Flight control systems properties and problems. Volume 2: Block diagram compendium

NASA

NASA CR-2501

I

:_ii C_$E FiLE

z

COPY

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 Center r_'2.6_191ro NATIONAL AERONAUTICS AND SPACE ADMINISTR_TIOH * WASHINGTON, D. C. • FEBRUARY 1975 1. Report No. -I 2. Government Accession No. 3. Reciplent's Catalog No.

NASA CR-2501

I

=, L, 4. Title and Subtitle 5.

Report Date February 1975 FLIGHT CONTROL SYSTEMS PROPERTIES AND PROBLEMS Performing Organization Code Volume II -- Block Diagram Compendium 6.

H-860 7. Author(s) 8. Performing Organization Report No.

TR-1018-1 Donald E. Johnston 10. Work Unit No.

9. Performing Organization Name and Address Systems Technology, Inc. 11.

Contract or Grant No.

Hawthorne, California 90250 NAS 4-1881 "13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Contractor Report - Final National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, D.C. 20546 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)) 18. Distribution Statement Aircral't control systems Systems design Unclassified- Unlimited Category: _dS, _ 22. Price* 19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages $5.75 Unclassified Unclassified 149 *For sale by the National Technical Information Service, Springfield, Virginia 22151 TABLE OF CONTENTS Pag.__e I I. INTRODUCTION II. BLOCK DIAGRAMS.

III. REFERENCES 139 iii

SECTION I

INTRODUCTION

This volume contains a compendium of 8ASand autopilot block diagrams

for some48 attack, bomber, cargo, drone, fighter, research, and transport

type aircraft. It also contains references to specific documentsfrom

which information was gleaned for this study.

This compendium incorporates and expandsupon an earlier effort (Ref. 67)

initiated by the A-18 AerospaceControl and GuidanceSystemsCommitteeof the

Society of Automotive Engineers. It is by no meansa complete exposition

of systemspast and present. There are manysystemsfor which no informa-

tion was available, and there are others for which the information available

was incomplete or conflicting, and therefore not included here.

An initial attempt was madeto put all block diagrams into a consistent

format which identified functional blocks and associated transfer charac-

teristics, functional switching, etc. However, it rapidly becameapparent

that such a task was beyondthe scope of this program. Therefore in most

instances the diagramspresented here have been reproduced directly from

the original documentslisted in the references. In all probability

they reflect but one version of systemswhich mayhave undergoneseveral

modifications. Consequently, additions or revisions are solicited from

those whomakeuse of these volumes.

_ECTION II _L0CK DIAGRAMS Ref. No.

Pages AIR_ 4-8 A3J- I I 9-11 A-4 12-14 A-7A 19-19 9, I0

B-pC

II, 32 20-29 B-98

3o

B-66 31-33

XB-70

34-49 16, 17, 19 C-5A KC- ]39 47-49 18, 20 XC- 142A too 90-91 E-1B too 92-53 S- 2D/S- 2E Regulus II 24, 31 99-96 ¢,-2C 57-98 25, 26, 33 BQ,M-34 59-6O MO,_I- 74A

61-63 67

F3H

64 34

F-4 F-8D F-14 67 37 F-86 38, 67 68-69 F-89 7o-72 41, 42, 67 F- IOOD/F 43, 67 F- I01A 43, 44, 67 74-77 F- I01B 78 49, 46 F-I02 79-81

F-I09A

82-83 F- 106

84-87 93-55

F-111 T-38 AVRO CF- I00 Ref. No.

AIR_

9O

Fiat G-91

91-95

Viggen (AJ-37)

VJI01-C

M2-F2 97

98-1oo 64, 69

X-15

101-103 67

B-707

I04-Io6 81

DC-8

L- 188 67

1o7-110

R/D SYSTEMS

GESAC 111-113 88, 89

114-118

HoneywellAdaptable

SFCS

119-124 9O 125-128 69-73

NASA F9F-2

TWEAD I 74, 75

129-13o

TWEAD II 131-134 78

135-137 79

AVRO-707C

138 67

Lear Rate Integrating

i .........

STICK MECHANICAL CONTROL _ SOLENOID L _ -- _ -._, . MECH_,NICAL FEEDBJ_CK r- - ! CLUTCH I I I- ..... .I __._ l l Aj,4S_rI.IIC't_ ACTUATOR MECHANICAL FEEDBACK IUNC._E _ -1 ACIUATOR FEEDBACK L (ELEC1RICA L ) eLECTRICAL) AClUA, T(_ CONTROL AUTOFLIGHT AND VALVES i M_CH TrIM SYNCHRO :

I

LATER._L TRIM I $TORIr | JECTION COMPUTER ELECTRICAL ACTIJ_TOR COMPENSATION I PORT SERIES (SERVO I ACTUATOR

t-

SERVO VALVE _ SERIES (SERVO] AJ_PLIFIER -'STABILIZER

L I S F^C, I

- i S'ERIES ACTUA'TOR l _- _ ACTUATO_ FTT_'_- ----_ | TRANSDUCER J , l ,N_,VAtvES I jl _.k, MECHANICAL FEEDE_AC ......

POSITION TRANSDUCER ,_ MACH NO.

ELECIRICAL FEEDBACK __J HYD f DIFF. PRESS,. --)- BALANCER TRANSDUCER ._,__..____j.I STAB POSITION l IRANSDUC[R BLOGK DIAGRAM A3J-I LONGITUDINAL CONTROL SYSTEM LATERAL CONTROL STICK F - -- "- -- "1 _,/MEC HANICAL FEEDBACK _ _,_ ' ELECTRICAL ROLL TRIM SWITCH ON CONSOLE LATERAL TRIM

q______j,wo

TRIM SELECTO_ SWITCH ON FLIGHT CONTROL PANEL ROLL TRIM SWITCH ON STICK LWDt FRWC> BLOCK DIAGRAM, S A3#-I LATERAL CONTROL SYSTEM I H£LD hp

J...... I GA'N I ...... f

LIMITER I___ A L FCS I ....

GAtiN _I SHAPING GAIN SIN 0 TAN £) MFRS

° 1

SIN _ TAN 0 PITCH o'_ SYNCH.

"e _7 HOLD FAST SYNCH.

hp Ah [ ADC

J

[

SLOW SYNCH.

hp L BLOCK DIAGRAM LONGI]UDINAL A3J-I AUTOMATIC FLIGHT CONTROL SYSTEM SYNCH.

SYNCH.

BANK ANGLE i ROLL I SWITCHES BANK HOLD HOLD HEADING SHAPING

° I0

HOLD BANK GAIN

t

SYNCH, AFCS

't'

ENGAGED HEADING + SYNCH.

HEADING HOLD HOLD '1 HEADING LIMITER NAV _ SHAPING STEERING ERROR HOLD BANK GAIN i BLOCK DIAGRAM LATERAL- DIRECTIONAL 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'_ _ I !._k,._.j_ illrROM'--m. I lli_:_'--_.., II H IIHT, r

HIIIH

'i \:. _rX__i.H_/

E

_-'_!.. _ -_J _j VERTICAL STA|ILIZEII. ACTUATO A''_ I

G'

• _-C_ECK VALV_ HYDRAULIC SCHEMATIC LEGEND n Y _JI'.A_J ;- tC /_ A3J-I DIRECTIONAL CONTROL SYSTEM STAN_ ELEVATOR SERVO AMP CURRENT "F_/_ _CH

" I

_ _,TCHT-- I_ I

I _ _'T°"I I I i

TRIM TRIM HORIZ STAB- ._PITCH LrJ TRANSFER HTRtMCONTROLI_HoRIZ'STA8' H I o_H_ F 4 (ZAS WrEGRATOR SERVO

-I

SWITCH 2A5

•

STORES I

'-[ 1 _'_ Ih I

, LOW PASS SWITCH I HIGH PASS FILTER I I I I I PITCH I, _111 FILTER I

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

_D [ GAIN I _ 5PEEDBRAKE r--- .......... "-'I , AJB-3 SYSTEM , HOLD ELEVATOR F 3 (l_) I , om_u. ," AMPLIFIER I L ........ .J ALT. o ITU_DE_ ALT I iNTEGRATOR I I SIN 8 RESOLVER I ' I eliB_. , '

t L_;';_--_°] ":'

Jl_ ......... Jl ATTITUOE - - .........

I f"Tc" I COSe ] _-- _J INTERLOCK _,o i I TR_'_I A-4 Elevator Channel CSS Er_.

Stondby Headin_ Synchronizer Servo A-5 Roll Channel RUDDER RUDDER RUDDER BANDPASS SERVO VALVE ACTUATOR DUAL INPUT _t FILTER AMPLIFIER I I I I I I MECHANICAL AF -- FOL LOW- UP LOST MOTION _.J LINK RUDDER PEDALS PILOT POSITION OR TRIM TRANSMITTER YAW RATE Fs (IAS) GYRO A-4 Yaw Channel i.,'r,c_'rO_T--'--" 1 zoo'."_ _" .......

-- I L._.. _ ,,#C_ I i I I pATC'O_ /t l,"o I "_'_#'l"°tl _E_vo I _#lAy,_l I _r_ F;.ap .S'cJ I S. JC'_ i _ F "t_l _'_: A-7A Pitch Axis A-?A Roll Axis _P F'D z UJu, I-U P Pd/l l_ // Y'D SE_VO lye r/l,# FO,_

rAW iC_A,vaIF,.-I sw :_s

#IAFOIVlFOR Fo_-uP _2 f occee_ uP AILE,_OAI UH T MU/.TI- fOSITlO_lj l PLIER Ot./A I.

A-7A Yaw Axis LATERAL ACCELERA.TTON I ies 1"t!9 J (VOLTS) B-52H 1.0 AIRPLANE i CrT/SEC21 -[ ACCELEROMrrER__ EQUATIONS OF MOTION | YAW RATE BS 695 J RATE GYRO l ] (s:_'l.e_is2._5o.62.5001 I [ _DEG/szc) "1 e75o I f IMPACT PRESSURE I I _._ (VOLTS) d S2 GAIN ra I SAS ELECTRONIC FILTER _.__ (S + .033} (S o ,25) (S * "/)2 !

SAS SERVOI. /_ [SCHEDULER ] J 10.5

I I

S 2 SCREDULER SAS ELECTROI_IC FILTER F .... J (VOLTS) (S + .033) (S + 1.5) (S + I"l) 3 • _ GAIN B-52 Modified Yaw SA3 Block Diagram MAllei POWER RATE GYRO pITCH RATE ELEVATOR B-52R ACTUATOR & ELEVATOR (BS 1327) MOTION _ AIRPLANE w 6,750 7.395 X !0 T (DEG/SEC) (DEG.) _ EQUATIONS OF MOTION $2_139S * 13,500 (S ÷ Yt,6) (S 2 + I50S * '*5,350) k i I I I I I" ......... !

IMPACT | pRESSURE I I !

SAS ELECTRONIC FILT]_ | 93'7.5 S 2 (S ') * 79.1S * 12,800) SCREDUL_ (I_.)

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

)

B-52 Modified Pitch SAS Block Diagram .250 v/_eu'sec.

RATE GYRO PR.E- AMP AMP- DEMOD : SW- MOD.

MOD PRE-AMP H AMP-DEMOD _ RATE GYRO

l _ H _,_ F_

GAIN CONTROL _°_w_ e"-] ENGAGE CRANK 1 SERVO DISP. __._ [TAP /"_ _ POSITION--_ _ _'_ DISP. FEEDBACK V CRANK POS.---_ ) _- GAIN TAP.

SYNCHRO "7" _ e3 c_ CLUTCH _ _ _ SERVOAMP" _ _'OLM_L_VRUP _$, "----0-- .................. SERVO---_C--RATE GAIN " ................ t_-_--- ITRIM METER] B-52 Original Yaw Damper COMPASS SPOILER MECHA_CALMODE !

FORCE !

= l STEER_G -- L_K !

COUPLER

I-q WHEEL }

!

GYRO ROLL A UTO- LAT.

MA-2/A-14 AUTOPILOT TRIM STABILIZER[ SENSOR MOTOR _ _ BOOM _ REFUEL ARSS & LL AMPLIFIER COUPLER ARSS & LL i

/ ^u,o_ |

I PITCH _L_ PILOT _--_ SERVO _m_ELEVATOP.S[ l PITCH GYRO

t

I - - L_K I !

I I ELEVATOR MECHANICAL MODE L .... ...2 PEDALS _q RUDDER I RU_:_ER

! ___DER I_

ELECTRO [YAW DAMPER I MECHANICAL -_'_ CLUTCH RATE -- -'_ ENGAGE l YAW DAMPER I YAW GY RO / SWITCH I I f B-52 Original AFCS r _ T I !

I I I I I I I TRANSDUCER PRELOAD AMP I PII.,OTS PITCH 'tl _ CIRCUIT DEMOD , ,, COPILOTS _ NULL I PITCH , ADJUST i I I TRANSDUCER Dis_ I I I A/R II ADD TO SERVO I L/L DISP-'_'O'_ DISPLACEMENT I ___.._ L/L I CHANNEL CIRCUIT I I SERVO I . TO THRESHOLD CONTROL CIRCUITRY THRESHOLD OVER POWER D TO OVERPOWER FORCE CIRCUITRY CIRCUIT BOEING __ SWITCHES GATE NORMAL 1 CIRCUIT ACCELEROMETER I "G" GATE I I J STICK STEERING COUPLER AUTOPILOT AMPLIFIER B-52 Longitudinal Control Wheel Steering , -I PILOT'S ROLL A/R D1SP.

TRANSDUCER PRELOAD MOD CIRCUIT I :__ TO AMP. l DEMOD.

AMP" H FILTER _ • _ " DLSP. INPUT[ ROLL L/L DISP° I COPILOT'S NULL TRANSDUCER ADJUST

C_

A/R RATE GATE

AIMITIs I

LTO >8" !

.[HEADING HOLD[

I

CIRCUIT I CIacUtTa_ ] L-- AUTOPILOT WHEEL STEERING COUPLER AMPLIFIER B-52 Lateral Control Wheel Steering

WASHOUT

GYRO ] [ SERVO,

iACCELEROMETER I n-1

TRIMAUTO "} ELEVON

ELEVATOR

_j._ RATIO I I _ "_-

LINKAGES CHANGER I - I v _.J ELEVON L --_

, P --IACTUATOR I-- _

FEEL &.H

I YAW RATE GYRO

TRIM.

CHANGER [--_ :L__

LINKAGES..H RATIO l_.J,,m J 5a , r -- - II

A/LERON

J l ELEC. LLJ MECH J

;.1_ DAMPER ,-.I INTERCON

SERVO "I [INTERCON,I v I

ro o

DAMPER L RUDDER L_a.r._ W

._,/"I 5ERVO I -"/ ACTUATOR I

I YAWRATE 6YRO

LATERAL J

RUDDER

ACCELEROMETERJ

__-H FEEL& - TP, IM HLINKA S I

B- 58 Stability Augment at ion

ELEVON

ELEVATOR A/P RATIO M I

B&N

,SERVO ,jil CHANGER

X

SYSTEM

E ACTUATOR_

I

R

I

I

I

B-58 Attitude _tabilization Mode Pitch I I

B_N

SYSTEM AILERONA/F SERVO ro ro

RUDPER

B-58 Attitude Stabilization Mode Lateral

Control St/ck 5t#ering

STABILITY

5Mtch D_r#ssed

AUGMENTATION

MODE

C.S.S. SWITCH

SWITCHIN6

SUBSYSTEM

r_)

ATTITUDESTABILIZATION

AND

Control Sitok Steering

OPTIONALMODES

5##ch Rele_seo'

B-58 Control Stick Steering Mode

PITCH

RATE

WASHOUT SERVO

H H DAMPER

6YRO

n-I

: TRIM

OMETER

ACCELER-1 AUTO

ELEVON

STICK ro

AIR DATA REPEATER

4=" M,XE_ tl ELEVO.

H MACH-ALT

SYSTEM SERVO

ACTUATOR

_ELEVATORI I

RATIO

Icos e

CHANGER

B&N'

SYSTEM

"_WASHOUT B-_ Maeh Mode

RATE WASHOUT

6YRO SERVO

ACCELEROMETER i n'l

i AUTO

TRIM

MIXER

I ELEVON

t

ELEVON

SYSTEM I ELEVATOR

I I WASHOUT STICK RATIO

ACTUATOR

ro

,COS@ _- i -_ _---'IAUTOPILOT

[ SERVO

i ELEVATOR

A-h I CHANNEL

IINTEORATOR

I

AIR

ALTITUDE AM

DATA

- SERVO6- --

REPEATER

I t' ENO, NO

THROTTLE _,l _._

SYSTEM

]_t MACH I WASHOUT

SERVO

B-58 Math-Altitude Mode

BANK

ANGLE

I IINTEGRATOR

_.J- LAT, ERROR

LIMIT ELEVON

DO 0"_ B-58 Constant Heading i 5TICK

INTEGRATOR ANGLE

LIMIT

ELEVON

E_ r-

I

B&N

AILERON

SYSTEM

"LI ELEVON 16_

A/P

_ MIXER

SERVO

I IACTUATOR[----_

ANGERIF

_IDAMPER

GYRO

ROLLRATE

L SERVO

TERCONNECT I"- |INTERCONNECT

I YAW RATE GYRO

ro -.i

YAW RATE

I DAMPER i---._/ IACTUATORI---

"I')'

6YRO -_I s_Rvo

RUDDER CHAN.

INTEGRATOR

RUDDER

LATERAL

I--

ACCELER-

OMETER

I

LATERAL

Ay

ACCELER-

OMETER

B-58 Heading Nay Mode

CIVIL NAVIOA-

_E. LAT.TRACKL _T,rv

TIONALAIDS

COMPUTER _ BANK J , "_"_.

SYSTEM

(Seam Error) _ ANOL.E[-7 _ _

I , ' _ I j II ELEVON

B&N

SYSTEk4

l , ,J_,. IAILERONI[VRATI 0 , -" , _-_

¢ YN H A/P ELEVON _a

}-_S C P,O_ SERVO_tCHANGER_"FL'>" I MIXER HACTUATORt-- _

ROLLRATE

GVRO

YAW RATE S SEL__ I ELECTRICAL L.J MECHANICAL J

po co

6YRO

//INTERCONNECT//INTERCONNECTI

YAW RATE L,-N/ IDAMPERI L'i"_jRUDDERL ar ./ d___Jl

GYRO

- -- _ =l SERVO I---'t/ IACTUATOR/---/ I

I

,....!RUPDER CHAN,L._ / I

J JINTEGRATOR I I _.

LATERAL J

a_ j " ' -'_]._-- RUDDER

AO_EEROMETER J

J LATERAL

ACCELEROMETER J

B-58 Localizer Mode R_rE WASHOUT SERV 0

P TCH HO MP

6YRO

MIXER. J ELEVON

J ELEVON

ACTUATOR

DO B-58 Automatic Glide Path Mode I PEOAL i i POSITION i F P-AN_'JCER$ f I(=) tlql_ mJl:_3E't AMI_..I ¢IER CAR_.S $ERvo " (ql [SYNCHRONIZER l (rc) SERVO _ &ILERON tlq) _(kMPLIFIER i_]. CABLES LOCALiZER O R EC...IV ER ,.J "_ Ilq) PRESSURE CONTROL STATI C _ ALTITUDE p'_"_ i,_-._ CC,NT ROL IL$ "] = IGLIDE SLOPE VALVE t r EL_v_ TRiM _TUATOR 1 (LOW SPEED L WINDING) _rc) |NO_,_T'_ llLOO_ F'_I_*TIONS W_qCM ARE PA f_T _F_ TH[ F'LJ_I4_ GON'IT_L.UE_ |(q) IN'_lC_'l'__S CAIN IS VAqlED A_ A FUNCTION :_r DIFF"L'_¢_:T1A_,. P_I[S_E I ('I"AS) tN_'1_$ GAIN I$ VARi£D AS A FUNCTION 0_" l_tl r A_ $PEE_ C_x'rA IN;_ B-66 Autopilot k_4 XB-70 Pitch Axis Augmentation ACI_TO,_ I ._ I.[ L'Ls'vOX I----)" 1_11o_ Q..4 CopJ.1o_ I'_-'l - '_ "_', _ ._ =,_ I I I _ _u_o. --_" _' I Nm _ _J x_ I _ _o.+ -- - _- <Te _, I e,_ _.-._,,_ I AC'P_TO._S - + _ , " I I , --I ÷ G'£T_O$ - I I DI_I, • i ±_y_,, ,-- + mML _ PALA_: XB-70 Roll Axis Au_ment,ation ,r, | !

6ms -+3'_.- + _v X.r- X£ _.

/ _°-*_g° I l 's'' "/_J

:LI.0 _8/se¢ C'/.A;::_L -- +1 3s÷l _/s i ._ ,/d.:do_ XB-70 Yaw Axis Augmentation I_I_I_A L & AUTOPILOT INPUTS Kql = 0.5 PITCH q I RATE DEUI Ei _ LIMIT I CYRO I • 0.05s DEG/SEC +_10 DEG I _ -11+0.1 s INBOARD ACTUATOR ELEVATOR kJ4 POSITION 4z- Kq2 = 2.0 SWITCH POSITION: 1 PITCH AUTOPILOT OFF PITCH AUTOPILOT _NGAGED C-5 A Pitch Stability Augmentation System I ROLL I I+0.05s _LL DEG/SEC A/P ON MANUAL & AUTOPILOT INPUTS CM)C] BENDING ACTUATOR + FILTER + GAIN, G SCHKDULED _)_ (1+0.06s) 2 I+0.25s

+_3oD_

ka4 k_ SAC GAIN SCHEDULE 0.48 G 0.055 , !

40 125 DYNAMIC PRESSURE, qc C-SA Roll Stability Augmentation System (SAS)

dsc uL l

DEG. -I GAIN,GI MANUAL & AUTOPILOT INPUTS BENDING FILTER + ACTUATOR _R 4 + _I SCHEDULED I

(1+o.o5_) 2

1+0.2_s DEC.

DEG/SEC-I GAIN, G2 I+0.05s + +20 DEG GAIN SCHEDULES 0.34 G1 G2 0.157 2.58 o.78 0.07 0.32 , i J 0 I I i 40 10o 230 4o 100 250 qc qc C-5A Yaw Stability Augmentation System (SAS) AUTOTR]M 70 190 70 19o kJ4 PITCH TRIM lq;OB DEO C-gA Pitch Autopilot: Inner Loops PROP n. - F_ (50_) GS - GLIDE SLOPE RA -RADAR APPROACH LIMIT 'r- ) SEC PL _ .I SEC fflg-I__ hFT RADAR ALT Ih_IBITS NOSE-DOWN INTEGRATION I + .5S (_ou.-o_) C-5 A Pitch Autopilot: Radar Approach, Glide Slope and Flare Modes INTEGRAL 0¢ DF_21 PROPORTIONAL 0c Dim V'J_AV COMPU_"_ DEG TERRAIN FOLLOWING DEG IAS - kt I O. " "_) VSFI C-5A Pitch Autopilot: Veruav, Terrain Following and Mach/IAS Modes Integral Proportional

%

%

Altitude Capture dee deg/sec

VSFI oI

_ Limiter I AC 7000 FPM Altitude Hold R.O.C.

ft/sec Y@ _cJJ@ CADC I h Height Error f_ "° _'"° AM C-gA Pitch Autopilot: Altitude Capture and Altitude Hold Modes 4O DEC,

SY_IC

I ATT

-_HCLD

DEC

r--] FI_.PS • 0.19 DEG.

TH_HOLD o_ _o_ I ....

HUB

FCRCE

LB.

±2.7LB DEADSPCT C-5 A Roll Autopilot: Inner Loops Including Control Wheel Steering

INTEGRAL

+I ÷

DEG

DEC

_ LIMITER _ .

PRETRACK

BEAM

+ +

ERROR

+I +45 DEC, _e COURSE CUT PROPORTIONAL y/e DEG COURSE ERROR (SINE FUNCTION) TACAN > 62 NM SUB -MODE VOR, ENTRY TACAN _ 62 NM CAPTURE 5.4 NM 5.0 DEG PRE-TRACK 2. I DEG 2.3]_ 1.2 DEG 1,3 ]_ TRACK C-5 A Roll Autopilot: V0R and TACAN Modes CK I I I INTEGRAL I I _ qc

, l,° i

• 4S _ I 'I, _ DEG.

CTD I

NAUTIC_.L

MILES

l qc PROPORTIONAL

_/e DEG

TRACK ANGLE

ERROR (TAE).

SUB-MODE CROSS-TRACK SINE FUNCTION. ENTRY DEVIATION (CTD) CAPTURE 5.8 NM TRACK 0.4NM C-SA Roll Autopilot: Courseline and Air-Drop Modes

DEG

_5.631 I "--_'[ i+1'6s" ] ROLL AMPLITUDE SUB- ANGLE LAGGED ROLL LIMIT MODE 25 DEG CAP, TRK 7.5 D_ GSC INTEGRAL ++ D_ I+O. 5s ERROI

,.%

GsC & _-A _ Rc

+ . I - _C

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

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

)

+ 1 + 478 TRK SUB MODE RA ENTRY 2.0 DEG CAP CAPTURE TRK TRACK 0.67 DEG GSC GLIDESLOPE CAPTURE RA RUNWAY ALIGN 20 FT hges r TOUCHDOWN RO ROLL-OUT C-5A Roll Autopilot: Localizer Mode, Including Autoland ÷ w k_ ltA_t ÷ PITCH AUTOPII_ BG 489 B S'*qTCHI/;G $IG.qAL )'(_ FlaRE RETARD _0_g@_D *FCS DIRECT THRO_fLE MODE CO:,L'#L%IFDS CONTROL

t _

C-gA Autothrottle Analtyical Diagram _M Ah _e -_ AI RFRA_J'E $4-

E

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

KC-135 Pitch Diagram AIRFRANE --_

E8

1.4.'/S,¢ L__, gr _[ ax Llmff J I / H5 Heading 5e|ect TC Turn _Oemand L Locsllzer KC-135 Lateral-Directional Axis Diagram I I I Coa_.rol _c_ I

I

] !

:1

I

J

Pcver Control XC-142A Pitch Control System Block Diagram CO XC-142A Roll and Yaw Control System Block Diagram Tea ".J_x-'L_ I -- I I I Tea_T_ T_

I

r $- kO GOLI4etI_ Feel I_o_t _og _rs A_tu_tor Tlxr_ .-_le Diac_o_ct _v_r_ (_) XC-14_A Collective-Throttle System Block Diagram I I DEMODULATOR_ "' I SERVO I I _J CONTROL I 6AIA9 / l WHEEL I EGI79AI /FEEDBACKI ' I EGI55A3 / PITCH I r--I i EGI55A3 I SERVO L_J ELEVATORLJ .__._._ EGI56A4_ PRE- AMPLIFIER LAG / FORCE _--_ qc I'-)l AMPLIFIER I EGI56A3 I _- AMPLIFIER AMPLIFIERI "I SERVO I 6AIA. I0 I 1 /TRANSDUCERI LTJ I 6ALAS I 6AIA4 6ALAS I _'AI;_L'_ E L I J HIPASS BYPASS

. J uP i

K DENOTES A MULTIPLIER CONSTANT ALTITUDE ._[ ROLL I ATTITUDE I "[ELEVATOR I A ENGAGE qc DENOTES AIRSPEED SCHEDULING I o R CSS DENOTES CONTROL STICK STEERING C R o EGI55A4 A o 1NTEGRATOR INTEGRATOR F -)l EG156A; =' t_ CONTROL "I ALTITUDE ___.

6AIA7

ALTITUDE I

,, 6AIA6 T ENGAGE "ICOMPENSATION

J BANK }___

EG156A4 }

DEMODULATOR I

6AIA3 I /

DISENGAGE /

382 I CSS EGIBOA4 II

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

-I P'TCH I

L 6A,A2 j? 6AIA, /

_7 ENGAGE E-IB Pitch Axis I W W , , 4_ .rl I IV_P- -- t-_ ,C _o_ .-I _q pq !

n,,, Iv) l,,g _,) w_ w m m 0_ I_) T | _--__

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

-3

I DEMODULATOR r(- I SERVO 6AIA9 ,/ |FEEDBACK (" WHEEL I

EG,SSA31 EG,79A, I I

__._ EGI56A4 I PRE- I SERVO I JELEVATOR

PITCH I I----I I

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

] OO.T_LI FORCE _ qc _

6AIAIO 6AIA8 I TRANSDUCERI L._ I

I I 6A,A4 1 6AIA5 1 '

I HI PASS BYPASS

_ J uP I

I SCHEDULING °° I

ATTITUDE

T

I i ELEVATOR[

ALTITUDE

L_J SANK ]

ENGAGE 0 "[ COMPENSATION / SCHEDULING INTEGRATOR INTEGRATOR CONTROL EGI56A2 6AIA7 ._ ALTITUDE 6AIA6 LIl ,, qc | ALTITUDE ro ENGAGE LIMIT MONITOR ALTITUDE I_I APN

EG,56A" I

DEMODULATOR k

6AIA3 I

.... D IScEsNsG A GE EGI8OA4 K DENOTES A MULTIPLIER CONSTANT AMPLIFIER ATTITUDE qc DENOTES AIRSPEED SCHEDULING 6AIAI

I

._ PITCH CSS DENOTES CONTROL STICK STEERING _ENGAGE m S-2D/S-2E Pitch Axis (---t-- "1 ., co.-_.o,_ I _ I s_.vo I ', WHEEL _" I A EGI56A4 .I EGI55A3 EGI79AI 1 ROLL EG 56 3 CS H EGI55A3 S SERVO IGH =,RANSDUCERJ = OA3A, FAGj IDEMO_TORI CASS I _3A7 / -_"AMPL'F'ER, A3A., AMPL,F,ERoA3A, ,ER._"o j A I C . HEADING R CONTROL A

---*( _ DEMODULATOR CSS DENOTES CONTROL STICK

. I EG'56A3 1

_' [ 6A3A6 HEADING (_ STEERING T • _ DEMODULATOR I ATTITUDE i._ ROLL

T I 6A3A3

i

I II 9373B2 IIEG,BOA4 ,SENGAGE. CSS.

SIGNAL _ HEADING _-_AMPLIFIER : "/ CONTROL i i 6A3AI .__" RATE I 6A3A2 $ ENGAGE E- 1B Roll Axis .j CONT,OL I . I sE,vo I: WHEEL 1 I I" ' I . IFEEDBACKI ; ROLL EGI56A3 CSS S ERVO HIGH EGI55A3 II / PRE- AILERON FORCE DEMODULATOR,. IAMPLIFIER.

L_ DEMODULATOR PASS AMPLIFIER AMPLIFIER SERVO J

I,,, "

TRANSDUCER 6A3A9 6A3A8 J I ] 6A3A7 / 6A3A4 6A3A5 CONTROL EGI56A3 qc DENOTES AIRSPEED SCHEDULING 6A3A6 HEADING STEERING . ROLL DEMODULATOR ATTITUDE 6A3A3 ._ EGI56A4 /H 937382 ___ EMGIBOA 4 DISENGAGE, CSS, • ROLL CONTROL RATE 6A3A2 [ 6A3AI NGAGE t SIGNAL A PLIFIERj _7 EEADING ._= S-2D/S-2E Roll Axis _3 STABILIT.ATION RACK

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

!

F L"--L_........

STABILI;ZATION RACK

÷L_2:/::,.

RACK ROLL G)'R---'_ I STABILIZATI ON L_$'t F]-:222 .......

Regulus II Lot I Autopilo,t c i i.

i-

i !. e°'-"A .I i_

MODE 1 MODE R .

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

! GT_IDE _TCHLgG ! _,0,._"_ & AL2ITUDE _-- PRiG ;--- i , k.,TI !

't.J'l

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

, _, i _ _----_

!' "v'z_ _

ELE- ° .... .

_'-_ ....'_'_ 7 ,_/'i'iX!_ .

___ a.- .... f _', I _m_

! _ " t,l+ _ s t _)_ _ _i \ j W;'.._: - m-

I _ _m_ ioo /f i! #, ' \ . AI'OR t i .................. ' _ ilI \ _. " i

i

1__..t

I _ _"-"'_ _- ' _ i i t sY_cm_o !

t __, _ I _ _lh ! _, _'tS'_ . o . G- 2 P' c O,'_#_h"D

i

i

iI I , , t ....... • ....

i Q-2C Longitudinal Control System IqlGHT TI_ !

!

x_

I !

!G =

s_o

Q-2C Roll Control System (s+40)(s+lO0) _

I K_s I

Derived Rote I Launch '+ _,_+ _ 8 (V.G.)

Condition Bias

/

Fitter AltCont. _'h Scheduled _b=f(h) Pitot- Static Rlter System I s+lO

I-

_'uS+ I IAS/qc POT IAScuo.

BqM-3h Pitch Axis Der.

Head.

A/F (V.G.)

_I Actuator

--

IAS Derived Rate co

s (s+ 401(s + I00)

+ Is_2 l- B_,[-34 Roll Axis kO

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

MQM-74A Elevator Control System J VO _.'T'$ _l ' o ..._ t._ _, _'e_ _ _T MQM-74A Aileron Control System

F3H PITCH C}L_NNEL

t_IRFRI_h'IE SE'RIF5 nlLFtf#_l AILEF_,;_I SEA vo $ (,_ ,qCTUt_'roR4 Ce_ANt,,_" c,,, y Po

"k

-

I T'RIM 10 X)EG /4 AN_'/,/V _ R VE',PT/ £F_,e CoNTRoL_.ER, I_._ _ l.,_,._.r I _ ,,J 0.35 Ri/,JCF L,£F: 3[,0 _e'&

l r li,÷o._s

_^&¢, i O_ ro <;;-& o/'_ _....% co_'lP/_.s5 "I'o.25 I I . _ ---ki_ FN_ ^&r RJ'LII _: i i i m i FDH ROLl CHANNEL _ TC _ A/N CAHClELL_I_ SERIE_ RUE_D_'R _UDD_,_ G,y_o r. NA_GE ._ R vo RCT_TO

©

:o.5 JNCM _--5 °_R F3H YAW CHA_L L.YNO

[ '"°'"'E I

28 vOt.TS DC CONTROL AMI_tF _R , t r ] IN .t.r C S I • 2 I/2 LB _ AUTOMATfC MC,'>! _No C - ; FOIEE PIT CPI _' R _ h'_ I _o_s _--_7

r;__--: _! --11 '_ ITHIN C'_, LI-INK SWITCH I-' .... "l CIRCUI,'_, I

C A,_CE It. [R .__T--__J lj ...... J STA_ lI.A' OR /""_ I I r:AIN (C_t) I I _ I I |O _G _.IMITS I I L____J ' i l_..... "I I PITCt_ 11 ^Ll ,, I U_.'C I ION I I -_- -- .... T -- -- J" -- -1

'r li

AIIENuAIOR r F

I" ..... JI !

I t o-.'._,lo,_ : I MOIIONAL I It- ..... -I PICKUP GAIN (IASt) I PAqAtLEL I CYLIh#[_ER _'* .... _ TRANSDUCER I i ' C!IANC_._tR " ' I OPt P_T ION I I I t. .... j .... J f / STA31LA TOR POWER ! L___ rtIc,t PIC K_F $ _'NCHIiO- SVNCHI_O- .__.J CONIIK_L CYLI_._ R r'---- 1 NI._ ING NIZING I PITCH I CIRCUIT I PI ICll I IOttOW-UP F CIRCUIT I t, _-o j I. THO_E ITEMS SHCJ_VN _Y DUllED LIN_S AR_ NOT COMPON- I ENTS OF TH1E AN/ASA-32H.

I I GAIN (Ck: f ) L 2. TH_ ENI"IR_ DIAGRAM USED IN AFCS MO0{. TH[ I_MS WITH CHANGER SHADED OUTLINE _ UTILIZED IN STAB-AUG MODE.

I L ..... J A_S I AN/AJB -3A F-4B PITCH CHANNEL i INS _-411 ROLL CHANNEL ,_'G _T I O'_ CONTROl. AMPI.IFIER r OA_ 1 SPCIt-_¢_ ['T'_ Je"'i7 , SIAR_ .D . ! ,J / I I I 4L_ ! I H[AD'NGI I ROLL I t I l I YiH_ SI_VO I I , S_vO t CY_zD_ _ I I AT:£_- F "'PL'"" L'J I i. ....... ._ L ..... ._ ......

_ STA SOA:'_ I i i LATC-;_ILSEII_S _--'J"---1 F:_,',_K l / --t/ / --J l i f "_T" _'--'_ \ _\ \

•

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

YAW CHAINNEL CONTROL AMPLIFIER A;V RUDDE" t _Jb_[ R POW_ RA_E Iii CANCF.LLIR

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

.j Y_w ACC C _.r- RO.vF. T'c. R • I L_TERM_ __; Leon- Lo_

_,;., ] (T,_,I_ |]

_o_d I ('ra**l)

L.._J T,, T_ i _1_ ..... ii ii ill ill i YAW A_i$ DAMPER, Tffm ROLL A"XIS _2AM£ER F-8D _1 5uv 4'olce Spofle.rs.__ Ac_umYor

Ru,ldev (L_,utln_/

..... "==1=" I

, i_o,_o_o. //4ov_zovlfell

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

o% c_

I

RudS_v _evvo --/Ac.l" aorh)v

k t'

/

cl3 YAW P_M_&

q

F-14 F-86 Pitch-up Preventer E_7 / 8+!

TTi m F-89 Sideslip Stability Augmenter _8 YAW RATE i GYRO | I ROLL i,----E, TO RUDDER CABLES I IDIRECTIONAL h I TR!M J-Z COMPASS , SYSTEM cTUTR_0L ROGL_ %AT __:)" ]

/

_t

I SERVO I [AILERON ill

TO AILERON _ AMPLIFIER _ SERVO I'_ CABLES I LS LOCALIZER COUPLER |-- RECEIVER TRIM i HEADING ; (FC)

®

CAGEABLE I_ I LS I IGLIDE SLOPE II VERTICAL t . _ , .

I GYR0 _ i I

GLIOE SLO_: _ CO_,_LER

JGL_L_.44A__JI ! . i

h RECE'VER I I_.G,"O3'_A-, .._ _----.._ I SERV0 II [ELEVATOR I / I TO ELEVATOR r, _ AMPL{FIER _ SERv0 CABLES " _ I RGTO64A-I i_ - I MG7OOIA-20B I L I ? L,.. _ '

IP,TCH RATE i /

GYRO | - ISYNCHRONIZERL.__J

i F_c._ SENSING

_SWITCHES IN "1 ELEVATOR "FEE'," CONTROL I SYSTEM PITCH t (FC) INTERRUPTER L " .EVATOR • -_ ACTUA'_OR j_' TRIM .tFC) INDICATES BLOCK FUNCTIONS WHICH ARE PART OF THE FLIGHT CONTROLLER - WG187.B-1 SG3A- I b 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 F-89 Autopilot 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. A ,/_ CLOSI'D 10 A ON AUIO-IADS IIU_IN, 10 f ON ALeIO-LAIIS PULL+I_.

I CLO$[D 10 A ON AUtO-LABS PIJU.-UP.

10 I licit4 R01L-OUT lliLAY IS [kEII- R GIZ[D.

A CJ+OSED WHEN kUIOPILm IS 0IS(M* C G_t,,[D. WH[N IIAMK AMG£..[ (XCEDS 60 O, WH(t+ P11C14 AI_L[ (XC._S S_. WH[N MACH OR ALl COk']iOL I$ R [_,AG[D, WP(l_ C$S IS OI_IIAT[.O AND Dl_ltdG AUIO-LAi$ PULL-U/'.

A d_ CLOUD 10 II WH(_ 14ikCit OI ALl CONTROL IS [N(,.AG[D. _41GM GAIN ON VUOCIIY FUDIIACI( CAU.T_S MO-

-8 F

TOQ 10 IIU_ Wiry SLOWLY |1415 IS [OiilVlliflll 10 A HIC_I-FA$$ N[I'- WOItI( WI1H A LON*G TIM[ C, ONS_IAN],I T OPlll li_[tl AOIOPltOi I$ OISili- G_(0. WH[_ lIAr( _ [XC(ED$ iO O. WHEN PIICH ANG_ [XP.I(O$ _+ D_14G AUTO-LAI$ P_l-UP Akll w_14 C$S 15 OP'IPA_D CLOSED vw(14 G$$ I$ OP(llAI_+ ,/_ CSS D(_T(S COi_lIOL SliCK _[E1- II_- I_liO SI[ICK5 Cmllr-lOOF 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 A FUNCIIOII 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_.

PITCH CHANNEL F-tO0 D/F Autopilot 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,M

GENTERING I I,_ I _R,_ II '_'ULSE _ AO OST j 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 / NOT{S: A ,/_ OPEN Wt4[N AUIOPILOI IS rNGACED.

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

R //_ CLOSED DURING AUTO-LABS PUL.L-UtL c _ C_OS[D DURING AUTO.LABS PULL-LPP.

R 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

A F!

DUPING AUTO.LAIR5 PULL-UP.

OPEN W'_'W AUIOPlE01 1S DISENGAGED, WHEN BANK ANGLE [XCIIDS T

&

60 o, WH[N PITCH ANGL| [XCE[DS ._,0 O, WHEN CSS IS OPERATED AND DURING AUTO-_.ABS PULL-UP.

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

A

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 ; [ COMPENSATION j AUTOPILOT CLOS,[D WHEN HIA01NG CON1ROL IS CLOSED W_N/_ IS OPEN - ALSO E _,GAC.f D , Sr/,_SITIVE _ • p...

i_1 < F'''--_ . [' PHASE i. ,<'x_ I u,4 _R[.CTIFIER COM _::. J 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.

, ]

A CSS DINOT[S CONTROL SLICK STEERING.

SYNC AMPL p-_l SYNCHRONIZER I _ COMPASS / F COMPASS I AND MOTOR | /S_NCHRO RO'IORJ A_

A TWO STICKS AND INDICATORS ONF-IOOF CO/_IGURATION

I HEADING SELECT INOJCAI[S GAIN SCHEDULED AS A FuNCIION OF AIRSPED, R©,,. L I _ , LEAD R_TE NETWORK {. GYRO j L---..

ROLL CHANN_.,L F-IO0 D/F Autopilot SENVO _ _ I-1"H CO"T_OL ------ AvP___.. J I S_S_M m OS_RT STROKEr-'--'---'-'l __ s_Rvo I _ NONUNE.&R _. ! Y,W RATIE I.

R I I s£Rvo FE_=OSACK J C R A F --4 T ""J_ piTCH RATE %2:-$; '..c'.E, ST_'C/<(. AgO',,T 36.5_ F[ET I LIMITS OPEN WHEN RUDDE_PT.D/d.S ARE PRESSED.

L_ PHASE I CO:qF|GURAT|ON I_._ I CAT_.S GAI_ S _"_UL[D AS A _:LI_ICTIO_I 01: AIRSPEED, //_ OMIT BLOCKFOE PHASE I CONFIGURATION P I"TCH DAMPER ,_ INO'ICATE_ GAIN _,E'DUI._ AS A FLIk_T, iOMOF AIRSPEED.

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

YAW DAMPE_ F- I00 D/F Autop__lot A I R C R A F T I RATE ROLL I GYRO

]VERT'cALL

GYRO g,__IO'RECTIONALL___

COUPLER I"

_ _ ISTAeiCATORI I sTAemLAT°RI IHYDRAULIC/ ,---,'(X_)--,_O(pI SeJwa I---ff SERVO _ SYSTErX I--------'

r ,.,,_.-----il I ' r:.-_l

T i "" " I G,i'i't_,I

,,,T<:,, ,& I"':RT'CAL L

_'°"_"°"_< _/'''''°_':_'°"11o_,.,,, _ t_t o,,,o ,

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

RATE 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_ F-IOIA Aut opilot

'iSERVO I

NOTES: AMPLIF: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 -4 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 CONTROL I P_TCH ] MACH SCHEDULING I_!", ICK STEERING _ AIRSPEED SCHEDULING STABT.LATOR BRIDGE CIRCUIT __J_. ALTITUDE SCHEDULING F-IOIB Autopilot KOiES: OPEN WHENAUIOPILOT IS ENGAGED.

A

A OPEN FOR CONIROL STICK STTERII4G

MODE.

A SWITCH POSITION SHOWNFOP,BEAM

GUI DANCEMODE.

CLOSED AFTER AUTOPILOT IS EN-

A

GAGED.

CLOSEDFOR FI RE CONTROLMODL

A

OPEN FORFIRE CONIROL MODE.

A

GAIN SrHEBU! ED AS A FUI_CIION GF

U

AIRSPEED.

INDICA_S SUMMING POINT.

®

VERTICALGYRO T?

A

AII,E._ON BRIDOE CIRCUIT F-IOIB Autopilot TRIM NETWORK LAG PRE-ENGAG i SERVO CONTROL -- SERVO RUDDER RUDDER AMPLIFIER SYSTEM

I

SERVO FEEDBACK / HIGH-PASS YAW RATE __ _ GYRO NETWORK

F

POSITION _ _ A TRANSMITTER I R O R A F T GYRO -- - ROLL RATE J_.

NETWORK LAG LAG NETWORK

]A CELEROME F--

NOTE: RUDDER TRIM ADJUST THIS LOOP IS NOT IN CIRCUIT WHEN DAMPER

A

OR AUTOPILOT IS ENGAGED.

INDICATES GAIN SCHEDULED AS FUNCTION OF AIRSPEED.

INDICATES GAIN SCHEDULED ._,S FUNCTION OF M._GH NU_,,',BER, RUDDE_ BRIDGE CIRCUIT F-101B Autopilot

I!

5_s_e_ PARALLEL 6ERVO

I

Swi_'ch I _=orce

?

F-IOIB Stick Pusher V-102 Y_W DA_PE_ F--IOZ P_TC_4 I)AkSPEIK "T$ m Ts+t F-102 -q _0 F-]OpA PITCH CHANNEL F- ]O_A RO.IiL C_NNEL I I ,R / R f I_'I_ ,,n E

I__,.o.oTs_

I

CANCEL Z E_' 6 YRO KcS

.><--- (,÷,.,_s)

O_ _z_ zA rE,_'A i.

Dg- sup R,_ 7"_" I F- I05A YAW CHANNEL

_ I:#

!

MANUAL IViOD_} T)ITCH _A_P{:_ /v}ODE A_JD. A[:C_ [AO'_{_ ,,Arc8 [L i:rT R K:/_L I:'I[{" D_ACK

[ _:_,L 1

AMPL I C_ _ I

I

M[CI.JA I,P i CA(, _ I_ [" _ _I_CIC

I

AI: C 6 /'p _Lo'r'S'_ CMoxs.)

\t_P,)T_,J i ,_,'_, :_:,{" _o$ jL____ i J l AILERON !_ • , l_.ER0hl I. A,T,S l.Er I ELEVON i I ,?. ALTO ._ I!W.,'I_._. .... II I I ATTACK l Co iAa L AS i ro i ] t_u.

iCOMUMI_ !PtTC. __ ----!

_L_

]

-A(C$ F-f06 FbT I I a_. &_R. D_Ta L_ _.J eo_ Pu're_c _ P.UDDEe. _ RILR_ (30 k_ c_,Noc_ j f 1 |tJpUT_.') t=E£ I,.

F-_o6 !

Go F-I 1 1 Pitch Channel Functional Diagram CO ....... J F-I 1 1 Roll Channel Functional Diagram S'_T EM C, tdNS 5--_ : ,_ "_/_c_c ¥ =32.2 _-_-17 _'".c_'_"/'_P LD6 GE AI:_ Ay ON LLDGC_AR YAW I_T (30 O'_ I I

L

YAW CHANNEL FUNCTIONAL DIAGRAM F-I 1 1 Yaw Channel Functional Diagram PILOT INPUT

{

CO>LMAND AUGMENTATION DYNAMI C S STRUCTURAL SENSORS MODEL --m- LIN]<AGE _-<'_---¢_ FI LTE R CHANGER __ GAIN DYNANiCS

Co

PRE ZERO CROSSING FILTER DETECTOR I NTEGP, ATOR I AERODYNA>Ff CS F-I I I Adaptive Principle

_,.-==_--_ TO PRE-Ak',PL (FUNCTIONAL)

TO FOLLOW-UP POTENTIOMETER CFAIL-SAFE)

CALIBRATION

MODULE

BALANCE

SERVO AMPLIFIER MODULE

I

r'SHAPING AND TRACING 1

I MODULE 1""-. _ I

'F-- l_.J .... _J AIRSPEED

I POWER SUPPLY I I _ • l JI"_ I IJH_;AM_'_ I COMPENSATOR l MODULE I I DEMODULATOR I I / _ . I

-:-N AND I _ I ==1 p,TOT

VALVE DRIVE AND II MODULATOR I /" ! l=_ STATIC QUADRATURE REJECTION NETWORK I --'T'--'_-- I RUDDER I | J l i I Tram

l I I IFA'L-SAFE I ! '

I

' i I I"N_;_O"_'I ' _I P,LOT_ L--

I , ! I I I _l CONTROL I---- I SUPPLY I I

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ll_V 400 CPS R£G B.I- STABILTY l TO MODULES AUGMENTER I ACTUATOR 44V DC I TO PILOT'S CONTROL FOLLOW-UP AND FAIL-SAFE POTENTIOME TER I,'I_l-' I15 V 400 CPS I II_ V 4.00 CPS L, ........

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[ i i C O ' : _ : O L I NOTES'- DOTTLE0 LINCg INO_-._TIE S'LOCKS, TO BE INSTALLED IN _ _RE.

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AVRO CF- I00 Autopilot

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05s+ I I.__.__J- ROTE: There is no Pitch Axis in this auto- pilot.

FIAT G-91 Lateral Diagram 9 o BEEPTRIM _ TRIM COMMAND ._ MOTOR _SP _ei, r"- _ -J_ _ -T LONGITUDINAL INNER [ LOOP ERROR j o.

ELEVON FSp, DEFLECTI ON LONGITUDINAL_ _ BUNGEE INNER ELEVON .... ..t MECHANICAL L_ SERVOACTUATOR STICK FORCE [q FORCE STATI C P ITOT STICK ] TRANSDUCER PRESSURE DIFFERENTIAL PRESSURE x.o _a Y, MODEL _ CO.AN D __ OUTER SHAPING ELEVON r"t"TO TRIM ACTUATOR DEFLECTI ON Nz, I NORMAL -'- OUTER | FREQUENCY

ELEvON

aCCELERATION --_+_

,,Boo hl

_BEI':DING[FILTERSHAPING/I.GAI N I"1 AUTHORITY SERVO / ACTUATOR |

q, _KN t AIRSPEED

PITCH RATE Zq

i

Viggen Pitch Axis Stability Augmentation and Control Stick Steering Mode BEEPTRIM _ TRIM CONV_V_ND I"_ MOTOR I, r"- -- 1 INNER LATERAL i LOOP ERROR_.j AILERON TICK DEFLECTION FSL, DEFLECTION NNER AILERON M_c,_,c_L._J, STICK FORCE EARING j---"l SERVO ACTUATOR} LATERAL FI BUNGEE

I

STICK FLAP EXTENS I ON FORCE SIGNAL TRANSDUCER x.O IX.)

_,"K) DEL OUER L,_ COt'_AN D h _ay, _1 I--TO TRIM ACTUATOR DEFLECTION SHAPING _,__+ AILERON (_i BENDING HSHAPING SCHEDULED AILERON

IBODY II IGA,N WLVE SERVO

_ /FILTER I I I I iVALVE I'll

ROLL ,-_ SHAPING RATE |

I

Viggen Roll SAS-CSS Loop

FRp

RUDDER

PEDAL

BUNGEE

FORCE

N

I

y'

TRIM _r,

I_ATERAL

MOTOR RUDDER

ACCEL ERATION

DEFLECTI ON

p

YAW RATE

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l-i glLTER GAIN VALVE ACTUATOR

INDICATED

P,

ROLL RATE =i SHAPING

S '

I

AIRSPEED i

INNER

_J SCHEDULED

SHAPING[._ '

AILERON

*IGAIN I

DEFLECTION

I NDICA'[ED

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Viggen Yaw Axis Stability Augmentation System SP, _ei LONGITUDINAL INN[ER STICK DEFLECTION ELEVON ' I IINNER 1 DEFLECTION AUTO-IR IM I'_ELEVON l I" _ ( I NTEGRATION) Jl SERVO- u ey, ACTUA_ _#R N | DEFLECTION PITCH 0 E EVON SYNCHRO- SHAPING ATTITUDE ; F RWARD S'ERVO

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LOOP ACTUATOR

SOL,° .STATE

_.0 STICK FORCE N z +q SAS FEEDBACKS

_ATEo_SC"EOOLEOL,'.*

AIRSPEED _'I GAIN IALT.+

I_c._ou,_ol

BEEP TRIM__I=_.=_ - HOLD !

CO_AND AT/ITUDE ALTITUDE

._GAINf I

HOLD I ,,,H _HAPINGL._,,_SCHEDULED1 1 ALTITUDE I ALT. [GAIN i--- , HOLD I_ IND ICATED J AIRSPEED Viggeu Pitch Outer Loops _SL LATERAL STICK 8ai, DEFLECTI ON INNER L.J INNER I AILERON JAUTOTRIM AILERON L DEFLECTION._ ACTUATOR | I ay, E INTEGRATI ON)I "I SERVO [| (_ " OUER r--- AILERON

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_ ACTUATORI

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TURN -'1 GAIN I-"

._ FORCE #if CO/VWIAND 4' INDICATED TURN

I SOLID I

AIRSPEED SSTD I_, _ STATE L..]SCHEDULED I HEADING -_i SYNCHRO-I-_GAIN

[NIZ_R I" t

STICK INDICATED FORCE AIRSPEED Viggen Lateral Outer Loops GENERAL BLOCK DIAGRAM FOR ROLL AND PITCH AXES STICK MECHANICAL , GEARING J POSITION AMPLIFIER SHAPING GAIN 8= & AGTUATOR NETWORK MODEL ENGINES & R_E FUEL CONTROL FEEDBACK ATTITUDE DYNAMICS

I FEEDBACK

RUDDER HN'SHAPIN G I I AMPLIFIER PEDAL POSITION ETWORKS, ' I-_-_G_ L'-'t AND

/_ I S, ERVO

GYRO i I TILT LACTUATOR i

RATE

YAW AXIS

BLOCK DIAGRAM

VJI01-C Rate _ro I _ I Lateral 1 I _-p -4 commands _p - I directional I II- tateral-direclional _1 I vehicle I =i dynamics: ] Rate gyro _shout arm I structural filter I M2-F2 Lateral-Directional Flight Control System I _0 CO

I i

i I J

I

I

X-15 Pitch Axis Configuration Block Diagram AUTOPILOT i

' j

X-] 5 Roll Axis Configuration m I L q-- --- ×

E_ REACTION CONTROL

i i

E

I I I l NE_N_ .C,_CTIr_ I I I X-15 Yaw Axis Configuration 1 O0 & / _.. r.,u,-,-_, " _'_,_a vo k'dlyCl_ I rO_.LQW. U_ Q i I _o_.._ _._ I I ELEVATOR CHANN_

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B-707 Autopilot PO [_>

®

B-707 Autopilot U I[CqAU I CA I.. LI kl _'_

S

_;[T IrOI *, M&](II_iUM _"rATl¢ _ILAlli • --i= • .... , ..... _/... _/,._ _' oN @,*'_8 S L * .2_1S * T_. wo_.T RUDDF_ CHANNEL B-707 Autopilot _AS_C ?_TC_ STABiLiZER V, Zgs

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

I I I I I I I I

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Ok)TE_ LOOPS DC-8 Pitch Axis 13ASIC _,0Lt. STA$_L_ZA-_ION Vos'_io_ 6_vvo __-I E/M L S= _Os J

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

IJ

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IL_ OoC.

_C _OL.L PAT_ A_) NA,_/ _AODE_ Aux. May.

0,,4"o, el 12" " DC-8 Roll Axis YAW STA_,_LlY__AT/0N ILS O,C, _r'_ DC-8 Yaw Axis Lagged BEAM RADIO LAG J Bea_ Error BEA_ MODULATOR _ GEOMETRY LOCALIZER 2/S.2 I SIMULATION SATURATION Error & AMPLIRER

-I

V.O, RL.1/1.SS 1 J InLCgrator Cutout LATF_J_L A/P AI_ON CHAA."__=L Until B.C.C. 0_erates LOCALIZL_ _,q_ V. 0. R.

& For $H Operation I INTEGRATOR | ALTITUDE ATTE,=_U AT0 R BEAM 4 _/S=O.O?41S LOCI-_- OUTPUT CAPTURE LINIITER CONTROL i _

2---

W/S=O. O81/S VOR___._ ILl _E DATA SMOOTHER .,( t LO°C'{/.O. R.

0¢ U.

I LOC DIS PLACE_AENT I o m_ -q LPAITER I J_--_ WIS+W ......

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W = 1/10 V.O._ TRACK W = 1/3 V.O. _ CAPTURE ROLL AILERON • & /VP COUPLER LIMITER DIRECT GYRO I S ERVO & A/P COUPLER VERT GYKI_ 1 I RUDDER SERVO L- 188 Autopilot = GYRO AND PITCH RATE A/P COUPLER GLIDE PATH MODE LONGITUDINAL A/P I LL _ I VERTICALGYRO I ELEVATOR I SERVO I "( OUTPUT LIMITER I m u DISPLACemENT i i - 11 LIMITER

I

I • _-f: vdt-/

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I

Co ._ INTEGF,. ,R _it Switch "ON"

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I 6]Ide Slooe INTEGRATOR Engage INTEGRATOR

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Engage; i700' O isengage;200' RADIO LAG

: I MODULATOR

3 It AMPLI FI ER

Beam_Reference E

$÷2 Beam Error

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I ANALYTIC MECHANIZATION OF BEAM ERROR L-188 Autopilot

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Present Heading Swi ch J> J WASHOUT SYNCHRONIZER l ' Cl_,_ed [ J'__4 Sec after AlP engage !

I_.. _ _ I'.--.=i _=,,,,o,, A/,ao_a,e I

_VP IL _ I I Reference -_7 \ Switehfor PSHCl°SedMode [ t4

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

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

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[ HYDRAUL,CRAM J I

' I

I I

, ¢ j VERTICAL .i, XL - ,-----"i GYRO& j

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FEEDBACK < i IA/P COUPLER] ".O

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g l

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RUDDER S ERVO l RATE I FEEDBACK jL" -- ]x.p t I{' ] YAW RATE uJ --_GYRO & A,' P LINKAGE I I AMPLIFIER I [ COUPLER ] & MODULAT- ri- J RvoT_ HYDRAULIC I i.

M.

l AL J ACCELERO.

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$ POOL Switch Open when A/P Engaged I AMPLIFIER I I _______J----_, '.(ETER J J, J F-O"".1_-_ Fixed Exc

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L- 188 Autopilot I

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I LOHGI_u_DINA L

I

RATE Xmp FEEDBACK -- ---- 1

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J

I

SERVO AMPLI FIER GYRO & AJP- LINKAGE AMPLIFIER & MO'DULATING -- -- _._ PITCH RATE COUPLER

I

PISTOH I , t

I

SPOOL

I MAIN BOOST I

J

HYDRAULIC

I

RAM

I

, I XL I 6E 6E/Xp LI.

._ VERTICAL GYRO J L-._ m _ mv/e,2oo NV/Pe_. J + PROP ERECT to _Deg.L_ Erection Rate= I - I 0UTPUT LIMITER I _ iJJ -_----_ ,f2O Peg/SEC/Oeg. j

F

SYNCHRONIZER ,,,( I _ Switch Own when 1 u.

A/P Engaged i

ALT SENSOR I #' INTEGRATOR ' I ; P--o"_ FIXED EXC, |

t

AIRSPEED ERROR COMPEN$ ATION FLAP POSITION '4" TRANSMITTER i & ATTENUATOR e Pitch Control 1 er Up lit itude J L- 188 Autopilot

[ I

PQaCE I PLOT STICK- ._ (I+A,S+A, Si)I'Iz ._ FgNC( i I roSE Sill 6 -,nc_u_r I ELECTRICAL GNN ou_t.rnJOE j C_MkIANO T(RM RAI"E G_mO LAI; ClI_:UIT -----4 t 1+2(I)S 4" "--_" _')tSI 0(G_JEC I: _'--t * 4.7 V(_-TS I÷_ VOLT 114_Sf_qS_q NCmUU. _ S'_&IGHT THJeJ 6A/N 14" _(L06)S 4. s8 9 1.2 VOLTS I F_ CUtISS TIP_ _STANT s LAPLACE TRA_SFOP_4 VARIABLE STZ_K MOTION Q_ANTITY STA_ILATOR DEFLECTIC_ I 2:2_ 10_O7)$ _CY OF SHORT PERIOD N(X_E KZPt_RAJ_ ]4OT'r(_ QU._rl"r'l'Y v _CRSPIU_ IIOI_IAL AC_LERAT IOi N_ o GESAC Pitch Channel (F-4A) - z.o --_

I+1

AIRCRAFT CAIN _I_OYN_S/MCS AJ_t.IFR_ S_mE5 58m_ LOOP _ ROL.L RATE S VOLT _ = 14"GI S iNCH I 12.7 DEG AlL b °++ °Is, __ 3 46 Va.TS m-io+_1-1,+ _F I'*'-1 I _'1 I'+_+_, ELECTRICAL GAIN COMMANO TERM LAG CIRCUIT RATE GYRO I+ z_'s+ s e oe_sec .

i ATTITUOIE GAiN W _GNN ERROR TERM oz+P

I -I-

IC_. e._,,+,u_ C_s4CI_.LI_R 8_ - _J_:_os VEFLZC'rIOH

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

- Ro_ _-

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GESAC Roll Channel (F-4A) RUO

_.- -°

OEG RUD

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GAIN I S_RIES _ & LATERAL.

CHANGF_R _ POWER BOOST _ ACCE1.ERATIONAT CG - VOLT I-m.d_.J_ . 21 s S 2

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II _-_ I

CANCELLER -IJuP_,c]g 'rR;mSFORM V,_ABI, E of _ RUDDER DEFLECTION w-FREQUENCY OP DUTCH ROLL MODE AI A2 -AIRFRA/4E. MOTION QUANTITY I 274(0033)s VOtTS_ V - VELOCITY ! I+(0033)S VOLT _..-EFFECTIVF CONTROL MOFIENT ARM FROH CG _V - YAW RATL - YAW ACCELF:RATION GESAC Yaw Channel (F-4A) F_, I $Y.1 s",1o.5 s+l_._t . ±;

I

._"-,..__6_s+,._7._1 ] i, "¢, BENDING FILTER I lOWLy SERIES ,SE,RVO POWER ACTIJATOR c.,_Eo_> I },,,, css -w Adaptable FCS Pitch Stability Augmentation System (F-4) STICK FORCE l LATE RAL [ (LBS) J

I

RA O/S[ E I ROLL RAT+ k..n RAD/SEC YAW RATE Adaptable FCS Lateral-Directional Stability Augmentation System (F-,4) I +0.3S

_,-F' _[_,_,. ,._

ACCEL. O+S.)_ "i'O.,2s) CIRCUIT J d -.35 i _-,,a S IPIrCH_rrl ! _=S 5 VALUE i I -Z_.j ,

! "_'° F_,+o._s.s

RAD/_Ec

I I IA,,,o,.,,', I

I ! _-_ VALUE I_AD .

[E L E VA TOR'_ !P°""°" i-7 z_.z.

NOTE : Z_ - 0.,2 1+0.35 Adaptable FCS Flight Condition Identifier (F-4) I pITCH ._A_; J ,, -t --t---

{L,_I_ I I LIM_T !

RAD/SEC o._s I I I PITCH RATE H 0.75,5 GYRO I + o. 75-5 .'_._ MACH | . OTHER ERROR I M H_OLD

i_+o-,'_>1 I I.."_-,,I

1 1+o._5 I I i l+°-_-s I HOLD

AANGLE OF l RAP . OT.ER J_Ltt !

: I

J'"_'l -I 1+o.3s5 I+ _ T TAC K ERt_ , I+o.osE I - o( HOLO OTHER _ J. I+5 PITCH ATTITUDE HER_ - e8 NORMAL I FT/SEC _ A CCEL" r__,, 15

_E_ I ,+lOS

i 9(I-SECO) I-1"105 PRESS.ALT. !

RATE J'FT/PSEC

E

÷ p, I BARO. ALT. I FT ERi_OR Adaptable FCS Pitch Autopilot Functions (F-4)

____ -_"_r_]

L{.. LATEF, AL .....

LIMIT LIMIT , ÷I.S K=, +- t.5 /_Ap/5_c

t' (RA D/._'Ec)

f

RAD ROLL OTH F R ATTITUDE "/tH E A DIIVG _" HOLD . T A ROLL ATT.

HOLD

I LIMIT ! i I

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_1 _-o.l_s _ _.7K_ L_

_ (ZAZ)) ' '_"'

HEADING I HOLD Adaptable FCS Lateral/Directional Autopilot Functions

• : i :: I _-J

F-_ SFCS Pitch Axis 8.'F-_ _c:i._'[ _:_S _T-,,'T • .

® -,..,, ® ,-..,.

eL s_ ----- AmO aP eL

-'-I-" I-- lama0 npU_

w,,,tO _ regal YIw O_f I ':_,_. _-.a.,,_ _ I / _ I I I "+'00" T,.im._:_| _dW I I I "--+ i Slmml _ll_Im" A,_II_ Cvl:r+'_ lab ¥,IV, Tt_| Fdlw ;3_V B iva,,, vl+n+r } j__ OV_G_V I'_"_ 1 lID_mn_ FwcliJ G_nlld w _ ItFI I 412,711 t+.l 20 lJ - |0 Gm'Ul t..:, ,ILO MI_ ._Uclz l_mllm Gaw llS O2S - 1,0 I<U& 10<U_ I%311> _lll< I Ittlh N l.m, G_,,n <10 <30 I_ Ills -+30 d_ IC 0 0325 O IS O0 IL0 0+.31_ LII IL0 KI 00 G0S 0*2 L0 O0 IL_ 0+0 0.l ut4t _II i IIJD DZ-I SO+ :_ 4-SS_1 It I [ Oil3 117 tit 3_13 m 117 m Ne_ C,_nC.l_._m T _SE.

t..

F-4 SFCS Directional Axis +SMRD_ 1 Switching Logic Variable Nominal I Range SW =C 1+C 2+C 3 +SMRD0 2 0.25 --1.0 K 1 0.5 V 1 = 1.66V Note: 0 to 100% Modulation TBA V 2 = 2.42V ,K2 15000 Occurs for Range of V 0 = 4.56V 3.0- - .12.0 K 3 6.0 0 to V 0.

BIAS = 30°e K 4 TBA K 5 TBA K 6 TBA TBA K 7 0.843 To CVU-1 Logic and K1S + 1 Switching

I

Pulse K 2 ....

Width Modulator BIAS S+K 31 [S+501 [S+501 -_ To CVU-2 Logic and _-- _x L1 0.6VlDeg,-----_ 0.166 _-_ Switching _ ro Po

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4_ Co mparator C 3 Comparator C 1 I _ Comparator C 2 c_ R1 0.6V/Deg_ •1_ To CVU-3 Switching

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(x R2 0.6V/Deg==--_ Logic and i o_ L2 0.6V/Deg--_. 0.166 _'_ [S 4- K4] [S + K51 IS+ K 31 [S+501 [S+501 ---_ To CVU-4 Logic and /I Switching _ (_1 g/Se_c K7S _1.._ I SMRD (_ 1 0.12 V/De KIS + 1 J SMRD0_J F-4 SFCS St&ll Warning Electrical Velocity Sen_ng. _:_ Channel 4 9ack-Uo Comparator, _ Chlmnel 3 Shut Off Logic _ Channel 2 Note: 7"m " 0.035

M;_-_S_ ,_. 1 Na- 2. 3. or 4

_J • # _,/-_) I $11500+ 1 I Number of U_its . -- T k pW / J _0_ Back-Up L__

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Demodu;ator Switch ITOLO I I [3 .... _1 Swi_chl_ _ I I ..... J L_L____1 " TOT BiN Display I = _ I

Coo,ro,.No, ., 1 'I

P,,_ L EBuO _j, vGoO ! _ L .... .J Demodulator LVDT Note: Dashed liner denote mechanical paths, Solid line= denote electrical paths.

F-4 Survivable Stabilator Actuator Package tD,.A (_1" Bandl.)as$ M6c To CVU-1 I I and Log,c I ] ' J,._ ! i _ lI |Ou at I hre_h°tdL---------- Mon,,or

I ,0,-,o, I] "'°I =-I i_o°_o0,_ _

-I_ MonitOr sig,.., 1 / A------------_ v;._ I/ / and Logic J / Controlled I/

R eference'--_ 1 Oscillator jj |Dual ThrcsholdL__

M6c "_l Monitor L_ 1o CVU.4 I) b I I Adaplive "-_ Gain Status Slat_ts F-4 SFCS Adaptive Gain Changer 1 24

$Cp

D e

Ser vo _ Servo i J EcloenVT;_ r

Airplane [j_!Ckle r _, [ FoU--G--_T-up-] I , -I and I /tachometer] F- "'-- -- --- ..... ----- -- l .......FL___ Amplifie, |[ Canceler _-----lond motofq-q selsyn I I Follow-up canceler system L__ ................

Pitch }_>_ ........

role gyro Veriicol [ gyro (pitch) <- Grumman F9F-2 Attitude Command FBW I PenduIum L

1-

I Yaw rote I= I gyro _z_.__ Amp,ifier L ] Canceler!

Canceler system ........... J Follow-up and L tachometer ] I ber v0 ___4 ':'er vo _1_ control amplhier 1 i motor] I _,,4tZ,_,J J om#ifier _] motor I-T7 control Airplane _!

_'- ,_---_ II system I I

_ Ser,vo ]_ Aileron lSoJ ! _71 1' --

and _ --- ' I tachometer [Roll rote]_ gyro J I [ Vertical 1

[_yro Iroll) j"

Directional] gyro ,7 . Note: Directional gyro is disconnected from system when contro! stick is moved laterally.

(b) Roll and yaw channels.

Grumman F9F- 2 Attitude Command BFW

H

Elevator Stick Servo Servo } >--,< conlrol Airplane

amplifier ;I

controller j system

mot°___:, I_ and

[tachometer

[_, _. / AmplifierJ jCanceler

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-4 Follow-up canceler system rale gyro Pitch _..

(a) Pitch ehannel, Grumman FgF-2 Rate Command FBW

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) Servo L__] Servo _::_rt:_e_i • irplane] ;'_ lamplifier[ 1 motor I I . // ontroller I "; i , P L_ . I [system It | [TO I1ow-uP]l _ chom_ter] ', .... _*m_o__o_e%_,

, - I[I

I l _r !'nd m°t°_ '''':<n I l

I ro oo I Canceler system I J[r Pitch l t,e gyro i oromcter :-- Grumman F9F-2 Normal-Acceleration Control System _TRUC TURAL FILTER 3+JE_- #+_Z I _ZtOgJ(TZ)S+ 7Z a $* _.? #_._r [ #__s_ $'+t(.Tj(c_o)s+ ¢o_ ,So G. $....._

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I t e" F"l_ I • 4/R _AM&" 3TIC_ DyIv/;MIC5 ,t4*t fo_ .._Y3TEM _t..OCK OF" PITCH C.A,$.

OIV_ ("H/JNNEL TWEAD I Pitch Axis

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L_TI r-T-I

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a_t TWEAD I Lateral-Directional i i AIRERAFT i i NOI_4AL i ACCEL_R,_TJO# LsrATro_JJ FEEL _IPRIN_ CAPJ1"I_.tevE TWEAD II Longitudinal Functional CAS Block Diagram I I I i_.-L

q-

C. F='°" i.iro I I P: I I

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i+<,,.. ,++..'¢ I /q/L E*RO/_

S_r_ VO -+?.S'" L lrl'_Kli L 5-rick Po s m o_ C,, Xj4 I ,,+/c / !

20.05" °¢°4_ LJ_TERA L /+ s !

ACC£L ER,#-/'/ o,v Ib_ 12UD D_'I_ i Ruo_ I

£1 .J_ P'EDXL

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t I WITH SIMPLE.

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ANALOGUE OF RUDDER ELECTRO HYDRAULIC 5ERVO AVRO Rudder Control System Including Yaw Damper (Simplex with Comparison Monitor) LONG [TUD[_JAL D[AaHAM LATERAL DIAGRAM F-tO0 Lear Rate Integratlng Autopilot 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 Stability and Control Data Summary for Several Selected Militar_ _Aircraft_ Volu_e I: 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, North American Aviation, Inc. Report NA 59H-98, 10 Apr. 1959.

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

7. Seth, W. A., A-TD Estimated Flying Qualities, LTV Vought Aeronautics Report No. 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 Paper D3-4525, presented to SAE Committee A-18 Aerospace Vehicle Flight Control Systems, 14 June 1962.

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

12. Rabenberg, B. E., and J. J. Gondek, XB-70 Fli6ht Control System Summary Test Report, 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 t Lockheea-Georgla Comply Report No. LGIUS#2-1-1, I Oct. 1966.

Jamison,GeneS.3 C-SA Flight Control System, SAE Paper No. 670574, presented

17.

at 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.

20. 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.

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

23.

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

24.

USAF T_e A/A37G-3 Flight Control Subsystem of the Type Q-2C Drone, Ryan Aeronautical 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.

Gerrity, Robert J., Test and Evaluation of a Versatile Drone Automatic Flight Control System for the B_M -34A_ Society of Flight Test Engineers Report No. 13, presented at the Symposium on Test and Evaluation of Automatic Control Systems, 31 Aug. m I-2 Sept., 1971.

27. 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 Flight Test Engineers Report No. 14, Aug.-Sept. 1971.

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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, AIAA Paper No. 66-998, Nov. 1966.

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

32. Report of the B-58 Flight Control System Review Board_ Sect. VII-A_Aerodynami c Trade-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., Astronics Div., Rept. AD-975, 17 July 1970.

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.

35.

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, Honeywell Inc., SEM No. 115.0090A, 6 Aug. 1970 37.

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

38.

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.

39.

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.

40.

Gaertner, R. V., R. C. Mclane, and V. Baxter, Flare Out Program for Air Force 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.

43.

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., Government and 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.

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47.

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48.

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49.

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

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

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Aircraft, 20 Dec. 1962.

_3. Round-Up Review_ Division Advisory Group-ASD_ 21 and 22 June 1 968_ 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) F-111 Category I Flight Test Progress Report_ Preliminary Stability and 55.

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.

57. 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.

_8.

Seacord, Charles L., The Honeywell AFCS (MH-I_7_ for the Swedish Viggen (AJ-37 _ Aircraft, Honeywell Inc , Rept. T-230, circa 1969.

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Naumann, Erwin A., and Herman Schmier, "Design and Development of the Stability 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.

61.

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.

62. 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.

63. Experience with the X-15 Adaptive Flight Contlol System, NASA TN D-6208, Mar. 1 971 • 64.

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.

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6g.

Tremant, Robert A., Operational Experiences and Characteristics of the X-15 Flight Control System, NASA TN D-14023 Dec. 1962.

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SJoberg, Sigurd A., Walter R. Russell, and William L. Afford, A Fli_ht Investigation of the Handling Characteristics of a Fighter Airplane Controlled through an Attitude Type of Automatic Pilot, NACA RM L56A1 2, Apr. ! 956.

70.

Russell, Walter R., Sigurd A. SJoberg, and William L. Alford, A Fli6ht Investigation of the Handling Characteristics of a Fighter Airplane Controlled Through a Rate Type of Automatic Control System, NACA RM 106F06, Sept. 1956.

71.

SJoberg, Sigurd A., Walter R. Russell, and William L Alford, Flight Investigation of a Normal-Acceleration Automatic Longitudinal Control System in a Fighter Airplane, NASA Memo I 0-26-58L , Dec. 1 958.

72.

Russell, Walter R., SigurdA. SJoberg, and William L. Alford, Flight Investigations of Automatic Stabilization of an Airplane Ha_tatic Longitudinal Instability, NASA TN D-173, Dec. 1959.

73.

Russell, Walter R., and William L. Alford, Flight Investigation of a Centrally Located Rigid Force Control Stick Used with Electronic Control Systems in a Fighter Airplane, NASA TN D-I02, Sept. 1959.

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78.

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80.

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83. Harris, Pat, Some Aspects of the 727 Flight Control System, presented at the SAE A-I_ Con_nittee Meeting No. I_, New York, July 1 964.

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85. Hanke3 C. Rodney, and Donald R. Nordwall, Simulation of a Jumbo Jet Transport Aircraft. Vol. II: Modeling Data, Boeing Co. Rept.

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