I : iiC $E FiLE COPY · PDF fileNASA NASA CR-2501 0 I z:_iiC_$E FiLE COPY FLIGHT CONTROL SYSTEMS PROPERTIES AND PROBLEMS Volume II- Block Diagram Comp-endium Donald E. Johnston = Prepared

NASA NASA CR-2501

0

I

z

:_iiC_$E FiLECOPY

FLIGHT CONTROL SYSTEMS

PROPERTIES AND PROBLEMS

Volume II- Block Diagram Comp-endium

Donald E. Johnston

=

Prepared by

SYSTEMS TECHNOLOGY, INC.

Hawthorne, Calif. 90250

for Flight Research Centerr_'2.6_191ro

NATIONAL AERONAUTICS AND SPACE ADMINISTR_TIOH * WASHINGTON, D. C. • FEBRUARY 1975

https://ntrs.nasa.gov/search.jsp?R=19750009300 2018-05-15T12:44:56+00:00Z

1. Report No. -I 2. Government Accession No. 3.

INASA CR-2501

4. Title and Subtitle 5.

FLIGHT CONTROL SYSTEMS PROPERTIES AND PROBLEMS

Volume II -- Block Diagram Compendium 6.

7. Author(s) 8.

Donald E. Johnston

10.

9. Performing Organization Name and Address

Systems Technology, Inc. 11.Hawthorne, California 90250

12. Sponsoring Agency Name and Address

National Aeronautics and Space Administration

Washington, D.C. 20546

Reciplent's Catalog No.

=, L,

Report Date

February 1975

Performing Organization Code

H-860

Performing Organization Report No.

TR-1018-1

Work Unit No.

Contract or Grant No.

NAS 4-1881

"13. Type of Report and Period Covered

Contractor Report - Final

14. Sponsoring Agency Code

15, Supplementary Notes

NASA Technical Monitor: Herman A. Rediess, NASA Flight Research Center

16, Abstract

The purpose of this program was to document and pass

on experience to current and future generations of flight

control engineers, hopefully, to prevent costly rediscovery

of past mistakes and to stimulate trade studies between

possible competing mechanizational approaches.

The documentation is divided into two volumes. Vol-

ume I (NASA CR-2500) contains the technical discussion

while this volume is a compendium of stability augmenta-

tion system and autopilot block diagrams and descriptive

material for 48 different types of aircraft. These provide

a broad representation of the many mechanizational

approaches which have been employed in the past.

17. Key Words {Sugg_ted by Author(s))

Aircral't control systems

Systems design

18. Distribution Statement

Unclassified- Unlimited

Category: _dS, _

19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages

Unclassified Unclassified 149

22. Price*

$5.75

*For sale by the National Technical Information Service, Springfield, Virginia 22151

I. INTRODUCTION

II. BLOCK DIAGRAMS.

III. REFERENCES

TABLE OF CONTENTS

Pag.__e

I

2

139

iii

SECTIONI

INTRODUCTION

This volume contains a compendiumof 8ASand autopilot block diagramsfor some48 attack, bomber, cargo, drone, fighter, research, and transporttype aircraft. It also contains references to specific documentsfromwhich information was gleaned for this study.

This compendiumincorporates and expandsupon an earlier effort (Ref. 67)

initiated by the A-18 AerospaceControl and GuidanceSystemsCommitteeof theSociety of Automotive Engineers. It is by no meansa complete expositionof systemspast and present. There are manysystemsfor which no informa-tion was available, and there are others for which the information availablewas incomplete or conflicting, and therefore not included here.

An initial attempt wasmadeto put all block diagrams into a consistentformat which identified functional blocks and associated transfer charac-

teristics, functional switching, etc. However, it rapidly becameapparentthat such a task wasbeyondthe scope of this program. Therefore in mostinstances the diagramspresented here have been reproduced directly fromthe original documentslisted in the references. In all probabilitythey reflect but one version of systemswhich mayhave undergoneseveralmodifications. Consequently, additions or revisions are solicited fromthose whomakeuse of these volumes.

AIR_

A3J- I

A-4

A-7A

B-pC

B-98

B-66

XB-70

C-5A

KC- ]39

XC- 142A

E-1B

S- 2D/S- 2E

Regulus II

¢,-2C

BQ,M-34

MO,_I-74A

F3H

F-4

F-8D

F-14

F-86

F-89

F- IOOD/F

F- I01A

F- I01B

F-I02

F-I09A

F- 106

F-111

T-38

AVRO CF- I00

_ECTION II

_L0CK DIAGRAMS

2

Pages

4-8

9-11

12-14

19-19

20-29

3o

31-33

34-49

46

47-49

90-91

92-53

54

99-96

57-98

59-6O

61-63

64

69

66

67

68-69

7o-72

73

74-77

78

79-81

82-83

84-87

88

89

Ref. No.

9

I

9, I0

II, 32

67

12

16, 17, 19

67

18, 20

too

too

22

24, 31

25, 26, 33

27

67

34

3

37

38, 67

41, 42, 67

43, 67

43, 44, 67

49, 46

67

67

93-55

99

67

AIR_

Fiat G-91Viggen (AJ-37)VJI01-CM2-F2

X-15B-707DC-8L- 188

R/D SYSTEMSGESAC

HoneywellAdaptableSFCS

NASAF9F-2TWEADI

TWEADII

AVRO-707CLear Rate Integrating

9O91-9596

9798-1oo

101-103

I04-Io6

1o7-110

111-113

114-118

119-124

125-128

129-13o

131-134

135-137

138

Ref. No.

67

58

61

62

64, 69

67

81

67

88, 89

35

9O

69-73

74, 75

78

79

67

i .........

STICK

r ...... 1

MECHANICAL CONTROL _ SOLENOID L _ -- _ -._, . MECH_,NICAL FEEDBJ_CKr- - ! CLUTCH I

I I-..... .I __._

l l Aj,4S_rI.IIC't_ ACTUATOR

IUNC._E _ -1 ACIUATOR FEEDBACK

L (ELEC1RICAL ) eLECTRICAL)

M_CH TrIM SYNCHRO :

I $TORIr | JECTION

COMPENSATION I

AUTOFLIGHTCONTROL

i

ICOMPUTER

MECHANICAL FEEDBACK

AClUA, T(_

AND VALVES

ELECTRICAL

LATER._L TRIM

ACTIJ_TOR

HYD f DIFF. PRESS,. --)- BALANCER

IRANSDUC[R

SERIES (SERVO I

AJ_PLIFIERSERVO VALVE _ SERIES (SERVO]

ACTUATOR

- i S'ERIES ACTUA'TOR l _-

POSITION

| TRANSDUCER J

,_ MACH NO.TRANSDUCER

._,__..____j.I STAB POSITION lTRANSDUCER

t- PORT

-'STABILIZER

L I S F^C,I_ ACTUATO_ FTT_'_- ----_, l ,N_,VAtvES I jl _.k,

MECHANICAL FEEDE_AC ......

ELECIRICAL FEEDBACK __J

BLOGK DIAGRAM

A3J-I LONGITUDINAL CONTROL SYSTEM

LATERAL CONTROL

STICK F - -- "- -- "1 _,/MEC HANICAL FEEDBACK _ _,_

' ELECTRICAL

ROLL TRIM SWITCH

ON CONSOLE

q______j,wo

ROLL TRIM SWITCH

ON STICK

LWDt FRWC>

TRIM SELECTO_ SWITCH

ON FLIGHT CONTROL PANEL

LATERAL TRIM

BLOCK DIAGRAM, S

A3#-I LATERAL CONTROL SYSTEM

J......I GA'NI......f

o'_

_I SHAPINGGAtiN

_7 HOLD"e

Jhp L

I H£LD hp

PITCH

SYNCH.

FAST

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SLOW

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LIMITER

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SIN 0 TAN £)

° 1SIN _ TAN 0MFRS

Ah [ ADC

[

0

hp

BLOCK DIAGRAMLONGI]UDINAL

A3J-I AUTOMATIC FLIGHT CONTROL SYSTEM

't'+

SYNCH.

HOLDBANK

ROLL ISYNCH.

STEERING ERROR

SYNCH,

HOLDHEADING

GAIN

HEADING

SYNCH.

GAIN i

BANK ANGLE iSWITCHES

HOLD HEADING

° I0HOLD BANK

t

_ SHAPING

BLOCK DIAGRAM

LATERAL- DIRECTIONAL

NAV

SHAPING

LIMITER

AFCSENGAGED

HOLD

'1 HEADING

HOLD BANK

A3J-I AIJ.T+_LG FUGHT CONTROL SYSTEM

TO FLAP CONTROL SYSTEM ,,_/7_

v:_TIC_L ETA IIL|ZEII --7

!_'-WASHOUT "1

ACTUATC_"_ GY_O

:: I ! FEED_d_.CK POTENTiOMETEll .--_ _

..... A_,_l..l_litiE_. ...... .a |_CTRICAL F|iDIkkCK /_CHANICAL FEEDa,,_CK

BLOCK DIAGRAM

;.J t[ FEEL IIUNGEE "=1 /SYSTEM _ i_Zf|i_-Tr_ ....... "............. -'-'.'-:_..._,t.,_,m,.4_k

kJ "-PRE | EUA| IIEDUc|R (RE F) _-.-._, / _ [-'RATIO CHAN GER _] I l'kl_ ...... • "*-'q'_ _

!._k,._.j_ illrROM'--m.Illi_:_'--_.., II HIIHT,r

HIIIH'i \:. _rX__i.H_/

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•_-C_ECKVALV_ HYDRAULIC SCHEMATIC

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LEGEND

n Y _JI'.A_J;- tC /_

A3J-I DIRECTIONAL CONTROL SYSTEM

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STORES I

SWITCH I HIGH PASS

FILTER

ALT. o ITU_DE_

HOLD

ALT

I iNTEGRATORI I

STAN_

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o_H_

F4 (ZAS WrEGRATORSERVO

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FILTER

I

-ISWITCH

2A5

ELEVATOR SERVO AMP CURRENT

" I_ _,TCHT--I_ II __'T°"I I I i

TRIM TRIM HORIZ STAB-._PITCH LrJ TRANSFER HTRtMCONTROLI_HoRIZ'STA8' H I

'-[ 1 _'_ Ih II I I I I PITCHI, _111

i ' ,I,.A_)n"T_'Ol' '1'

[ GAIN I _ 5PEEDBRAKE r--- .......... "-'I, AJB-3 SYSTEM ,

ELEVATOR F3 (l_) I , om_u. ,"AMPLIFIERI L ........ .J

t L_;';_--_°] ":'SIN 8 RESOLVER I ' I eliB_. , '

Jl_ ......... Jl

I f"Tc" I COSe ] _-- _JATTITUOE - - .........

INTERLOCK

_,o i ITR_'_I

A-4 Elevator Channel

0

Headin_Synchronizer

Servo

CSS

Er_.

Stondby

A-5 Roll Channel

RUDDERBANDPASS

FILTER

RUDDERSERVO

AMPLIFIER DUAL INPUT _tVALVE

I

RUDDER

ACTUATOR

MECHANICAL

FOL LOW- UP

LOST MOTION

LINK

POSITION

TRANSMITTER

RUDDERPEDALS

OR TRIMPILOT

Fs (IAS)YAW RATE

GYRO

IIIII

_.J

AF --

A-4 Yaw Channel

i.,'r,c_'rO_T--'--" 1 zoo'."_ _" .......

-- I L._.. _ ,,#C_

I

pATC'O_

I "_'_#'l"°tlI _#lAy,_l

1

F;.ap .S'cJI S. JC'_

i _ F "t_l _'_:

Ii

I

/t l,"o

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I _r_

A-7A Pitch Axis

A-?A Roll Axis

rAW iC_A,vaIF,.-Isw :_s

AILE,_OAI UH TMU/.TI-

fOSITlO_lj lPLIER

Ot./A I.

_P

F'Dz UJu,I-UP

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#IAFOIVlFORFo_-uP

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A-7A Yaw Axis

l ] (s:_'l.e_is2._5o.62.5001 I

GAIN

SAS SERVOI. /_ [SCHEDULER

10.5

I I

• _ GAIN

SCREDULER

LATERAL ACCELERA.TTON

I ies 1"t!9 J

i CrT/SEC21 -[ACCELEROMrrER__

B-52H 1.0

AIRPLANE

EQUATIONS

OF MOTION | YAW RATE BS 695 J RATE GYRO

[ _DEG/szc) "1 e75o

I

f IMPACT

PRESSURE

II

_._ (VOLTS)d

ra!

]J

F .... J (VOLTS)

(VOLTS)

I SAS ELECTRONIC FILTER _.__

S2

(S + .033} (S o ,25) (S * "/)2

SAS ELECTROI_IC FILTER

S2

(S + .033) (S + 1.5) (S + I"l)3

B-52 Modified Yaw SA3 Block Diagram

k

(I_.)

MAllei POWER

ACTUATOR & ELEVATOR

7.395 X !0 T

(S ÷ Yt,6) (S 2 + I50S * '*5,350)

ELEVATOR B-52R

MOTION _ AIRPLANE

(DEG.) _ EQUATIONSOF MOTION

iI

I

II

I" ......... !IMPACT

| pRESSUREI

I

GAIN _

SCREDUL_

pITCH RATE

(BS 1327)w

(DEG/SEC)

RATE GYRO

6,750

$2_139S * 13,500

!SAS ELECTRONIC FILT]_ |

93'7.5 S 2 (S') * 79.1S * 12,800)

(S ° .15) (S * .25) (S + 150.) (S + 283.12 /

)

B-52 Modified Pitch SAS Block Diagram

15

c_

.250 v/_eu'sec.

l _ H _,_ F_RATE GYRO PR.E- AMP AMP- DEMOD : SW- MOD.

PRE-AMP

RATE GYRO

GAIN CONTROL

_°_w_ e"-]ENGAGE CRANK 1 SERVO DISP. __._ [TAP/"_ _ POSITION--_ _ _'_

DISP. FEEDBACK VCRANK POS.---_ ) _- GAIN TAP.

SYNCHRO "7" _ e3

H AMP-DEMOD _

MOD

CLUTCH

_ _ _ SERVOAMP" _ _'OLM_L_VRUP

_$, "----0-- .................. SERVO---_C--RATE GAIN "................ t_-_--- ITRIM METER]

1

B-52 Original Yaw Damper

PILOT

_q RUDDER IPEDALS

[YAW DAMPER I

-- -'_ ENGAGE l

/ SWITCH I

I

COMPASS

SPOILER MECHA_CALMODE

I-q FORCE

L_KWHEEL }

= l STEER_G --COUPLER

ROLLGYRO

BOOMSENSOR

i

l PITCHGYRO

- - L_K

I

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A UTO-

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_ REFUEL ARSS & LLCOUPLER ARSS & LL

/ ^u,o_ |I PITCH _L_

ELEVATOR MECHANICAL MODE

MA-2/A-14AUTOPILOTAMPLIFIER

!!!!

TRIM STABILIZER[MOTOR _ _

_--_ SERVO _m_ELEVATOP.S[

tII!I

...2

I YAW

RATE

GY RO

ELECTRO

MECHANICAL -_'_

YAW DAMPERCLUTCH

f

! ___DERI_RU_:_ER

B-52 Original AFCS

r _

I

I PII.,OTS PITCH 'tl _

TRANSDUCER

COPILOTS _ NULL

PRELOAD

CIRCUIT

AMP

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, ,,,

I TRANSDUCER

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CONTROL

BOEING __FORCE

SWITCHES

PITCHADJUST

OVER POWERCIRCUIT

THRESHOLD

CIRCUIT

GATE

NORMAL 1

ACCELEROMETER

I JI "G" GATE I

CIRCUIT

Ii I

Dis_ I II

A/R II ADD TO SERVO I

L/L DISP-'_'O'_ DISPLACEMENT I

___.._ L/L I CHANNELIII

. TO THRESHOLDCIRCUITRY

D TO OVERPOWERCIRCUITRY

STICK STEERING COUPLER AUTOPILOTAMPLIFIER

B-52 Longitudinal Control Wheel Steering

C_

PILOT'S ROLL

TRANSDUCER

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roo

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iACCELEROMETERI n-1ELEVATOR

I YAWRATEGYRO

I YAWRATE6YRO

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B&NSYSTEM

ELEVATORA/P RATIO

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B-58 Attitude _tabilization Mode

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AUGMENTATION

MODE

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ATTITUDESTABILIZATIONAND

OPTIONALMODES

B-58 Control Stick Steering Mode

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SYSTEM ]_t MACH I

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B-58 Constant Heading

i

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LATERALACCELER-OMETER

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CIVILNAVIOA-TIONALAIDS

SYSTEM

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I

LATERAL J

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J ELEVONACTUATOR

B-58 Automatic Glide Path Mode

OLOCALiZER

R EC...IV ER ,.J "_

STATI C _ ALTITUDE p'_"_PRESSURE CONTROL

IL$ "] = IGLIDE SLOPE

i POSITION i

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C_x'rA IN;_

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1_11o_ Q..4 CopJ.1o_

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-- +1 3s÷l _/s i

._ ,/d.:do_

XB-70 Yaw Axis Augmentation

6ms -+3'_.-

kJ44z-

PITCH

RATE

CYRO

Kql = 0.5

q

DEG/SEC

Kq2 = 2.0

I

I • 0.05s

I_I_I_AL &

AUTOPILOT

INPUTS

_ LIMIT I+_10 DEG I _ -11+0.1 s

ACTUATOR

DEUIEi

INBOARD

ELEVATOR

POSITION

SWITCH POSITION: 1

2

PITCH AUTOPILOT OFF

PITCH AUTOPILOT _NGAGED

C-5A Pitch Stability Augmentation System

ka4k_

I ROLL I

CM)C]

G

I+0.05s

DEG/SEC

_LL

A/P ON

+

SCHKDULED _)_GAIN, G

MANUAL &

AUTOPILOT

INPUTS

BENDING

FILTER

(1+0.06s) 2

+_3oD_

SAC

+

0.48

0.055

0

GAIN

SCHEDULE

, !

40 125

DYNAMIC PRESSURE, qc

ACTUATOR

1

I+0.25s

C-SA Roll Stability Augmentation System (SAS)

dsc uL lDEG. -I GAIN,GI

_ISCHEDULED I

DEG/SEC-I GAIN, G2 I+0.05s+

MANUAL &

AUTOPILOT

INPUTS

BENDING

FILTER

4 +

(1+o.o5_)2+20 DEG

+ ACTUATOR _R

1+0.2_s DEC.

0.34

G1

0.157

0.07

0

GAIN SCHEDULES

2.58G2

o.78

0.32I I i

40 10o 230

qc

, i J

4o 100 250

qc

C-5A Yaw Stability Augmentation System (SAS)

36

kJ4

70 19o

70 190AUTOTR]M

PITCH

TRIM

lq;OBDEO

C-gA Pitch Autopilot: Inner Loops

n. - F_ (50_)

GS - GLIDE SLOPE

RA -RADAR APPROACH

hFTRADAR ALT

PROP

LIMIT

I + .5S

'r- ) SEC PL _

.I SEC fflg-I__

Ih_IBITS NOSE-DOWN

INTEGRATION

(_ou.-o_)

C-5 A Pitch Autopilot: Radar Approach,

Glide Slope and Flare Modes

38

V'J_AV COMPU_"_

DEG

TERRAIN FOLLOWING

DEG

VSFI

IAS - kt I O. " "_)

INTEGRAL

PROPORTIONAL

0cDim

0¢DF_21

C-5A Pitch Autopilot: Veruav, Terrain Following

and Mach/IAS Modes

39

Integral

Proportional

Altitude Capture

VSFI

Altitude Hold

R.O.C.

CADC

Height

Error

ft/sec

h

f_

oI

_ Limiter I

7000 FPM

%dee

AC

Y@ _cJJ@

I

"°_'"° AM

%deg/sec

C-gA Pitch Autopilot: Altitude Capture andAltitude Hold Modes

4O

DEC,

DEC

I ATTSY_IC-_HCLD

HUBFCRCE

LB.

r--] FI_.PS •

o_ _o_ I ....

±2.7LB

DEADSPCT

0.19 DEG.

TH_HOLD

C-5 A Roll Autopilot: Inner Loops IncludingControl Wheel Steering

41

DEC

BEAMERROR

PRETRACK

INTEGRAL

+I ÷

_ LIMITER _ .

+ ++I +45 DEC, _e

COURSE CUT

PROPORTIONAL

DEG

y/e DEG

COURSE ERROR

(SINE FUNCTION)

SUB -MODE

ENTRY

CAPTURE

PRE-TRACK

TRACK

VOR,

TACAN _ 62 NM

5.0 DEG

2. I DEG

1.2 DEG

TACAN > 62 NM

5.4 NM

2.3]_

1,3 ]_

C-5 A Roll Autopilot: V0R and TACAN Modes

42

CTDI

NAUTIC_.LMILES

_/e DEG

TRACKANGLE

ERROR (TAE).

SINE FUNCTION.

CK

I I I INTEGRAL

I

I _ qc

, l,° i•4S _ I 'I,

l qc PROPORTIONAL

SUB-MODE

ENTRY

CAPTURE

TRACK

CROSS-TRACK

DEVIATION (CTD)

5.8 NM

0.4NM

_ DEG.

C-SA Roll Autopilot: Courseline and Air-Drop Modes

43

DEG

ROLL

ANGLE

I "--_'[ i+1'6s" ]

LAGGED ROLL

INTEGRAL

_5.631

AMPLITUDE SUB-

LIMIT MODE

25 DEG CAP, TRK

7.5 D_ GSC

ERROI

DEG

I+O. 5s

+ . I-i'"'i _o '! _.sY-oi_f.

1 + 478 TRK

T - 6.7 SEC RO- 0 SEC O_-_i-_ER

++ D_

,.%GsC & _-A _ Rc

- _C

)+

RA

CAP CAPTURE

TRK TRACK

GSC GLIDESLOPE CAPTURE

RA RUNWAY ALIGN

RO ROLL-OUT

SUB MODE

ENTRY

2.0 DEG

0.67 DEG

20 FT hges rTOUCHDOWN

C-5A Roll Autopilot: Localizer Mode, Including Autoland

44

k_

PITCH

AUTOPII_

BG 489 B

*FCS

CONTROL

S'*qTCHI/;G $IG.qAL )'(_ FlaRE RETARD _0_g@_D

DIRECT THRO_fLE MODE CO:,L'#L%IFDS

÷

ltA_t

÷

w

t _

C-gA Autothrottle Analtyical Diagram

_e -_ AI RFRA_J'E

E

kutomatic Trim workl from different|a,servo ¢|utch current.

_M

Ah

$4-

KC-135 Pitch Diagram

AIRFRANE --_

gr _[ ax

E8

1.4.'/S,¢ L__,

Llmff J I

/

H5 Heading 5e|ect

TC Turn _OemandL Locsllzer

6

KC-135 Lateral-Directional Axis Diagram

46

III

II]!

:1IJ

Coa_.rol_c_

PcverControl

XC-142A Pitch Control System Block Diagram

CO

XC-142A Roll and Yaw Control System Block Diagram

$-

kOGOLI4etI__rs

_v_r_ (_)

I

I

Tlxr_ .-_leDiac_o_ct

Feel I_o_t _ogA_tu_tor

I --

I

r

Tea ".J_x-'L_

Tea_T_ T_

I

XC-14_A Collective-Throttle System Block Diagram

o

AIRCRAFT

I

_J CONTROL Il WHEEL I

/ PITCH I r--I i

/ FORCE _--_ qc I'-)l

/TRANSDUCERI LTJ I

J

._[ ROLL IATTITUDE I

"I ALTITUDE ___.CONTROL

-I P'TCHIATTITUDE

EGI56A3 I _-AMPLIFIER LAG

6AIA. I0

. J uP i"[ELEVATORI

o

ALTITUDE

ENGAGE

.__._._EGI56A4_

DEMODULATOR_ "'6AIA9 /

HIPASS BYPASS

-)l EG156A; =' t_1NTEGRATOR

,, 6AIA6

J BANK }___"ICOMPENSATION

EGI55A4

INTEGRATOR6AIA7

I 1

EGI55A3 IAMPLIFIER I

6ALAS I

EGI55A3

PRE-AMPLIFIER

6AIA4

I

I SERVO I I

EGI79AI /FEEDBACKI 'ISERVO L_JELEVATORLJ

AMPLIFIERI "I SERVO I

6ALAS I _'AI;_L'_ E L I

ALTITUDE

ENGAGEo

I

K DENOTES A MULTIPLIER CONSTANT

qc DENOTES AIRSPEED SCHEDULING

CSS DENOTES CONTROL STICK STEERING

EG156A4 }

DEMODULATOR I6AIA3 I /

DISENGAGE /382 I CSS EGIBOA4 II

-ISIGNAL CONTROL I_---o-_ _--" AMPLIFIERp "--J

L 6A,A2 j? 6AIA,/_7 ENGAGE

E-IB Pitch Axis

I

n,,,Iv) l,,g _,)

w_

m

I

1

W W

, ,

4_

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I ooz_-,,'o._, _z; JI

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I

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(" WHEEL I

PITCHI I----I IFORCE _ qc _

TRANSDUCERI L._ I

I

ATTITUDE

._ ALTITUDECONTROL

I_I APN

117

._ PITCH

ATTITUDE

m

AMPLIFIER LAG

6AIAIO

_ J uP I

I iELEVATOR[

L_J SANK]"[ COMPENSATION /

SCHEDULING

,, qc | ALTITUDE

ENGAGE

LIMIT

ALTITUDEMONITOR

I

__._ EGI56A4 I

DEMODULATORr(-6AIA9 ,/

HI PASS BYPASS

EGI56A2INTEGRATOR

6AIA6

6AIA8 I

I SCHEDULING°° IT

I SERVO

|FEEDBACK

EG,SSA31EG,79A,I IPRE- I SERVO I JELEVATOR

[-_--'IAMPLIFIER IAMPLIFIER[ "1 SERVO

I I 6A,A41 6AIA51 '

ALTITUDE

ENGAGE 0

INTEGRATOR6AIA7

EG,56A"IDEMODULATORk

6AIA3 I.... D IScEsNsGA GE

382EGI8OA4

AMPLIFIER6AIAI

-3

K DENOTES A MULTIPLIER CONSTANT

qc DENOTES AIRSPEED SCHEDULING

_ENGAGE CSS DENOTES CONTROL STICK STEERING

S-2D/S-2E Pitch Axis

(---t-- "1., co.-_.o,_I _ I s_.voI ',WHEEL _"

I A EGI56A4 .I EGI55A3 EGI79AI 1ROLL EG 56 3 CS H EGI55A3S SERVO IGH

=,RANSDUCERJ= OA3A,FAGjIDEMO_TORICASSI _3A7/ -_"AMPL'F'ER,A3A.,AMPL,F,ERoA3A,,ER._"ojAI

C . HEADINGR CONTROLA

T

i._ ROLLI ATTITUDE

iI

.__" RATE

. I EG'56A31---*(_ DEMODULATOR CSSDENOTESCONTROLSTICK_' [ 6A3A6 HEADING (_ STEERING

•_ DEMODULATOR

T I 6A3A3

II 9373B2 IIEG,BOA4 ,SENGAGE.CSS.SIGNAL _ HEADING_-_AMPLIFIER

: "/ CONTROL i i 6A3AII 6A3A2 $ ENGAGE

E- 1B Roll Axis

.jCONT,OLI . IsE,voI:WHEEL 1 I I" ' I . IFEEDBACKI ;I,,, "ROLL EGI56A3 CSS S ERVO HIGH EGI55A3 II /FORCE DEMODULATOR,. IAMPLIFIER.

PRE- AILERONL_ DEMODULATOR PASS AMPLIFIER AMPLIFIER SERVO J

TRANSDUCER 6A3A9 6A3A8 J I ] 6A3A7 / 6A3A4 6A3A5

CONTROL EGI56A3 qc DENOTES AIRSPEED SCHEDULING

6A3A6 HEADING STEERING

._ EGI56A4 /H

. ROLL DEMODULATOR

ATTITUDE 6A3A3

937382 ___ EMGIBOA4 DISENGAGE, CSS,

t SIGNAL A PLIFIERj _7 EEADING

• ROLL CONTROL

RATE 6A3A2 [ 6A3AI NGAGE._=

S-2D/S-2E Roll Axis

_3

STABILI;ZATIONRACK

÷L_2:/::,.

STABILIT.ATION RACK

F--G--L__F-_--P_

FL"--L_........

ROLLG)'R---'_I STABILIZATION

F]-:222 .......

RACK

!

L_$'t

Regulus II Lot I Autopilo,t

k.,TI't.J'l

i i.

MODE

! GT_IDE _TCHLgG! _,0,._"_ & AL2ITUDE_-- PRiG

c

i-i !. e°'-"A .I i_

1 MODE R .I _,x-_ _, t i G ._o._1___%

1

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/ I _T.ZO ._.',_Z,_

, _, i _ _----_!' "v'z_ _

° ....._'-_ ....'_'_ 7 ,_/'i'iX!_ .

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! _, _'tS'_ . o . G- 2iP' c O,'_#_h"DiiII , ,

t ....... • ....

i

ELE-

i

1__..t

Q-2C Longitudinal Control System

x_

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s_o

!

I !

Q-2C Roll Control System

I

Launch

Condition

Bias

Scheduled

_b=f(h)

I K_s I(s+40)(s+lO0) _

Derived Rote

'+ _,_+ _ 8 (V.G.)

Fitter AltCont. _'h

/

Rlter

Is+lO

IAScuo.

Pitot- Static

System

I-_'uS+ I

IAS/qcPOT

BqM-3h Pitch Axis

co

Der.Head.

--IAS

_I Actuator A/F (V.G.)

Derived Rate

s(s+ 401(s + I00)

Is_2 l-

+

B_,[-34 Roll Axis

kO

_.'._._,,""_._1 )

MQM-74A Elevator Control System

o

VO _.'T'$

_l '

..._ t._ _,

_'e_ _ _T

J

MQM-74A Aileron Control System

F3H PITCH C}L_NNEL

O_ro

c,,,y Po Ce_ANt,,_"

VE',PT/ £F_,e

3[,0 _e'&

I T'RIM10 X)EG1_ ,,J 0.35

l r li,÷o._si

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CAHClELL_I_ SERIE_ RUE_D_'R _UDD_,_

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F3H YAW CHA_L

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PICKUP

TRANSDUCER

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IIII AN/AJB -3A F-4B

i INS _-411

I

I

! I H[AD'NGI I ROLL I t

I YiH_I lI I

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I L____J

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I" ..... JI!

I It- ..... -IGAIN (IASt)

I i ' C!IANC_._tR " ' I

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CONTROL AMI_tF _R

PITCt_

C A,_CE It. [R

AIIENuAIOR

I PI ICll I

$ _'NCHIiO-

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CIRCUIT

I GAIN (Ck: f ) L

CHANGER

L ..... J

A_S

28 vOt.TS DC

IN .t.r C S

MC,'>! _No C'_ ITHIN C'_,

|O _G _.IMITS

r F

IOttOW-UP F

SVNCHI_O-

NI._ ING

CIRCUIT

, t r ]I • 2 I/2 LB _ AUTOMATfC

- ; FOIEE PIT CPI _' R _h'_ I

LI-INK SWITCH I-' .... "l CIRCUI,'_, I

.__T--__J lj ...... J STA_ lI.A' OR /""_

I

' i l_..... "II

-- .... T -- -- J" ---1

I t o-.'._,lo,_ :

I PAqAtLEL I CYLIh#[_ER _'* .... _

OPt P_T ION I I

I t. .... j .... J/ STA31LA TOR POWER

.__.J CONIIK_L CYLI_._ R

I. THO_E ITEMS SHCJ_VN _Y DUllED LIN_S AR_ NOT COMPON-

ENTS OF TH1E AN/ASA-32H.

2. TH_ ENI"IR_ DIAGRAM USED IN AFCS MO0{. TH[ I_MS WITH

SHADED OUTLINE _ UTILIZED IN STAB-AUG MODE.

PITCH CHANNEL

:::!::!_!_!!:Z!i`_L:_!::;!:::i_::!:!!:1:_(_.!::_::i:i:_!¢`_L_`_i:_`:_i:_:_:_`_:B?_:_<_$`_!_:_`_3!_:i:_!_$_:i:i:!:_@_#_:_ ' ,._^ ._.. ,,._.t..,..,..'...,_...._._ ........... .._:..,...,,_.,..,_.,,.:-_.,_.,..+¢_,..-..>.._>.,:P_._.>, _.._. .,_._._._ ........ ..... :....,.:,.,..,., ,,, > .......

ROLL CHANNEL ,_'G_T

CONTROl. AMPI.IFIER r OA_ 1 SPCIt-_¢_ ['T'_ Je"'i7, SIAR_ .D . ! ,J / I I

_ STASOA:'_ I i i LATC-;_ILSEII_S _--'J"---1 F:_,',_K l / --t/ /

SI_VO I I , S_vO t CY_zD_ _

AT:£_- F "'PL'"" L'J I i. ....... ._ L..... ._ ......

l i f "_T" _'--'_ \ _\\" L---I s;_,_< t ----_;_\\ \

LEFT

CONTROL AMPLIFIERYAW CHAINNEL

RUDDE"t _Jb_[ R POW_

,!"'";"'! t L- 'A;V

RA_E Iii

• IL_TERM_ __;

ACC C _.r- RO.vF. T'c. R .j Y_w

CANCF.LLIR

Leon- Lo_

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L.._J T,,

T_ i _1_ ..... ii ii ill ill i

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ROLL A"XIS _2AM£ER

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.... I

ROLL t:2,A'TE COMMAND AUGI_rr,.N3"gR.

o%c_

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YAW P_M_&

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F-14

F-86 Pitch-up Preventer

E_7

/

TTi m

8+!

F-89 Sideslip Stability Augmenter

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®

J-ZCOMPASS

SYSTEM

I LS

LOCALIZERRECEIVER

YAW RATE i

GYRO |

I ROLLi,----E,I IDIRECTIONAL h I TR!M

cTUTR_0L ROGL_ %AT__:)" ]

COUPLER |--

ILS I IGLIDE SLOPE II

GLIOESLO_:_ CO_,_LERhRECE'VERI I_.G,"O3'_A-,

PITCH tCONTROL

(FC)

i HEADING ;TRIM

(FC)

IP,TCHRATEiGYRO |

_t

,TO RUDDER

CABLES

.tFC) INDICATES BLOCK FUNCTIONS WHICH ARE PART OF THE FLIGHT CONTROLLER - WG187.B-1

SH,A, DED BLOCKS INDICATE AUTOMATIC GAIN CONTROL FUNCTIONS OF THE AIRSPEED COIVlPENSATOR - PG70078-.1

f (q) INDICATES GAIN IS VARIED AS A FUNCTION OF" DIFFERENTIAL PRESSURE

f ('rAS} INDICATES G_.IN IS VARIED AS A FUNCTION OF TRUE AIR ._PEED

(_ SYMBOL INDICATES SIGNAL SUMMING

/I SERVO I [AILERONill

_ AMPLIFIER _ SERVO I'_TO AILERON

CABLES

CAGEABLE I_

VERTICAL t . _ , .I GYR0 _ i I

JGL_L_.44A__JI! . i.._ _----.._ I SERV0 II [ELEVATOR I / Ir, _ AMPL{FIER _ SERv0

" _ I RGTO64A-I i_ - I MG7OOIA-20B I

L I ? L,.. _ '/

- ISYNCHRONIZERL.__J

j_' TRIMINTERRUPTER

SG3A- I

TO ELEVATOR

CABLES

iF_c._SENSING_SWITCHES IN"1ELEVATOR "FEE',"

I SYSTEM

L " .EVATOR• -_ ACTUA'_OR

b

F-89 Autopilot

-8

j/_ OltS.N _I[N AUIOPILOI IS [NGAGI.D.

j_ _OS(0 W_N _EADI_ C_MmOL IS[_G_(D IX(IF? WH(N MACH CON-

1ROt IS AI.SO (kGAGI.D.

A CLO$[D 10 A W',4114MACH CO_II_

I$ (_._,,l.O, 10 II m4114 N.1 CON-

IIKX 15 [kT, AGED.

Z_ CLOS[D 10 | WH[ll ALT COMIICL I$

INIGAGI+O+l/_ CLOSED _ At*lO LAIS I_+llW.

,/_ CLOSI'D 10 A ON AUIO-IADS IIU_IN,10 f ON ALeIO-LAIIS PULL+I_.

CLO$[D 10 A ON AUtO-LABS PIJU.-UP.10 I licit4 R01L-OUT lliLAY IS [kEII-

GIZ[D.

A CJ+OSED WHEN kUIOPILm IS 0IS(M*

G_t,,[D. WH[N IIAMK AMG£..[ (XCEDS

60O, WH(t+ P11C14 AI_L[ (XC._S

S_. WH[N MACH OR ALl COk']iOL I$

[_,AG[D, WP(l_ C$S IS OI_IIAT[.O

AND Dl_ltdG AUIO-LAi$ PULL-U/'.

d_ CLOUD 10 II WH(_ 14ikCit OI ALlCONTROL IS [N(,.AG[D. _41GM GAIN

ON VUOCIIY FUDIIACI( CAU.T_S MO-

TOQ 10 IIU_ Wiry SLOWLY |1415 IS

[OiilVlliflll 10 A HIC_I-FA$$ N[I'-

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OPlll li_[tl AOIOPltOi I$ OISili-

G_(0. WH[_ lIAr( _ [XC(ED$

iO O. WHEN PIICH ANG_ [XP.I(O$

_+ D_14G AUTO-LAI$ P_l-UP Akll

w_14 C$S 15 OP'IPA_D

CLOSED vw(14 G$$ I$ OP(llAI_+

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J_{)N¢I CUQ AI ION, I

CIOSIS 4 $ $IC_$ Nr'_l LAIS PUtt-

UP SIARI$+ OP|m WH[N AIRC_

IIt_CP($ A_d(,L,t _ _LI. s{'rlING ON

V£ciC,q GY;'01114tS N[TVeO_K IS NOt

I_/CLUD(D 114 PHAS[ II GoMrI'GUI_A -

TI+ON.i

_ IklOICARS GAIN SCli[DIIL[O AS AFUNCIIOII OF AIilSP([D.

r---] ik'_lCM[s GAIN scHr_UL[I) AS A |U14L'r ION 0r Mk_H IlUMIOI.. t

_ II_I4PJOI(S C_dl,lll ;$OI[OU_D AS A IrUNO+ION OF NI I$,11_._ AND MACH IIIMI_.

A

I

R

C

R

A

F

T

PITCH CHANNEL

F-tO0 D/F Autopilot

,, >

&A&

A

AA

NOT{S:

,/_ OPEN Wt4[N AUIOPILOI IS rNGACED.

L_ CLOSED WHEN RO(L-OUT RELAY IS AUTO-LAI$EN[I_I?TO AT END OF

PULL -UP.

//_ CLOSED DURING AUTO-LABS PUL.L-UtL

_ C_OS[D DURING AUTO.LABS PULL-LPP.

CLOS[D 10 POSIIlON !1 WHEN ROLL.OUT RnAy '1S [NERIGIZEO.

OP[N WHEN ROLL-OUI RELAY IS |NER{;IZED.

CLOSED 10 POSITION A DURING LABS RUN-IN, CLOS[D 1"0 POSITION II

DUPING AUTO.LAIR5 PULL-UP.

OPEN W'_'W AUIOPlE01 1S DISENGAGED, WHEN BANK ANGLE [XCIIDS

60o, WH[N PITCH ANGL| [XCE[DS ._,0O, WHEN CSS IS OPERATED AND

DURING AUTO-_.ABS PULL-UP.

OPEN WHEN HtADING CO_,'IROL IS ENGAGED IHEADING CO_IROL IS IN-

GAG[I) _'HEN BANK ANCL[ IS L(SS IHAN T-|120 IF C$S IS NOI OP{RAT[ I_,

RI1CH AhGLE IS LESS 1HAN _ AND AU10-LABS IS NOT [NGAGED.I

CLOSED W_N/_ IS OPEN - ALSO CLOS,[D WHEN HIA01NG CON1ROL IS

E_,GAC.f D

CLOSED 10 B WHEN fl[ADING CONTROL iS (NGAG[D. It_[[ HOlE 9.1

CLOS_D I0 A _lt[N HEADING CONTROL IS NOT ENGAGED.

CSS DINOT[S CONTROL SLICK STEERING.

TWO STICKS AND INDICATORS ONF-IOOF CO/_IGURATION

INOJCAI[S GAIN SCHEDULED AS A FuNCIION OF AIRSPED,

I ROLL OUT I I RATE _ *',NO /I COMMAND J ,, GYRO ; -I DISCR/

" ROLL AILERON R,ooE, ["E"oR l o' AU*O ,LO, TR,MGENTERINGI I,_ I _R,_ II '_'ULSE_AO OSTj Zm | , ,

TOPI T [_(_, -- __AUTOPILOT_ LO

" - F _1_ _1_ _ _K ; C I S E.R_.O I I SERVO ] I I ACTUATOR I

, ,, T T r__j- -, [,_,_, _ jl L --

I I _ _---.---tFOR ASYMMETRICAL_ --

STORES /

; [ COMPENSATION j AUTOPILOT

, Sr/,_SITIVE _ • p...i_1 < F'''--_ . [' PHASE i. ,<'x_ I u,4

_R[.CTIFIER COM _::. J

_ COMPASS/ F COMPASSI, ]

SYNC AMPL p-_l SYNCHRONIZER I

AND MOTOR | /S_NCHRO RO'IORJA_

I HEADING

SELECT

LEAD

NETWORK

A

I

R

c

R

F!

T

_ ,R©,,. L IR_TE

{. GYRO j L---..

ROLL CHANN_.,L

F-IO0 D/F Autopilot

--4

OS_RT STROKEr-'--'---'-'l

I I s£Rvo FE_=OSACK J

""J_ piTCH RATE

%2:-$;

'..c'.E,ST_'C/<(.AgO',,T36.5_ F[ET I LIMITS

I_._ ICAT_.SGAI_ S_"_UL[D AS A _:LI_ICTIO_I01:AIRSPEED,

P I"TCH DAMPER

m

RCRAFT

SENVO _ _ I-1"H CO"T_OL ------AvP___..J I S_S_M

__ s_Rvo I

_ NONUNE.&R _. ! Y,W RATIE I.

OPEN WHENRUDDE_PT.D/d.SARE PRESSED.

L_ PHASE I CO:qF|GURAT|ON

//_ OMIT BLOCKFOE PHASE I CONFIGURATION

,_ INO'ICATE_GAIN _,E'DUI._ AS AFLIk_T,iOMOF AIRSPEED.

'_ IMOICATESGAIN$CHEDt.E,ED/kS AFUNCTIONOFAIrItSPEEOANDMACH _M_ER.

YAW DAMPE_

F- I00 D/F Autop__lot

g,__IO'RECTIONALL___COUPLERI"

I

ROLL IRATEGYRO

]VERT'cALLGYRO

_ _ ISTAeiCATORIIsTAemLAT°RIIHYDRAULIC/,---,'(X_)--,_O(pI SeJwa I---ff SERVO _ SYSTErXI--------'

r ,.,,_.-----ilI ' r:.-_l

_'°"_"°"_<_/'''''°_':_'°"11o_,.,,,_ t_t o,,,o,T i "" " I G,i'i't_,I

,,,T<:,, ,& I"':RT'CALL

c.._OL :1 --' P,TC,IRATE I'

L CYRO I

(_INBICATES SIGNAL SUMMING

[] INDICATES GAIN VARIED AS A FUNCTION OF INDICATED AIR SPE,ED

[] INDICATES lAIN VARIED AS A FUNCTION OF TRUE AIR SPEED

(FCilHDICATES PART OF FLIGHT CONTROLLER

DASHED LINE ENCLOF, ES DAMPER CONFIGURATION BLOCK_

A

I

R

C

R

A

F

T

F-IOIA Aut opilot

73

-4

STABT.LATOR BRIDGE CIRCUIT

NOTES:

I P_TCH ]CONTROL

I_!",ICK STEERING

'iSERVOIAMPLIF:ER 1

CLOSED TO B WHEN MACH HOLD IS

ENGAGED AND CLOSED TO A WHEN

ALTIIUDE HOLD ':SENGAGED

CLOSED TO D WHEN FIRE CONTROL

MODE IS ENGAGED

OPEN FOR ATTITUDE HOLD

OPEN FOR CONTROL STI CK STEER-

ING AND FIRE CONTROL

CLOSED FOR PITCH ATTITUDE

HOLD

OPEN FGR MACH HOLD

CLOSED FOR ALTITUDE HOLD

CLOSED FOR BEAM GUI DANCE

CLOSED FOR CONTROL STI CK STEER-

ING

TA SCHEDULING

MACH SCHEDULING

_ AIRSPEED SCHEDULING

__J_. ALTITUDE SCHEDULING

F-IOIB Autopilot

VERTICALGYROT?

KOiES:

AA

A

A

AA

U®

OPEN WHENAUIOPILOT IS ENGAGED.

OPEN FOR CONIROL STICK STTERII4GMODE.

SWITCH POSITION SHOWNFOP,BEAMGUI DANCEMODE.

CLOSED AFTER AUTOPILOT IS EN-

GAGED.

CLOSEDFOR FI RE CONTROLMODL

OPEN FORFIRE CONIROL MODE.

GAIN SrHEBU! ED AS A FUI_CIION GFAIRSPEED.

INDICA_S SUMMING POINT.

A

AII,E._ON BRIDOE CIRCUIT

F-IOIB Autopilot

75

1

RUDDERSERVO

AMPLIFIER

HIGH-PASSNETWORK

LAGNETWORK

SERVO FEEDBACK

PRE-ENGAG i

TRIM

SERVO

IRUDDER

CONTROL --SYSTEM

/YAW RATE __ _

GYRO F

POSITION _ _TRANSMITTER

ROLL RATE J_.GYRO -- -

LAGNETWORK

NOTE:

A THIS LOOP IS NOT IN CIRCUIT WHEN DAMPEROR AUTOPILOT IS ENGAGED.

LAG

NETWORK

]A CELEROME F--RUDDER TRIM

ADJUST

INDICATES GAIN SCHEDULED AS FUNCTION OF AIRSPEED.

INDICATES GAIN SCHEDULED ._,S FUNCTION OF M._GH NU_,,',BER,

RUDDE_ BRIDGE CIRCUIT

AIRORAFT

F-101B Autopilot

76

I!

5_s_e_

PARALLEL 6ERVO

II _=orceSwi_'ch

?

F-IOIB Stick Pusher

V-102 Y_W DA_PE_

F--IOZ P_TC_4 I)AkSPEIK

"T$m

Ts+t

F-102

78

-q_0

F-]OpA PITCH CHANNEL

F- ]O_A RO.IiL C_NNEL

O_

I I

I__,.o.oTs_I

,R/R f I_'I_,,nE

F- I05A YAW CHANNEL

CANCEL Z E_'

KcS

.><---(,÷,.,_s)

6 YRO

_z_ zA rE,_'A i.

Dg- sup R,_7"_"

I

_ I:#!

Coro

AI: C6CMoxs.)

J

I.A,T,Sl.Er I,?.ALTO ._

ATTACK l

iAa L AS ii

MANUAL IViOD_} T)ITCH _A_P{:_ /v}ODE A_JD. A[:C_ [AO'_{_

] t_u.iCOMUMI_

!PtTC. __

----!

,,Arc8

AMPL I

[L i:rT R K:/_L I:'I[{"D_ACK

I

I

[ _:_,L 1C_ _ I

M[CI.JA I,PiCA(, _ I_ [" _ _I_CIC

l AILERON !_

/'p_Lo'r'S'_\t_P,)T_,J

•,l_.ER0hli,_,'_,:_:,{"_o$ jL____ i

I!W.,'I_._. .... II I IELEVON i I

_L_

]-A(C$

F-f06

(30k_

|tJpUT_.')

1

_ P.UDDEe. _ RILR_

f 1

FbT

c_,Noc_ j

t=E£ I,.

I I a_. &_R. D_Ta

L_ _.J eo_ Pu're_c

F-_o6

Go

!

F-I 1 1 Pitch Channel Functional Diagram

CO

....... J

F-I 11 Roll Channel Functional Diagram

(30O'_

Ay

LD6 GEAI:_

ONLLDGC_AR

YAW I_T

II

L

S'_T EM C,tdNS

5--_: ,_ "_/_c_c¥

=32.2

_-_-17_'".c_'_"/'_P

YAW CHANNELFUNCTIONAL DIAGRAM

F-I 1 1 Yaw Channel Functional Diagram

Co

PILOT INPUT

{

SENSORS

CO>LMAND

AUGMENTATION

DYNAMI CS

MODEL STRUCTURAL

FI LTE R __ GAINCHANGER

PREFILTER

ZERO CROSSING

DETECTOR INTEGP,ATOR I

AERODYNA>Ff CS

--m- LIN]<AGE _-<'_---¢_

DYNANiCS

F-I I I Adaptive Principle

CALIBRATIONMODULE

_,.-==_--_TOPRE-Ak',PL(FUNCTIONAL)TOFOLLOW-UPPOTENTIOMETERCFAIL-SAFE)

BALANCE

r'SHAPING AND TRACING 1

I MODULE 1""-. _ I'F-- l_.J...._J AIRSPEED• l JI"_ I IJH_;AM_'_ I COMPENSATORI I DEMODULATOR I I / _ . I

-:-N AND I _ I ==1p,TOTII MODULATOR I /" ! l=_ STATIC

I --'T'--'_-- I RUDDERI | J l i I Traml I I IFA'L-SAFEI ! '' i I I"N_;_O"_'I' _I P,LOT_L--, ! I I I _l CONTROLI----

l"ll_V 400 CPS

STABILTY l

AUGMENTER IACTUATOR

IFOLLOW-UP

POTENTIOME TER

l MODULE

IIII

I

L_

SERVO

AMPLIFIER

MODULE

II POWER SUPPLY I I _

VALVE DRIVE AND

QUADRATURE

REJECTIONNETWORK

1SUPPLY

R£G B.I-TO MODULES

44V DCTO PILOT'S CONTROL

AND FAIL-SAFE

I,'I_l-' I15V 400 CPS

I II_V 4.00 CPS

L, ........

! J ..... HYDRAULIC J:::::=t 5HU,TO; F L.. / SERVO ..... VALVE l

i -- :_---_ J SYSTEM

PlLOT'SIFLIGH T i::]

........ CONTROL I:pUT ........ .......... _ I

T-38 Stability Augmentation System

88

o:)',,D

IFI_ E

CO_4PU*'ER f ! CCUPt__q ! PITCM

J - Z COMPASS" F._ PJIF'Ec'rlONAI'. _

A_::A OP ILS ! I

LCJCAUZE_ I--- I_ A_D IR_CE|VEm | -- S-'A e ILI_TICIN r

I | rll?E .... _ f|q)

; I ÷.'_1÷,_11

L__ ;,_I --l

AMPLIFIER ¢rVOOE-R

flq)

[........L._ UN,T j

I

I

i L.I t A T,Too ---n'[ I J I I

_'ECE IVER | I .... " / , / _ ,_

...... _J ,, / ;

I ,i,:. ] L[ ii CO':_:OL I

NOTES'-

DOTTLE0 LINCg INO_-._TIE S'LOCKS, TO BE INSTALLED IN _ _RE.

're INDICAT{_ BLOCKS" THAT ARE PART OF THE I_I.IGL.rT CONTROLI.£q,

_PJ"/7_ Sk&_Eo 13(.0CKS" It_UICATIE AUTOMATIC GAIN CONTROL._

I_ THE AIC_E_'.D COMmENSATOm

f Iq I INDICATES" GAIN IS, VARIED AS" A _'-U_K:TIO_I OF' _IF'FERIENllJllI. PI_I_JSI.I_E.

F ICAt.

e(q)

-, ]TO

l AMPLIFIER E_.EVAT

[ J;;%. _. t

I TRIM E_ ¢-VATOR

ACTUATOR T_IM C._G I,,_ _

AVRO CF- I00 Autopilot

_J !_

05s+ I I.__.__J-

ROTE:

There is no PitchAxis in this auto-pilot.

FIAT G-91 Lateral Diagram

9o

x.o

BEEPTRIM _ TRIM

COMMAND ._ MOTOR

r"- _ -J_ _ -T

[ LOOP ERROR jFSp,

LONGITUDINAL_ _ BUNGEE

STICK FORCE [q

STICK ]FORCETRANSDUCER

_ CO.AN D __MODELSHAPING

Nz,

NORMAL -'-

aCCELERATION--_+_

q, _KN tPITCH RATE Zq

i

_SP

LONGITUDINAL o..... ..t MECHANICAL L_

STATI C PITOTPRESSURE DIFFERENTIAL

PRESSURE

INNER ELEVONSERVOACTUATOR

r"t"TO TRIM ACTUATORI

,,Boo hl FREQUENCY_BEI':DING[FILTERSHAPING/I.GAI N I"1 AUTHORITY

AIRSPEED

_ei,

INNERELEVONDEFLECTION

_aY,

OUTER

ELEVON

DEFLECTION

OUTER |ELEvONSERVO /

ACTUATOR|

Viggen Pitch Axis Stability Augmentation and

Control Stick Steering Mode

x.OIX.)

BEEPTRIM _ TRIM

CONV_V_NDI"_ MOTOR

r"- -- 1

i LOOPERROR_.j

FSL,

LATERAL FI BUNGEE

STICK FORCE

STICK

FORCE

TRANSDUCER

LATERAL

TICK DEFLECTION

M_c,_,c_L._J,NNER AILERON

EARING j---"lSERVO ACTUATOR}

IFLAP EXTENSI ONSIGNAL

I,

INNERAILERONDEFLECTION

L,_ COt'_AN Dh _ay,_,"K)DEL OUER

SHAPING _,__+ AILERON_1 I--TO TRIM ACTUATOR DEFLECTION

IBODYII IGA,N WLVE SERVO(_i BENDING HSHAPING SCHEDULED AILERON

_ /FILTER I I I I iVALVEI'll

ROLL ,-_SHAPINGRATE | I

Viggen Roll SAS-CSS Loop

_0

FRp

RUDDERPEDALFORCE

Ny'

I_ATERALACCELERATION

p

YAW RATE

P,ROLLRATE

INNERAILERONDEFLECTION

BUNGEE

=i SHAPING

I

_J SCHEDULED

*IGAIN

I NDICA'[ED

AIRSPEED

I

TRIM _r,

MOTOR RUDDER

DEFLECTION

l-i glLTER GAIN VALVE ACTUATOR

S 'INDICATED

AIRSPEED i

SHAPING[._ '

I

Viggen Yaw Axis Stability Augmentation System

_.0

PITCHATTITUDE SOL,° .STATESYNCHRO- SHAPING

STICK FORCE

_ATEo_SC"EOOLEOL,'.*AIRSPEED _'I GAIN IALT.+

BEEP TRIM__I=_.=_ - HOLD !

CO_AND AT/ITUDEALTITUDE

,,,HALTITUDE

I_c._ou,_ol._GAINf I

HOLDI

_HAPINGL._,,_SCHEDULED1 1

I ALT. [GAIN i---, HOLD I_

INDICATED

J AIRSPEED

SP, _eiLONGITUDINAL INN[ERSTICKDEFLECTION ELEVON

' I IINNER 1 DEFLECTIONAUTO-IR IM I'_ELEVON l I" _

( I NTEGRATION)JlSERVO- u ey,ACTUA_ _#R N

| DEFLECTION

[s.s0 E EVON; F RWARD S'ERVO

LOOP ACTUATOR

Nz +q

SAS FEEDBACKS

Viggeu Pitch Outer Loops

',,O',jl

ROLL

ATTITUDE

HEADING

SOLIDSTATE

SYNCHRO-

NIZER

tSTICK

HOLD

._ FORCE #if

STANDAR ,_JSCHEDULED L

TURN -'1 GAIN I-"CO/VWIAND 4'

INDICATED

AIRSPEED SSTDI SOLID I

I_, _ STATE L..]SCHEDULED IHEADING -_i SYNCHRO-I-_GAIN

[NIZ_R I" t

_SL

LATERAL

STICK 8ai,DEFLECTION INNER

L.J INNER I AILERONJAUTOTRIM AILERON L DEFLECTION._

E INTEGRATI ON)I "I SERVO [| (_ "ACTUATOR | I ay,

OUERr--- AILERON/ DEFLECTION/ I OUTER I

+_ AILERON L

S RVOI"_ ACTUATORI

ATr-_'_p, LoopFORWARD

ISHAP'NG'I _O_L RATE

FEEDBACK

STICK INDICATED

FORCE AIRSPEED

TURN

Viggen Lateral Outer Loops

STICK

POSITION

GENERAL BLOCK DIAGRAM

FOR ROLL AND PITCH AXES

MECHANICAL, GEARING J

GAIN 8=MODEL

SHAPINGNETWORK

AMPLIFIER& AGTUATOR

R_EFEEDBACK

ENGINES &FUEL CONTROL

IATTITUDE DYNAMICSFEEDBACK

RUDDERPEDAL

POSITION

YAW AXISBLOCK DIAGRAM

HN'SHAPIN G I I AMPLIFIER

ETWORKS, ' I-_-_G_ L'-'t AND/_ I S,ERVO

RATEGYROi I TILTLACTUATOR i

1

VJI01-C

96

-4

tateral-direclional _1

commandsII-

Rate_ro I

_ I Lateral 1 I

- I directionalII vehicle I

=i dynamics: ]

Rategyro_shout arm I

structural filter I

_-p_p

M2-F2 Lateral-Directional Flight Control System

_0CO

i

I

I

I

I iIJ

X-15 Pitch Axis Configuration Block Diagram

AUTOPILOT i

' j

X-] 5 Roll Axis Configuration

m

E_

E

×

I

IL

q-- ---

REACTION CONTROL

i i

II l NE_N_ .C,_CTIr_

I

II

X-15 Yaw Axis Configuration

1O0

& / _.. r.,u,-,-_, " _'_,_avo

_o_.._ _._

k'dlyCl_

Q

i

I

II

.-."_ _ ..,!......_-,,_..-=...,-_

I rO_.LQW. U_

ELEVATOR CHANN_

B-707 Autopilot

PO

[_>

®

B-707 Autopilot

S

oN

U I[CqAU I CA I.. LI kl _'_

_;[T IrOI *, M&](II_iUM _"rATl¢ _ILAlli • --i= •

.... , ..... _/... _/,._ _'

@,*'_8 S L * .2_1S * T_. wo_.T

RUDDF_ CHANNEL

B-707 Autopilot

V, Zgs

(2_.0(.oz_+1)(zs,,)

_AS_C ?_TC_ STABiLiZER

IIII

IIII

J

Ok)TE_ LOOPS

DC-8 Pitch Axis

6

_C

13ASIC _,0Lt. STA$_L_ZA-_ION

_Os J IJ/

IL_ OoC.

Vos'_io_ 6_vvo

__-I E/M L S=

5_,,o| _-"C======-

_OL.L PAT_ A_) NA,_/ _AODE_

Aux. May.

0,,4"o,el 12" "

DC-8 Roll Axis

YAW STA_,_LlY__AT/0N

_r'_

ILS O,C,

DC-8 Yaw Axis

o-q

ILl

_E

.,(

0¢

U.

m_

BEAM

_ GEOMETRYSIMULATION

LATF_J_L A/P AI_ON CHAA."__=LLOCALIZL_ _,q_ V. 0.R.

DIRECT GYRO I• & /VP COUPLER

VERT GYKI_ 1& A/P COUPLER

BEA_

SATURATION

OUTPUTLINIITER

Error &

4

i _

RADIO LAG J

LOCALIZER 2/S.2 I

V.O, RL.1/1.SS 1 J

LaggedBea_ Error

InLCgrator CutoutUntil B.C.C. 0_erates& For $H Operation

I INTEGRATOR |

_/S=O.O?41S LOCI-_-

W/S=O. O81/S VOR___._

-IMODULATORAMPLIRER

BEAMCAPTURE

CONTROL

DATA SMOOTHER

I LOC

J_--_ WIS+W ......

W = 1/10 V.O._ TRACKW = 1/3 V.O. _ CAPTURE

ROLLLIMITER

I

ALTITUDEATTE,=_UAT0 R

2---

t LO°C'{/.O. R.

DIS PLACE_AENT I

LPAITER I

I

AILERONSERVO

RUDDERSERVO

L- 188 Autopilot

Co

PITCH RATE= GYRO AND

A/P COUPLER

_ I VERTICALGYRO

m u

._ INTEGF,. ,R _it

• _-f:vdt-/

ft

Engage; i700'

O isengage;200'

Beam_Reference

IIIII

OERIII

: I

II

ANALYTIC MECHANIZATION OF BEAM ERROR

OUTPUT LIMITER I

i -11

I

LONGITUDINAL A/P IGLIDE PATH MODE

I ELEVATOR ISERVO I

I

1.4AXIMUM iINTEGRATOR

INTEGRATOR

RADIO LAG3

$÷2 E It

Beam Error

MODULATORAMPLI FI ER

DISPLACemENT i

LIMITER

LL

"(

Switch "ON"6]Ide Slooe

Engage

L-188 Autopilot

r I

6".O

Present Heading

Reference -_7 \ SwitehforPSHCl°SedMode [t4

i--------J, I DIRECTION [ HEADING j+p_ --

I - ' GYRO AND I = I INTEGRATOR + + )

, ¢ j VERTICAL

- ,-----"i GYRO& j< i IA/P COUPLER]

CONTROLLER 1 "_ ?_

I I

i.Switch Open when A/P Engaged

J F-O"".1_-_ Fixed Exc

r-A---_--- 3-- _: ]

I{' ] YAW RATE

--_GYRO & A,' P

[ COUPLER ]

l AL J ACCELERO.

I_______J----_, '.(ETER J

I IAT_RAL

Swi ch J> J WASHOUT SYNCHRONIZER l

' Cl_,_ed [ J'__4 Sec after AlP engage !

I_.. _ _ I'.--.=i_=,,,,o,,A/,ao_a,eI_VP IL _ I I

L_ I_2__ __ _ _'2 ..... J!

Open for i ---RATE lI A/, _ _--I!FE_D_ACK_---_ .... ---,:,,gage I I _, F'_ f J

J HYDRAULIC ' LINK '

I I I [----"I & MODULAT. " ' " ,

1 lm ' ' I lING PISTON t l

I _ SERVO J ' IMAIN BOOST I I

j I'_'---"Or_ AMPL'F'ER I I SPOOL I i

Ii FEEDBACKL

[ HYDRAUL,CRAMJ I' I

.i,XL

g li ........

RUDDER S ERVO

l RATEFEEDBACK jL" -- ]x.p

J RvoT_ HYDRAULIC I

I AMPLIFIER I& MODULAT-

J _ SE ING PISTON

I AMPLIFIER I I

I

L i FEEDBACK

I

t

LINKAGE I

MAIN BOOST J$ POOL

J,I HYDRAULICRAM I

_,xk

J J

uJ

ri-

M.

OC

L- 188 Autopilot

I

LI.

I LOHGI_u_DINA L

I_._ PITCH RATE

GYRO & AJP-COUPLER

._ VERTICAL GYRO J

mv/e,2ooNV/Pe_.JPROP ERECT to _Deg.L_Erection Rate= I -

-_----_ ,f2O Peg/SEC/Oeg. j

+

ALT SENSOR I

AIRSPEED ERRORCOMPEN$ ATION

e

I POSITION t 8E

RATE Xmp

FEEDBACK -- ---- 1

J

SERVO AMPLI FIERAMPLIFIER & MO'DULATING -- --

PISTOH

L-._ m _

I 0UTPUT LIMITER I_

ELEVATOR S ERVO

LINKAGE

I

, t

I MAIN BOOSTSPOOL

HYDRAULIC

RAM

, I XL

6E/Xp

SYNCHRONIZER

I _ Switch Own when 1

A/P Engaged i#' INTEGRATOR ' I ; P--o"_ FIXED EXC, |

Pitch Control 1er Up lit itude

F

t'4" FLAP POSITION

TRANSMITTER

& ATTENUATOR

lIIIIIIIJIII 6E

iJJ

,,,(

u.

i

J

L- 188 Autopilot

PQaCE

PLOT

STICK-FgNC(

ELECTRICAL GNNC_MkIANO T(RM

I

LAI; ClI_:UIT

_'--t * 4.7 V(_-TSI÷_ VOLT

S'_&IGHT THJeJ 6A/N

I 2:2_ 10_O7)$

[

roSE Sill

ou_t.rnJOE

RAI"E G_mO

-----4 t 1+2(I)S 4""--_" _')tSI 0(G_JEC I:

114_Sf_qS_q NCmUU. _

1.2 VOLTS14" _(L06)S 4. s8 9

II

._ (I+A,S+A, Si)I'Iz ._i I

6 -,nc_u_r Ij

F_

s

vN_

o6

CUtISS

TIP_ _STANT

LAPLACE TRA_SFOP_4 VARIABLE

STZ_K MOTION Q_ANTITY

STA_ILATOR DEFLECTIC_

_CY OF SHORT PERIOD N(X_E

KZPt_RAJ_ ]4OT'r(_ QU._rl"r'l'Y_CRSPIU_

IIOI_IAL AC_LERAT IOi

GESAC Pitch Channel (F-4A)

m-io+_1-1,+_FELECTRICAL GAIN

COMMANO TERM

ATTITUOIE GAiN

ERROR TERM

I+1- z.o --_

__ 3 46 Va.TSS VOLT

CAINAJ_t.IFR_ S_mE5 58m_ LOOP

b °++°Is,I'*'-1 I _'1 I'+_+_, I 12.7 DEG AlL_ = 14"GI S iNCH

AIRCRAFT_I_OYN_S/MCS

LAG CIRCUIT RATE GYRO

I+ z_'s+ se oe_sec .

i

W _GNN

I -I-oz+P

C_s4CI_.LI_R

l co_o_-m,-+,'_-'+L

,. ,_+-..+'+'-Tr

IC_. e._,,+,u_

8_ - _J_:_os VEFLZC'rIOH- Ro_ _-

_ ROL.LRATE

GESAC Roll Channel (F-4A)

Iil_.--°RUOOEG RUD

GAIN I S_RIES _ & LATERAL.

CHANGF_R _ POWER BOOST _ ACCE1.ERATIONAT CG

l'i t- VOLT I-m.d_.J_ . 21 s S 2

IATMAXG_INt- i(l+_)(,+_ ) VOLT '+-_--+_)z _ 573g(I +T, S)

LAG CIRCUIT

= _ 1+2S VOLT

STRAIGHT THRU GAIN

VOLT

CANCELLER

I 274(0033)s VOtTS_! I+(0033)S VOLT

_a_ORMER RATE GYRO

-]-.-_- -_-f-l--ln, Z(.S+ s_ _c

"_A_FORMER LATERAL ACCELEROMETER

0.4 _1----t I+z(J)s+ s g n_II _-_ I

-IJuP_,c]g 'rR;mSFORM V,_ABI, Eof _ RUDDER DEFLECTION

w-FREQUENCY OP DUTCH ROLL MODEAI A2 -AIRFRA/4E. MOTION QUANTITY

V - VELOCITY

_..-EFFECTIVF CONTROL MOFIENT ARM FROH CG

_V - YAW RATL

- YAW ACCELF:RATION

GESAC Yaw Channel (F-4A)

-w

Is",1o.5 s+l_._t . ±;._"-,..__6_s+,._7._1] i, "¢,BENDING FILTER I lOWLy

c.,_Eo_> I },,,,

css

F_,I $Y.1

SERIES ,SE,RVO POWER

ACTIJATOR

Adaptable FCS Pitch Stability Augmentation System (F-4)

k..n

l LATE RAL [

STICK FORCE

(LBS) J I

I ROLL RAT+RA O/S[ E

YAW RATERAD/SEC

Adaptable FCS Lateral-Directional Stability Augmentation System (F-,4)

5 VALUE i

ACCEL. O+S.)_ "i'O.,2s) CIRCUIT J

IPIrCH_rrl ! _=S

! "_'° F_,+o._s.sRAD/_Ec

I_AD .

[E L E VA TOR'_

!P°""°" i-7 z_.z.

I I IA,,,o,.,,',I! _-_ VALUE I

I +0.3Sd

I -Z_.j ,

_,-F'_[_,_,.,._-.35 i _-,,aS

NOTE :

Z_ - 0.,21+0.35

Adaptable FCS Flight Condition Identifier (F-4)

I pITCH ._A_; J

RAD/SEC

PITCH RATE H 0.75,5GYRO I + o. 75-5

o._s I I I

MACH | . OTHER.'_._

ERROR I M H_OLD

AANGLE OF l RAP

T TAC K ERt_

. OT.ER J_LttJ'"_'l -I 1+o.3s5 I+ _

o( HOLO

PITCHATTITUDE_ J. I+5

HER_

- e8

NORMAL I FT/SEC_

A CCEL" r__,, 15

_E_ I,+lOSi 9(I-SECO)

I-1"105

PRESS.ALT. !RATE J'FT/PSEC

I BARO. ALT. I FTERi_OR

,, -t --t---{L,_I_I I LIM_T!

1 1+o._5 I I i l+°-_-s Ii_+o-,'_>1I I.."_-,,I

HOLD

: I !, I+o.osE I -OTHER

E÷p,

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Grumman F9F-2 Attitude Command FBW

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Airplane _!

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Grumman F9F- 2 Attitude Command BFW

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LONG [TUD[_JAL D[AaHAM

LATERAL DIAGRAM

F-tO0 Lear Rate Integratlng Autopilot

138

2_FESENCE_

I • Johnston, D. E., and D. H. Weir, An Assessment of Operational and Cost Tradeoff

Factors for a T_r_ical High Performance AFCS, Systems Technology, Inc.,TR-119-I, June 1962.

2. "TA-4F Accident Provides Some Costly Lessons_ Approach, Vol. 15, No. 8, Feb.

1970, pp. 36-41.

o Schuetzj A. J., R. L. Fortenbaugh, and W. E. Becker, An Aerodynamic Stabilityand Control Data Summary for Several Selected Militar_ _Aircraft_ Volu_eI: Conventional Aircraft, Naval Air Development Center Report AM-7106,

28 Sept. 1971.

o Burtner, S. K., and Charles T. Garrington, Automatic Control and Stabilization

S_steml En6ineerin6 Report, North American Aviation, Inc. Report NA59H-238,19 May, 1959.

_. Hilburger, E. A., Control Systems Desi6n Re_ort for A3J-I Attack Air_lane, NorthAmerican Aviation, Inc. Report NA 59H-98, 10 Apr. 1959.

6. Simulator System Test Re_ort for A2F-I Airplane t Part a, Grumman AircraftEngineering Corporation, Report No. AV-128R32.0, no date.

7. Seth, W. A., A-TD Estimated Flying Qualities, LTV Vought Aeronautics ReportNo. 2-_3320/8R-8089, 15 Jan. 1968.

o Bielka, R. P., A. P. Kavalok, W. L. Johnson, and R. E. Reel, Aircraft Fli6ht

Control Systems Field Safety Experience, Air Force Flight Dynamics Lab.TR-72-33, May 1972

9. B-_2 Autopilot Modification, Boeing Company Document D3-4360, 15 Mar. 1962,

presented at the Boeing Conference on Manned Vehicle Flying Qualities,I_-16 Mar., 1962j Seattle, Washington.

10. Newberry, C. F., B-O2 AutopilgtModification , Boeing Company Technical PaperD3-4525, presented to SAE Committee A-18 Aerospace Vehicle Flight ControlSystems, 14 June 1962.

11. B-_8 Flight Control S_stem Air Force Review Board, General Dynamics/Fort WorthFZE-4-049, 6 Nov. 1962.

12. Rabenberg, B. E., and J. J. Gondek, XB-70 Fli6ht Control System Summary TestReport, North American Aviation, Inc. Report NA-66-360, 30 Sept. 1966.

13. Flight Manual --USAF Series C-130A Aircraft, Air Force T.O. IC-130-I,I0 Jan. 1963.

14. Fli6ht Manual --USAF Series C-133A and C-133B Aircraft, Air Force T. O.IC-133A-I, 14 June 1962.

19. Flight Manual --C-13_A and B- , Air Force T. O. IC-135A-I, I Mar. 1963.

16. Tomlin, K. H., C-_ Flight Control Report (Aerospace Vehicle) Stability and Control tLockheea-Georgla Comply Report No. LGIUS#2-1-1, I Oct. 1966.

139

17.

20.

Jamison,GeneS.3 C-SA Flight Control System, SAE Paper No. 670574, presentedat the Aerospace Systems Conference, Los Angeles, Calif., 27-30, 1967.

Fling, G. K., XC-124A Control S_stem, SAE Paper No. 670571, June 1967.

Hart, John E., and Harold A. Valery, C-5A Flight Control Report (Aerospace Vehicle).

FllghtControl Subsystem. Volume It Lockheed-Georgla Company Report No.LGIUS42-2-1, 17 Dec. 1966.

Shields, M. E., Estimated Flying Qualities XC-142_A V/STOL Assault Transport,LTV Vought Aeronautics Division Report No. 2-53310/4R 939, 22 May 1964.

21. S-_A Automatic Thrust Control System, Naval Air Systems Command, no report no..no date.

22.

23.

24.

Guion, H. D., Re6ulus II Lot I Autopilot q Section IX, Chance Vought AircraftService Training Manual, 11 Jan.. 1996.

Preliminary Flight Manual DSN-3 Drone and Target Control System AN/SHW-4B,Bureau of Naval Weapons NAVWEPS 01-150DHB-1, I Jan. 1952.

USAF T_e A/A37G-3 Flight Control Subsystem of the Type Q-2C Drone, RyanAeronautical Co. Spec. 124_9-2A, no date.

go Seeman, William G., and Floyd H. Moody, Usin6 the Man to Test Unmanned Aircraft,Society of Flight Test Engineers Report No. 16, presented at Symposium

on Test and Evaluation of Automatic Control Systems, 31 Aug. -- I-2 Sept., 1971.

26.

27.

Gerrity, Robert J., Test and Evaluation of a Versatile Drone Automatic Flight

Control System for the B_M -34A_ Society of Flight Test Engineers ReportNo. 13, presented at the Symposium on Test and Evaluation of AutomaticControl Systems, 31 Aug. m I-2 Sept., 1971.

Teper, Gary L., and Richard H. Klein, Analysis for the MQM,74A Drone Control System,Systems Technology, Inc., TR-279-I, Feb. 1968.

28. McEntire, Kenneth G., and E. H. Underwood, Jr., Flight Test Evaluation of the

A-7D/E Emergency ("Rack-Up") Flight Contro_fsystem, Society of FlightTest Engineers Report No. 14, Aug.-Sept. 1971.

29. Dempster, John B., and James I. Arnold, Flight Test Evaluation of an AdvancedStabilltyAugmentation System for the B-52 Aircraft, AIAA Paper No.

68-1068, Oct. 1968.

30. Dempster, John B., and Kenneth L. Roger, Evaluation of B-52 Structural Response

to Random Turbulence with Various Stability Augmentation Systems, AIAAPaper No. 66-998, Nov. 1966.

31. Aston, P., _-2C Pitch Axls Control S_stemAnal_sls, Lear Siegler, Inc., AstronlcsDiv., Inter-Office Correspondence SA69-239, 15 Oct. 1969.

32. Report of the B-58 Flight Control System Review Board_ Sect. VII-A_Aerodynami cTrade-Off Team Report, Aeronautical Systems Div., 5 Dec. 1962.

33. Proposal for a product Improvement program for the BQM-34A Automatic Flight

Control System (Versatile Drone Autopilot), Lear Siegler, Inc., AstronicsDiv., Rept. AD-975, 17 July 1970.

140

35.

Maintenance Instructions _nual, Navy Models F-4B and RF-4B Aircraft,Flight Control Group AN/ASA-32 Series and Related Systems, NAVWEPS

01-245FLB-2-6. 3, I Dec. 1965.

Abrams, C. R., A New Concept in Automatic Flight Control _ Final Report,NADC-AM-6904, 13 Feb. 1969.

36. Falkner, V. L., Functional Configuration of Pre-Production No. 3 AFCS,

37.

38.

39.

40.

43.

Honeywell Inc., SEM No. 115.0090A, 6 Aug. 1970

Hurt# George J., Jr., and James B. Whitten_ Flight Investigation of anAutomatic Pitchup Control, NASA TN D-] 14, Aug. 1960.

Johnston, D. E., O. Imai, and D. D. Miles, F-89 D Sideslip Stability Aug-

menter Operation and F_intenance_ Airplanes N-2216 through N-4_77,Northrop Aircraft, Inc., Rept. No. NAI-_4-767, 15 Oct. 1953.

Ciscel, B. H., A Description of the Honeywell E-10 Flight Control System,

Minneapolis-Honeywell Regulator Co. Rept. R-ED 9048-2, 28 May 1954.

Gaertner, R. V., R. C. Mclane, and V. Baxter, Flare Out Program for AirForce Type E-I 0 Automatic pilot, Minneapolis-Honeywell Regulator Co.Aero Rept. AD5501 -TRI, 15 Aug. 19_7.

Flight Manual_ USAF Series F-IOOC, Air Force T.O. IF-I00C-I, 22 Dec. 1960.

Flight Control S_stems for F-100FAirplane, North American Aviation, Inc.,Rept. NA96-731, 1956.

FliSht Manual_ USAF Series F-101A and F-101C_ Air Force T.O. IF-101A-I,15 May 1962.

44. The Honeywell Flight Boundary Control System, Honeywell Inc., Governmentand Aeronautical Products D_v., Brochure_ADC 364, Jan. 1972.

45. Maintenance Manual a Fli_ht Control Systems, USAF Series F-102A and TF-102A,

Air Force T.0. IF-IO2A-2-7, 5 Jan. 1962.

46.

47.

48.

49.

Fli_ht Manual I USAF Series F-I02 and TF-102A, Air Force T.0. 1F-102A-I,4 Oct. 1962.

Hoey, Robert G., and Louis W. Schalk, Air Force Evaluation of the AutomaticPitch Control for the F-IO4A, AFFTC TN _7-11, Feb. 1957.

Flight Manual - USAF Series F-104A and F-104B, Air Force T.0. 1F-104A-1,I_ Dec. 1961.

Sexton, H. A., Jr., Flight Testing the F-I04 Automatic Flight Control

System, AIAAPaper No. _-328, July 1964.

50. Flight Fenual_ USAF Series F-105B, Air Force T.O. 1F-10_B-1, 15 July 1962.

]41

51.

52.

I_Gue, T., F-IO6A Damper Systems, Convair Rept. DC-8B-135, Rev. A,11 Mar. 19_8.

Maintenance Manual_ Flight Control _ystems_ USAF Series F-I 06A and F-I 06B

Aircraft, 20 Dec. 1962.

_3. Round-Up Review_ Division Advisory Group-ASD_ 21 and 22 June 1968_ Flight

Control System/Stability slud Control, General Dynamics/Fort Worth Div.,

Rept. FZM-12-5964-2, 21 June 1968_ (Report Confidential, Title un-

classified)

_4. Preliminary Flight Control Subsystem Analysis for the F-I 11A/B Airplanes,

General Dynamics/Fort Worth Div. 3 Rept. FZM-12-278, 16 Aug. 1963 •

(Report Confidential, Title Unclassified)

55.

57.

_8.

59.

61.

62.

63.

64.

F-111 Category I Flight Test Progress Report_ Preliminary Stability and

Control/Fllght Control Subsystem Flight Test Results, General Dynamics/

Fort Worth Div., Rept. FZM-12988-13-23 14 Feb. 1966. (Report confiden-

tial, Title Unclassified)

Presentation to ASD Division Advisory Group, General Dyns_nics/Fort Worth

Div., Rept. FZM-12-2357, June 1966.

Sanctuary, G. E., and A. M. Roberto, Low Speed "Adverse" Yaw Flight Simu-

lator Evaluation, General Dynamics/Fort Worth Div., s/C TM No. 52,

_8 Oct. 1966.

Seacord, Charles L., The Honeywell AFCS (MH-I_7_ for the Swedish Viggen

(AJ-37 _ Aircraft, Honeywell Inc , Rept. T-230, circa 1969.

Organizational Maintenance_u_l_ Flight Control Systems_ USAF Series

T-_BA, Air Force T.0. IT-38A-2-3, I Sept. 1962.

Naumann, Erwin A., and Herman Schmier, "Design and Development of theStability Augmentation System for the Lockheed/Army XV-4A," Proc. of

the 20thAnnual National Forum of the American Helicopter Society,

Washington, D. C., May 1964, pp. 140-I_I.

Mueller, Leo J., Some Experiences in VTOL Automatic Flight Control,

presented at t_e SAE A-18 Committee Meeting No. 14, New York, July 1964.

Kempel, Robert W., Analysis of a Coupled Roll-Spiral-Mode_ pilot-Induced

Oscillation Experienced with the M2-F2 Lifting Body, NASA TN D-6496,

Sept. 1971.

Experience with the X-15 Adaptive Flight Contlol System, NASA TN D-6208,

Mar. 1971 •

Lindahl, J.# W. McGuire, and M. Reed, Advanced Fli6ht Vehicle Adaptive

Flight Control System. Part VII: Final Report on Study, Development_

and Test of the MH-96 System for the X-15, WADD-TR-60-651(VII),

Dec. 1963.

gS. MH-_6 Flight Control System for the X-15 Aircraft. Vol. V: System

Description and Bench Test Procedure, Minneapolis-Honeywell Regulator

Co. Aero Rept. 2373-TM1 (Vol. V), 31 Aug. 1962.

6g.

69.

Tremant, Robert A., Operational Experiences and Characteristics of the

X-15 Flight Control System, NASA TN D-14023 Dec. 1962.

Current Autopilot Block Diagrams, SAE A-18 Committee, Oct. 1959.

Martin, C. E., Preliminary Flight Control Subsystem Engineering Report

for the F-111A/B Aircraft, General Dynamics, Fort Worth, Rept.

FZM-12-874, 21 Oct. 1964, (Rev. 26 Jan. 1965).

SJoberg, Sigurd A., Walter R. Russell, and William L. Afford, A Fli_htInvestigation of the Handling Characteristics of a Fighter Airplane

70.

Controlled through an Attitude Type of Automatic Pilot, NACA RM

L56A1 2, Apr. !956.

Russell, Walter R., Sigurd A. SJoberg, and William L. Alford, A Fli6ht

Investigation of the Handling Characteristics of a Fighter Airplane

71.

72.

Controlled Through a Rate Type of Automatic Control System, NACA

RM 106F06, Sept. 1956.

SJoberg, Sigurd A., Walter R. Russell, and William L Alford, FlightInvestigation of a Normal-Acceleration Automatic Longitudinal Control

System in a Fighter Airplane, NASA Memo I 0-26-58L , Dec. 1958.

Russell, Walter R., SigurdA. SJoberg, and William L. Alford, FlightInvestigations of Automatic Stabilization of an Airplane Ha_tatic

73.

Longitudinal Instability, NASA TN D-173, Dec. 1959.

Russell, Walter R., and William L. Alford, Flight Investigation of aCentrally Located Rigid Force Control Stick Used with Electronic

74.

7P.

76.

Control Systems in a Fighter Airplane, NASA TN D-I02, Sept. 1959.

Rickard, Richard R., and Jerauld R. Gentry_ Development Testing of a High-

Gain Adaptive ControlAugmentation System Installed in an F-4C Aircraft,

AFFTC-TD-70-4, Vols. I and II, Sept. 1970.

Rickard, Richard R., Stability and Control Evaluation of an F-4C Aircraft

with a High-GainAdaptive Control Augmentation System, AFgvfC-TR-71-1_,

June 1971.

Rickard, Richard R., Richard H. Kogler, and Cecil W. Powell, Stability and

Control Evaluation of an F-4C Aircraft With a High-Gain Adaptive

77.

78.

79.

80.

Control Augmentation System, AFFTC-SD-71 -I 7, June 1 971 •

Carleton_ David L., and Cecil W. Powell, Limited Air-to-Air Trackin_ and

Qualitative Flying Qualities Evaluation of Selected Flight Control

System Configurations in the F-4C_E Aircraft, AFFTC-TD-71-4, AUg. 1971.

Carleton, David L., Richard E. Lawyer, and Cecil W. Powell, Development

and Evaluation of the TWeaD II Flight Control Augmentation S_stem,

AFFTC-TD-72-1, Nov. 1972.

Howell, G. C., Flight Experience of Rate Demand Control Using Electric

Signalling in the Avro 707C Aircraft, AGARD Report No. 536, May 1966.

Miller, H., and R. H. Wagner, Flight Control System for Jet Transports,

Sperry Gyroscope Co., no date.

143

81. Transfer Functions and Block Diagrams of the SP-30AL Automatic pilot and

Z-14 Flight Director as Applied to the Douglas Model DC-8-60 Series

of Aircraft, material transmitted to STI in Sperry Flight SystemsDivision letter of 29 Sept. 1969.

82. Eldridge, W. M., Lateral Control Augmentation for Transport Aircraft,

presented at the Boeing Conference on Manned Vehicle Flying Qualities,Seattle, Wash., Mar. 1962.

83. Harris, Pat, Some Aspects of the 727 Flight Control System, presented atthe SAE A-I_ Con_nittee Meeting No. I_, New York, July 1964.

84. Devlin_ B. Terry, and Robert H. Parker, "The SP-77 Automatic Flight Con-

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U.S. GOVERNMENT PRINTING OFFICE: 1975--635-(_/80

Documents

I : iiC $E FiLE COPY · PDF fileNASA NASA CR-2501 0 I z:_iiC_$E FiLE COPY FLIGHT CONTROL SYSTEMS PROPERTIES AND PROBLEMS Volume II- Block Diagram Comp-endium Donald E. Johnston = Prepared