st-120 stabilizing platform familiarization
TRANSCRIPT
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