epared by: Dariie

The purpose of t h i s manual i s t o f i l l the need f o r a single source

of descriptive information concerning the Eclipse-Pioneer ST-120 Stabilized

Platform, The level of presentation i s that of an introductory familiari-

zation leading t o a basic understanding of the operation of the platform,

i ts function a s the heart of the Pershing Guidance System, and i ts relat ion-

ship t o other parts of the system.

More detailed information i s available i n the Eclipse-Pioneer

manuals and publications l i s t e d i n the bibliography* Many of them served

as technical references fo r t h i s work,

In addition, the authors are indebted t o Messrs* F, Hanusek,

L. Alperwitz, G o Jeffy, Fo W, Meyer, R. A, Taylor and numerous other Eclipse-

Pioneer personnel for t h e i r valuable contributions of information, con-

struct ive criticism, and c l e r i c a l assistance during the preparation of t h i s

text,

TABLE OF CONTENTS

I, Introduction

A, Pershing

B, Functfons of the ST-120 Pla t fom

C, Functions of Associated Component

11, Stable Platform

A, Coordinate Systems

1, Missile Coordinates

2, Platf o m Coordinates

3 Guidance Coordinates

B, Main Assemblies

1, $haft

2, Roll and Yaw Centerpiece Assembly

3, Inner Gimbal Assembly

4* Carrier Ring Assembly

C, Components

1, AB-5 Stabilizing G y m

2, A1UIAB-3 Accelerometer

3, S e m Motors

4, Microsyns

5, PenduLums

6, Azimuth Rck-up

7 , Pitch Control T~ansfomer (C ,T, )

8, Pitch Resolver

Page

1

I.

2

3

4

4

4

5

6

8

8

8

8

9

9

9

12

3-4

15

16

17

18

3.9

9 , Nulling Card

10, Caging Motor

11, Porno Prism

12, Pneumatic System

13. Miscellaneous Componen$

a, Cover Assembly (Heater Encloswre)

b, Temperature Sensors

c, Elapsed T b e Indicator

111. The ST-120 Servo Amplifier Box

A, Introductian

B, Pitch Cam Prog rmer and Relay Assembly

C, Auto Transformer

D, Amplifier Modules ,I

IV, ST420 Platform Operation

A, Alignment Loops

le X Alignment Loop

2, Z A l i m e n t Loop

3, Y Alignment h o p

a, Horizontal Alignme

b, Azkuth ALipenPI

B, S tabi l iza t isn Loops

1, X Stabilfza

2,, Y Stabi l f za t f on Loop

3, Z S tab i l i za t i

C, Accelerometer Loopa

D, Attitude Loops

1, Yaw A t t i t u d e Loop

2* R o l l Attitude Loop

3 . Pitch Atti tude Loop

Bibliography

LIST OF IUUSTRATIOKS

Figure 1

Figure 2

f i gu re 3

Figure 4

Figurz 5

F igwe 6

Photo U2523

Photo u5795

Photo Us788

Photo U571f;

Photo u5792r.

Photo US712

Photo 7nJ2252

Figure 7

Figure 8

Figure 9

Photo Us713

Photo W222.3-1

f igure 10

Figure II1

photo W2908

Missile S e e t i

MissiEe Csordka te System

Platform Coordilnates

Guidmce C o o r ~ n a t e s

Hain Shaft d t h Flanges

ST-3.20 Yaw and Roll AS

Inner Gimbal Assembly

i e r Ring t o Inner Gimbal Assembly

ST-120 I n t e m e d i a t e Shaf t Assembly

ST-120 In t emedfa t e Assellib

s Relationship

kB-5 Stabi l fx ing

h AeceSe~mete r

BPIAB-3 In tegra t ing Aceelea~ometer Assembly

AMAB-3 Aecelenoomete~ C

l\tlierosvl. Assemb3.y and Rotor

Follows

Fi sure

Figure 12(a)

(b 1

( ~ 1

Photo I42907

Figure 13

Figure

(b 1

( 4

Figure lS(a)

(b1 Photo 61-3468

Figure lh(a)

(b 1

(C > Figure 17

Figure 18(a)

(b

Photo U.5491

Figwe 19

Figure 20

Figure 21

Photo 61-176-1

Figwe 22

Description

IJIicrosyn a t Null

Plicrosyn off Null

P'iierosyn Loop

A i r Bearing Pendulum

A i r Bearing Pendulm Cutaway

Pendulum a t N u l l

Pendulum off Null

Positioning of Pendulums on Carrier Ring

Azimuth Pick-up

Azimuth Rek-up Schematic

Transformer-Resolver and Connector Assembly

Pitch COT, a t M u l l

Pitch COT, off N u l l

Pitch C.T. i n the Loop

Pitch Resolver

Nulling Card Adjustments

Nulling Card Schematic

ST-120 Caging Hechanism Assembly

Caging Mechanism Operatic.

Pomo Prism

ST-120 P n e w t i e System

ST-120 Servo Amplifier Box

Servo Amplifier Box Input & Output Voltages

Follows Page

Figure 23

Figure 24

Figure 25

Figure 26

Figure 27

Figure 28

Figure 29

Pi tch Cm Programm

Relay Assembly

Servo Amplifier Module Block Diagram

Alignment Loops

S tab i l i za t ion Loops

Accelerometer & At"tf"cude Loops

Guidance System Block Diagram

FolLows Page

W range i s achieved by aiming %he ar%fZPery

elevation of 45°, By contra

and. i s propelled by rocket p

the missile a greatly fncke

guiding Lhe m i s s %

%he b a l l i s t i c t r a j e c t o v ,

a 1 from an a z b u t h pickoff, After lif'P;-of'f, three s tabi l iz ing gyros

provide signals t o hold the platform i n e r t i a l l y in the Bsked at t i tude.

2, The p la t fom provides signals f o r missile a t t

control, Signals f o r missile a t t i tude contro

in yaw and r o l l , and by a control t r m s f o m e r

guidance in cross range, s l an t range m d s lan t a l t i tude amp

three integrating accelerometers mounted on the platform,

C, Funct ionsofA sociated Components

Four major cmporients w e assoe%a%ed Pla%Pom, A pre-

f l i g h t component,located in the F P o v m e r is pap% of the

Ground Support Equfpmernt, The other three %her with the

ST-120 Pla t fom comprise the Guidance Sys

Guidance and Control section o f t h e missilec

1, Alf gnment AmpPif i e r (manufactwed by Eclipse

during pre-flight al%gnment of the ST420 PZatf l i m e n t Amp1ifi.e~

receives signals frorn the ST-120 A i r Bearing Pendue d the AzSmuth

Pick-of% and amplifies them sufficientP$ t o ope rrs f o r positioning

the s t ab i l i z ing m o s o The os in turn control the pos f t i

The Alignment Amplifier i s in the Station and does

not become a i ~ b o m ,

2, Semo Amplifier Box (mnUfactwed by Eclipse

signals from pickoffs on the ST-120 Stabil izing Gy~os

t o drive servomotors which position the platform and which servo the

in tegra t f ig acceleroraeters, The h p l i f i e r Box a l so can s a Pitch Cam

Programer and a Refay Assembly, which w i l l be discusae

longitudinal, with the yaw vector pointing outward in the same direction

as vane number I, Pitch displacement ($ P) i s rotat ion about a th i rd

mutually perpendicular axis with the pitch vector pointing outward from

the side of the missile between vanes 1 and 111, 1%-ssile rotation about

these three axes i s .sensed by the and r o l l microsyns and the pi tch

control transformer

By definition, vane number I point;s t n the missile

is aligned i n azimu d vmes 11 and III are sequen-

t i a l l y clockwise as vie d from the rear of the missile, For r o l l control,

a l l three vanes deflect the same %mom% and in the same direction, clock-

wise or counter c l o e M s e on t h e i r shafts , For yaw control, vane I de-

f l e e t s i n the appropriate direction, while vanes I1 and I11 deflect half a s

far i n the opposite direc$ion on %heir shafts, For p i tch control, vanes

I1 and I11 deflect equal amounts but in opposite direct ions on the i r

shafts while vane I remains s t a t i

When the missile i s i n a ve r t i ca l a t t i tude a t l i f t - o f f , azimuth correc-

t ions are made about the missile ro Figure !A), A s the missile pitches

in to the ba l l i s t i c trajecLory, corrective actfon t o maintain target azinuth

changes progressively from missi e r o l l control t o yaw control,

2 , Platform Coordinates

The ST-120 Platform coordinate system consists of t h e e mutually

perpendicular axes passing %hrough the center of gimbal f~eedom about

which the platform ca r r i e r r ing is Sgned and stabil ized (Figure 5 ) ,

The Z, axis is pa ra l l e l t o the bottom surface of the ca r r i e r r i n g

and concentric with the ca r r i e r s ing opening, with the Ze vector pointing

FIN I

TCH

A TFOR ES

f an inductive pickup assembly made

up sf t w o lm ndings connected in a bridge

c i rcu i t ; and ed, ZateraIZy and vertically,

between the? p

ndings is baPanc d so %he bridge o.u'tput i s at

s p ~ m i d e an output

r0 al pingo Thus, the

TRANSFORMER-RESOLVER AND CONNECTOR ASSEMBLY

a t s r of the p i t c con"r;ol t r m s f o m r i s fixed to the ca r r i e r

ring and the rotor i s geared $0 the inner gimbal ring, A s the missile

ro ta tes about the p i t h g roLates wfth it, ro-

The s ta to r leads sf %h sfomer are connected t o

the s ta to r leads of a sFebo- eaf which is par

pitch cam progra

the i r rotors are posi

The ro"t;oaso of the i t t e r i s moved by t pitch cam .to

program the deskred missi f t u d e f o r any ins tant dwing the

guided portion of the f l i g h t , Pf Ghe pitch a t t i tude of the mfssiX@ also

changes so as 4x1 keep the ro ctr s f the p$deh control t-ansfsmer synchro-

nized with that of the p teh transmitter, no mro r s i a1 output i s pro-

duced, If, hDdeqrsr, the pitch a t t i tude of the missile deviates from $hat

called f o ~ by e pi tch e m programmer, an eyror s i al i s produced sf a

and the rotor is direc Xy coupled to %he r o t o r of the pi%eh control trans-

e r (photo 61=-3LcjR), Thus, bte resolver ro tor moves: with changes

missile pi tch a t

czw La

Pl TCH TRAMS M l T TER CON TROL 7RA NSFORMER

a. P/TCH C.T. A T NULL klr. PITCH C.T OFF NULL c. PITCH C.7 THE LOOP

r r ing are boQh ver t ica l , the three

the carrier ring, A s the missile

roll and yaw axes rota te with

rs move witk the

ROLL SERVO M O T O R

SERVO M o m \

NCj. I7 PITCH RESOLVER

ROLL MICROSYN h

< YA W MICROS YN I r+-+

N/C@SYNS

NULL. ASSEMBLY 7------ 1

8 makes it d i f f i cu l t t o achieve

% by mechaniaa fonfng the i r rotors on the

ing the resistance

eratea a caging a c t u a t o ~

ST-120 CAGING MECHANISM ASSEMBLY

outward from the W ~ P ide, fnR.len the p la t fom and the missile are

i n f i r i n g posi is of the platform para l le ls the p i b h axis

of the missile,

The Y, axis is per ~&%r t o %he bottom surface of the carr ier

ring, with the vector p ward from the r o l l gyro side of the

ca r r i e r ring, When the o m and the missile are fn f i r ing position,

the Y, axis of %he? pP a ra l l e l s the r o l l axis of the missile,

The Xc axfa is para l l e l t o She bo tom surface of %he ca r r i e r r ing

and mutually perpendicular and 2, axes, with the vector

pointing outward from %he pi%eh side of the ca r r i e r rings When the

p la t fom and the missi e are i n the ve r t i ca l f i r ing position, the Xc

axis of the p la t fom paraPlieis %he axis of the missile with both axes

pointing toward the

o m ca r r i e r r ing are three i n t e g r a t b g

%ion of the missile along

h a t e s designated zeta ( f )

For cross ~ange , a ( Y\ ) fo r slant

%nee coordhate system is

ordinate system, but dis-

direction about the ca r r i e r

) -is pa ra l l e l s the c a r r i e ~

(s lant a l t i tude) axes l i e in

Ye axes, wiLh x i rotated

e%a perpendiculm t o x i i n the

The relationship be a t fom and guidance coordinates is such

tha t when the platform csordfnates are aligned i n horizontal and azbu th ,

the guidance cosrdfn es define an i n e r t i a l frame of reference for sensing

movements of red phase of i t s f l igh t ,

The xi axis extends from %he lamch s i t e a t rn angle of elevation of

42,s0 i n the direction of t h get, This angle was chosen t o correspond

t o the ~ 2 . 5 ~ s l e a t the point where the warhead

should begin i%s free ba l l i a range accelerometer

senses accelerations a l m g $he x i axis a s the basis f o r integrating s l a n t

range velocity and s lacement, %en the guidance computer

sees t h a t the missile has achieved the r igh t combination of velocity and

displacement a l g the x i axfa, 5% i n i t i a t e s the second stage cutoff

signal.

The e t a a s ax the Sauneh point upward a% an angle normal C

t o the slope of %he axis; and the s l an t a l t i tude acceleromete~ senses

a positive accelera e t a axis as the missile r i s e s toward

the balPist ic t r a j e e t am generator located in t h e guidance

computer develops a p em of signals which must be matched by the s l a n t

a l t i tude a c c ~ l e r m e t e r t o establish %he correct f l i g h t path, A s the

missile pitches over h % o %he k2,5O fntercept lines, the s l an t a l t i tude

Ian% a l t i tude velocity signal

m u s t reach a ond stage cutoff t o oecurc

launch point i n a hor imnta l

missile f l igh% traJectorya Sensing

posftive t o %he r ight , looking down-

aBs are used t o keep

the missile on trac and the cross range velocity signal must be a t n u l l

i n order fo r second stage cutoff t o occur,

11, B, Hain AssembPfe

Shaft 1, P

The shaft, (Photo Up524 i s the assembly foundation of the ST-120

Stable Platfom, On e i ther end sf the shaft, a b e l l flange i s assembled,

These flanges eonta gs (2 per flange), t ha t serve as positioning

and fastening devices fo r m0 able platform t o the missile, The

shaf t i s r ig id ly Past missile, and therefore w i l l follow any

changes i n position s e body, The shaft i s mounted para l l e l

t o the pitch axis of $he missiPe,

2,

d the r o l l and yaw centerpiece

assembly (Photo U5795),, The r o l l centerpiece i s r ig id ly secured t o the

yaw centerpiece, which turn i s supported within the shaft on bearings

t o provide the rol and yaw centerpiece assembly ~ 5 t h approximately plus

and minus 15 degrees r o t a t i a l freedm i n yaw, The yaw microsyn s t a t o r

assembly i s secured o the shaft , The yaw microsyn rotor i s mounted on

the yaw centerpiece, which a s con t ahs the yaw servo motor, The roll

servo motor, r o l l micros org and azimuth induetfve pickoff are mounted

on the r o l l cente

3.

The inner gimbal. assembly (Photo US7881 is assembled over the r o l l

centerpiece, being suppor ed on the r o l l centerpiece by bearings t o provide

approximately p us 3.5 degrees freedom i n r o l l , This, together

7 BRPORIITIBH -----

ri l les l P i l * i i i ClWlllON iiiissoD0 NEW 1 E 0 W

"Inner G i m b a l Assembly".

F T ASSEMBLY

of the gyro whesP t o cause precession of the gyro about i t s output ax is ,

Relative t o the AB-5 S tabi l iz ing 2yx-o, the output ax is (x) is

concentric t o the housing and the inner cylinder assembly ( ~ i ~ u r e 8), The

input a x i s (2) i s normal t o the output ax is and passes through the a i r

f i l t e r ( i n l e t ) adapter, The gyro spin axis ( y ) i s normal t o both of the

above axes, The d i rec t ion of ro t a t ion of the g p o wheel is such t h a t i t s

per iphera l movement i s from the a i r f i l t e r adapter toward the pickoff and

torquer which are d i r e c t l y under the crown of the cover and f i l t e r

assembly,

d, Application

A s applied t o the ST-120 Stabi l ized Pf-atform, each of the

three AS-5 Stabi l iz ing i;yros is mounted on the c a r r i e r r ing with i ts input

ax i s pa ra l l e l ing tha t platform coordinate axis about which it controls

s t a b i l i z a t i o n (Figure 91, The Pi tch Stabi l iz ing Gyro Unit (ZGU) has i t s

input ax is ZZw i n the same d i rec t ion a s the p l a t f o ~ m 2, axis , The Roll

Stab i l i z ing Gyro Unit (YGU) has i t s input ax is ZyCU in the same d i rec t ion

Y, axis* And the Yaw S tab i l i z ing Gyro Unit (XGU) has i t s

axis ZXGU i n the same directfon a s the platform Xc axis , A d i s t u r b h g

torque? exerted on the platform about any of i t s axes appears a s an input

t o the corresponding gyro, causing t h a t g y ~ o t o precess, The resulLfPlg

pickoff s igna l f s ampli f i e by the servo amplif ier s u f f i c i e n t l y t o d r i

the corresponding servo motor, which ap es t o the platform a torque

equal and opposit t o t h e o r ig ina l d i s t In t h i s way

platform is s t ab i l i zed with a r i g i d i t y ivaQent t o the s t i f f n e s s of t he

s t a b i l i z i n g servo loop,

To establish i t i a l orientation of the platform pr ior t o

l i f to f f , torquing si l i f i e d by the A l i m e n t W l i S e r and

applied t o the torquers i n the s tabi l iz ing gylros, Application of voltage

t o a gy.0 torquer forces uaP re-srienta e gyro spin axis

result ing i n a pickoff s i which drives the servo motor for repositioning

the platforms So Pang a s the torquer receives voltage, the semo motor

applies counter-torque a t f o m t o preven ther displacement

r drives the platform a t a ra te pro-

portional t o the torqu

2, BPIIAB-3 Acceleromtes

a, The APllGB-3 is a two degree of freed integrating gyro-

accelerometer, used t o pro-rl.de ctP-jica% velocity output signal in

response t o aece s i t i v e axis, Three AMAB-3 accel-

ed on the ca r r i e r ring of the ST-120 Stabilized Plat-

form (Photo ~573.3) with i ts sensit ive axes pa r a l l Zing the guidance

( f ) Slant Range and e t a ( r()

romete~ (Photo W2223-1) i s the

12,000 Rf3M ( ~ i g m e lo ) , The ro to r

irnder assembly, which acts as

e inner cylinder assembly is

leave and f o i assembly, This

ch i s s e t om b a l l bearings within

sf fiaedsm, Tho housing is mounted

ASSEMBLY WITH ACCELEROMETERS

AMAB-3 INTEGRATING ACCELEROMETER ASSEMBLY

on the p la tYmn c a r r i e r r ing, The inner cylinder asso~fibly i s mda pendulous

so it w i l l be torque by T i n e a ~ acceQerations. A I-i.ck-up f o ~ sensing the

pcsi-Lion aC "ci;? inner c y l i n d e ~ asserci%ly wi%? rcs-x:ct t o the intermediate

assembly i s nzol~nted on the h t e m e d i s i e ase;emby~y, 54th the shorted turn

a-ttached t o the inner cylindep assembljr, t ~ r e a ~ m p l i f i e r b u i l t i n t o the

accelerometer un i t r a i s e s the pickoff s igna l t o a l eve l su i t ab l e f o r trans-

mission t o the Scmo Amp r f i e r , The s t a t o r of t he controB (servo) motor

a s well as the seyne o %ransn:E?;ter a re secured t o ?;he houshg while t h e i r

ro to r s zrc pcsitioned by a largc Eear fastened t o the intermediate assemblye

c, Principle of Operation

lrshen?, t h e wi t i s acmlera ted along i t s sens i t i ve axis , t'ne

force of accelerat ion act ing or, the pendulous m i q h t produces a torque

about the a i r b g axis , This torquine: of the ~ y r o about t he a i r bearing

ax i s causes t he t o precess, r e su l t i ng i n ro ta t ion of the intermediate

assembly a t h i n tho housfng, I f the intermediate assembly i s re tarded by

bearing and gear f r i e t fon , there will be a s igna l from the pick-up, This

s igna l i s a m ~ l i f i e d by "r;e preamplifier and t h e servo amplif ier t o dr ive

o Hotor Lo overcome t h a t f r i c t i o n , Rotation of the intermediate

assembly is continous a s long a s t h accelerat ion ex is t s , Through s u i t -

ab le gearing, the in t emed ia t e assembly posi t ions the r o t o r of the synchro

t ransmit ter , producing an angular velocidy s igna l outpuk from i ts s t a t o r ,

d, AppLicati

A s applied t o t h e ST--120 S+,;?bilized Platform, nach cf the tkree

AGiB-3 Accelerometers i s mount d on the c a r r i e r r i ng with i t s sens i t i ve

ax is para l le l ing one of Vne kidance Coordinates, along which it senses

acceleration,

- l 3 -

cePerometer ha i t s sensit ive axis along the

i t y s ignal proportfonaP t o the

e r t o be used for

s sensitive axf mgular velocity

ge Accelerometer has

i ts sensitive ba%e, + 14;n angular veloeity

sent t o the Guidance

Comlptuter w h e ~ e second stiag

cut-off,

PHASE

SERVO MOTOR OPERATION

Each of the three ae@elerometers on the platform car r i e r ring

contains a servo motor9 the fune ion of which i s t o torque the accelerometer

intermediate assembly and s p c h r o transmitter, The ra te of rotat ion of

the servo motor i s proportiona91 t o the pick-off s ignal result ing from dis-

placement of the pendulous a i r beaping gimbal due to acceleration sensed

along the input axis.

4.

The mierosyn i s an angrrar position. transducer (Pho W2908). Two

ident ica l mierosyns are i r ~ c o ~ o ~ a t e d i n the ST-120 Stabilized Platform

gimballing system, designated $@Yaw MicrospH and itRoll Microsynn, These

microsyns sense a t t i tude deviations of the missile frame re la t ive t o the

platform, acting as er ror detectors i n the yaw and r o l l servo loops. A

block diagram representing a se loop is shown in (Figure 1 2 ) a

When the missil turns about the yaw axis, the yaw microsyn pro-

duces an error s i a9 voltage having an amplitude proportional t o the

amount of yaw, and a phase correspornding t o the direction of yaw, This

er ror signal is fed in to the control computer which commands missile

steering t o correct the missile a t t i tude thus reduce the error signal

voltage t o null , The ro E m%crssyn? servo loop operates Sn a manner

similar t o the y a w servo l o ~ ~ e The sens i t iv i ty of both microsyns is

300 mv/degree ,

The rotor of the yaw micros i s affixed t o the yaw center-

piece, and the s ta to r i s on the main shaft, liahen the missi le ro ta tes

about i ts yaw s, the main shaft ro ta tes with the missile frame, while

the yaw centerpiece re ta ins the reference of the pla t fom, Thus, missile

"Microsyn Assembly and Rotor".

INPUT

a. MICROSYN N OFF NULL

"Air Bearing Pe?ndulmw.

EXCITATION VOLTAGE

SLUG AIR BEARING

FIG. 13 AIR BEARING PENDULUM CUTAWAY

ROLL

FIG. 15 a. AZIMUTH PICK- UP

AZIMUTH PICK-UP SCHEMATIC

o reflecting surfaces

disposed a t right It is used during

of the ST-128 PlaL-

h g s o that jita dihedral

o the f i r ing az&nutho

$e assembly beemes

bough $he main

s of the h d i v i

BRACKET SICET

INPU T5 OUTPUTS

I G y m 4 ACCEL.

d,26<400-- WHEEL EXCI TA TION

PITCH CT( OUT COMM. f 2 8 V - D.C.

+ 28 V-D.C.

PRE -AMP SUPFL Y

u5q 400- GIMP4L 1 SERt'J ,115&400- &lv^T>fl

OUTPUT YAW SEFVO MOTOP

ROLL SERVO MOTOR

PITCH SEPVO MGTJt?

C/R ACCEL . P/O OUTPUT

4 CCEL. SEK I/O M O TOI:

ACCEL. SERVO MOT2R

/ ' CONTRQL I STATOR \ I I CONTROL.

TRANS FORMER

TO CONTROL COMPUTER

F/C;. 23 Pl TCH CAM PROGRA MMING

L.R. l6PCjM LIMIT

pendulum error signal is Sntegrated and used

potentiometer, The potentiometer supplies t o

signal suffieien

Carpier ring dispfaceme

z,) i s corrected in the s

pi tch alignmen

OOPS

P for proeess

circuitso

P be sensed by the

msmf t tad by the

against extraneous disturb

in flight, Any roll diap

f o m causes the P

summing networks

the roll error 81

4, Pit& Attitud

e pfteh attitud

gram, and of stabflixhg the

transient pitchin

pfteh progrm is genera 8

Pi f Per Box,

s the rotor of ov

from tha cause

Security Classification

None

None

None

None

Mone

None

Mone

Non

None

Mone,

None

Con fidsntial

Code Number Description Secuxi t y Classification

2 -51~-261 Missile Borne Guidance Computer Type No. Confidential 10586500-19 Gear and Elect r ica l Schematic Drawing and Description of the Slant Altitude Channel

2-SIC-261 Missile Borne Guidance Computer Type No, Confidential 10586500-19 Gear and Electr ical Schematic Drawing and Description of the Cross Range Channel

2 -5D-Es6X Missile Borne Guidance Computer Type Noe Confidential 10586500-19 Electromechanical Schematic hawing and Description of the Cutoff and Arming Circuit