Download - ST-120 Stabilizing Platform Familiarization
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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,
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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, $haft
2, Roll and Yaw Centerpiece Assembly
3, Inner Gimbal Assembly
4* Carrier Ring Assembly
C, Components
1, AB-5 Stabilizing G y m
2, A1UIAB-3 Accelerometer
3, S e m Motors
4, Microsyns
5, PenduLums
6, Azimuth Rck-up
7 , Pitch Control T~ansfomer (C ,T, )
8, Pitch Resolver
Page
1
I.
2
3
4
4
4
5
6
8
8
8
8
9
9
9
12
3-4
15
16
17
18
3.9
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9 , Nulling Card
10, Caging Motor
11, Porno Prism
12, Pneumatic System
13. Miscellaneous Componen$
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
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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
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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
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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
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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
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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 ,
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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
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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
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FIN I
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TCH
A TFOR ES
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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
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TRANSFORMER-RESOLVER AND CONNECTOR ASSEMBLY
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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
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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
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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
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ROLL SERVO M O T O R
SERVO M o m \
NCj. I7 PITCH RESOLVER
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ROLL MICROSYN h
< YA W MICROS YN I r+-+
N/C@SYNS
NULL. ASSEMBLY 7------ 1
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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 ~
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ST-120 CAGING MECHANISM ASSEMBLY
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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
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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
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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
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7 BRPORIITIBH -----
ri l les l P i l * i i i ClWlllON iiiissoD0 NEW 1 E 0 W
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"Inner G i m b a l Assembly".
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F T ASSEMBLY
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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,
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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
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ASSEMBLY WITH ACCELEROMETERS
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AMAB-3 INTEGRATING ACCELEROMETER ASSEMBLY
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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 -
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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,
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PHASE
SERVO MOTOR OPERATION
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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
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"Microsyn Assembly and Rotor".
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INPUT
a. MICROSYN N OFF NULL
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"Air Bearing Pe?ndulmw.
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EXCITATION VOLTAGE
SLUG AIR BEARING
FIG. 13 AIR BEARING PENDULUM CUTAWAY
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ROLL
FIG. 15 a. AZIMUTH PICK- UP
AZIMUTH PICK-UP SCHEMATIC
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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
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BRACKET SICET
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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
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/ ' CONTRQL I STATOR \ I I CONTROL.
TRANS FORMER
TO CONTROL COMPUTER
F/C;. 23 Pl TCH CAM PROGRA MMING
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L.R. l6PCjM LIMIT
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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
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OOPS
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P for proeess
circuitso
P be sensed by the
msmf t tad by the
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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
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Security Classification
None
None
None
None
Mone
None
Mone
Non
None
Mone,
None
Con fidsntial
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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