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EARTH ORBIT POSITION & TRAJECTORY DETERMINATION

GN-180 + )

MIDCOURSE POSITION & TRAJECTORY DETERMINATION

NEW COMPUTED TRAJECTORY

GN-182 (;)

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CSM V • 5285 FPS LEM INJECTION AV • 98 FPS

HOHMANN DESCENT ORBIT

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POWERED DESCENT TRAJECTORY

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GN-241

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LUNAR ORBIT ASCENT TRANSFER ORBIT

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FAM-1006 (M)

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LAUNCH AIM POINT DETERMINATION

ENTRY POINT

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S/M RCS FUNCTIONS

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C/M ENTRY ATTITUDE

RETURN GEOMETRY

GN-204()

S/M JETTISON

SEQ-59B610)

ENTRY BOUNDARIES ENTRY POINTS

NOMINAL TRAJECTORY

PERIGEE OF OVERSHOOT TRAJECTORY

ATM OS PHERE INTERFACE

ATMOSPHERE

400, 000 FT

VACUUM TRAJECTORY

LAND IN SITE

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SEPARATION

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GN-197B-1( )

VACUUM TRAJECTORY

GN-205 A LIP))

ENTRY PROFILE T

GN-9008

STEERING SIGNALS

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OPTICAL NAVIGATION

INERTIAL GUIDANCE

GN-197B-24)j

OPTICAL r - -C

SIGHTINGS OPTICAL INSTRUMENTS

SPACECRAFT CONTROL

INTERFACE OF G AND N SUBSYSTEMS

•

STATUS OF INERTIAL SUBSYSTEM

ALIGNMENT AND CONTROL COMMANDS

CHANGES IN VELOCITY

ATTITUDE

COMPUTER SUBSYSTEM

TO STABILIZATION ► AND CONTROL

STATUS OF OPTICS

SYSTEM •

OPTICAL ANGLES AND MARK COMMANDS •

THRUST COMMAND

ATTITUDE COMMAND

INERTIAL SUBSYSTEM

OPTICAL SUBSYSTEM

TO STABILIZATION AND CONTROL SYSTEM

STEERING ERROR

2% GN-9088A

G&N HARDWARE

GN-223( +)

G & N SYSTEM

NVB

GN-190

IMU

GN-192 re)

OPTICS-INERTIAL ASSEMBLY

PSA

REMOVABLE CORE ROPE MODULES

POWER CONNECTOR 05A5P5

(LOGIC) - TRAY A

(MEMORY) - TRAY B COLD PLATE

TEST CONNECTOR 05A5P3

OUTSIDE WORLD CONNECTOR 05A5P4

N GN-229A(*)

BLOCK I COMPUTER 100 SERIES

COVER PLATE

CDU

GN-191

MAIN DISPLAY AND CONTROL PANEL

G&N SYSTEM EQUIPMENT LOCATION

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C/M RCS B

AGC PWR FAIL

CO2 PP HI

S/M RCS A

S/M RCS B

S/M RCS C

S/M RCS D

A A&C ROLL CHAN

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BODY AXIS INDEX PITCH ANGULAR VELOCITY

0 ROLL ATTITUDE MARKER

PITCH ATTITUDE ERROR

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YAW ANGULAR VELOCITY YAW ATTITUDE ERROR

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SCS CONTROL PANEL

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MAX .1.)

ATTITUDE

OFF

.4

FLIGHT DIRECTOR ATTITUDE INDICATOR

NOTES, 1. ATTITUDE ERROR = ATTITUDE DESIRED - ACTUAL ATTITUDE. 2. THE BALL IS OF THE INSIDE-OUT CONVENTION. 3. EULER ANGLE CONVENTION IS PITCH, YAW, ROLL 4. THE BALL ATTITUDE SHOWN IS PITCH 345° , YAW 335° , AND

ROLL 300° , WITH RESPECT TO THE NAVIGATION BASE INDEX. SCS- 100B

SCS-106B

LOWER EQUIPMENT BAY PERSPECTIVE

G&N OPTICS CONTROL PANEL 100 SERIES

G&N INTERFACE SYSTEMS COMMUNICATIONS & INSTRUMENTATION SYSTEM

/ler / /OPTICAL I /

LINE-OF-SIGHT

STEERING ERROR & THRUST COMMANDS COOLANT

FLUID ENVIRONMENTAL CONTROL SYSTEM STABILIZATION

& CONTROL SYSTEM PRIMARY

POWER

CHECK COOLANT

MARK

ENABLE

off *

CONDITION LAMPS

*cff 8

SPEICS

0

O

O

O

0

0

•

DOCK HECK MODE CONDITION

LAMPS 0LAMPS

CALL HP CODE NUMBERS

GN-500A

ATTITUDE CONTROL SIGNAL

ATTITUDE

I 1—

ELECTRICAL POWER SYSTEM

REACTION THRUSTCONTROL

CONTROL VEHICLE i SIGNAL DYNAMICS i REACTION JET SYSTEM

i SERVICE P ROPU LS ION

MAIN PROPULSION ENGINE SYSTEM

SPACECRAFT CONTROL LOOP

IMU MOUNTING PADS 141 NAV. BASE

IMU LOCATING PINS

NAV. BASE ISOLATION MOUNTS 131

STUD HOLES FOR MOUNTING BELLOWS

OPTICAL SYSTEM MOUNTS (3)

SPACE SEXTANT

SCANNING TELESCOPE

BALL MOUNT

OPTICAL BASE

COOLANT SYSTEM CONNECTIONS

TELESCOPE PANEL

SEXTANT PANEL

OPTICS SUBSYSTEM

GN-220(+- )

OPTICAL SUBSYSTEM AND NAV. BASE

GN-9120A +

FIELD 60 DEG MAGNIFICATION 1X

SEXTANT SCANNING TELESCOPE

LINE OF SIGHT 1 LINE OF SIGHT 2 LINE OF SIGHT TRUNNION DRIVE

1.1

ZERO OPTICS SHAFT AXES AND TRUNNION AXES COINCIDENT WITH NAV. BASE AXES

OPTICAL SCHEMATIC

GN-176 A (*)

OPTICAL SYSTEM AXES

GN-9175A

GN-9121A

SCANNING TELESCOPE OPTICAL SCHEMATIC

EYEPIECE

FOCAL PLANE

DOUBLE-DOVE PRISM

RETICLE

FOCAL PLANE

PECHAN PRISM

EYEPIECE WINDOW

EYEPIECE PRISM ASSY

GN-9122 A

SCANNING TELESCOPE CUTAWAY

1. WINDOW 2.

ELECTRICAL CONNECTOR

3. RELAY LENS ASSEMBLY 4. OPTICAL BASE 5. PECHAN PRISM 6. BALL MOUNT 7. TRUNNION DRIVE WORMSHAFT 8. PRISM & MOUNT ASSEMBLY 9. CAM

10. SPRING & CAMFOLLOWER (ANTI BACKLASH) 11. OBJECTIVE LENS ASSEMBLY 12. RETICLE 13. RETICLE ILLUMINATION 14.

STUD HOLES FOR BELLOWS COVER

15. SHAFT DRIVE GEAR BOX 16. HEAT EXCHANGER CHANNELS 17. COUNTER (SHAFT AXIS) 18. EYEPIECE ASSEMBLY

MX RESOLVER STATOR 64 X RESOLVER ROTOR

BEAMSPLMER

1X RESOLVER STATOR

1X RESOLVER ROTOR

TRUNNION AXIS BALL BEARING 121

TRUNNION DRIVE GEAR

MIRROR

TRUNNION DRIVE MOTOR MIRROR MOUNT

SEXTANT CUTAWAY 1. OPTICAL BASE 2. COOLANT CONNECTIONS 3. BALL MOUNT 4. STUD HOLES FOR MOUNTING BELLOWS

COVER 5. FIXED RIGHT-ANGLE MIRRORS 6.

TRUNNION AXIS RESOLVER (64XI

7. COVER-FASTENING ROD 8. INDEXING MI RROR 9. BEAM SPLITTER

10. TRUNNION DRIVE GEAR BOX 11. OBJECTIVE LENS ASSEMBLY

13 12. INTERMEDIATE LENS ASSEMBLY

3 13. SHAFT AXIS DRIVE MOTOR 14. RETICLE 15. LIGHT-TRANSMITTING ROD 16. RETICLE LAMP 17. SHAFT-AXIS RESOLVER (16X)

15 18. SHAFT DRIVE GEAR BOX 19. EYEPIECE SOCKET & SEAL 20. EYEPIECE OBJECTIVE LENS 21. EYEPIECE MIRRORS 22. EYEPIECE OCULAR

GN-9124 A

SEXTANT TRUNNION AXIS ASSEMBLY

GN-9125A (+7.)

114 SPEED RESOLVE

I SPEED RESOLVER

SLEW SWITCH

1/2 SPEED RESOLVER

DISPLAY DIALS

SEXTANT OPTICAL SCHEMATIC

REFLECTING MIRRORS

INDEXING MIRROR

BEAM-SPLITTER

OBJECTIVE LENS ASSEMBLY

INTERMEDIATE LENSES

-RETICLE FOCAL PLANE

0 WINDOW

J EYEPIECE OBJECTIVE

EYEPIECE OCULAR

GN-9126A

COUPLING DISPLAY UNIT

MANUAL DRIVE

CDU BLOCK DIAGRAM

GN-9130

OPTICS MECHANIZATION BLOCK I 100SERIES

TRUNN I ON A° 1. TO CDU AGC

AGC DAC

POSI TI ON LOOP

SXT TRUNNION INTEGRATING

LOOP

•

110. INTEGRATING

LOOP STAR PRESENCE

TO AGC

STAR TRKR & OPTICS

SCT TRUNNION REPEATER OPTICS

CONTROLLER HORIZON SENSOR & OPTICS AS AUTO

MARK

AGC DAC

SXT SHAFT INTEGRATING

LOOP

POSITION LOOP

_101 SCT SHAFT I

REPEATER

SHAFT I AO

CDU TO AGC

GN-731 (E

AGC

OPTICAL INTEGRATING AND RESOLUTION CIRCUIT

CDU'S GN-9146A (*)

IMU

1111 DISPLAY AND CONTROL PANEL

CDUS AND ELECTRONICS

-71

6

4,

OPTICAL CONTROL LOOP

STABILIZATION AND CONTROL SYSTEM

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OPTICAL MEASUREMENT

LAND MARKS

IMU ALIGNMENT MEASUREMENT Xsm

STABLE MEMBER COORDINATES

GN-9100A( 4- )

ORBITAL NAVIGATION MEASUREMENT X SC

GN-9102A (+))

IMPROVED ESTIMATE OF POSITION

EARTH ORBIT NAVIGATION

MIDCOURSE POSITION DETERMINATION STAR

GN- 183A

MIDCOURSE NAVIGATIONAL MEASUREMENT

LANDMARK

to,

FIXED MIRRORS

SEXTANT FIELD OF VIEW

TELESCOPE FIELD OF VIEW

GN-9103A ()

TRACKER & HORIZON SENSOR LOCATION

GN-212 l ♦ '1

S. L. O. S.

PHOTO TUBE

TRACKER LINE OF SIGHT

PHOTO TUBE

OBJECTIVE FOCAL COLLECTOR LENS PLANE LENS

HORIZON SENSOR F. L. O. S.

OBJECTIVE FOCAL COLLECTOR LENS PLANE LENS

.,.- GN-214 (4)0 )

TRACKER OPTICAL SYSTEM

I SEXTANT HEAD I INDEX MIRROR

TRUNNION (SIDE TAB)

AXIS PICK UP FORK COIL A (COLLECTOR ) (2)

APERTURE

FORK

TO PHOTO MULTIPLIER

RIGHT ANGLE MIRRORS

HOUSING AND LENS ASSEMBLY

A-POS LENS B-NEG LENS (OBJECTIVE)

STAR TRACKER MIRROR

B

TUNING FORK RESONATOR ASSEMBLY

G N- 230 'I.(*)

FORK B PICKUP COIL

FORK B DRIVE COIL

0 4

FORK A PICKUP COIL

TINE OF TUNING FORK A

APERTURE SLOT, FORK B

TINE OF TUNING FORK B

SECOND HARMONIC

TRACKER SCANNING MECHANISM

GN-213A(,

STAR SIGNAL WAVEFORMS ••■■•••

■0"

El;

• •

001 4

FORK DRIVE SIGNAL (MOTION)

LIGHT TO PH OTOTU BE

SIGNAL CONTENT

TIME

FUNDAMENTAL

0° 9o° 180° 270°

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,./

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FUNDAMENTAL AND SECOND HARMONIC

GN-217 (40)

VARI HIGH VOLTAGE PIS & STAR PRESENC E

DETECTOR

100 KC STAR PRESENCE

CONTROL AMP

X AXIS FORK DRIVE AMP

455 CPS

Y AXIS FORK DRIVE AMP 356 CPS

GN-210A (0)

NBA 910 CPS

NBA 712 CPS

►-0 455 CPS

NBA

NBA 356 CPS

LELECTRONICS ASSY

STAR -PRESENCE

OUTPUT

■11.

AGC & STAR P--4P PRESENCE

SIGNAL

TRKR DEMOD H X

OUTPUT

TRKR DEMOD -4P Y

OUTPUT

TUNING FORKS & APERTURE

OBJECTIVE COLLECTOR LENS. LENS

OTOMULT I PL I ER TUBE

PRE AMP

DET

DET

DET

SXT HEAD

L

ELECTRONICS STAR TRKR Y AXIS-111.

STAR PRESENCE

STAR TRACKER

STAR TRACKER MECHANIZATION

HOR ZON GATE

AGC

_41 NARROWH PEAK BAND AM

550 CPS DETECTOR

•

GN-209A ira,-‘ §AP2)/

SOURCE

TUNING FORK/'-' & APERTURE

FIXED HIGH VOLTAGE POWER

SUPPLY

[FORKAMP DRIVE

550 CPS

PREAMP COMPARATOR

1/2 RECTIFIED SIGNAL I (PEAK VALUE IS STORED) 1

NEGATIVE RECTIFIED SIGNAL

RECTIFIED DETECTOR OUTPUTS

SUM OF DETECTOR OUTPUTS

+ VOLTS

0

- VOLTS

+ VOLTS

0

- VOLTS

HORIZON SENSOR

OBJECTIVE COLLECTOR PHOTOMULTIPLIER LENS LENS TUBE

HORIZON SENSOR WAVEFORMS

HOR IZON SIGNAL

ALTITUDE

GN-218 rH

I RIG

PIP

ADA

I GA

INERTIAL SUBSYSTEM

GN-221( +))

APOLLO STABLE MEMBER CONFIGURATION

GN- 9007A ( )

OUTER GIMBAL AXIS (OGA)

SUPPORT GIMBAL (CASE)

OUTER GIMBAL

MIDDLE GIMBAL AXIS (MGA)

LIMIT SWITCH ±60°

STABLE MEMBER (INNER GIMBAL)

INTERGIMBAL ASSEMBLY (6)

MIDDLE GIMBAL

INNER GIMBAL AXIS (IGA)

COARSE RESOLVER GYRO ERROR RESOLVER

MIDDLE GIMBAL STABLE MEMBER

DC TORQUE MOTOR

IMU GIMBAL ASSEMBLY

GN-9155A

INTERGIMBAL ASSEMBLY

SLIP RING ASSEMBLY

BEARI NGS

GN-9038At'rj

GN-9064A INERTIAL MEASUREMENT UNIT

XaXgXsm

Za ZgZsm

Ya Ysm Yg ADArg/

STABLE MEMBER

\ ANGLE = CONE

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SPACECRAFT

ENTRY ROLL AXIS

STAR LOS LANDMARK LOS

X SC (ROLL)

X NB

ZERO AXIS ALIGNMENT

G&N FUNCTIONAL SCHEMATIC

OGA

GN-196A f.Vt)

I NPUT AX IS

CASE

SPIN AXIS .*%**-►

SPIN GYRO WHEEL REFERENCE ASSEMBLY AXIS

OUTPUT AXIS

GN-240 ((*)

PRIMARY 2 EXCITATION

PRIMARY 2 EXCITATION

7 COUNTER-CLOCKWISE ROTATION

25 IRIG, SIMPLIFIED CUTAWAY VIEW

DUCOSYN SIGNAL GENERATOR OPERATION

GN-239

MAGNETIC C2 SUSPENSION MAGNETIC EXCITATION SUSPENSION

EXCITATION

DUCOSYN TORQUE GENERATOR OPERATION

TG+

TG

TG(COMM)

POSITIVE TORQUING SIGNALS APPLIED

GN-238 1,)

MAGNETIC SUSPENSION

GN-237 (+7)

STABILIZATION LOOP IMU

ANGULAR DIFFERENTIATING ACCELEROMETER

CASE INPUT AXIS

STOP

COIL PERMANENT MAGNET

FLUID ± 15°

COIL

FLOAT

S

CASE

PERMANENT MAGNET

PSA

BELLOWS

GN-9048A *)

TORQUE MOTOR INNER

GIMBAL ADA

Y IRIG

TORQUE MOTOR

EIYg)

TORQUE MOTOR

FILTER SERVO AMP

MIDDLE GIMBAL

ADA FILTER

SERVO AMP E(Zg)

Z IRIG

OUTER GIMBAL

ADA FILTER

SERVO AMP

RESOLVER

E(X9 I X IRIG P REAM P

TORQUE MOTOR

TORQUE MOTOR

TORQUE MOTOR

INNER GIMBAL AX IS

MIDDLE GIMBAL AX IS

OUTER GIMBAL AX IS

GN-9068A .+))

MAGNETIC SUSPENSION

CENTER OF MASS OF FLOAT LOCATED AT POINT OF EQUIVALENT PENDULOUS MASS

PRA PENDULOS I TY PAA REFERENCE AXIS PENDULOUS ARM AXIS

GN-179

FLOATED PENDULUM UNIT

ACCELEROMETER LOOP

SWITCHING PULSE FROM APOLLO

INTERROGATOR PULSE GUIDANCE COMPUTER

L DATA PULSE

+T SET BINARY CURRENT

-T SET SWITCH

+ TORQUE

IMU POWER SERVO ASSEMBLY

PRE AMP

AC DIFF AMP

• INTERROGATOR

SG 16 PIP

L +TORQUE

TG 4

• -TORQUE CALIBRATION

MODULE

DC AMP AND PRECISION

VOLTAGE REFERENCE

- TORQUE

NEGATIVE VELOCITY PULSE

POSITIVE IVELOCITY PULSE

+AV •

FORWARD TO APOLLO BACKWARD GUIDANCE COUNTER -AV COMPUTER

GN-9039A

G N-9033

WATER-GLYCOL COOLANT PASSAGE

BACKUP

NOX AUTO ALARM OVERRIDE

-(PROPORTIONAL)

( EMERGENCY ) ►

( ALARM )

HEATER CURRENT

AMP

EMERG HEATER

CONTROL

TEMP CONTROL SENSORS

NORMAL

TEMP CONTROL

AMP

EMERGENCY

--10 CONTROL HEATERS

L 0

E R

TEMP INDICATOR

TEMP ALARM & BACKUP

AMP

REGULATED FIXED +28 VDC ACCEL

POWER SUPPLY HEATERS

EMERG HEATERS

FORCED CONVECTION IN IMU

IMU TEMPERATURE CONTROL

GN-219

STAB LOOP

COARSE ALIGN AMPLIFIER

xcatra

AGC

STABILIZATION LOOP ELECTRONICS

CDU AND ELECTRONICS

IMU

COARSE ALIGN LOOP

GN-9099A +1)

STAB I L I ZATI ON LOOP

ELECTRONICS

FINE ALIGNMENT TORQUING

ELECTRONICS

STAB LOOP a

GN-9104

COARSE ALIGN

FINE ALIGN

ATTITUDE ERROR TRANSFORMATION

1G EMG EG

ERROR SIGNAL TRANSFORMATION AXES 1

INNER CDU C

a MIDDLE CDU

C

1(2 0

IG

MG

• PITCH YAW

RESOLVER

EYNB

EY SC

EZ NB

ENTRY PITCH •

v*<- -- -BODY

7,--" ENTRY YAW 9(

---BODY

• • ix

• 1

AOG

Z SC

SPACECRAFT

FIXED EX

E OG EX N RESOLUTION TRANSFORMER

____ BODY ROLL •

ISOLATION TRANSFORMER

EX NB --- ENTRY

GN-9144A

RELATIONSHIP OF BALL INDICATOR AND IMU

BALL ATTITUDE INDICATOR

oe-EP:cs, SPACECRAFT ROLL AXIS

SC

INNER AXIS ALIGNED .......1<-...- NORMALTO ORBIT PLANE

DURING ORBITAL OPERATIONS

G a N INERTIAL MEASUREMENT UNIT

GN-184 (*)

BODY AXIS INDEX PITCH ANGULAR VELOCITY

ROLL ATTITUDE MARKER

NAV-BASE INDEX

PITCH ATTITUDE ERROR

POLARITY RATE -- ATTITUDE ERROR+

YAW ANGULAR VELOCITY YAW ATTITUDE ERROR

•1

LOWER DISPLAY AND CONTROL PANEL

10"41

MAIN DISPLAY AND CONTROL PANEL

G AND N SYNC SWITCH

STABILIZATION AND CONTROL SYSTEM

MANUAL CDU Io• MODE FINE ALIGN

MODE

FLIGHT DIRECTOR ATTITUDE INDICATOR

NOTES: 1. ATTITUDE ERROR ATTITUDE DESIRED - ACTUAL ATTITUDE. 2. THE BALL IS •OF THE INSIDE-OUT CONVENTION. 3. EULER ANGLE CONVENTION IS PITCH, YAW, ROLL 4. THE BALL ATTITUDE SHOWN IS PITCH 345° , YAW 335° , AND

ROLL 300° , WITH RESPECT TO THE NAVIGATION BASE INDEX. SCS-100B

GN-9150A k(,75i

STABILIZATION LOOP ELECTRONICS

16 IS

IMU

AGC

E ENGINE ON AND OFF DISCRETE

(LOWER DISPLAY AND ► CONTROL PANEL l

GN-9I49A t.V.,7))

RESOLVER NETWORK

(VELOCITY STEERING L00. 1) STABILIZATION AND

CONTROL SYSTEM 4-

SERVICE PROPULSION

SYSTEM

SPACECRAFT THRUST VECTOR CONTROL VSC

PSA FAMILY TREE POWER SERVO

ASSEMBLY

TRAY I GIMBAL SERVO

ELECTRONICS

TRAY 2 POWER

SUPPLY ELECTRONI CS

TRAY 3 GYRO

ACCEL ELECTRONICS

TRAY 4 GYRO

ACCEL ELECTRONICS

TRAY 5 CDU & GYRO

ACCEL ELECTRONICS

GIMBAL SERVO AMPL

PULSE TORQUING

POWER SUPPLY

AC DIFF AMPL

AC DIFF AMPL

FORWARD BACKWARD

COUNTER

GIMBAL COARSE

ALIGN AMPL

I% POWER AMPL

BDE1,28V

INTERRO-GATOR

INTERRO-GATOR

PUL TORQUE SUP BACK UP

MODE

-28VDC POWER

SUPPLY

5% POWER AMPL

BOWE/

BINARY CURRENT SWITCH

BINARY CURRENT SW ITCH

O-A CONVERTER

I% POWER AMPL 3. DEC

MICR & SUSP

AAC 8008.18V

DC DIFF AMPL & PVR

DC DIFF AMPL & PVR

ENCODER

AUTO AMPL 2KC MICR & SUSP

EXCITATION

25. 6KC ENCODER

EXCITATION PIPA CALIB PI PA CAM

CDU ZEROING & LOCK RELAYS

TEMP CONT POWER

SUPPLY 3200,20V

LOAD COMPENSA- TION IMU

PULSE TORQUE

GYRO CAL

PULSE TORQUE

GYRO CAL LAMPS

FAILURE INDICATOR

TERNARY CURRENT SW ITCH

TRAY 6 CDU & POWER

SUPPLY ELECTRONICS

TRAY 7 MI SC

TRAY 9 OPTICAL

ELECTRONICS

TRAY 9 OPTICAL

ELECTRONICS

TRAY 10 POW DI & SIG COND

ELECTRONICS

MOTOR DRIVE AMPL & SELECTOR

TEMPERATURE CONTROLLER

MOTOR DRIVE AMPL

MOTOR DRIVE AMPL

SIGNAL CONDITIONER

CDU ZEROING XFMR & RELAYS

ENCODER OPTIC

2 - SPEED SWITCH

2-SPEED SWITCH

BLOCK DIODES

5% POWER AMPL

1300,x28V

PULSE TORQUING

POWER SUPPLY

COSECANT GENERATOR

ISOLATION XFMR

IN POWER AMPL

800.1,28V

CDU FIX RESTRANS & ENTRY MODE

MOTOR DRIVE PREAMPL

INTEGRATOR

MOTOR DRIVE PREAMPL

SERVO

JUNCTION BOX

ASSEMBLY

AAC 8008.28V

IMU TEMP IND ALARM & BACK UP CONTROL

RELAYS RELAYS

CDU RESOLVER

LOADS

BUFFER CIRCUIT

BUFFER CIRCUIT

RESOLVER DRIVE AMPL

DA CONVERTER

XFMR ZERO OPTICS

GN-9044A

ENCAPSULATED MODULES

CONNECTING HARNESSES COVERED WITH POTTING

MOUNTING "T"

THERMAL INTERFACE MATER IAL

COLD PLATE

PSA TRAY

COMPUTER SUBSYSTEM

GN-222

COMPUTER SUBSYSTEM, GENERAL INTERFACE

DISPLAY DATA TO TELEMETRY'

BLOCK UPLINK

COMPUTER SUBSYSTEM

DISPLAY AND KEYBOARDS

( DSKY' SI

MODE SWITCHING

A I DISPLAY DATA AND

I ALARMS

MANUAL INPUTS

• SPACE-CRAFT

INERTIAL SUBSYSTEM

ALARMS 4

ENGINE CONTROL • RADAR TIMING, CONTROL, AND STATUS SIGNALS (NOT USED)

DOWNLINK WORD ALARMS

I MODE INDICATIONS

I VELOCITY INCREMENTS

I CDU POSITION

APOLLO GUIDANCE COMPUTER

I ALARMS

I CDU DRIVE SIGNALS

TIMING SIGNALS

'GYRO TORQUING COMMANDS

1M1■1=1■1

MODE SCANNING TELESCOPE INDICATIONS AND SEXTANT DRIVE

SIGNALS

OPTICAL SUBSYSTEM

SCANNING TELESCOPE AND SEXTANT SHAFT ANGLES

fr:), GN-215 O)/

TIMING SIGNALS 4

DOWNLINK SYNC SIGNALS

UPLINK WORD

AGC WORD FORMAT

DATA WORD ADDRESS

115 14 13 12 11 10 9 8 7 6 5 4 3 2 1 0 1 I

OPERATION DATA WORD CODE ADDRESS

PARITY BIT

INSTRUCTION WORD

SIGN

DATA WORD NOTE EACH INSTRUCTION AND DATA WORD HAS ITS OWN ADDRESS WHICH DEFINES WHERE IT IS LOCATED IN THE MEMORY.

GN-9086Ai.

"R" ROPE

BANK BANK BANK BANK 1

I 2

I 3 I

BANK BANK BANK BANK 5 6 7 8

8 STRANDS

16 8 STRANDS STRANDS {

2 3 4 5 6 7 8

SELECTION x BOTTOM

SW ITCHES c(S3. 2 , I )

CORE ARRAY

RIN

G

132 X 32 X 16 1

FIXED MEMORY ORGANIZATION

WORD SELECTION

L SELECT 1 OF 3 ROPES (8,192 WDS OF 24,576 WDS)

2. SELECT 2 OF 8 BANKS (2,048 WDS OF 8,192 WDS)

3. SELECT 2 OF 256 CORES (16 WDS OF 2,048 WDS)

4. SELECT 1 OF 16 STRANDS (1 WD OF 16 WDS)

HSU

ROPE

"T" ROPE

••■•■

TOTAL WORDS - 24,576 TOTAL CORES - 3,072 1 ROPE - 8,192 WORDS

- 8 BANKS - 128 SENSE LINES - 16 STRANDS

1 BANK - 128 CORES -1024 WORDS

1 CORE - 8 WORDS

1/2 ROPE

112 ROPE

GN-9021B (i)

ADDRESSING, READING, AND WRITING INTO CORE ARRAY

GN-9020A

A 0 Z LP P B C X Y

U

I NO I NI I N2 I N3

OUTO OUT1 OUT2 OUI3 OUT4

• OUTPUT

INTERFACE

GN-9026A t, (9,A,

SEQUENCE GENERATOR

* 4' •

TIMING PULSES

TIMER j

COUNTER INCREMENT

PROGRAM INTERRUPT

PRIORITY CIRCUIT

0 I BNK r. 4 •

FIXED MEMORY

ERASABLE MEMORY

t CENTRAL PROCESSOR

INPUT INTERFACE

AGC GENERAL BLOCK DIAGRAM

no,

O

0

l■ Ca la ■ig

C4

as &VI E 4.;

.1P=2,1 O

A 0 Z LP P B C X Y

U

I NO I NI I N2 I N3

OUTO OUT1 OUT2 OUI3 OUT4

• OUTPUT

INTERFACE

GN-9026A t, (9,A,

SEQUENCE GENERATOR

* 4' •

TIMING PULSES

TIMER j

COUNTER INCREMENT

PROGRAM INTERRUPT

PRIORITY CIRCUIT

0 I BNK r. 4 •

FIXED MEMORY

ERASABLE MEMORY

t CENTRAL PROCESSOR

INPUT INTERFACE

AGC GENERAL BLOCK DIAGRAM

no,

O

0

l■ Ca la ■ig

C4

as &VI E 4.;

.1P=2,1 O

w O

co 4

z 0

OL OL 1.■

z

ua 0 4

0 '— vs

rii r: -1 F-- 1 1 1I

▪

L__J L__J L__J .

• F-- 1 r --1 ■ '4 li q iiq1

L__J L__J L__J L__J F-- 1

11 1 I L__J L__J L__J

0

0

1

0

• Q

KEY

BO

AR

D

O 0

[111 LC

r 1

ru

0

IJI

gyp'

ru

CO

INS

TRU

CTI

ON

0'

C.D

MEMORY

ADDRESSES COMMUNICATION LINK

ENGINE

CONTROL b. SPACECRAFT

DOWNL INK WORD

AGC POWER FAIL

ALARM ► SPACECRAFT AND INERTIAL

TIMING p. SUBSYSTEM

SIGNALS

CDU ► DRIVE INERTIAL SIGNALS SUBSYSTEM

GYRO ►

TORQUING COMMANDS

OPTICAL SCT AND ►

SUBSYSTEM SXT DRIVE SIGNALS

COMPUTER SUBSYSTEM 28 VDC (BUS AI II •

SPACECRAFT 28 VDC (BUS BI

ENGINE CONTROL

RADAR SIGNALS

SPACECRAFT UPLINK WORD

DOWNLINK SYNC

SIGNALS

OPTICAL SUBSYSTEM 1 SCT AND SXT

SHAFT ANGLES

CDU, PIPA. AND IMU ALARMS ►

MODE INDICATION

(INCLUDES MARK)

VELOCITY INCREMENTS

CDU POSITION

TIMER

+3 VDC AND TO ALL 111 FUNCTIONAL

+13 V DC AREAS

MANUAL INPUTS 11•■•■•

AND ALARMS • DOWNLINK SYNC SIGNALS

DOWNLINK END PULSE AND RATE SIGNALS

DATA INPUTS

OUTPUT PROGRAM INTERRUPTS AND COUNTER INCREMENTSJ

INHIBIT UPSYNC AND

CLEAR INO

t CONTROL PULSES

TO ALL FUNCTIONAL AREAS EXCEPT

DSKY'S REAL (ACCUMULATED) TIME WORD

► TO ALL FUNCTIONAL AREAS

POWER

MODE INDICATIONI.

INERTIAL SUBSYSTEM

INPUT

TEST AND RESET ALARMS

DISPLAY AND

KEYBOARDS (DSKY'S)

MODE SWITCHING AND ALARMS

DISPLAY DATA TO TELEMETRY

BLOCK UPLINK

DISPLAY DATA

MAIN TIME PULSES

V

PRIORITY CONTROL

ADDRESSES

INTERRUPT REQUEST AND

INSTRUCTION COMMANDS

DATA AND CENTRAL PARITY ALARM

PROCESSOR

SEQUENCE GENERATOR

ORDER CODE

TIMING PULSES

.SPACECRAFT

SPACECRAFT ► AND INERTIAL

SUBSYSTEM RADAR SIGNALS

110

START SIGNAL ► TO ALL FUNCTIONAL AREAS

EXCEPT INPUT AND DSKY'S

GUIDANCE k NAVIGATION ABBREVIATIONS

ACSP ADA

AGC AGE AMR

A.C. SPARK PLUG ANGULAR DIFFERENTIATING ACCELEROMETER APOLLO GUIDANCE COMPUTER APOLLO GUIDANCE EQUIPMENT ATLANTIC MISSILE RANGE

LOS LLOS LSB MGA MIT

LINE OF SIGHT LANDMARK LINE OF SIGHT LEAST SIGNIFICANT BIT MIDDLE GIMBAL AXIS MASSACHUSETTS INSTITUTE OF TECHNOLOGY

CDU C.G.

COUPLING DISPLAY UNIT CENTER OF GRAVITY

MAG AMP MSB

MAGNETIC AMPLIFIER MOST SIGNIFICANT BIT

CSS COMPUTER SUB SYSTEM M&DV MAP k DATA VIEWER

DNLK DOWNLINK NVB OR NB NAVIGATION BASE

DSPY DSKY

DISPLAY DISPLAY & KEYBOARD

OGA OA

OUTER GIMBAL AXIS OUTPUT AXIS

ECS ENVIRONMENT CONTROL SYSTEM OSS OPTICAL SUB SYSTEM

E/M E01

ERASABLE MEMORY

EARTH ORBIT INJECTION

PIP OR PIPA

PULSED INTEGRATING PENDULOUS ACCELEROMETER

EPS ELECTRICAL POWER SYSTEM PSA POWER SERVO ASSEMBLY

FDAI FLIGHT DIRECTOR ATTITUDE INDICATOR PRA PENDULOSITY REFERENCE AXIS

F/M FIXED MEMORY RCS REACTION CONTROL SYSTEM

G.C. GIMBAL CASE RSVR RESOLVER

IA NPUT AXIS SA SPIN AXIS

IRIG NERTIAL REFERENCE INTEGRATING GYRO S/C SPACECRAFT

IGA NNER GIMBAL AXIS SLOS STAR LINE OF SIGHT

IMU NERTIAL MEASUREMENT UNIT SCT SCANNING TELESCOPE

!SS NERTIAL SUB SYSTEM SCS STABILIZATION & CONTROL SYSTEM

1U NSTRUMENT UNIT SDOF SINGLE DEGREE OF FREEDOM

UN GUIDANCE & NAVIGATION SM STABLE MEMBER

KYBD KEYBOARD SRA SPIN REFERENCE AXIS

LNDMK LANDMARK SPS SERVICE PROPULSION SYSTEM

LOI LUNAR ORBIT INJECTION SXT SPACE SEXTANT

GN 244