion to IECO
S-IVB average first burn thrust, from 90%thrust to TI
S-IVB average second burn thrust fromTI to cutoff
Average S-IB flow rate, from first motionto IEC0
-129-
APPENDIX C : "TRAJECTORY LISTINGS, ENGLISH UNITS"
-130-
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DISTRIBUTION
W. H. Mann, Jr.
L. L. McNair
I-I/IB-E
R-AERO-P
(z)
(180 and 1 reproducible)
-174-
