OR 13,149

Pershing Ia System Description June 1974

OR 13,149

MARTIN MARIE'ITA AEROSPACE ORLANDO DIVISION P.O. BOX 5837

T h e P e r s h i n g Weapon y s t e m constitutes one of the United State?s major nuclear iy in Europe and continues t o d e t e r r e n t forces, The s y s t e m is deployed operat r and t h e maintenance of peace, stantial contribution t o the balance of m

a ) which was derived by a n evoiutionary I he c u r r e n t v e r s i o n i s the P e r s h i n g m e n t s t o the initial s y s t e m iguralion, This book p r o c e s s of continuous i m p r on of the P e r s h i n g la m a j o r ipment items, provides a functional d e s c r under t h e direction of Ro e r t L. Ferguson, This book was nd was composed, edited, and for atted by Charles E. Waters, System Engineeri P e r s h i n g Presentations.

Reprinted by Army Field with permission of Martin Marietta Cfirporation.

.G e n e r a l System Description

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P e r s hing I a F i r i n g B a t t e r y Components

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Chapter One

Missile . . . . . . . . . . . . . e . e . ~ . . . . . . . E r e c t o r - Launcher P r o g r a m m e r - T e s t Station and P o w e r Station Azimuth Laying Set B a t t e r y Control C e n t r a l Radio T e r m i n a l Set

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....................................... ...................... ...................................... ................................... ...................................... R e a r A r e a Support Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

............................. ................................... ......................................... ................................. issile . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

System Components T e s t Station Power Station Equivalent Support Shops MissileSectionContainers

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Chapter Two Airframe

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3 3 4 4 6 6 7 7 7

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........................................ 9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 Propulsion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2 Propellant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . F i r s t Stage Motor Assembly and C a s e . . . . . . . . . . . . . . . . . . . . . . . . . . otor Assembly and C a s e . . . . . . . . . . . . . . . . . . . . . . . . . 14 ulatioa . . . . . . . . . . . . . . . . . . . . . . . . . . . . . a * . . . . . ......................................... F i r s t and Second Stage otor Nozzles . . . . . . . . . . . . . . . . . . . . . . . . . 16 Warhead Section GuidanceandControlSection o r Section r Section

Guidance and Control

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Guidance Scheme Control Scheme entati.cn ntation Referenee System ntrol Computer Actuator System

........................................ .................................. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . . ............................ ............................. ........................................ Electrical . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Static I n v e r t e r . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ain Distributor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

.................................. .................................... e r T h r e e .E r e c o r - l a u n c her . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . High Energy F i r i n g Units P o w e r Distributor Additional Equipment

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...................................... .......................................... ..................................... ............................................. ............................... ................................... ..............................*..me.. ................................ ................................ ................................

e r Assembly ernbly Azimuth Ring Assembly ast on Handling Device itAssembly tions

............................... ................................ ................................ ads . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ................................ Associated Corn onents . . . . . . . . . . . . . . . . ................................ ................................ ................................

......*.................................*..... ......................................... .... ................................ . . . . . . . . . . . . . . . . . . . . . . . . . . . .. ........................................... .................................. ................................... ...........................

Booms issile Cradle Retaining Ring Half War head Section Handling eviee Control Box raulie Control P a n e l Hydrauli or Erection lock and Associated Corn onents Transporter Asse b l y . . . . . . . . . . . . . . . . . * e . . . . . . . s . e . . e e e e *

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P h y s i c a l Data Functional Data Leveling System

.......................................... ................................ ................................ Erection System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Level Sensor E l e c t r i c a l Control C i r c u i t r y anual Drive

.............................. ................................... ........................................... ......................................... .................... ..................................... ......................................... .......................................... ................................. ............................. ................................... .............................................. ......................................... ....................................... ............................ .................................... ................ Chapter F o u r - P r o g r a m m e r - T e s t Station . . . . . . . ; . . . . . . . . . . . . . . . . . . Shelter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Hydraulic E r e c t i o n Assemblies Hydraulic Accumulator. Pilotvalve Selector Valve E r e c t i o n Manifold and Associated Components Hydraulic Actuators Electric Pump anual Pump ydraulic S y s t e m Oil Tank Mechanical E r e c t i o n Assemblies Azimuth Ring Assembly Booms Missilecradle Retaining Ring Half Uplock and Associated Components Cable Mast Assembly Azimuth Ring Assembly Clamp Release echanism

.............................................. ................................................ Operations Control Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Command and Monitoring Function . . . . . . . . . . . . . . . . . . . . . . . . . . . P l a t f o r m Alignment Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AC /DC Stimuli Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Measurements Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . P r e s e t t i n g Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Modules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Adapter F i l t e r Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Adapter E l e c t r i c a l Equipment Rack . . . . . . . . . . . . . . . . . . . . . . . . . . . voltage Measurement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stimulus Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inverter Frequency . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Synchro P r e s e t . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Remote F i r e Box . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Console . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Azimuth Laying Control P a n e l Assembly . . . . . . . . . . . . . . . . . . . . . . . itor P a n e l Assembly . . . . . . . . . . . . . . . . . . . . . . . Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tape Reader . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Countdown Control P a n e l Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . Utility P a n e l Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Teleprinter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Launch Control Panel. Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Computer Adapter

63 63 63 64 64 64 64 64 64 64 64 66 66 67 67 67 67 69 69 69 69 72 73 75 76 77 77 79 79 79 79 79 79 8 81 81 81 81 82 82 83

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................................... G e n e r a l Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . G a s Turbine Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Gearbox . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . High P r e s s u r e Air System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Air Cycle Conditioning System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DC Power System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AC Power System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . h e r Subsystems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Chapter Six .Azimuth Laying Equipment Set . . . . . . . . . . . . . . . . . . . . . . . . Equipment Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ~ o r i z o n t a l / V e r t i c a lLaying Theodolite . . . . . . . . . . . . . . . . . . . . . . . . . Orienting Station Theodolite . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Orienting Line T a r g e t . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Azimuth Laying Control Box . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Miscellaneous Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Chapter F i v e

.Power Station

.......................................... General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E r e c t and F i r e Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V e r t i c a l Laying Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Chapter Seven .B a t t e r y Control C e n t r a l . . . . . . . . . . . . . . . . . . . . . . . . . . . Physical Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E l e c t r i c a l Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Chapter Eight .Communications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Laying Methods

.............................. ............................. Chapter Nine .Ground Networks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Chapter T e n .System Components T e s t Station . . . . . . . . . . . . . . . . . . . . . . . E x t e r i o r Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SCTS Major Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Major PTS Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Major SCTS Consoles and Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . Assembly T e s t e r . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pneumatic T e s t Console . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Distribution Console . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cable Entry P a n e l s . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Equipment Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANiTRC.80. Radio T e r m i n a l Set ANITRC- 133A. Radio T e r m i n a l Set

AC /DC Differential Voltmeter and Oscilloscope t e r Eleven

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.ARS/SLA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Automatic Reference System Azimuth Reference Unit Reference Assembly . . r o n i c s Unit . . . . .

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................................... ment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ueritial Launch A er . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . de . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ......................................... r i e a l Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . neurnatic Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ly

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Typical P e r s h i n g Flight Scenario P e r s h i n g Ia F i r i n g B a t t e r y Components Surface Attack Guided Missile XMGM-31A ( P e r s h i n g Missile) T r a c t o r with Erector-Launcher P r o g r a m m e r - T e s t StationlPower Station Azimuth Laying Set B a t t e r y Control C e n t r a l Radio T e r m i n a l Set AN/TRC-80 S y s t e m Components T e s t Station Power Station Equivalent Typical R e p a i r Shop Typical Maintenance Shop and Supply Van M i s s i l e Section Shipping and Storage Containers P e r s h i n g M i s s i l e A e r o and S t r u c t u r a l Components P e r s h i n g M i s s i l e Sections P e r s h i n g F i r s t and Second Stage Motors F i r s t Stage Motor Section. Inboard P r o f i l e Second Stage Motor Section. Inboard P r o f i l e Guidance and Control Section Guidance and Control S y s t e m Functional Schematic Missile Guidance Coordinates and E r r o r s M i s s i l e Attitude E r r o r s Missile Response t o Attitude E r r o r s Missile Coordinate S y s t e m Pitch/Yaw Loops Rollhop Steering Scheme e r t i a l System i s s i l e Axes Orientation ST- 120 Gimbals AB-5 Gyroscope

The P e r s h i n g Ia Weapon System i s a tactical, mobile ballistic m i s s i l e s y s t e m possessing the capability t o respond effectively to any nuclear o r m a j o r nonnuclear t h r e a t to the United States o r its allies. The s y s t e m i s comprised of all firing b a t t e r y components required to conduct launch operations a s well a s equipment n e c e s s a r y f o r r e a r a r e a support and maintenance functions. In i t s basic s c e n a r i o , the m i s s i l e d e l i v e r s a nuclear warhead to preselected t a r g e t out to a range of 4C0 m i l e s f r o m the launch point ( F i g u r e 1-1). When the m i s s i l e is f i r e d , the f i r s t stage rocket motor i s ignited, Pershing liftoff o c c u r s and the m i s s i l e begins a predetermined pitchover maneuver toward the target. When f i r s t s t a g e burnout is achieved the m i s s i l e e n t e r s a c o a s t period. At the end of the coast period, f i r s t stage separation o c c u r s and the second s t a g e rocket motor i s ignited to a c c e l e r a t e the remaining m i s s i l e sections along the flight path. During second stage burn, the guidance computer constantly computes the m i s s i l e ' s velocity and displacement. When the p r o p e r values of attitude, r a n g e , and velocity have been attained a t h r u s t termination signal i s applied, second s t a g e s e p a r a t i o n o c c u r s , and the warhead i s spun a t 32 r p m t o stabilize its forward motion a s it continues on a ballistic t r a j e c t o r y t o the t a r g e t .

SEPARATION

-I

BURNING PHASE

Per

a

The various components required t o conduct launch operations a t the firing battery a r e the m i s s i l e , e r e c t o r - l a u n c h e r , p r o g r a m m e r - t e s t station and power station, azimuth laying s e t , b a t t e r y control c e n t r a l , and the radio t e r m i n a l s e t . A l l of these components a r e mounted on wheeled vehicles ( F i g u r e 1 - 2 1 except f o r the azimuth laying s e t which i s t r a n s p o r t e d on a 2 1/2 ton c a r g o vehicle and unloaded f o r use.

T h e P e r s h i n g m i s s i l e ( F i g u r e 1- 3) is a two-stage, s u r face-to-surface ballistic weapon c a able of engaging t a r g e t s miles. It has an all-inertial guidance s y s t e m e s t h e nuclear warhead in a preselected ballistic t r a j e c t o r y by using data inserted into t h e guidance and cont e r before liftoff. Once t h e m i s s i l e is airborne, etely f r e e of ground control and t h e r e f o r e unaffected by a l l known methods of guidance countermeasures.

Designed f o r simplified transportation and fast erection and firing of the P e r s h i n g m i s s i l e , the e r e c t o r - l a u n c h e r (Figure 1-41 i s capable of paved road o r c r o s s country t r a v e l . At the firing s i t e automatic erection and leveling contribute t o a v e r y rapid r a t e of f i r e . The e r e c t o r - l a u n c h e r ( E L ) with m i s s i l e aboard i s towed by the XM757 t r a c t o r . The e r e c t o r - l a u n c h e r with m i s s i l e aboard can a l s o be transported by C-130, (2-133, and C - 1 4 1 a i r c r a f t .

r o g r a m m e r - t e s t station own in F i g u r e 1 - 5 i s 656 vehicle and feat u r e s rapid m i s s i l e checkout and countdowns, with complete computer control, and automatic s e l f t e s t and malfunction isolation. Additionally, the P T S p e r f o r m s t e s t s that simulate a i r b o r n e m i s s i l e operation, p r o g r a m s the t r a j e c t o r y of the m i s s i l e , and controls the firing sequence. Modern electronics packaging, featuring plug-in micromodules, i n c r e a s e s maintainability and allows the PTS o p e r a t o r to perform 80 percent of all r e p a i r s at the f i r ing position. The power station, which provides the p r i m a r y e l e c t r i e a l and pneumatic power f o r the m i s s i l e and ground support equipment a t the firing position, i s t r a n s ported on the s a m e vehicle.

The azimuth laying s e t ( F i g u r e 1 - 6 ) , which i s s i m i l a r in design and function to standard surveying equipment, i s used to align the m i s s i l e i n e r t i a l guiance s y s t e m t o the c o r r e c t t a r g e t azimuth. All of the equipment i s s t o r e d in two protective containers and c a r r i e d aboard an auxiliary equipment vehicle.

T o control the Pershing e n s u r e nuclear safety, the battery commander monitors and d i r e c t s firing s i t e activities by maintaining communications with ail units f r o m a firing battery con-

is a l s o linked with other b a t t e r i e s and ion headquarters f o r positive com-

T o control and coordinate firing batt e r y operations, s e v e r a l communication links a r e established with higher headq u a r t e r s . Battalion communications a r e maintained with the radio t e r m i n a l s e t , g u r e 1-8). The radio d e r provides voice and t e l e type communications between m i s s i l e firing units and higher headquarters. During t r a v e l the inflatable antenna is stored in a r e c e s s e d space in the roof of the RTS. Like the other elements of the firing b a t t e r y the RTS i s c a r r i e d on an M6 56 vehicle. Radio t e r m i n a l s e t , A N / T R C - ~ ~ ~i sA , a l s o used at the firing s i t e a s the p r i m a r y QRA (Quick Reaction Alert) r e l e a s e m e s sage s y s t e m . T h e A N / T R C - ~ ~ Si sAgove r n m e n t furnished equipment.

elements of the s y s t e m a r e maintained in a s t a t e of combat r e a d i n e s s by Lie r e a r a r e a support e

The s y s t e m components t e s t station (SCTS} i s used t o perform r e a r a r e a maintenance of the Pershing s y s t e m ( F i g u r e 1-91. Housed in a mobile c e n t e r , the SCTS utilizes a computer and tape p r o g r a m s f o r testing m i s s i l e sections, assemblies, c a r d s , r e l a y s , and modules f r o m the guided m i s s i l e and associated ground support equipment. Diagnostic tape p r o g r a m s a r e a l s o provided f o r verification and troubleshooting of m a j o r SCTS a s s e m b l i e s . The SCTS contains a dismounted PTS and h a s facilities whereby one m i s s i l e guidance section can be tested and another r e p a i r e d simultaneously under controlled t e m p e r a t u r e conditions. Power f o r the SCTS originates f r o m the power

T h e power station equivalent (PSE) provides the s a m e outputs a s the firing battery power station but i s capable of m o r e sustained o p e r a tion. Comprised of two t r a i l e r mounted power stations and one facilities distribution t r a i l e r F i g u r e 1-10), the PSE furnishes a l l the power required for r e a r a r e a checkout.

S e v e r a l shops and s e m i t r a i l e r vans ( F i g u r e s 1-11 and 1-12) a r e assigned to the r e a r a r e a t o provide facilities f o r e l e c t r i c a l and mechanical maintenance and r e p a i r , p a r t s s t o r a g e , and offices f o r direction and control of d i r e c t support and general supp o r t maintenance functions.

Separate r e u s a b l e shipping and s t o r a g e containers (Figure 1-13) a r e provided f o r each of the four m i s s i l e sections. The containers protect the m i s s i l e sections f r o m the effects of e x c e s s i v e vibration, abnormal handling, and intolerable atmospheric conditions.

P e r s h i n g i s a two s t a g e , solid propellant b a l l i s t i c m i s s i l e ( F i g u r e 2-1). T h e m i s s i l e a i r f r a m e is 415.27 i n c h e s long, h a s a m a j o r d i a m e t e r of 40 i n c h e s , and weighs approxim a t e l y 10,000 pounds. Monocoque in construction, the m i s s i l e h a s an o u t e r skin a s s e m bled t o t r a n s v e r s e r i n g s f o r rigidity during flight and ground handling. Splice r i n g s m a k e warhead s e c t i o n s , guidance and c o n t r o l s e c t i o n s , and second and f i r s t s t a g e m o t o r s e c t i o n s completely interchangeable. Flight c o n t r o l is maintained by using s e t s of t h r e e a i r and jet v a n e s a t the aft end of e a c h m o t o r section; t h e s e v a n e s a r e mounted 1 2 0 d e g r e e s a p a r t around the m o t o r p e r i p h e r y . Specific locations along the m i s s i l e longitudin a l line a r e m e a s u r e d in i n c h e s f r o m s t a t i o n 100, a point 3.99 i n c h e s in front of the m i s s i l e nose. P e r s h i n g i s s t r u c t u r a l l y and functionally divided into four s e c t i o n s : the w a r head s e c t i o n , the guidance and c o n t r o l section, and the second and f i r s t s t a g e m o t o r s e c tions ( F i g u r e 2-2).

T h e warhead s e c t i o n is c o n s t r u c t e d on an aluminum s u b s t r u c t u r e with an ablative type p l a s t i c s h e l l of v a r y i n g t h i c k n e s s . T h i s s h e l l is fabricated f r o m l a y e r s of pheonolici m p r e g n a t e d , r a n d o m o r i e n t e d a s b e s t o s tape, c u r e d into a homogeneous s t r u c t u r e under heat and high p r e s s u r e . T h e s u r f a c e is h a r d and b r i t t l e with ablative c h a r a c t e r i s t i c s . In the final phase of flight, the warhead s e c t i o n b e c o m e s a r e e n t r y body exposed to the heating e f f e c t s of high speed p a s s a g e through a t m o s p h e r e . T h e varying t h i c k n e s s of the s k i n is designed in a c c o r d a n c e with the r a t e of ablation experienced by the r e e n t r y body when subjected t o t h e s e heating effects. Nose cone, c e n t e r , and aft s u b s e c t i o n s f o r m the warhead section.

BODY SECTION, GUIDED M I S S I L E , WARHEAD ( X M 2 8 )

1 2 PAD, AIR VANE ( 3 ) 13 SHELL, BODY, F I R S T STAGE 1 4 ROCKET MOTOR ASSEMBLY, F I R S T STAGE 15 J E T VANE ( 3 ) 1 6 FLAME S H I E L D ( 3 ) 17 BOLT, MACHINE (~ 21- , i s AIR VANE ( 3 ) 19 PAD, A I R VANE ( 3 ) 2 0 BAND, SECTION ( 4 ) 21 SHELL, BODY, SECOND STAGE 2 2 ROCKET MOTOR ASSEMBLY, SECOND STAGE 23 CASE VENTING- SYSTFM - - 2 4 THRUST REVERSAL PORT COVER ( 3 ) 25 THRUST REVERSAL PORT ( 3 ) 2 6 BOLT. MACHINF ( 7 1 2 7 CONNECTING L I N ~ S ' ( P ) 2 8 BASE STRUCTURE ASSEMBLY 2 9 COVER ASSEMBLY 30 BOLT, MACHlNE ( 2 )

BODY SECTION, GUIDED M I S S I L E , GUIDANCE AND CONTROL ( X M 9 2 )

BODY SECTION, GUIDED M I S S I L E , SECOND STAGE (XM102)

T h e n o s e cone subsection is a plastic cone a s s e m b l e d with a n o n s t r u c t u r a l nose l i n e r having an aluminum s p l i c e ring a t the aft end. The c e n t e r subsection i s a double-cone f r u s t u m shaped a s s e m b l y with the p e r i p h e r a l s h e a r type of aluminum s p l i c e r i n g s located at i t s f o r w a r d and aft ends. An additional f r a m e with longitudinal s t i f f e n e r s placed r a d i ally in the aft end is used to support the warhead and related networks. T h e aft s u b s e c tion, s i m i l a r in construction t o the c e n t e r subsection, is mated to the c e n t e r subsection with an aluminum s p l i c e ring. An insulated, domed aluminum bulkhead, located at the aft end of this subsection, i s the c l o s u r e f o r the warhead s e c t i o n . Both the spin s y s t e m and c o v e r plate a r e mounted on t h i s bulkhead. A s p l i c e ring a s s e m b l y c o u p l e s the w a r head s e c t i o n with the guidance and c o n t r o l section. T h e s p l i c e ring is held together by explosive bolts to p e r m i t inflight s e p a r a t i o n of the two s e c t i o n s .

The guidance and c o n t r o l section i s a two piece, m e t a l conical, f r u s t u m shaped s t r u c t u r e p r e s s u r i z e d t o p e r m i t t e m p e r a t u r e and p r e s s u r e c o n t r o l f o r a i r b o r n e guidance and c o n t r o l equipment. T h e two p i e c e s a r e the c o v e r forward section) and the b a s e tion), A s p l i c e ring a s s e m b l y joins the guidance and c o n t r o l section and second s t a g e m o t o r section. Conventional bolts a r e used t o hold the s p l i c e ring together s i n c e no i n flight s e p a r a t i o n o c c u r s at this i n t e r f a c e . Support b r a c k e t s f o r the components and wiring, and the a i r d u c t s and manifold f o r the ST-120 a i r supply a r e i n t e g r a l p a r t s of the i n t e r n a l s t r u c t u r e .

T h r e e m a j o r s t r u c t u r a l p a r t s c o m p r i s e the second s t a g e m o t o r section: the second s t a g e m o t o r c a s e , the f o r w a r d m o t o r a d a p t e r , and the aft c o n t r o l s package. T h e hydrospun, high s t r e n g t h D6AC s t e e l c a s e s e r v e s a d u a l p u r p o s e in being both the propellant c o n t a i n e r a r d the o u t e r skin of the m i s s i l e in the c e n t e r of the section. T h e f o r w a r d m o t o r a d a p t e r , attached t o the domed end of the m o t o r c a s e , adapts to the guidance and c o n t r o l section by a V-band s p l i c e ring. T h e f o r w a r d m o t o r a d a p t e r is 4 i n c h e s in d i a m e t e r and 19.93 i n c h e s wide. S t r u c t u r a l s u p p o r t between t h e second s t a g e m o t o r c a s e and t h e f i r s t s t a g e motor Feetion is provided by the aft c o n t r o l s package which h o u s e s the a i r vane and jet vane a s s e m blies, t h r e e hydraulic a c t u a t o r units, a f l a m e s h i e l d , and a i r vane pads. In addition t o the i n t e r n a l s t r u c t u r e , a conduit c o v e r and c a s e venting shaped c h a r g e s a r e attached t o the o u t e r skin of the m i s s i l e .

Like the second s t a g e , the f i r s t s t a g e i s c o m p r i s e d of t h r e e m a j o r s t r u c t u r a l p a r t s : f i r s t s t a g e m o t o r c a s e , f o r w a r d m o t o r a d a p t e r , and aft c o n t r o l s package. M a t e r i a l and c o n s t r u c t i o n techniques used f o r the f i r s t and second s t a g e m o t o r c a s e s a r e the s a m e ; however, the f i r s t s t a g e is l a r g e r and h o u s e s no i m p u l s e c o n t r o l equipment. The f i r s t s t a g e m o t o r c a s e a l s o s e r v e s a s the o u t e r m i s s i l e skin in the c e n t e r portion of the s e c tion. T h e forward m o t o r a d a p t e r is provided to adapt the f i r s t s t a g e m o t o r section t o the second s t a g e . T h e s p l i c e r i n g V-band, a four s e g m e n t band having explosive links with detonator a s s e m b l i e s adapted t o i t , m a t e s the s e c t i o n s . S t r u c t u r a l s u p p o r t between the f i r s t s t a g e m o t o r c a s e and the azimuth ring of the e r e c t o r - l a u n c h e r is provided by the f i r s t s t a g e aft c o n t r o l s package. It a l s o provides s u p p o r t and housing f o r the t h r e e hydraulic actuation s y s t e m s , f l a m e shield, a i r and jet v a n e s , f o r w a r d a i r vane pads, and the t a i l plug a s s e m b l y . In addition to the i n t e r n a l s t r u c t u r e , a conduit c o v e r i s e x t e r n a l l y mounted between the forward m o t o r a d a p t e r and the aft control package.

T h e p r i m a r y function of the r o c k e t m o t o r s ( F i g u r e 2-3) i s to propel the Perstling m i s s i l e f r o m liftoff to f i r s t s t a g e s e p a r a t i o n and f r o m second stage ignition to cutoff. At t h i s t i m e the warhead section i s s e p a r a t e d f r o m the guidance and c o n t r o l and second s t a g e s e c t i o n s and b e c o m e s a f r e e b a l l i s t i c m i s s i l e .

Pro hifotor propellant used is of a composite c a s t f o r m u l a using aluminum powder a s the fuel, ammonium p e r c h l o r a t e a s the o x i d i z e r , and polybutadiene a c r y l i c acid (PBAA) a s the binder (the PBAA a l s o s e r v e s a s a fuel). Both m o t o r s have an i n t e r n a l burning c y l i n d r i c a l c o r e which t e r m i n a t e s in a dome shaped s l o t at the head end. Since PBAA b i n d e r i s b a s i c a l l y a synthetic r u b b e r , t h i s f o r m u l a and configuration r e s i s t c r e e p o r s l u m p during s t o r a g e p e r i o d s .

T h e f i r s t s t a g e m o t o r a s s e m b l y c o n s i s t s of o n e solid p r o p e l l a n t r o c k e t m o t o r with i n t e g r a l f o r w a r d a d a p t e r , one V s p l i c e band, two f i r i n g unit a s s e m b l i e s , t h r e e h y d r a u lic packages, t h r e e a i r v a n e s , t h r e e jet v a n e s , t h r e e a i r v a n e pads, f l a m e s h i e l d , i n i t i a t o r s , d e t o n a t o r s , s e p a r a t i o n l i n k s , torquing links, e l e c t r i c a l n e t w o r k s h a r n e s s e s , and e x t e r n a l conduit c o v e r ( F i g u r e 2 -4).

A hydrospun c y l i n d r i c a l s e c t i o n , the f i r s t s t a g e motor. c a s e is g i r t h welded t o an e l l i p t i c a l forward dome and a conical aft dome. T h e e n t i r e c a s e i s m a d e of DGAC high s t r e n g t h s t e e l , T h e forward dome h a s an opening i n the c e n t e r f o r the pyrogen unit and the aft dome contains provisions f o r attaching the nozzle t o the m o t o r . il f o r w a r d adapte r is riveted to the c a s e to provide f o r i n t e r s t a g e connectiotl. T h e P B A A propellant i s c a s t into the m o t o r c a s e , then c u r e d , and the nozzle attached.

Except f o r length the second s t a g e m o t o r a s s e m b l y i s s i m i l a r to the f i r s t s t a g e . S h o r t e r than the f i r s t s t a g e m o t o r a s s e m b l y , the second s t a g e c a s e a l s o h a s a c a s e venting s y s t e m and i m p u l s e c o n t r o l s y s t e m ( F i g u r e 2-5). An i m p u l s e c o n t r o l s y s t e m is provided t o reduce f o r w a r d t h r u s t of the second s t a g e m o t o r , a t any p r e d e t e r m i n e d time o v e r the designed operatirlg r a n g e of the s y s t e m , t o p e r m i t effective warhead section separa"con. The s y s t e m c o n s i s t s of t h r e e p a r t s placed s y m e t r i c a l l y , 120 d e g r e e s a p a r t i n the m o t o r f o r w a r d dome. An irnpulse c o n t r o l tube p r o j e c t s f r o m e a c h port at an angle of 3 i i . 5 d e g r e e s f r o m the m o t o r longitudinal c e n t e r line t o an opening in the m o t o r forward a d a p t e r . Each port i s plugged with an aluminum

e retainer assern

The case venting system mounted on the external hor ucing flow interference etween the war

Air

ane

3

Vent

m 121

SECTION 6-C

ir Vane

Air Vane

During burning, the m o t o r c a s e i n t e r i o r i s protected by a combination of the unburned propellant, a l a y e r of l i n e r , swept-in-insulation in the f o r w a r d d o m e insulation is a c a r boxyl t e r m i n a t e d PBAA ( C T P B ) p o l y m e r composition which i s swept into the f o r w a r d d o m e . T h e aft d o m e insulation, a h a r d , premolded p l a s t i c , s e a l e d with an epoxy and polysulfide composition, i s bonded t o the aft d o m e of the m o t o r with the s a m e m a t e r i a l used f o r the f o r w a r d insulation.

P e r s h i n g m o t o r s a r e ignited by a pyrogen unit which, i n t u r n , i s ignited by two e x ploding b r i d g e w i r e i n i t i a t o r s and a s m a l l pyrotechnic c h a r g e . T h e pyrogen unit i s a m i n i a t u r e r o c k e t m o t o r which v e n t s i t s r o c k e t exhaust p r o d u c t s i n t o the combustion c h a m b e r of the m o t o r t o b r i n g the t e m p e r a t u r e and p r e s s u r e up to the point w h e r e the propellant g r a i n will ignite. T h e g r a i n of the pyrogen unit is a l s o PBAA c a s t and shaped t o expose as m u c h burning s u r f a c e a s possible. T h i s , in t u r n , p r o v i d e s a v e r y s h o r t burning t i m e f o r achieving t h e highest possible p r e s s u r e and t e m p e r a t u r e in the f i r s t s t a g e m o t o r combustion c h a m b e r t o e n s u r e i n s t a n t a n e o u s ignition, T h e pyrogen unit c a s e is filament wound f i b e r g l a s s attached t o a s t e e l a d a p t e r t o p e r m i t attachment t o the m a i n m o t o r c a s e , E a c h pyrogen unit is fitted with two i n i t i a t o r s , e a c h on a s e p a r a t e channel t o e n s u r e ignition.

T h e f i r s t s t a g e flight nozzle h a s an a v e r a g e expansion r a t i o of 7.06; the second s t a g e r a t i o is 15.06. T h e s e n o z z l e s c o n s i s t of interlocked s t e e l attachment r i n g s , a n e n t r a n c e and exit section of molded chopped g r a p h i c cloth, a c a r b o n t h r o a t i n s e r t , and a f i b e r g l a s s shell. T h e s h e l l is a combination of r e s i n - i m p r e g n a t e d , b i d i r e c t i o n a l g l a s s cloth and a l t e r n a t e l a y e r s of r e s i n - i m p r e g n a t e d , c i r c u m f e r e n t i a l f i b e r g l a s s winding, attached t o the aft end of the m o t o r c a s e with bolts through the s t e e l attachment ring.

T h e guidance and c o n t r o l s e c t i o n ( F i g u r e 2 - 6 ) contains the e l e c t r i c a l and e l e c t r o n i c a s s e m b l i e s that c o n t r o l the t r a j e c t o r y of the m i s s i l e . T h e m a j o r a s s e m b l i e s of the guidance and c o n t r o l section a r e the ST-120 stabilized platform and i t s a s s o c i a t e d s e r v o a m p l i f i e r , the guidance and c o n t r o l c o m p u t e r ( G & C C ) , m a i n d i s t r i b u t o r , and power supplies. T h e p r i m a r y power s u p p l i e s c o n s i s t of the m i s s i l e b a t t e r i e s and a s t a t i c i n v e r t e r . O t h e r components a r e an a i r bottle, a h i g h - p r e s s u r e a i r distribution s y s t e m , and s a f e t y r e l a y s f o r discontinuing a f i r i n g sequence, if n e c e s s a r y , a f t e r ground power h a s been r e m o v e d . T h e guidance s y s t e m d e t e c t s e r r o r s in the m i s s i l e t r a j e c t o r y , a s c o m p a r e d to the p r e d e t e r m i n e d flight path, and c o n v e r t s these e r r o r s into guidance s i g n a l s . T h e c o n t r o l s y s t e m c o m b i n e s the guidance s i g n a l s with attitude s i g n a l s t o g e n e r a t e a c o r r e c t i v e s i g n a l f o r t r a n s m i s s i o n to the c o n t r o l packages. ?In the guidance s y s t e m , the ST-120 provides m i s s i l e attitude and velocity information f r o m which deviations f r o m the progra-mmed t r a j e c t o r y a r e computed by the C;&CC, T h e s e r v o a m p l i f i e r w o r k s with t o c r e a t e a s t a b l e r e f e r e n c e f r o m which the t r a j e c t o r y deviations a r e o b tained. T h e G&CC combines the guidance s i g n a l s with the m i s s i l e attitude r e f e r e n c e d a t a f r o m the ST-120 to c r e a t e the combined c o n t r o l s i g n a l that o p e r a t e s the c o n t r o l packages. T h e guidance s y s t e m continuously m o n i t o r s the a c t u a l velocity and d i s p l a c e m e n t of the m i s s i l e along the t r a j e c t o r y , c o m p a r e s the a c t u a l d a t a with the p r e s e t i n f o r m a t i o n , and c a l c u l a t e s the e x a c t instant f o r second s t a g e cutoff and warhead s e p a r a tion.

WINDOW

ea

The improved PZa guidance and control s y s t e m i s designed t o function in an almost identical fashiori a s i t s p r e d e c e s s o r . The irn Zernentation of both the guidance scheme and the control scheme w e r e ased on identical c a r r y o v e r r e q u i r e m e n t s f r o log m i s s i l e , The guidance s c h e m e is an implicit scheme which is based on b e r of computer flown t r a ~ e c t o r i e st o a r r i v e a t t h e p r e s e t s f o r a given mission. The a s a function of s t e e r i n g scheme i s o timized so that two basic pitcho l t a r g e t s o v e r the P e r s h i n g The control. s y s t e m type of s y s t e m using m i c r o koffs from the ST-12 eh, yaw, and r o i l command e commands which cirive f o r m simultaneous guidance and control i n all t h r e e such a fashion to and control s y s t e m is shown in F i g u r e 2 - 7 . Basically, g r a m of the guida rovides t h r e e velocity and t h r e e attitude s i g n a l s to the G&CC f o r guidance and control computations, r e ectively. The C & C t e s the n e c e s s a r y ane commands and i n i t i a t e s uring flight,

SECOND STAGE

LIFT AND CUTOFF TO WARHEAD

NOTE

SL CR RN PO

= = = =

T h e P e r s h i n g guidance s c h e m e c o n s t r a i n s the t o t a l t i m e of flight s u c h that the t a r g e t position at i m p a c t and the f i r i n g a z i m u t h c a n be computed. T h i s r e d u c e s the guidance problem t o a p l a n a r p r o b l e m of r e a c h i n g the r e q u i r e d cutoff conditions a s defined i n the guidance plane, T h e guidance c o o r d i n a t e s and guidance e r r o l - s a r e i l l u s t r a t e d i n F i g u r e 2-8. T h e c r o s s r a n g e c o o r d i n a t e , by definition, l i e s p e r p e n d i c u l a r t o the guidance plane defined by the s l a n t altitude and s l a n t r a n g e c o o r d i n a t e s . T h e s t e e r i n g s c h e m e always d r i v e s the c r o s s r a n g e v e l o c i t y and position e r r o r s t o z e r o . T h e s l a n t range c o o r d i n a t e is not used f o r s t e e r i n g but f o r computing a p r e c i s e cutoff t i m e b a s e d on the p r e s e t s i.e., s t o r e d velocity a s i l l u s t r a t e d i n F i g u r e 2-8) f o r a given t a r g e t . T h e s l a n t altitude c o o r d i n a t e i s used f o r pitching o v e r the m i s s i l e s o t h a t i t s velocity and position h i s t o r y and final v a l u e s a r e a s near- a s p o s s i b l e t o the n o m i n a l t r a j e c t o r y preflown i n deriving the p r e s e t s .

P e r s h i n g e m p l o y s air- and jet v a n e s , actuated by hydraulic a c t u a t o r s , f o r c o n t r o l . M i s s i l e attitude e r r o r s a r e s e n s e d by the ST-120; guidance path e r r o r s a r e d e r i v e d in t h e G & C C , T h e s e e r r o r s i g n a l s a r e o p e r a t e d on by compensation f i l t e r s in the G & C C and r e s o l v e d i n t o individual vane c o m m a n d s .

M I S S I L E GUIDANCE ERRORS

DOWN RANGE

TRAJECTORY

SLANT ALTITUDE ERROR

SLANT RANGE ERROR

/

CUTOFF POINT, EPIPSURED VELOCITY = STORED

OFF POINT, MEASURED OCITY > THAN STORED

POINT, MEASURED VELOCITY < THAN STORED

SLANT RANGE COORDINATE

Missile rotations in r o l l and yaw a r e sensed a s e r r o r s relative t o the ST-120 r e f e r ence; i.e., outputs of the r o l l and yaw gimbal angle synchros a r e used d i r e c t l y a s e r r o r signals. The pitch attitude e r r o r is computed by subtracting (by m e a n s of a synchro differential) the pitch gimbal angle synchro output f r o m a cam-generated pitch attitude program. Sign conventions relative t o attitude control a r e defined in F i g u r e s 2-9 and 2-10. In F i g u r e 2-9, the s e n s e of the attitude e r r o r s i s defined for roll, pitch, and yaw motions. In F i g u r e 2-10, fin rotations and resulting m i s s i l e attitude c o r r e c t i o n , corresponding to a given attitude e r r o r , a r e tabulated. The axes of the t h r e e integrating a c c e l e r o m e t e r s mounted on the ST-12 acceleration in c r o s s range, slant altitude and slant range a r e defined in F i g u r e 2-11. Velocity outputs of the a c c e l e r o m e t e r s a r e fed into the C & C C . The slant range velocity input is used to determine second stage cutoff. The c r o s s r a n g e velocity input is used d i r e c t l y a s a guidance path e r r o r since a z e r o value of c r o s s r a n g e velocity i T h e slant altitude velocity ihput is effectively compared to a stored p r o g r a m G&CC) to derive a slant altitude velocity e r r o r signal. Attitude control, is accomplished by processing the pitch, yaw, and r o l l attitude e r r o r s in the G&GC t o generate corresponding vane commands. Guidance is accomplished by processing the slant altitude and c r o s s range a c c e l e r o m e t e r outputs, The resulting

attitude and guidance components of the vane c o m m a n d s a r e s u m m e d t o g e n e r a t e e r r o r s i g n a l s f o r the hydraulic a c t u a t o r s . T h u s , five c o n t r o l loops e x i s t :

-I

P i t c h attitude

2 Yaw attitude 3 Slant altitude -

4 C r o s s range 5 Roll attitude. -

YAM ATTITUDE ERROR

TRAJECTORY

COORDINATE P I T C H ATTITUDE ERROR

, \

PITCH DOUR

PIT

/ TRAJECTORY

ROLL

ATTITUDL ERROR

FIN 1

ALTITUDE COORDINATE

F i n Corrections

2W = CLOCKWISE CCW =

COUNTER-CLOCKNISI

PITCH

SLANT ALTITUDE

I

The f i r s t four of these loops a r e block diagrammed in F i g u r e 2-12, F o r yaw attitude a r e s e t to z e r o . The attiand c r o s s range control, the programmed inputs sampled at 122 s a m p l e s demodulated and analog filtered p r i ps) r a t e . The sampled a t t i t ~ d ee r r o r signal is compensated by a digital f i l t e r . T h i s filter i s depicted a s ( -F.als)D(Z)in the block d i a g r a m to e inherent in the digital f i l t e r , The " proportional-plus-derivative t e r the attitude compensation block r e p r e s e n t s the higher frequency roll-off t e r m s ,

ATTITUDE

The accelerometer outputs are demodulated atid analog filtered prior to being sampled at 30.5 sps. The guidance error signal, -

112 /3

Y

T h e s t e e r i n g function i s a c c o m p l i s h e d the ST-120, G R - C C , vanes and a c t u a t o r s , and n e c e s s a r y n e t w o r k s i n t e r c o n n e c t i n g tiie s u b s y s t e m s .

- C r o s s r a n g e s t e e r i n g i s i i l n s t r a t e d i n F i g u r , ~Z - l 3 ( ~ i ) . Tlhe c r o s s r m g e a c c e l e r o m e t e r . p r o v i d e s velocity info:-mation to tile G & C C . T h i s v e l o c i t y i s s a m pled f r e q u e n t l y by the GR-CC analog-to-digital ( A / D ) c o n v e r t e r to d e t e r m i n e the amount of c r o s s r a n g e v e l o c i t y e r r o r . By i n t e g r a t i n g t h i s inpu; the position e r r o r i s a l s o c a l culated. P r o p e t . g a i n s a r e applied to the velocity and position e r r o r s to f o r m a yaw c o m -

is summed with the yaw attitude compensation output and mand, T h i s command resolved into p r o p e r vane commands before b utputted by the G&CC. The outputting is accomplished through the digital-to-analog converter, with the resulting dc voltage applied to the vane actuators. The vane deflections r e d i r e c t the m i s s i l e ' s flight path to null out these e r r o r s .

- The slant altitude steering is implemented in a s i m i l a r fashion to tsated in Figure 2-13(b). The slant altitude a c c e l e r o m e t e r is SamT h e slant altitude A I D converter to obtain slant altitude velocit r e d to a slant altitude velocity p r o g r a m value ontinuously computed a s a function of t i m e in the C&CC)to obtain the slant altitude v ocity e r r o r . In the s a m e fashion a s c r o s s range, the velocity and position e r r o r s a r e weighted and summed to f o r m a pitch command. (The position input, however, is neither used nor integrated until the second s t a g e of flight,) T h i s pitch command &A) is then summed with the pitch attitude compensation output and resolved into proper vane commands before being outputted by the G&CC, These outputs, through the D / A converter, a r e applied to the vane a c t u a t o r s , The vane deflections r e d i r e c t the m i s s i l e flight path t o null out these errors.

The completion of the P e r s h i n g guidance function o c c u r s when the cutoff command i s issued and the warhead section s e p a r a t e s from the second stage beginning i t s f r e e flight ballistic path to the target. T h e cutoff solution i s calculated exclusively from the slant range a c c e l e r o m e t e r output and the p r e s e t s stored prior- to flight. The following cutoff equation is solved by the C & C C : SRV

P

SRV) T +

= the cutoff p a r a m e t e r

where

SRVp = the slant range velocity p r e s e t negative value) = the slaiit r a g e displacement p r e s e t

T = the weighting factor applied to the velocity e r r o r ant range a c c e l e r o m e t e r provided velocity

SRD

= slant range displacement (integrated from SRVf =

The cutoff p a r a m e t e r ) a t liftoff i s a l a r g e fiegative value and r e a c h e s z e r o well into second stage flight a t which t i m e the cutoff command i s issued. As A n e a r s zero: the d e t e r m i n e s the p r e c i s e instant of cutoff by using a East, iterative countdown routine.

i n e r t i a l r e f e r e n c e system W i g c r e 2 - 151, consisting of a stable platform l i f i e r assembly, provides an e a r t h fixed e o o r d i n a t ~r e f e r and an a s s o c i a t e 'rnuth at the launch s i t e . At ystem defined by the local horizontal this orientation becomes space fixed

Roll Axis of Missile

,

,,

X Axis of ST-i20 Roll Axis

X'S

-1~0

Yaw Axis o i bjvlissiie

Target Direction

X Axis

Yaw Axis

l Y Axis

of Missile

!

s s i l e d i s t u r b a n c e s a r e s e n s e d through tin igidly connected t o the m i s s i l e s a1 a r r a n g e m e n t supporting "re stabilized tions of the missile: T h r e e A B - 5 stabilizing g y r o s aPar t o e a c h o t h e r on t h f i e r s and m o t o r s hold the platforrri s p a c e fixed during flight, FiXED TO MISSILE W L L

H A I N SUAFT

ROLL BEARING STABILIZED CARRIER RIN MISSILE HULL

SLANT ALTITUDE ACCELEROMETE

ROSS RANGE ACCELEROMETER

'

sile is pitched over into the desired attitude for second s b g e motor cutoff,

CONTROL COMPUTER

OUIPU'

0 I

MICRCSYN AT W i L POSITION

OF R C L L

EIET%kT

_ 2 2

"

2

DEGREE f 5 4 FREEDOM 9

90.1

-0 ClRRiER RING W W L C FROM A X W k TtE PLATFORM

~s~'To"[

! iST-120 FIXED) j j

m -

I

; FIXEC)

INDUCED PITCH SiGNAL TO CONTROL CCMPGTER

AE-3 accelerometers mounted on the carrier ring so that each accelerometer is sensitive tion along a specific direction. Acceleration is sensed in the direction illustrated in Figure 2-19. The cross range, slaqt range, and slant altitude acee erometers are of the integrating gyro type. The output of each m i t is a recessional rate proportionalto-input acceleration with the total displacement angle being the integral of the tot-" a1 iicceleration. Synchro transmitters supply this output to the guidance computer,

leveling errors about the X - a x i a d direction of leveling e r test station. The arnplifieG gyro torquer, causing the s EXCITATION VOLTAGE

STABILIZATION LOOP

The azimuth pic off is a high-sensitivity bridge-type microsyn used only in the e pickoff provides information n e c e s s a r y to align the m i s ground alignment s c h e F i g u r e 2 - 2 6 ) . A p o r r o p r i s m is mounted on the c a r r i e r s i l e and platform in azi azimuth heading. It i s oriented s o that a reflected image ring f o r determining pl X r e f e r e n c e axis. The heading (theodolite light s o u r e t e s perpendicularity to t of the platform, with r e s p e c t to t r u e north, i s viewed d e g r e e s f r o m this heading, The pendulums, azimuth pickoff, and p o r r o p r i s m have no function a f t e r launch. ALIGNMENT AMPLIFIER

ST-120

l

IN

i

7

A

NULL POT

1ION

INPUT ROLL ANGLE CCW ROTATION OF STATOR WITH RESPECT TO ARMATURE VIEWED FROM ABOVE THE

AZIMUTH PICKUP AT NULL POSITION

L ANGLE WIRING DRUM

ACTION IN LOOP TAKES PLACE ORDER

@@@@

00 INPUT ROLL ANGLE COUNTERCLOCKWISE ROTATION OF MAIN SHAFT ABOUT PLATFORM "Y" AXIS WITH RESPECT TO CARRIER RlNG VIEWED FROM ABOVE THE PLATFORM

- The s e r v o a m l i f i e r assembly, used in conjunction f o r m , contains s i x a l i f i e r s : t h r e e AMAB-3 electronic control amplifiers, and t h r e e A B - 5 electronic cont two types of amplifiers differ only i n c i r c u i t cornpone s e n s o r provides the a r e used with the t h r e e a c c e k r o m e t e r s . The a c c e l e r of the a c c e l e r o m e t e r input signal to the amplifier with power to the control s e r v o m o t o r provided by tine amplifier output,

.!3

(a) Ass

INDICATOR

A

One A B - 5 amplifier provides power to the control phase winding of the r o l l gimbal s e r v o motor, and the o t h e r provides power t o the yaw gimbal s e r v o motor. The inputs t o these two amplifiers r o i l and yaw) a r e the outputs of the pitch r e s o l v e r . Resolver e s a r e dependent upon the pitch angle of the m i s s i l e and the output of the X recession sensors, The third AB-5 am l i f i e r r e c e i v e s an i n ut f r o m the Z gyro precession s e n s o r , P o w e r to the control phase of the gimbal s e r v o motor i s provided by the am put. P o w e r t r a n s f o r m e r s a r e used to rovide the required excitation voltages f o r the pendulums, g y r o s , a c c e l e r o m e t e r s , s e r v o m o t o r s , and attitude sensing devices. itch c a m p r o g r a m m e r is a modular electromechanical device which produces a variable e l e c t r i c a l reference f r o m which the itch attitude e r r o r many be m e a s u r e d , The c a m profile provides both a long and s h o r t coast the p r o g r a m selection being dependent on direction of rotation of the c a m , Th base f o r the p r o g r a m is supplied by a synchronous m o t o r which d r i v e s the c a m through F i g u r e 2 - 2 8 ) , A r e l a y a s s e m b l y provides the switcha g e a r reduction and clutch d presetting the pitch p r o g r a m , ing function r e

e c a m is turning i n the tch control t r a n s m i t t e r

p r o g r a m m e r i s checked t o d e t e r m i n e whether o r not ograrn, During flight, the ated by the groove in the use the m i s s i l e t o a s s u m e the t r a j e c t o r y attitude,

y s y s t e m provides the clean, d r y a i r required ing controlled flight. The a i r s y s t e m , located in the guidance sad control section, c o n s i s t s of a s p h e r i c a l a i r bottle, fi?t t o r s , and a h e e s e r v e s as a storage a r e a and contains inches of a i r , 0 pslg, The bottle is charged by a i r f r o

station through the umbilical m a before launch, the umbilical cou

hen the m a s t is disconnected, just

ve s e a l the missile air system,

c t s the installation of the a i r d i s t r i &ion system while Figure functional diagram, ClMBlLlCAi

T h e digital guidance and contr.01 c o m p u t e r is a Bendix BDX 8 2 computer- coiltaining p r o c e s s o r designed l o i n t e r f a c e a c e n t r a l p r o c e s s o r and m e m o r y , an input loutput (1'0) with the P e r s h i n g m i s s i l e and ground support equipment, and a power supply, The c o m p a t e r i n t e r f a c e s w i t h the ST-120 stabilized platform, and contains a l l n e c e s s a r y functions to p r o p e r l y condition the a c c e l e r o m e t e r output and attitude r e f e r e n c e s i g n a l s r e q u i r e d f o r controlling the m i s s i l e f i r s t and second s t a g e c o n t r o l s i i r f a c e s , I n t e r f a c e s a l s o e x i s t between t!le c o m p u t e r 2nd tile m i s s i l e m2in distributor-, telemetr-:)t r a n s m i t t e r , and prelaunch ground support equipment. In addition, s p e c i a l i n t e r f a c e p r o v i s i o n s a r e m a d e t o facilitate testing and m e m o r y loading at the SC'I'S. A s y s t e m organization d i a g r a m is shown in F i g u r e 2 - 3 1 ,

GUIDANCE - - -AND - -CONTROL - - -COMPUTE? --

C o m p u t e r power is obtained f r o m the m i s s i l e e l e c t r i c a l bus s y s t e m m d converted to voltages r e q u i r e d by the c e n t r a i p r o c e s s o r , m e m o r y , and 1 / 0 p r o c e s s o r . T h e guidance and c o n t r o l c o m p u t e r a l s o g e n e r a t e s t i m e sequence s i g n a l s t o the m i s s i l e f o r staging and a cutoff s i g n a l t o t e r m i n a t e second s t a g e m o t o r t h r u s t and c a u s e warhead s e p a r a t i o n when guidance p a r a m e t e r s a r e s a t i s f i e d . W h e r e possible, design c o n s i d e r a t i o n s f o r the digital c o m p u t e r use existing m i s s i l e e l e c t r i c a l and m e c h a n i c a l i n t e r f a c e r e q u i r e m e n t s , T h e guidance and c o n t r o l s o f t w a r e and h a r d v ~ a r euse s t a t e of tihe art techniques t o produce acceptable r e l i a b i l i t y a g a i n s t guidance s u b s y s t e m f a i l u r e .

F i g u r e 2-32 is a signal flow d i a g r a m of the guidance and control functions performed by the computer. The functions a r e specified by the r e q u i r e m e n t s f o r a delta-minimum guidance profile. The a j r b o r n e functions m a y be divided into s i x groups: guidance, stability, control, good guidance, time d i s c r e t e generation, and telemetry. The computer accepts bus 2 8 Vdc and 115V, 400 Hz power, and converts the power to usable voltages for the c e n t r a l p r o c e s s o r , 110, m e m o r y , and s e n s o r excitations. The detailed design of the functions is discussed below. Hardware and software a r e defined such that optimum a c c u r a c i e s and timing efficiency a r e achieved. Reliability of the guidance and control function is optimized by software techniques, such a s redundant calculation and self-test f e a t u r e s . Scaling to optimize word a c c u r a c i e s and an extended length algorithm a r e used t o i n c r e a s e a c c u r a c y in the cutoff solution. AIDand D / A conversions a r e multiplexed to and f r o m a common ladder network, and 1/O analog signal processing is designed t o optimize use of the full digital 110 word.

nee E'unetion - The guidance function accepts the m i s s i l e velocity signals in the f o r m of a c c e l e r o m e t e r synchro voltages and outputs yaw and pitch s t e e r i n g signals t o the control function and a cutoff signal t o the good guidance function. The input sign a l s f r o m the a c c e l e r o m e t e r s a r e t h r e e groups of amplitude modulated signals between the s t a t o r t e r m i n a l s of s y n c h r o t r a n s m i t t e r s and r e p r e s e n t instantaneous m i s s i l e veloc i t y along each of the t h r e e mutually perpendicular axes. The guidance function converts the sampled input signals to d c signals proportional to the s i n e and cosine of c r o s s r a n g e velocity, slant range velocity, and slant altitude velocity. T h e s e dc signals a r e used a s excitations f o r the A / D converter. The A / D converter in turn u s e s a s u c c e s s i v e approximation technique f o r determining digital w o r d s proportional t o the s i n e and cosine of the scaled velocity signals. The c r o s s r a n g e guidance function i n t e g r a t e s the c r o s s r a n g e velocity to obtain a c r o s s r a n g e displacement signal, and s c a l e s and s u m s the velocity and displacement signals t o f o r m a c r o s s r a n g e s t e e r i n g command f o r the control function. The slant altitude guidance function s u b t r a c t s f r o m the slant altitude velocity s i g n a l a d e s i r e d velocity profile f r o m the slant altitude p r o g r a m to f o r m a slant altitude velocity e r r o r signal. The slant altitude velocity e r r o r s i g n a l is integrated, a s in the c r o s s r a n g e guidance function, t o f o r m a s l a n t altitude displacement e r r o r signal, which in t u r n is scaled and summed with the velocity e r r o r to f o r m a slant altitude s t e e r i n g signal f o r the cont r o l function. The slant range c o m p a r a t o r guidance function s u b t r a c t s f r o m the slant range veloc i t y a ground p r e s e t velocity value. The velocity difference s i g n a l is integrated to f o r m p rt e s e t value. The r e a displacement signal which is in turn reduced by a d i s p l a ~ e ~ m e n sultant displacement difference and velocity difference signals a r e used to solve the cutoff equation, A. A cutoff d i s c r e t e s i g n a l is i s s u e d by the slant range eorn a r a t o r guidance function when 1 changes sign a f t e r second stage ignition. T h i s cutoff s i g n a l in conjunction with the good guidance determination i s used to t e r m i n a t e second s t a g e t h r u s t and initiate

e function are irn tant errors are small for the cross-

t altitude, due to closed nt integration, being

idance generator is designated as a f a i l ate does riot allow a ted m l y when the ocity error less tin

-

2 S l a n t altitude velocity error less t h a n limit; -

-3

Slant range velocity difference within tolerance;

4 -

Slant r m g e dispiaeerneat dif erence within tolerance;

ut bas not exceeded 1

5 ST-

-7 -

onitor signal present;

Pressure monitor signal present; uter has notffai an a predetermined value, iscrete generator function issups rr,rnanri vane unlock, an3 first sta at prescribed times signal is issced to the controi function system currect and eedback s.s;-itching, i t y function accepts m i s iie attitude signals from

ressed carrier arxplilu.de modulaied icrosyri outpxs c is the o u t p u t of a CX-CT pair, and is the difference betweec actual missile attitu red pitch program angle, M a x i m u m input voltage for :he yaw voltage for the pitch ckannel is I T 5 V r m s isat is saturaeve1 for I ~ O d e s i g n eorisidera"cioils, Sahration of the pitch input signal does not degrade performance, s computer gains of this magnitude s i g n a l saturate the vane output signals an6 no over o w detection is required ir, software, and TOEiriptits are

T h e input s i g n a l s , designated @yaw, $roll, and @pitch9a r e demodulated and f i l t e r e d . T h e r e s u l t i n g d c voltages a r e converted t o digital w o r d s i n the common A / D c o n v e r t e r . T h e digital @ s i g n a l s a r e then p r o c e s s e d t o provide r o p o r t i o n a l and difain compensation of t h e input, with additional filtering of the d i f f e r e n t i a l ath t o f o r m a f o r w a r d t r a n s f e r function meeting defined m i s s i l e s t a b i l i t y r e T h e f i l t e r s a r e s e l e c t e d in r e l a t i o n t o the timing s i g n a l s g e n e r a t e d by the t i m e d i s c r e t e g e n e r a t o r function t o provide compensation f o r changing m i s s i l e d y n a m i c s ant consumption, a e r o d y n a m i c s , and staging. F i l t e r c h a r a c t e r i s t i c s a l s o d i f f e r f o r long and s h o r t range t r a j e c t o r i e s . T h e digital f i l t e r is e s s e n t i a l l y a difference equation of f o u r t h o r d e r m a x i m u m f o r yaw and pitch, and second o r d e r f o r r o l l ,

- T h e c o n t r o l function a c c e p t s the s i g n a l s f r o m the guidance and stabil r o c e s s e s t h e m t o f o r m command s i g n a l s f o r the vane c o n t r o l hyd r a u l i c a c t u a t o r packages, T h e p r o c e s s e d Byaw s i g n a l is s u m m e d with the c r o s s r a n g e s t e e r i n g s i g n a l t o g e n e r a t e the Qyaw s t e e r i n g signal. T h e p r o c e s s e d signa s u m m e d with the s l a n t altitude s t e e r i n g s i g n a l t o g e n e r a t e the $pitch s t e e r i n g signal. T h e $roll s t e e r i n g s i g n a l alone c o m p r i s e s the @ r o l ls t e e r i n g signal. T h e output d a t a in body s p a c e is then t r a n s f o r m e d into t h r e e vane position command s i g n a l s , designated 01, U2, and 03, according t o the following m a t r i x definition:

P o s i t i v e Gyaw is defined a s the s t e e r i n g command about the body yaw a x i s which is d i r e c t e d downrange a t launch. P o s i t i v e roll is the s t e e r i n g command about the body r o l l a x i s which is d i r e c t e d away f r o m the e a r t h a t launch. P o s i t i v e @pitchi s the s t e e r ing command completing a right-handed orthogonal yaw-roll-pitch coordinate s y s t e m . T h e vane command v e c t o r s lie in a plane n o r m a l t o the m i s s i l e r o l l a x i s , with the positive d i r e c t i o n defined outward f r o m the m i s s i l e body. T h e 01 command v e c t o r p a s s e s through the vane 1 a x i s of rotation and l i e s p a r a l l e l to the m i s s i l e downrange yaw a x i s . T h e a 2 and U3 command a x e s p a s s through v a n e s 2 and 3, r e s p e c t i v e l y , and a r e o r i e n t e d a t a n g l e s of 120 d e g r e e s and 240 d e g r e e s r e s p e c t i v e l y , counterclockwise f r o m the U l v e c t o r when viewed looking down the m i s s i l e body f r o m the m i s s i l e nose. E a c h of the t h r e e vane d r i v e r s provide a c o n t r o l c u r r e n t t o one hydropack valve which is p r o p o r t i o n a l t o the a l g e b r a i c d i f f e r e n c e between commanded v a n e angle (Ql, o2, o r a 3 ) and the a c t u a l vane position ( P I , P2, o r p3). T h e command angles (CT) a r e converted,,to s c a l e d analog s i g n a l s i n the multiplexed D / A c o n v e r t e r and c o m p a r e d d i r e c t l y t o the d c vane position feedback signal ( p ) f r o m the hydropack. T h e s t a g e switching function a c c e p t s the vane driving c u r r e n t s i g n a l f r o m the vane d r i v e r and a l s o r e c e i v e s the vane position and vane d r i v e c u r r e n t feedback signals f r o m both f i r s t and second s t a g e hydropacks. During f i r s t s t a g e flight, the switching function d i r e c t s the vane driving c u r r e n t s i g n a l t o the f i r s t s t a g e hydropacks and connects the vane position and vane d r i v e c u r r e n t feedback s i g n a l s f r o m the f i r s t s t a g e hydropacks t o the vane d r i v e r . In addition, during f i r s t s t a g e flight, the switching function i n v e r t s the second s t a g e vane position feedback s i g n a l and connects i t d i r e c t l y t o the input of the second s t a g e hydropack t o hold the second s t a g e v a n e s a t z e r o deflection. Upon r e ceipt of t h e f i r s t s t a g e s e p a r a t i o n / s e c o n d s t a g e ignition command, the switching function r e d i r e c t s the vane driving c u r r e n t s i g n a to the second s t a g e hydropacks and con-

ition and vane vane drive, di

ve c u r r e n t feed nnecting and de

stage connections.

-

A dc to dc converter in the I / O unit converts the +2 the I / O and c e n t r rocessor. Inverter 4 demodulation i a s supplies fo ower supplied

u t e r I/O unit contains s e r i a l i z e r and a r i t y g e n e r a t o r for digital word t r a n s f e r t o the t e l e m e t r y s y s t e m , T e l e m e t r y out ut is under software control in the c e n t r a l p r o c e s s o r , Required analog signals and voltages i n the I / O and signal d i s c r e t e s a r e a l s o available at the t e l e m e t r y connector,

requirement, T h e computer organization is shown in F i g u r e 2-33. DRO CORE 8 M N I T O R SIGNAL FLOW hYD

iNTE RFACE NOT SHOWN.

CRY

SAV

SRV

/Oa d d r e s s and control.

/ A - A / D c o n v e r t e r unit a l s o aece t s digital d a t a f r o 0 a d d r e s s and control unit, and i n a r y number r e sented by the input, T h e the analog dernult e x e r unit which, under direction of the c o n v e r t e r unit to a r e used f o r self t e s t purposes, Each s

proportional t The i n p u t d i s c r e t e logic unit acce t s 28 Vdc inpat. d i s c r e t e signals and t r a n s c signals, When a d them to the 5 Tide level of all guidance a n d control co control logic unit, the d r e s s e d by the CPU, and under direction of the i / O a essing a n d / o r s t o r a g e . input d i s c r e t e logic unit t r a n s f e r s the data into the CP7; for logic unit, under direction of the eerning ouxput ciiscretes From the

d r e s s and control logic unit, V d e si n a l s and t r a n s f o r m s

PT; as a 5

PNEUMATIC BALL LOCKPIN

PRESSURE REGULATING VALVE 3000 PSIG TO MISSILE

!

SWITCH ACTUATOR (AZIMUTH RING CLAMP SEGMENT)

MAST CLEAR SWITCH -7--

1

1 I

CHECK VALVE

--.. SWITCH

3000 PSIG POWER STATION

PISTON HYDRAULIC FLUID

FLUID PRESSURE DAMPENER

ACCUMULATOR ASSEMBLY

1 - REMOTE FIRING BOX 2 - AZIMUTH LAYING CONTROL BOX 3 - AIR DUCT REGISTER 4 - PHONE CONTROL PANEL ASSEMBLY 5 - ADAPTER 6 - STORAGE CABINET 7 - CARD AND MODULE TEST SET 8 - POWER DISTRIBUTION ASSEMBLY 9 - POWER DISTRIBUTION ASSEMBLY CIRCUIT BREAKER PANEL 10 - SIGNAL DISTRIBUTION BOX 1 7 - COMPUTER BOX FRONT ACCESS PANEL 12 - COMPUTER BOX TOP ACCESS PANEL

14 15 16 17

? - LAUNCH CONTROL PANEL ASSEMBLY 2 - MAINTENANCE PANEL ASSEMBLY 3 - STORAGE CABINET 6 - UTILITY PANEL ASSEMBLY 5 - UTILITY CIRCUIT BREAKER PANEL ASSEMBLY 5 - AIR DUCT REGISTER 7 - TELEPRINTER 8 - TAPE STORAGE CABINET 3 - AIR CONDITIONER 1 0 - AIR SUPPLY REGISTER 11 - AIR CONDITIONER FILTER 12 - AIR CONDITIONER CONTROL PANEL IS - REWOTE FIRING BOX CABLE REEL ASSEMBLY (TRAVEL POSITIONj 14 - STORAGE CABINET 15 - CONVENIENCE OUTLET (4) 16 - AUXILIARY HEATER 17 - WORKBENCH 18 - SIGNAL OiSTRlBUTION BOX 19 - BLOWER 20 CONSOLE VOLTAGE-PHONE MONITOP PANEL ASSEYBiv COUNTDOWN COVTROL PANEL ASSEMBLY AZIMUTH LAYING CONTROL PANEL ASSEWBLY TAPE READER HAND LANTERh

-

-

AIR FILTER FIRST AID KIT BLOWER STORAGE CABINET

The b a s i c controlling and sequencing element in the PTS i s a compact g e n e r a l - p u r pose computer, The computer i s a stored program, parallel, binary, fixed point m a chine, whose m a j o r components a r e a c e n t r a l data p r o c e s s o r , an input/output assembly, f o u r c o r e m e m o r y units, a power supply assembly and an e l e c t r i c a l equipment rack a s s e m b l y ( F i g u r e 4-4). The basic word length i s 23 data bits plus sign and parity ( 2 5 bits total). T h e m e m o r y i s magnetic c o r e , random a c c e s s , with a 4 microsecond cycle time. The computer i s normally supplied with 16, 384 words of m e m o r y capacity, but can be expanded without redesign. The computer employs 47 basic instructions, but by using m i c r o p r o g r a m m i n g techniques, up to 300 instruction variations a r e available to the prog r a m m e r . The m e m o r y i s protected s o that accidental interruption of input power to the computer will not cause the contents of the m e m o r y to be altered. The input and output c i r c u i t s of the computer a r e compatible with devices using field data codes. F i g u r e 4-5 p r e s e n t s a simplified block diagram of the computer. CENTRAL DATA PROCESSOR

CORE MEMORY U N I T 5

ELECTRICAL EOUIPMENT

STUD ASSEMBLY LOCKING -/OUTPUT ASSEMBLY POWER SUPPLY ASSEMBLY

CORE MEMORY U N I T 0 CORE MEMORY U N I T 1

CORE MEMORY U N I T 2

The input/output a s s e m b l y i s the unit through which all signals to the computer a r e routed, The input c i r c u i t s decode input information to the c e n t r a l data p r o c e s s o r and the c o r e m e m o r y units. The output c i r c u i t s decode output information, which is routed to the adapter for controlling m i s s i l e functions and to the console where it i s displayed visually a n d / o r printed out on the t e l e p r i n t e r . The c e n t r a l data p r o c e s s o r i s the h e a r t of the computer. It c o n s i s t s of t h r e e i n t e r related s u b s y s t e m s : arithmetic and logical operations, p r o g r a m execution and control, and input/output control. All a r i t h m e t i c operations (addition, subtraction, multiplication, and division) and manipulation of data to accomplish a d e s i r e d r e s u l t a r e performed in the arithmetic and logical operations s u b s y s t e m , All n e c e s s a r y timing signals and subcommands required in the instruction execution a r e generated in the p r o g r a m execution and control subsystem. T h e input/output control subsystem controls the t r a n s f e r of data between the c o r e m e m o r y units and the input/output assembly,

T h e c o r e m e m o r y units s t o r e a l l r e q u i r e d data. E a c h unit i s capable of s t o r i n g 4 , 0 9 6 w o r d s of 2 5 b i t s e a c h . T h e countdown c o n t r o l panel a s s e m b l y is used for manually e n t e r i n g d a t a into the c o m p u t e r d u r i n g p r o g r a m execution. A v i s u a l d i s p l a y i n d i c a t o r on t h i s panel indicates which phase of the p r o g r a m i s in p r o g r e s s , the r e a s o n f o r hold conditions when a hoid condition e x i s t s , and the c a u s e of a malfunction when a malfunction o c c u r s , T h e t a p e r e a d e r is used f o r e n t e r i n g v a r i o u s taped p r o g r a m d a t a into the c o m p u t e r , T h e t e l e p r i n t e r p r o v i d e s a h i s t o r i c a l r e c o r d of a l l d a t a and a l l information displayed on the countdown c o n t r o l panel a s s e m b l y information readout i n d i c a t o r during a f i r e sequence. T h e m a i n t e n a n c e panel a s s e m b l y i s used in conjunction with prepunched diagnostic t a p e when fault i s o l a t i o n p r o c e d u r e s a r e being p e r f o r m e d on the c o m p u t e r . It contains t h r e e a l p h a n u m e r i c d i s p l a y t u b e s , A n u m b e r i s displayed f o r e a c h s t e p of the t e s t . C o m p a r i s o n of the n u m b e r displayed wi t t ~s i m i l a r n u m b e r s in the r e p a i r d a t a t a b l e s r e s u l t s in i s o l a t i o n of the malfunction.

MOliIlOP N4 D COL!TR3L

s1s:iALs

FROM ADAPTE P

C3'111A:i D

-

i:iPUT/OUi?UT

ASSEMBLY

i-

S!G':fiLS TO ADAPTER

T h e a d a p t e r s e r v e s a s the e l e c t r i c a l i n t e r f a c e between the c o m p u t e r and the r e s t of the m i s s i l e s y s t e m . All e l e c t r o n i c c i r c u i t s of the PTS which a r e not p a r t of the cornp v t e r , the utility c i r c u i t s , o r the console equipment a r e included in the a d a p t e r

O p e r a t i n g u n d e r t h e control of t h e comcircuits perform most olling and monitoring function of t h e PTS, T h e r e a r e 215 cont r o l l i n e s which c a n be switched on and off by t h e c o m p u t e r through a d a p t e r c i r s ; t h i s n u m b e r c a n be i n c r e a s e d t o without b a s i c d e s i g n changes if r e q u i r e d by f u t u r e developments. An addit i o n a l 215 l i n e s a r e monitored f o r t h e p r e s e n c e o r a b s e n c e of s i g n a l s ; t h i s ncmb e r c a n b e i n c r e a s e d t o 396 without b a s i c d e s i g n changes if r e q u i r e d in t h e future. T h e a d a p t e r a c c e p t s digital information, in t h e f o r m of a n 18-bit p a r a l l e l word, f r o m t h e c o m p u t e r and c o n v e r t s t h i s information into analog information f o r p r e s e t t i n g the guidance s y s t e m and sequencing t h e countdown of the m i s s i l e f o r flight. C i r c u i t s within t h e a d a p t e r a l s o convert analog inf o r m a t i o n f r o m t h e c a r d and module t e s t s e t (CMTS) and t h e ground support equipment t o digital information f o r the comput e r ( F i g u r e 4-7).

POWER

POWER

POWER

ASSEMBLY A1

STRAIGHTENER

RACK A7

Operating under c o m p u t e r control, the operations c o n t r o l function r e c e i v e s r e s e t , row s e l e c t , and d a t a s e t s i g n a l s f r o m the c o m p u t e r . T h e s e s i g n a l s c a u s e command signaIs t o be g e n e r a t e d that a r e used throughout the a d a p t e r , CX'ITS, azimuth laying c o n t r o l box, and console. T h e command s i g n a l s c o n t r o l a s p e c i f i c function in the m i s s i l e o r the a d a p t e r . Monitor s i g n a l s a r e s e n t to the o p e r a t i o n s c o n t r o l function f r o m throughout the a d a p t e r , azimuth laying c o n t r o l box, and CMTS. T h e m o n i t o r s i g n a l s indicate that a function n e c e s s a r y t o complete an operation h a s been accomplished s u c cessfully, The s i g n a l s a r e converted t o an acceptable voltage l e v e l and routed to the computer.

T h i s function produces c o n t r o l s i g n a l s that a r e applied t o the m i s s i l e , ground s u p port equipment, and CMTS and I e c e i v e s m o n i t o r s i g n a l s f r o m the s a m e equipment. T h e control s i g n a l s a r e initiated by the command s i g n a l s f r o m the o p e r a t i o n s c o n t r o l function. T h e command and monitoring function r o u t e s countdown s t a t u s indications to the r e m o t e firing box and r e c e i v e s f i r i n g c o n t r o l s i g n a l s f r o m the r e m o t e firing box. Manua l l y g e n e r a t e d command s i g n a l s s u c h a s " m i s s i l e power on" and "counting" a r e r e c e i v e d by t h i s function f r o m the countdown c o n t r o l panel a s s e m b l y . Status i n d i c a t o r s i g n a l s such a s "holding, counting, and m i s s i l e power on" a r e fed f r o m the command and m o n i toring function t o the countdown c o n t r o l panel a s s e m b l y .

-

CONSOLE

STATUS I N D I CATOR SIGNALS

NSO

AL AND ALS

-

-

I

I

ADAPTER i

GUIDANCE SECTION

1

MONITORING SIGNALS FROM MISSILE,

PLATFORM P O S I T I O N I N F SIGNALS TO M I S S I L E AN0 M I S S I L E SECTIONS I N CONTAINERS

s

EQUI lVID M I S S I L E SECTIONS I N CONTAINER5

AC/DC S T I M U L I TO MISSILE, GROW0 SUPPORT E Q U I P K N T , CARD AND MODULE TEST SET, AN0 M I S S I L E SECTIONS I N CONTAINERS

S l GNALS FROM EMOTE F I R I N G BOX

AC/DC M I S S I L E AND CARD AN0 MODULE TEST SET DC SIGNALS FROM PGWER STATION PRESETTING KSPONSE FROM GUIDANCE AND WARHEAD SECTIONS

POSITIOfJING SIGNALS TO GUIDANCE AND UARNEAD SECTIONS CONTROL SIGNALS TO M I S S I L E GROWD SUPPORT EQUIPMENT, CARD AND WDULE TEST SET, AN0 M I S S I L E SECTIONS I N CONTAINERS EIERGENCY INTERRUPT SIGNAL TO COMPUTER

MONITOR SIGNALS FROM CARD AND MODULE TEST SET

COUNTDOWN STATUS I N 0 1 CPTORS TO REMOTE F I R I N G BOX

TO CARD AND

COLUMN SELECT

I

j

36 M N I T O R I ! I G OUTPUTS TO COMPUTER

NOTE :

T h i s function, operating in conjunction with either the azimuth lay5ng control box o r the azimuth laying control panel assembly, is used to align the ST-12 the function i s controlled by command signals f r o m the operations con stimuli a r e applied a s reference signals to the function during testing of malfunctions. A measurement signals a r e sent to the m e a s u r e m e n t s function during n o r m a l operation t o indicate that the platform alignment function i s operating correcxly. During testing, the ac measurement signals indicate the location of malfunctions.

T h i s function provides variable level ac and dc signal voltages for use in the platfor-m alignment, command and monitoring, m e a s u r e m e n t s , and presetting functions, The level of the ac o r dc stimuli i s controlled by the computer. n addition, the a c j d c stimuli is a l s o fed t o the m i s s i l e , ground support equipment, CMTS, and m i s s i l e sections in containers.

T h i s function, under computer control, p e r f o r m s a c / d c voltage m e a s u r e m e n t s , a c frequency m e a s u r e m e n t s , and a c phase comparison checks on signals received from the m i s s i l e , GMTS, power station, command and monitoring function, and a c / d c stimuli function.

T h i s function f o r m s a loop with c i r c u i t s in the warhead and guidance sections of the m i s s i l e . The signals applied to the loops a r e used to p r e s e t the guidance and warhead sections f o r a particular firing. P r e s e t information is routed to the measuremefits function to determine the level of the next presetting signal to be sent to the guidance o r warhead sections.

F i v e types of modules a r e used in the adapter: command modules, monitor modules, m a t r i x d r i v e r modules, capacitor modules, and load modules. A decal on the top of each module identifies the type. The command, monitor, and capacitor modules and t h e i r respective receptacles a r e keyed to prevent a module f r o m being i n s e r t e d into an i n c o r r e c t receptacle. F i g u r e s 4-8 and 4-9 show t h e type, quantity, and proper location of t h e modules used in the adapter.

T h e adapter f i l t e r assembly c o n s i s t s of t h r e e low-pass ac f i l t e r s for the 4 power input to the adapter. The f i l t e r s a r e mounted on a c h a s s i s on the right-hand panel inside the cabinet.

COMMAND MODULE (55)

\

MODULE (21) \

CAPACITOR MODULE (8)

COMMAND MODULE (541

I

1

I"] ~lo["l

MATRIX DRIVER MODUiE (20)

CAPACITOR MODULE (8)

/

OR0

0

CilD

0

GRC

MONITOR MODULE (271

LOAD MODULE (5,

MONITOR MODULE (27)

LOAD MODULE (6)

ale Locations

1

T h e m a j o r p o r t i o n of t h e adapter c i r c u i t s c o n s i s t s of 70 printed c i r c u i t c a r d s ( 1 8 d i f f e r e n t t y p e s ) mounted o n a swingout e q u i p m e n t r a c k ( F i g u r e 4- 10). T h e p r i n t e d c i r c u i t c a r d s a r e of an epoxy f i b e r g l a s s base m a t e r i a l l a m i n a t e d w i t h copper and e t c h e d o n both sides. T h e c o n n e c t o r s f o r e a c h t y p e of c a r d a r e individually k e y e d t o p r e v e n t a c a r d f r o m being i n s e r t e d i n t o an i n c o r r e c t location.

,

PRINTED CIRCUIT CARDS A6 THRU A9, A l 2 , A l 3 ,

TRANSFORMER T i PRINTED CIRCUIT CARDS A25 THRU A27, A29 THRU A34, A36 THRU A44 PRINTED CIRCUIT CARDS A49 THRU A51, A53 THRU A58, A60 THRU A68, A71, PRINTED CIRCUIT CARDS A73, A75, A77, A79, A81, A83, A85, A89, A91, A93, PRINTED CIRCUIT CARDS A I O I , AlO3, A l 0 5 , A l 0 7 , PRINTED CIRCUIT CARDS A l l l , A I 1 3 , A l l S , Ai17,

JUNCTION BOX TRANSFORMER T2 TRANSFORMER T3

P R I N T E ~CIRCUIT CARDS A97 A98

\TRANSFORMER

T4

The d c voltage m e a s u r e m e n t capability.of the adapter c i r c u i t s over the whole environmental range is a s follows: Voltage Range

Accuracy

1.0 t o 128.0 volts

50.5% of the reading

0.010 volt t o 1.0 volt

+0.010 volt

T h e a c voltage m e a s u r e m e n t capability of the adapter c i r c u i t s i s a s follows: Voltage Range

Accuracy

4 volts to 128 volts r m s

1% of the reading

0.5 volt t o 4.0 volts r m s

2 70of the reading

0.010 volt t o 0.5 volt

10 millivolts

In the basic m e a s u r e m e n t mode, the root mean square ( r m s ) value of the fundamental 400 Hz sinusoidal component of the unknown i s m e a s u r e d ; all other frequency components a r e attenuated. Accuracy r e q u i r e m e n t s stated above apply t o signals with a fundamental frequency between 380 and 420 Hz with not m o r e than 5 percent total harmonic distortion.

The stimulus voltage generating capability of the adapter- i s a s follows:

I F o r dc voltages, 0 to 1 6 volts in 2 millivolt s t e p s , e i t h e r polarity 2 F o r ac voltages, 0 to 35 volts in 2 millivolt s t e p s , in phase with any of the t h r e e phases of the 400 Hz supply voltage.

T h e final stimulus voltage amplitude i s s e t with the voltage m e a s u r e m e n t c i r c u i t s monitoring it, s o that the accuracy of the stimulus voltages is essentially the s a m e a s the m e a s u r e m e n t c i r c u i t s , plus an additional e r r o r of rt2 milliwatts due t o the r e s o l u tion of the stimulus g e n e r a t o r s .

T h e i n v e r t e r frequency can be monitored by the PTS with a m e a s u r e m e n t e r r o r of l e s s than 50.01 Hz.

The adapter c i r c u i t s p r e s e t the synchros of the guidance computer well within the required accuracy of 0-3 m e t e r p e r second f o r the slant range velocity channel and 30 m e t e r s for the slant range displacement channel under w o r s t c a s e conditions. The w a r head synchros a r e p r e s e t with an accuracy of 9 d e g r e e s of the warhead fine synchro under worst c a s e conditions.

i n F i g u r e 4 - 11 'is considered a functional p a r t of the T h e r e m o t e f i r e box t is connected t o the P T S by a 500 foot cable and provides the n e c e s s a r y cont r o l s and i n d i c a t o r s t o initiate the firing sequence and i n d i c a t e s that the firing sequence is in p r o g r e s s .

Key -

2

Control o r Indicator

Function

F I R E swi t c n e s

*ihen both switches a r e pressed s i m u l t a n e o u s l y , i n i t i a t e s f i r i n g phase.

READY i n d i c a t o r

Indicates that missile i s ready t o f i r e .

3

>Jhen l i t , i n d i c a t e s t h a t f i r i n g phase i s progressing normal l y .

4

Provides emergency s t o p p i n 9 of f i r e sequence u u to f i r s t stage ignition.

3

VOLUNE control

Provides adjustment for volume of headset connected t o 33.

6

BATTERY ACT1 !JATE; indicator

jndicates that missile b a t t e r i e s have been a c l i va t e d .

7

'VOLUME control

Provides adjustment f o r volume of h e a d s e t connected t o 3 2 .

8

R I N G switch

vihen p r e s s e d , l i g h t f l a s h e s on BCC intercom s e l e c t panel.

T h e r e m o t e f i r e box h a s e x t e r n a l r e c e p t a c l e s f o r two h e a d s e t / m i c r o p h o n e c a b l e s . T h e s e r e c e p t a c l e s a r e enabled at the "warhead p r e s e t and verification" point in the countdown sequence and provide a c c e s s t o both " a l l phones" and " d i s c r e t e t t c i r c u i t s up t o the r e m o t e t r a n s f e r point, and " d i s c r e t e t ' only f r o m r e m o t e t r a n s f e r t o the end of the countdown. T h e R F B h a s 2 ring button which e n a b l e s i t to r i n g e i t h e r the P T S o r ECC depending on the communication network hookup. It a l s o h a s individual volume c o n t r o l s f o r e a c h of the r e c e p t a c l e s .

T h e console provides the c o n t r o l s and i n d i c a t o r s by which the o p e r a t o r c o n t r o l s and m o n i t o r s the operation of the PTS ( F i g u r e 4-3). F r o m the console, the o p e r a t o r cont r o l s the application of power t o the a d a p t e r and the c o m p u t e r , e n t e r s data, and o b s e r v e s i n d i c a t o r s that display the s t a t u s and condition of the f i r e sequence. The console contains the azimuth laying c o n t r o l panel a s s e m b l y , voltage-phone m o n i t o r panel a s s e m b l y , m a i n l a s s e m b l y , utility panel tenance p a n e l a s s e m b l y , tape r e a d e r , countdown c o n t r ~ panel a s s e m b l y , t e l e p r i n t e r , and launch c o n t r o l panel a s s e m b l y .

T h e azimuth laying c o n t r o l panel a s s e m b l y ( F i g u r e 4-3) contains c o n t r o l s and indicat o r s f o r p e r f o r m i n g azimuth layigg p r o c e d u r e s f r o m i n s i d e the P T S if the azimuth laying c o n t r o l box o r i t s c a b l e i s defective. An indicator on the panel i n f o r m s the o p e r a t o r when the azimuth laying p r o c e d u r e s a r e to be performed f r o m inside the PTS.

T h e upper portion of the voltage-phone monitor panel a s s e m b l y ( F i g u r e 4-3) contains a m e t e r f o r monitoring a l l i n t e r n a l PTS power supply voltages and a n indicator f o r monit o r i n g t h e p r i m a r y a c and d c power. The lower portion of the panel contains a headset connection point f o r establishing intercommunications with a l l s t a t i o n s o r d i s c r e t e s t a tion-to- s t a t i o n contact between t h e PTS,BCC, and r e m o t e f i r i n g box only.

T h e maintenance panel a s s e m b l y ( F i g u r e 4-3) contains c o n t r o l s and i n d i c a t o r s f o r troubleshooting the computer. A t h r e e - c h a r a c t e r readout i n d i c a t o r d i s p l a y s d a t a f r o m a punched tape o r f r o m the c o m p u t e r p r o g r a m . I n d i c a t o r s i n f o r m the o p e r a t o r when the c o m p u t e r power supply is malfunctioning, when the c e n t r a l d a t a p r o c e s s o r (CDP) is o p e r a t i n g under p r o g r a m control, when a c o m p u t e r timing e r r o r e x i s t s , o r when an i n put p a r i t y e r r o r f r o m the tape o r k e y b o a r d s e x i s t s .

T h e tape r e a d e r ( F i g u r e 4-3) contains c o n t r o l s and i n d i c a t o r s f o r e n t e r i n g the tape p r o g r a m s into the computer. Operation of the tape r e a d e r can be controlled automatic a l l y by s i g n a l s g e n e r a t e d through use of the tape r e a d e r controls. T h e tape r e a d e r u s e s t h r e e types of c i r c u i t network modules (CNM) of the s a m e b a s i c design a s those in the c o m p u t e r , and they a r e identified in a like m a n n e r . Eight CNM1s a r e used i n the tape r e a d e r .

T h e countdown control panel a s s e m b l y ( F i g u r e 4-3) contains c o n t r o l s and i n d i c a t o r s f o r m a n u a l e n t e r i n g d a t a into the c o m p u t e r , and sequencing the firing sequence. Cont r o l s a r e a l s o included f o r applying power t o the a d a p t e r , c o m p u t e r , and m i s s i l e , and f o r t r a n s f e r r i n g c o n t r o l of the firing sequence t o the r e m o t e firing box. T h e a s s e m b l y u s e s s e v e n types of CNM's of the s a m e b a s i c design a s those in the c o m p u t e r , and they a r e identified in a like m a n n e r . F i f t y s i x C N M ' s a r e used i n the countdown c o n t r o l panel a s s e m b l y .

T h e utility panel a s s e m b l y ( F i g u r e 4-31 contains c o n t r o l s f o r regulating the b r i g h t n e s s of the P T S s h e l t e r lights and the console panel lights. T h e panel contains an 8-day clock, t h r e e elapsed t i m e m e t e r s , a s i g n a l h o r n switch, s w i t c h e s f o r turning the s h e l t e r lights on and off, and i n d i c a t o r s that signify a r e q u i r e m e n t f o r s h e l t e r heating, a l o s s of airflow through the equipment, and c o m p u t e r overheating. T h e a s s e m b l y a l s o contains a f i r e warning h o r n that sounds in the event of a f i r e in the power station.

T h e t e l e p r i n t e r F i g u r e 4-3) supplies a permanent r e c o r d of the calculated firing d a t a , It c o n s i s t s o a p r i n t e r unit and a p a p e r takeup unit. T h e p r i n t e r unit contains c o n t r o l s f o r applying power and f o r manually advancing the t a e . The p a p e r takeup unit contains a paper takeup r e e l and p a p e r t r a n s p o r t m e c h a n i s m . T h e t e l e p r i n t e r is capable of printing a t the r a t e of 30 c h a r a c t e r s p e r second.

T h e launch c o n t r o l panel a s s e m b l y F i g u r e 4-3) provides an additional s a f e - a r m f e a t u r e that e n a b l e s the P e r s h i n g l a s y s t e m t o m e e t n u c l e a r s a f e t y r e q u i r e m e n t s . T h e s a f e - a r m f e a t u r e c e n t e r s around a m e c h a n i c a l s a f e l a r m switch that i n t e r r u p t s t h r e e c r i t i c a l a r m i n g and firing s i g n a l s . T h e s e s i g n a l s a r e " f i r s t s t a g e ignition a r m c o m mand, f i r s t s t a g e ignition f i r e plus (+I, and m i s s i l e b a t t e r y activate command". A s a f e condition is in effect when the switch i s s e t to the s a f e position. An a r m condition is in effect when the switch is s e t t o the a r m position. T h e panel provides the n e c e s s a r y h a r d w a r e f o r s e c u r i n g the s a f e - a r m switch in a s a f e condition by m e a n s of a combination lock, which p r e v e n t s unauthorized operation of the switch to the a r m position. T o p r e vent unauthorized r e m o v a l of the launch c o n t r o l panel a s s e m b l y , the h a r d w a r e that s e c u r e s the a s s e m b l y t o the console i s bound by s a f e t y w i r e and s e c u r e d with m e t a l l i c seals.

T h e power station F i g u r e s 5-1 through 5-3) is a self contained multipurpose unit of the P e r s h i n g s y s t e m , capable of delivering e l e c t r i c a l power, pneumatic power and conditioned a i r f o r the m i s s i l e and launch s i t e ground s u p p o r t equipment. It is c a r r i e d aboard the s a m e vehicle a s the PTS. T h e power station i s contained in a skid mounted aluminum housing lined with sound absorbing m a t e r i a l t o r e d u c e the noise l e v e l produced by the g a s turbine engine. T h e power station is c o m p r i s e d of the following m a j o r functional components: 1 G a s t u r b i n e engine Z A i r c o m p r e s s o r and purification s y s t e m -

3 A l t e r n a t o r (with voltage r e g u l a t o r and e x c i t e r ) 4 DC g e n e r a t o r and r e g u l a t o r ( 2 ) -

5 Air cycle conditioning s y s t e m -

-6

M i s c e l l a n e o u s - e l e c t r i c a l d i s t r i b u t i o n center. and c o n t r o l cubicle

7 Fuel system -

8 Cranking s y s t e m -

-9

B a t t e r y charging s y s t e m

10 Unit protection -

WARNiYF HORN

LEFT

SIDE VIEW

5 - 1 . Power Station E

BATTERY ACCESS DOOR

I

I

AC STATIC

I

1

A C VOLTAGE

DC GENERATOR N O 2 VOLTAGE RLGJLATOR

VOLTAGE REGULATOR

TEMPERATURE CONTROL UNIT i 7 F I F C l R i C i ; D I S T R I b U i l O N CENTER

FUEL TANK VENT

\

VENTILA7ING FAN 51

BATTERY (2).

T h e g a s turbine engine is a lightweight, c o m p a c t s o u r c e of shaft power and b l e e d - a i r pneumatic power. Shaft power f r o m the engine i s d e l i v e r e d through a g e a r b o x to d r i v e the a c g e n e r a t o r , two d c g e n e r a t o r s , and an a i r c o m p r e s s o r ( F i g u r e 5 - 4 ) . T u r b i n e bleed a i r is d e l i v e r e d to the a i r conditioner. T h e engine, which h a s two c e n t r i f u g a l c o m p r e s s i o n s t a g e s and a s i n g l e t u r b i n e s t a g e , r u n s a t a constant speed of 42,000 r p m . Speed is a u t o m a t i c a l l y controlled by a g o v e r n o r ; however, fine speed a d j u s t m e n t is o p e r a t o r controlled by a switch on the c o n t r o l cubicle panel. Engine s t a r t i n g power i s d e r i v e d f r o m a 24-volt d c b a t t e r y supply o r f r o m an e x t e r n a l a u x i l i a r y power s o u r c e .

Figure 5-4. Engine Powered Assemblies

T h e g e a r b o x and engine a r e coupled together by a turbine-gearbox coupling. T h e coupling c o n s i s t s of two coupling halves clamped together by a V-type clamping r i n g , with a s i n g l e locating s h e a r pin t o prevent rotation by torquing effects. The engine and g e a r b o x can be quickly s e p a r a t e d by r e l e a s i n g the clamping ring. T h e two coupling h a l v e s f o r m a matched s e t and m u s t be retained together. A 6-inch floating splined shaft in the coupling p r o v i d e s the d r i v e connection f r o m the engine to the g e a r b o x . T h e g e a r b o x d r i v e s the t h r e e g e n e r a t o r s a t 6,000 r p m , and the a i r c o m p r e s s o r a t 3,064 rpm.

T h e power s t a t i o n h a s two s e p a r a t e h i g h - p r e s s u r e a i r s y s t e m s ( F i g u r e 5-5). T h e p r i m a r y s y s t e m is c o m p r i s e d of an a i r c o m p r e s s o r that supplies h i g h - p r e s s u r e a i r to an a i r purification unit, which in t u r n s u p p l i e s purified h i g h - p r e s s u r e a i r t o the m i s s i l e through a network of h o s e s and valves. T h e a i r c o m p r e s s o r d e l i v e r s a i r a t a p r e s s u r e of 3000 f 200 psig a t a flow r a t e of 9 s t a n d a r d c f m minimum. T h e s e c o n d a r y h i g h - p r e s s u r e a i r s y s t e m , r e f e r r e d t o a s the i n s t a n t a i r s y s t e m ( F i g u r e 5 - 6 ) , u s e s a p r e s s u r i z e d a i r cylinder t o provide a limited supply of h i g h - p r e s s u r e a i r to the a i r purification unit f o r use by the m i s s i l e until the p r i m a r y h i g h - p r e s s u r e a i r s y s t e m i s fully activated. The instant a i r s y s t e m is provided s o l e l y a s s u p p o r t f o r the p r i m a r y s y s t e m .

,

, I

GEARBOX

AIR SUPPLY

/

AIR PURIFICATION UNIT

PUR'IFIED HIGH~PRESSURE AIR

The a i r c y c l e conditioning s y s t e m c o n s i s t s of: 1 Panel control assembly 2 Temperature sensor assembly -

3 A i r cycle a s s e m b l y -

-4

T e m p e r a t u r e selection a s s e m b l y

P r e l a u n c h cooling and heating to the m i s s i l e during ground t e s t and checkout a r e p r o vided by t h i s s y s t e m ( F i g u r e 5-5). Operating in conjunction with the m i s s i l e a i r cycle conditioning s y s t e m , the t e m p e r a t u r e c o n t r o l s y s t e m i s e n e r g i z e d by a sensing e l e m e n t located in the m i s s i l e i n s t r u m e n t c o m p a r t m e n t , T e m p e r a t u r e c o n t r o l i s provided by a modulating valve which t e m p e r s the a i r t o maintain a m i s s i l e c o m p a r t m e n t t e m p e r a t u r e within f l ° F . At a l l stabilized t e m p e r a t u r e points (40' i 5OF, 77O t l ° F , and 160' i 5OF) the conditioned a i r flow i s 25 pounds of a i r p e r minute under s e a l e v e l operating conditions.

The power station d c power s y s t e m c o n s i s t s of two d c g e n e r a t o r s , e a c h with a voltage r e g u l a t o r and output wiring. Each d c g e n e r a t o r is compound wound and self ventilated with a rating of 300 a m p e r e s a t 30 v o l t s and a nominal speed of GO00 rprn. All windings of the g e n e r a t o r a r e ungrounded and isolated e l e c t r i c a l l y f r o m e a c h o t h e r and, with the voltage r e g u l a t o r disconnected, can be used a s a s t a r t i n g m o t o r . After s t a r t u p , a t r a n s f e r r e l a y c o n v e r t s the s t a r t i n g m o t o r t o a g e n e r a t o r . With the g e n e r a t o r under c o n t r o l of i t s voltage r e g u l a t o r and d r i v e n at a n y constant speed of 6000 i. 120 r p m , and adjusted t o deliver- any voltage within the specified range (25-35) a t any load between no load and r a t e d load, the voltage r e m a i n s within 2 0.5 p e r cent of the a v e r a g e no load and full load voltage. A t any constant load, the g e n e r a t o r t e r m i n a l voltage i s within 0.5 p e r c e n t of i t s a v e r a g e value. The voltage r e g u l a t o r i s used f o r e i t h e r r e m o t e o r l o c a l sensing, and is equipped with compensating provisions which l i m i t t o l e s s than 1 p e r c e n t the voltage d r i f t caused by w a r m - u p of the shunt field and voltage r e g u l a t o r , and changes in ambient t e m p e r a t u r e .

The power station a c power s y s t e m c o n s i s t s an a c g e n e r a t o r o r a l t e r n a t o r with voltage regulation and excitation, and output wiring. T h e a l t e r n a t o r i s self ventilated and h a s a rotating field synchronous a l t e r n a t o r r a t e d a t 40 kVA, 0.75 power f a c t o r lagging, 1201208 v o l t s , 400 Hz, 3-phase, four w i r e connected. T h e voltage r e g u l a t o r and excitation s y s t e m a r e completely s t a t i c d e v i c e s . P a r t of the a l t e r n a t o r output is fed back i n t o the a l t e r n a t o r field f o r excitation; the amount of

the feedback is dependent on the power f a c t o r of the load and i s approximately equal t o the field excitation to s u p p o r t that load. Both the a v e r a g e and highest phase voltage a r e s e n s e d by the s e n s i n g c i r c u i t . In n o r m a l operation, the a v e r a g e s e n s i n g provides the signal t o the r e f e r e n c e c i r c u i t , With unbalanced loads, highest phase sensing t a k e s o v e r . Regulator compensation m i n i m i z e s d r i f t in the regulated voltage caused by w a r m - u p of the a l t e r n a t o r field, e x c i t e r , and r e g u l a t o r , o r changes in ambient t e m p e r a t u r e . Voltage d r i f t d o e s not exceed 1 p e r c e n t when the equipment i s installed i n the power station, Using a m a n u a l s t e p l e s s r h e o s t a t , i t is possible t o adjust the regulated line-to-line voltage at any value between 200 and 218 volts, at any load f r o m no load to full load, a t any ambient t e m p e r a t u r e within the specified t e m p e r a t u r e r a n g e , and a t any frequency between 380 and 420 Hz.

Other power station s u b s y s t e m s a r e the fuel s y s t e m , cranking s y s t e m , b a t t e r y c h a r g ing s y s t e m , and unit protection s y s t e m . T h e fuel s y s t e m includes a fuel f i l t e r , engine d r i v e n high p r e s s u r e fuel pump, fuel flow regulating provisions i n t e g r a l with the engine c o n t r o l s y s t e m , and the r e q u i r e d tubing and fittings. T h e c r a n k i n g s y s t e m s t a r t s the power station engine and b e c o m e s inoperative when the engine i s running. T h e cranking s y s t e m h a s a b a t t e r y , one of the d c g e n e r a t o r s used as a s t a r t i n g m o t o r , and a s t a r t i n g r e l a y a s s e m b l y , After the cranking period i s o v e r , the d c g e n e r a t o r s a r e e l e c t r i c a l l y isolated f r o m the b a t t e r y . T h e b a t t e r y charging s y s t e m c o n s i s t s of a t r i c k l e c h a r g e r fed f r o m the a l t e r n a t o r , with a charging i n d i c a t o r provided on the c o n t r o l cubicle. Independent of the a l t e r n a t o r output voltage, the charging r a t e i s adjustable, with a c u r r e n t limiting device to prevent overcharging. T h e s y s t e m m a i n t a i n s the b a t t e r i e s in a s t a t e of full c h a r g e through a r e a d i l y a c c e s s i b l e waterproof r e c e p t a c l e mounted on the power station s o the b a t t e r i e s c a n be c h a r g e d , in place, f r o m an e x t e r n a l s o u r c e . Engine, gearbox, and a i r c o m p r e s s o r low o i l p r e s s u r e , a i r c o m p r e s s o r high-stage p r e s s u r e , and engine o v e r s p e e d malfunctions will automatically produce station engine shut down. T h e protection d e v i c e s which p e r f o r m t h i s automatic shutdown make up the unit protection s y s t e m . P o w e r is disconnected by a c o r d c s h o r t c i r c u i t , ac and d c overvoltage, and a c undervoltage malfunctions. With the protection switch in the bypass position, the power s t a t i o n will continue operating u n l e s s the malfunction is engine o v e r s p e e d o r an a c o r d c s h o r t c i r c u i t .

T h e a z i m u t h l a y i n g s e t p r o v i d e s the m e a n s for, la>-ing tile P e r s t l i n g m i s s i l e on i t s f i r i n g a z i m u t h by e s t a b l i s h i n g t h e g u i d a n c e p l a t f o r m heading. T h e e q u i p m e n t i n c l u d e s s t a n d a r d o p t i c a l s u r v e y i n s t r u m e n t s mounted on l a t h e bed t r i p o d s . T h e p a r t i c u l a r m e t h o d t o be e m p l o y e d ( h o r i z o n t a l o r v e r t i c a l laying) is d e t e r m i n e d by i n i t i a l e r , e c t o r , l a u n c h e r a l i g n m e n t with r e s p e c t t o the f i r i n g a z i m u t ! ~l a y i n g e q u i p m e n t and t h e m i s s i l e f o r both a l i g n m e n t s c h e m e s is i n d i c a t e d in F i g u r e 6 - 1 . A p o r r o p r i s m a t t a c h e d t o t h e r e f e r t o F i g u r e 2 - 1 9 ) is viewed t h r o u g h a window on t h e m i s s i l e s k i n and is u s e d a s a r e f e r e n c e i n p l a c i n g t h e ST-120 on t h e d e s i r e d h e a d i n g . T h e p o r r o p r i s m is d i s p l a c e d to the d e s i r e d !leading by i n s e r t i n g a n e l e c t r i c a l b i a s i n g s i g n a l i n t o t h e p l a t f o r m a z i m u t h a l i g n m e n t loop.

T h e azimilth l a y i n g s e t c o n s i s t s of three r e f e r e n c e t h e o d o l i t e s ( t h e o d o l i t e ' I ' Z with m i l s c a l e s ) , two wood t r i p o d s t r i p o d T 2 ) , two m e t a l t h e o d o l i t e t r i p o d s ? two t h e o d o l i t e bed a s s e m b l i e s , one s u r v e y i n g t a r g e l s e t , tht e e s u n s i i i e l d t e c t s , one i l l u m i n a t e d sunsihade a s s e m b l y , t h e e s u r v e y o r ' s u n h h r c l i a s , s i x headset-rnicrop!hone a s s e m b l i e s , t h r e e e y e p i e c e a d a p t e r a s s e m b l i e s , and t h r e e w i n t e r i z a t i o n k i t s . T w o a z i m u t h l a y i n g s e t s ar.e a s s i g n e d t o t h e f i r i n g s e c t i o n . T v o s h i p p i n g and s t o r a g e c o n t a i n e r s p e r azimutih l a y i n g s e t a r e f u r n i s h e d f o r c a r r y i n g t h e l a y i n g e q u i p m e n t , An a z i m u t h laying c o n t r o l box (AT,CB), s t o r e d in t h e P'rS, and c a b l e a s s e m b l i e s , s t o r e d i n the a u x i l i a r y e q u i p m e n t v e h i c l e , a r e used i n c o n j u n c t i o n witil t h e a z i m u t h ?a,ying s e t .

-

1 he h o r i z o n t a l laying iiieocio!ite (H1,T) and vel.tica1 laying theoclolite (V1,T) a r e i d e n t i c a l . T!le I11,T o r V L T c o n s i s t s of a ti:eodolit,e, bed a s s e m b l y , an6 m e t a l t r i pod ( F i g u i , e ( i - 2 ) . One c o n t r o i box i s used with both the li1,'i' and VL'I'. T h e I I I , T i s used it: aligning the ST-120 platform on the firirlg ;izirnutti when tile m i s s i l e h e x ing i s ivil!liii ? i s : ? m i l s (7.5') of the firir:g ;lzimuti:; ii i s ;iiso used lo :ic~ter~rnir:ethe heaciitiq of tile S'T-120 p1atfor.m wiieti ttie m i s s i l e h ~ a c i i n gi s not within +-I33m i l s but within ~ 1 5 8 2m i l s (Si? d e g ~ , e e s of ) the fii,ing : ~ z i m u t h . T h e V1,T i s used in aiigniiig tile ST - 1 I70 pltitfoim on tile f i r i n g a z i ini~tii;tftcli t i l e m i s s i l e i s r,otntec! to a nrw f i r i ~ l g; t z i m u ~ h . 7

T h e o r i e n t i n g s t a t i o n theodolite c o n s i s t s of a theodolite rnountecl on a t r i pod T2 (Figure ( i - 3 ) . ' r h e OST i s used t o tr,;msfer d i r e c t i o n a l c o n t r o l t o a l l of tihe o t h e r i n s t r u m e n t s used in laying the m i s s i l e . D i r e c t i o n a l cont.rai i s transfer.r,eti using tile p r , o c e s s of i ~ e e i p r o c a lcollirnation ( c o m m o n l y r e f e r r e d to a s r.eciproc;il laying), a f t e r the OST h a s been o r i e n t e d .

Orienting

rge

T h e orienting line t a r g e t (OLT) cons i s t s of a t a r g e t , t r i b r a c h , b a t t e r y box, and tripod T 2 ( F i g u r e 6-4). A night light attachment i s mounted on the back of the t a r g e t f o r d a r k d a y s and night operation. T h e OLT is used t o obtain d i r e c t i o n a l orientation.

h t r o l or Indicator .AY

FLATF i n d i c a t o r

Function ;hen on, i n d i c a t e s t h a t ST123 cap b e r o t a t e d . tihen flashing, i n d i c a t e s t h d t 51-120 c a n be r o t a t e d aqd t n a t l l 0 I i i i O P ssii t c h can be pressed.

>anel l i g h t ( 5 )

3 r o v l d e s i l ~ u r i n d t i o r if o r pme1

1O:JSTOP svii t c h

1ni:iates moni t o r i n g s e quence a f t e r ST-120 i s a l i g c e d on f i r i n g a z i m u t h .

IONITOR i n d i c a t o r

,hen on, i n d i c a t e s t h d t ST1?0 1s t o b e observed, b u t not rotated.

iiitO"GI?P control

C o n t r o l s i n t e n s i t y o f theodol i t e iiqht.

P;iL LIGI!TS control

C o n t r o l s i n t e n s i t y of panel llgiits,

PCSET \r,i t c h

Extends f i riri,; sequence t o a l l o w f u r t t i e r d l i j n l l e n t of ST-120.

liI'ii1LiTf r w i t c h

I n i t i d t e s the next s y i t a : i e r j u c n c r when e l t i l e r h o r i rontrii o r v e r t i c a l dzi-uth layinil function i s c o w ~letec.

1kEAGSfT VCL control

Controls s i g n a l s t r e n g t n t o the headset earphones.

PLATF CONTROL switch

Controls s i g n a l f o r r o t a t i n g t h e ST-120

Figure 6-4. Orienting Line Target

Figure 6-5. A z i ~ u t hLaying Control Box

T h e azimuth laying c o n t r o l box ( F i g u r e 6 - 5 ) is a r e c t a n g u l a r m e t a l box containing e l e c t r i c a l c i r c u i t s which a r e connected ( b y cable) t o and powered by the p r o g r a m m e r - t e s t station. T h e s e c i r c u i t s provide illumination f o r the theodolite and the c o n t r o l box panel i n d i c a t o r s , bias volta g e s f o r controlling the ST-120 i n e r t i a l guidance platform, and s w i t c h e s f o r controlling the application of power t o the PTS m o n i t o r , r e s e t , and complete r e l a y c i r c u i t s , When the m i s s i l e i s horizontal, the c o n t r o l box i s used with the h o r i z o n t a l laying theodolite. When the m i s s i l e i s v e r t i c a l , the c o n t r o l box i s used with the

v e r t i c a l laying theodolite. If the c o n t r o l box o r i t s c a b l e is defective, azimuth l a y ing p r o c e d u r e s m a y be p e r f o r m e d inside the PTS, using the azimuth laying c o n t r o l panel a s s e m b l y .

T h e azimuth laying c o n t r o l box s i g n a l flow d i a g r a m i s shown in F i g u r e 6 - 6 and a d e s c r i p t i o n of the signal function i s given below. T h e azimuth positioning signal is developed in t h e p l a t f o r m control c i r c u i t in t h e control box f r o m a 28 Vdc position excitation s i g n a l r e c e i v e d f r o m t h e power d i s t r i b u t i o n a s s e m b l y in the PTS. T h i s s i g n a l is sent t o the platf o r m alignment c i r c u i t in t h e P T S and is used f o r rotatin,: t h e ST-120, T h e monitor command initiate s i g n a l is generated in t h e control box monitor switch c i r c u i t when the control box MONITOR switch is p r e s s e d . T h i s s i g n a l i s s e n t t o t h e p l a t f o r m alignment c i r c u i t in the P T S and is used f o r init i a t i n g a n optical monitoring period. T h e l a y p l a t f o r m command signal is s e n t f r o m t h e p l a t f o r m alignment c i r c u i t in the P T S t o t h c l a y platform indicator c i r c u i t i n the c o n t r o l box. T h i s signal is used f o r lighting t h c c o n t r o l box LAY P L A T F indicator. A s t e a d y o r flashing LAY P L A T F indic a t o r signifies t h a t t h e ST-120 m a y be rotated. T h e s t e a d y indication i s used f o r informing t h e theodolite o p e r a t o r when azimuth laying p r o c e d u r e s a r e t o be s t a r t e d and when f a s t s l r w ( r o u g h alignment) of t h e ST- 120 c a n be p e r formed. T h e flashing indication is used t o i n f o r m t h e o p e r a t o r when fine s l e w (fine alignment) of t h e ST- 120 can be p e r f o r m e d .

1

AZI W T H LAY 1:IG CONThnL BOX

LAY I'l.ATFOCI1

PROGRAMHE R-

TEST STATION

CO?!III1ND

l i I P 1 CATOK

I

Figurn 6-6. Azimuth Laying Control Box

T h e lay r e s e t command s i g n a l i s g e n e r a t e d in the c o n t r o l box r e s e t switch c i r c u i t when the control box RESET switch i s p r e s s e d . T h i s s i g n a l i s s e n t to the platform alignment c i r c u i t in the PTS, and i s used f o r informing the c o m p u t e r pr,ogr,am that f u r t h e r positioning of the ST-120 is r e q u i r e d . T h e monitor command i s s e n t f r o m the platform alignment c i r c u i t in the P T S to the m o n i t o r indicator c i r c u i t in the control box. T h i s s i g n a l i s used f o r lighting the c o n t r o l box MONITOR i n d i c a t o r , indicating that the ST-120 stabilized platform should be monit o r e d but not r o t a t e d . The complete command s i g n a l i s g e n e r a t e d in the c o n t r o l box complete switch c i r c u i t when the c o n t r o l box C O M P L E T E switch i s p r e s s e d . T h i s s i g n a l i s s e n t to the platform

alignment c i r c u i t i n the PTS and i s used for terminating the horizontal o r v e r t i c a l laying verification phase.

The major items of equipment w h i c h support azimuth laying o p e r a t i o n s a r e illustrated i n Figure 6-7.

With the equipment a r r a n g e d a s i l l u s t r a t e d in F i g u r e 6 - 8 , the m i s s i l e i s oriented in azimuth by using e i t h e r the e r e c t - a n d - f i r e mode ( s t a n d a r d o r quick count) o r the v e r t i c a l laying mode of azimuth laying. The e r e c t - a n d - f i r e mode i s used when the m i s s i l e heading is within 133 m i l s ( 7 . 5 d e g r e e s ) of the firing azimuth (FA). T h e v e r t i c a l laying mode is used when a new t a r g e t is s e l e c t e d and the m i s s i l e heading i s not within 133 m i l s ( 7 . 5 d e g r e e s ) of the FA. Azimuth laying p r o c e d u r e s p e r f o r m e d d u r i n g ;I confidence count a r e i d e n t i c a l with t h o s e p e r f o r m e d during a standard count.

T h i s mode r e f e r s t o the operation performed t o align the ST-120 on the F-4 while the m i s s i l e i s in the horizontal position. T h e m i s s i l e i s then e r e c t e d and fired and r o l l s to the F A i m m e d i a t e l y following liftoff. During this operation, the OST i s used to t r a n s f e r d i r e c t i o n a l c o n t r o l t o the HLT. The ALCB, in conjunction with the HLT, is used to t o r q u e the ST-120 until i t is a c c u r a t e l y aligned on the FA, and t o o b s e r v e , maintain, and m o n i t o r the alignment of the ST-120 until the C O M P L E T E switch on the ALCB i s p r e s s e d . In the confidence and s t a n d a r d counts, the HLT o p e r a t o r t o r q u e s the ST-120 platform into rough alignment and fine alignment. During the confidence count, a voltage equivalent t o the angular r e l a t i o n s h i p between the m i s s i l e longitudinal a x i s and the f i r i n g azimuth of the ST-120 i s s t o r e d in the P T S c o m p u t e r m e m o r y f o r use in the quick count. During the quick count, the f a s t slewing of the ST-120 platform to rough alignm e n t i s automatic, and the azimuth laying sequence following the optical monitoring period is g r e a t l y reduced a s c o m p a r e d with the confidence and s t a n d a r d counts.

T h i s mode r e f e r s t o the operation p e r f o r m e d when a new t a r g e t i s s e l e c t e d a f t e r the E L , with m i s s i l e , h a s been emplaced and the FA of the new t a r g e t is not within & I 3 3 m i l s (7.5 d e g r e e s ) but within +I582 m i l s ( 8 9 d e g r e e s ) of the i n i t i a l m i s s i l e heading. (If the FA of the new t a r g e t i s within 'r133 m i l s of the initial m i s s i l e heading, the laying p r o c e d u r e s p r e s c r i b e d for the e r e c t - a n d f i r e mode a r e performed.) The HLT, in conjunction with the ALCB, is used to d e t e r m i n e and m o n i t o r the heading of the ST-120 until the COMP1,ETE switch on the ALCB i s p r e s s e d . T h e position of the ST-120 i s d e t e r m i n e d while the m i s s i l e i s horizontal. 'The m i s s i l e i s then e r e c t e d and manually rotated until i t i s roughly aligned on the FA. During t h i s operation, the OST i s used t o t r a n s f e r d i r e c tional control to the HLT and VLT. After the m i s s i l e i s e r e c t e d and rotated t o within 5 m i l s of the F A , the ALCB, in conjunction with the VLT, is used to torque the ST-120 until i t i s a c c u r a t e l y aligned on the F A . T h e VLT is then used t o m o n i t o r and maintain the alignment of the ST-120 until the C O M P L E T E switch on the ALCB i s p r e s s e d .

I

/I I

I

GUIDANCE SECTION WINDOW

ORIENTING LINE TARGET

MISSILE HEADING 2 1 3 3 MILS 17.501 MAXIMUM FIRING AZIMUTH

I

HORIZONTAL LAYING THEODOLITE

THEODO SUNSHIELD TENT

30 TO 50M (98 TO 164 FT)

' VERTICAL LAYING THEODOLITE (IF REQUIRED)

APPROX 16M 152 FTI

/

/

20M 16.6 FT) MINIMUM

*---

-

MISSILE ERECTED

20 to 30M \65 to 98 FTJ (SEE NOTE)

i?

ORIENTING STATION THEODOLITE

NOTE. IF DISTANCE IS GREATER THAN 24M (79 FT), AN ADDITIONAL 60W43 MUST BE USED.

The b a t t e r y control centra! ( R C C J i s a t r a n s p o r t a b l t unit that p r o v i d e s the firing b a t t e r y c o m m a n d e r o r duty- officer a c ~ n i r a l i z e t facility i for exprcising ail battery command and control functions and a c c e s s t o a!: e x t e r n a l anti i n t ~ r n a !communications. It contains the n e c e s s a r y communications, display b o a r d s , and o p e r a t o r work stations t o p e r m i t the b a t t e r y c o m m a n d e r o r his r e p r e s e n t a t i v e to l n o ~ i t o rthe firing platoon activities, and e x t e r n a l communications f r o m one iocaiiot? on a 2 4 hour b a s i s . -4 block d i a g r a m of the BCC equipment is shown in I:igure 7-1. The BCC provides iandline communication with the l"i'S!s in the t h r e e f i r i n g platoons, allo-wing the b a t t e r y c o m m a n d e r or. duty officer to maintain control and monitor the f i r i n g platoon a c t i v i t i e s f r o m a c e n t r a l i z e d location ( F i g u r e 7-2). In addition, !3CC t e r minations for- a local field switchboard and an a r e a a l e r t s y s t e m a r e provided. The BCC enables f i r i n g platoon control b y m e a n s of the b a t t e r y intercom, s t a t u s dispiay facility, r e m o t e f i r e boxes, and 7'-1300 c o n t r o l l e r s . The i n t e r c o m p e r m i t s the b a t t e r y c o m m a n d e r to r e c e i v e platoon s t a t u s information: initiate and monitor c o ~ ~ n t downs, and change t a r g e t a s s i g n m e n t s . T h e s t a t u s display facility p e r m i t s a c u r r e n t display of platoon s t a t u s . T h i s information i s continuou.sly available f o r upline s t a t u s r e p o r t i n g and f o r use in scheduling and controlling platoon activities. The r e m o t e f i r e box (RFB)and p r e s c r i b e d action iink (PAL)c o n t r o i l e r (1'-1500) provide the c o m m a n d e r with the final authority t o c o n t r o l m i s s i l e launch and warhead enablement. T h e "good'" light on the T-1500 a s s u r e s the b a t t e r y c o m m a n d e r that the warhead h a s been enabied while the "ready" light on the i i F B provides an indicatior, that the countdown h a s p r o g r e s s e d t o the point w h e r e the m i s s i l e m a y be f i r e d . T h e s e indications and the HF'B f i r e buttons p e r m i t the b a t t e r y c o m m a n d e r t o positively coordinate and c o n t r o l mu-itipie launches a s r e q u i r e d . T h r e e T-1500's and t h r e e HFB's a r e located in the RCC?. T h e s e units a r e hardwired d i r e c t l y t o the m i s s i l e l a u n c h e r s and PTS, r e s p e c t i v e l y , and the EF'R's a r e provided a two-lock cover. During t r a n s i t the T-i5OO's and R F B ' s a r e c a r r i e d on "Le I'TS vehicle to provide autonomous f i r e platoon capability.

-I

--

-

1 BATTERY CONTROL CENTRAL I

S lGNAL ENTRANCE

!

I PANEL

!

I

7---I

1

TO MISSILE 1

I 1

1 ;:FIE

I

1

/

RECORDER'S 3

BOX 3

/TO

PTS 2

TO

KLAXONS

N-----

-

* i I TELEPHONE i Tk-3?2/PT

*i

1

TO LOCAL FIELD SWITCHBOARD

TELEPHONE TF-3li'IPT

ON REAR OF VAN !

T h e BCC is housed i n a n M - 4 expansible van mounted on a modified M656 vehicle ( F i g u r e s 7 - 3 and 7-41. P r i m a r y power f o r o p e r a t i n g t h e RCC is n o r m a l l y supplied by Hz, 120/208 volt, 3-phase t r a i l e r - m o u n t e d g e n e r a t o r which is towed behind t h e BCC. E m e r g e n c y power is supplied by b a t t e r i e s on t h e 1VI656 vehicle.

ree

rior Vie

The BCC expands to approximately twice the volume it encioses when r e t r a c t e d . To expand the BCC the side panels a r e expanded and the counterbalanced hinged roof and floor sections a r e unfolded. The BCC is sealed against the entrance of water and the e s c a p e of light in both the expanded and r e t r a c t e d positions. An entrance door n e a r the r e a r on each side of the RCC provides a c c e s s when the BCC i s expanded. Two entrance doors in the r e a r of the BCC provide a c c e s s when the BCC is e i t h e r expanded o r r e t r a c t e d . Two l a d d e r s , stored on the r e a r doors, provide a c c e s s t o the RCC floor level. A signal entrance panel is mounted in the r e a r of the BCC next t o the r e a r door on the left side. A 36, 000-Btu a i r conditioning unit and t.wo 60, 000-Btu heating units a r e installed in a bonnet extending f r o m the front of the BCC. The units provide heating and cooling f o r personnel. and environmental protection f o r equipment in the BCC, Two fm antennas a r e mounted oil the BCC' with quick-disconnect fasteners. One of the fm antencas is located on the left front of the bonnet, and the other fm ante?nna i s located on the right r e a r of the R C C . Feedthrough f o r the antennas i s through a receptacle panel located below each antenna mount. The arltenna matching units may Se left in the mounts and the whip sections tied down to cleats on the BCG d w i n g t r a v e l in a r e a s f r e e of obstructions. A r e m o t e antenna can be used instead of an f m antenna mounted on the BCC. When the r e m o t e antenna i s used, it i s connected t o the receptacle panel. One antenna; used f o r a m and fm receiving, i s m ~ u n t e c ldirectly above and through the signal e n t r a n c e panei a t the left r e a r of the BCC. The i n t e r i o r of the BCC i s divided into two functional a r e a s : the command and cont r o l a r e a on the right side, and t'ne recording a r e a on the left side. The command and control a r e a contains the equipment required for conducting tactical command and cont r o l functions. The equipment in the recording a r e a is used f o r administrative and r e cording functions ir? support of the command and control ope-rations. F i g u r e s 7 - 5 and 1-5 show the equipment locations for the left and right s i d e s of the BCC.

The trailer-mounted 15 kiV gerierator supplies a c power f o r operation of "Le a i r conditioner, h e a t e r s , and lights, and supplies i20 volt, 6 0 Hz power f o r operation of equipment in the S C C . Five c i r c u i t b r e a k e r switches distribute a c power to the BCC equipment. TIC power required f o r operation of the equipment i s normally obtained f r o m two 2 5 Vdc power supplies and one 9 Vdc power supply. Two telephones r i ' A - s I Z / PT and two telephone switchboards 13-221PT contain an internal 3V battery power s o u r c e . E l e c t r i c a l power o r signal voltage f o r operation of the rerno-ce firing boxes o r remote s p e a k e r console i s supplied by the equipment t o which it i s connected outside the BCC. The two radio s e t c o n t r o i s , connected t o the remote frn t r a n s c e i v e r s , contain an internal battery power s o u r c e . During emergency power operation, dc power, which is normally supplied by the 2 3 Vdc power supplies and the 9 Vdc power supply, i s obtained f r o m the vehicle battery. Emergency power is x e d only for selective e q u i p ~ e n tand emergency lights. The vehicle battery power i s applied through the emergency power entrance panei t o the power panei. i\1.70

19

LEFT SIDE

3 - IS0 Vac convenience - Telephone switchboard SB-22/PT (3) 5 - Headset H-167j)/U storage bin ( 3 ) 5 - Recorder's control box ( 3 ) d i o s e t control C-2328/GRA-39 ( 3 ) g n e t i c chal kboard per t r a n s f e r s l o t 10 - Clock 1; - Ghal k tray a 2 - FM trafisceiver noise suppression cover (2) 13 - Blower u n i t 14 - Typewriter storage area 15 - Ground cable ( 2 )

i

18

16 - Klaxon ( 3 ) and storage f i x t u r e 17 - Emergency lantern (2) and storage Fixture

25 26 27 28 29 30

-

Antenna storage box Security s a f e F i l e cabinet (two-drawer) Chair Klaxon t r i p e Typewriter

i 6 M T SIDE

emote f i r i n g box housing ( 3 ) 2 - PAL u n i t T-1560 mount ( 3 ) - PAL u n i t i-I500 connector ( 3 ) - Remote f i r i n g box connector ( 3 )

15 - Radio s e t control C-2328/GRA-39 ( 3 ) 76 - Paper transfer s l o t I7 - TRC-80 pane? 18 - C h a l k t r a y

22

-

(Deleted)

T h e P e r s h i n g s y s t e m u s e s r a d i o and w i r e communications to p e r f o r m command and c o n t r o l , l o g i s t i c s , and a d m i n i s t r a t i v e functions. F i g u r e 8- 1 shows the communications network utilized f o r quick r e a c t i o n a l e r t RA) o p e r a t i o n s . For- these operations the AWiTRC-133-4, r a d i o t e r m i n a l s e t single s i d e band o r SSE in QK-4 r e l e a s e m e s s a g e communications m e a n s . T h e A N j ROFO in F i g u r e 8-11 is used a s backup f o r the QR-A r e i e a s a g e and for battalion l o g i s t i c s and a d m i n i s t r a t i v e functions, Short range F M / U R C - 4 f i 9 AN/ C R C - 4 7 , etc.), indicated a s F M i n F i g u r e 8-1, and w i r e communications a r e provided f o r additional Sack up f o r the . A W / T R C - ~ ~and ~ A ANiTRG-80. T h e communications within the firing b a t t e r y , whidh inciude icterflices with the BCC, a r e shown in F i g w e 8-2,

T h e . A N ~ ' I ' R C - ~F Oi g u r e 8-3) functions p r i m a r i l y a s a r a d i o c i r c b i t t e r m i n a l , c a p d r e c e i v i n g s p e e c h and voice frequency r a d i o - t e l e t y p e w r i t e r ble of t r a n s m i t t i n g s i g n a l s simultaneously, using the tropospher- s c a t t e r method of prgpagation. 0 m i l e s is dependent on the urn o p e r a t i n g d i s t a n c e of up t o approximately horizon angle and on the d e g r e e of r e l i a b i l i t y d e s i r e d ,

T h e AN/TRC-BO s h e l t e r h o u s e s the communications equipment, antenna, and engine g e n e r a t o r and is t r a n s p o r t e d by an MGSG vehicle. T h e m a ; o r equipment of the AN'TRC-80 c o n s i s t s of the following:

1 C i r c u i t c o n t r o l and operating equipment 2 F r e q u e n c y g e n e r a t i o n equipment -

LAND LiNE

1

USAREUR

/

TAC ALERT NET

DIRECT LINE

TOR

JLY

BRIGADE OPERATIONS CENTER TRO BATTALION OPERATiONS CENTER TROP

BCC

\ i i

LEGEND

-

- FIELD WIRE - - -.CABLE RADIO

TO BATTALION

TO BATTALION AND HIGH HEADQUARTERS

@VOICE @SIGNAL @ TELETYPE

4 Radio f r e q u e n c y a m p l i f i e r 5 Antenna -

6 Radio r e c e i v e r -

-

-8

o w e r equipment A i r conditioning equipment

T h e c i r c u i t c o n t r o l group of equipment i s c o m p r i s e d of the power distribution p m e l , communications c o n t r o l p x i e i , teletype switch panel, t e l e g r a p h t e r m i n a l , and a d e multiplexer-multiflexer, F r e q u e n c y g e n e r a t i o n equipment c o n s i s t s of t n r e e s y n t h e s i z e r units which supply l o c a l o s c i l l a t o r s i g n a l s t o the two c o n v e r t e r s i n the r e c e i v e r znd the c a r r i e r s i g n a l tc the t r a n s m i t t e r c o n v e r t e r , T h e e x c i t e r c o n s i s t s of a m o d u l a t o r - m u l t i p l i e r and an amplifier-converter., The m o d u l a t o r - m u l t i p l i e r r e c e i v e s and c o n v e r t s a modulating s i g n a l f r o m the multiplexer and p r o v i d e s a moduiated s i g n a i t o the a m p l i f i e r c o n v e r t e r . T h e a m p l i f i e r - c o n v e r t e r r e c e i v e s a modulated s i g n a l f r o m the modulator-multi and a c a r r i e r s i g n a l f r o m a s y n t h e s i z e r , and d e l i v e r s output -frequency driving power t o the output power a m p l i f i e r ,

I

~ r r a~d i eo frequency a m p l i f i e r a c c e p t s a frequency modulated s i g n a l f r o m the a m p i i f i e r - c o n v e r t e r and a m p l i f i e s t h e s i g n a l t o an output power of 1. r-7

t

T h e A N / T R C -8 antenna a s s e m b l y c o n s i s t s of an inflatable f a b r i c bag having one metalized i n n e r s u r f a c e that f o r m s a p a r a b o l i c r e f l e c t o r when the bag i s inflated. Bag infiation i s maintained by a blower. T h e blower and the c o m p r e s s o r a r e mounted on the antenna platform on one s i d e of the lower s u p p o r t platform.

BE azimuth m a r k e r s t r i p , c a l i b r a t e d in hundreds of m i l s , i s located w o u n d the b a s e of the azimuth p l a t f o r m , The antenna azimuth may be changed manually i;i I c r e r n e n t s . F i n e azirnath adjustment i s controlled f r o m i n s i d e the s h e l t e r . T h e 1,adio r e c e i v e r c o n s i s t s of an a m p l i f i e r - c o n v e r t e r ( r e c e i v e , an i n t e r m e d i a t e f r e q u e n c y a m p l i f i e r , and two power supplies. Two complete r e c e i v e r s a r e used. P r i m a r y power f o r the A N / T R C - 8 0 i s supplied by a gasoline engine g e n e r a t o r s e t . T h e engine g e n e r a t o r i s mounted on slide [ . a i l s and i s pulled out for operation and servicing,

T h e ~ ~ / ' r ~ C - 1 3 is 3 -a! s i n g l e sideband voice r a d i o t e r m i n a l mounted in an 5-141/6 t y p e s h e l t e r with r a d i o equipment i n s t a l l e d . A 2 - 1 1 2 ton t r u c k is used t o t r a n s p o r t the s h e l t e r and pull t h e pourer- unit t r a i l e r . The A N I T R C - I ~ ~sA h e l t e r contains five r a d i o positions, e a c h using a. r a d i o r e c e i v e r t r a n s m i t t e r ( T R - 7 8 / F R C - 9 3 ) , with r a d i o s e t c o n t r o l power supply q u a r t z c r y s t a l anit s e t ( C K - 3 1 / F PP-~WO/FRC-~~ ~ - 1 2 1 7 / ~ R G - 9 3 )E . a c h of the five r a d i o e q u i p m e n i s can be connected t o a s e p a r a t e doublet anzenna provided a s p a r t of the s h e l t e r equipment, P o s i t i o n 5 is a l s o capable of o p e r a t i n g with a 15-foot whip antenna when the r a d i o t e r m i n a l s e t i s mobile. The five r a d i o eqiiipments a r e powered f r o m !15V, 60 Hz, s i n g l e - p h a s e a c power when the t e r m i n a l is in a fixed o r semifixed position. P o s i t i o n 5 r a d i o equipment i s powered By the 2 8 Vdc v e h i c u l a r e l e c t r i c a l s y s t e m d c power supply, P P - 4 1 5 1 , / F ~ C - 9 2 )d a r ing mobile o p e r a t i o n . Radio f r e q u e n c y T N - ~ ~ ~ / G ) isRused f o r ope ration of tine mobile r a d i o t e r m i n a l s e t (position 5) on f r e q u e n c i e s below 2 0 M H z , P r o v i s i o n s a r e m a d e f o r mounting the tiedown of a 15-foot whip antenna on the outs i d e f r o n t w a i l of the s h e l t e r . Nine s t a n d a r d antenna m a s t s ( A I 3 - 1 5 5 / ~ ) , antenna w i r e , c o a x i a l c a b l e and a s s o c i a t e d h a r d w a r e a r e provided to e r e c t five doublet antennas f o r connection to the ac-powered r a d i o s e t s when "Ie r a d i o t e r m i n a l s e t is used in a fixed o r semifixed position, T h r e e A B -1 5 5 / ~ ' )s u p p o r t e a c h of the doublet antennas.

A r e m o t e s p e a k e r console is provided to allox$- o p e r a t i o n a"; r e m o t e s i t e , T h e audio ou-cput f r o m the four mor~mallya c - p o w e r e 2 r a d i o s e t s ( p o s i t i o n s 3 through 4) can be switched t o either of two s p c a k c r s i n t b r r c m o t c s p e a k e r c o n s o l e ( s p e a k e r s 1 and 2). T h e audio output of position 5 i s connected d i r e c t l y t o s p e a k e r position 5 of the r e m o t e s p e a k e r c o n s o l e , -4 jack i s provided f o r e a c h r e m o t e speaker position to p e r m i t heads e t monitoring. T h e r e m o t e eonsoie c o n t r o l s the s i g c a l volume t o e a c h s p e a k e r o r head-

set,

The P e r s h i n g ground networks consist of e l e c t r i c a l cables, high p r e s s u r e air. lines, and air conditioning ducts. The c a b l e s , lines and ducts a r e constructed in such away as t o provide protection against the weather and hostile E P environments, Table 9-1i s a listing of the c a b l e s / a i r l i n e s used in a tactical s i t e layout. Ground networks interconnections a r e shown in F i g u r e s 9 - 1 and 9 - 2 , F i g u r e 9 - 1 shows the f i r i n g position f o r one m i s s i l e ; F i g u r e 9 - 2 shows the firing position for t h r e e

42W50 42W5-i fiOVv'3 60WS 60bVlO 60iVli 60LV12 60CV16 6011117 60WlR 6OWZl fiOW32 fiOM'34 6OW40 6OW43 14) SOW44 f i O W l 0 1 17) 60U'lOS 6OW105 6OW139 6OW-115 C o n d i t i o n & A i r Duct

-8 shows the exterior of the forward siorage compartment w h i l e Figure I shows the interior and the eqiliprnent it contains,

1

- 3 i s t r i b u t i o n zonsoie

2 - Cond: t i m e d - a i r d u c t 3 - Cable s t o r a g e c a b i n e t 4 - Tape s t o r a g e c a b i n e t

3 - S u l t h e a d aoor 6 - hcrsiop 7 - 3ocr h a n a i e 3 - Retdrn-air ~ r i i i e

1 - L i g h t switch

2 - Level sensor ! e v e l i n g f i x t u r e 3 - I n v e r t e r case 4 - Light fixture 5 - B r a c k e t and f a s t e n e r ( 3 ) 6 - I n d o o r r e t u r n - a i r damper c o n t r o l ( 3 ) 7 - O u t d o o r - a i r damper c o n t r o l ( 3 ) 8 - Return-air register (3) 9 - Thermostat (3) 10 - S e l e c t o r s w i t c h ( 3 )

11

-

Heater (3)

-

T e r m i n a l box

C i r c u i t breaker

12 - S t o r a g e box 13 14 15 16 17 18

- S t o r a g e compartment - Inverter fixture

- Terminal board - Zonduit 19 - i n v e r t e r

utioa console, bulkhead d o o r s , cable s t o r a g e cabinet, axi t a f o r m the a c c e s s a r e a t o the f o r w a r d s t o r a g e c o m p a r t m e n t , Bu head d o o r s contain two hen the d o o r s a r e closed, the air Inside the SCTS van is pu return-air grilles, through the g r i l l e s a d t h e i r f i l t e r s and into the r e t u r n - a i r r e g i s t e r s cf the t h r e e air c o n d i t i o n e r - h e a t e r s , w h e r e the a i r is recycled. T h e conditioned-air d u e t which extends t h r e e - f o u r t h s the length of the SCTS van, c a r r i e s conditioned air to the working a r e a of the van, T h e i n t e r i o r of the f o r w a r d s t o r a g e c o m p a r t m e n t contains equ merit associated with the a i r c o n d i t i o n e r - h e a t e r s , portable h e a t e r s , the r o t a r y i n v e r t e test fixtures, a fight, a switch, a s t o r a g e box, and a t e r m i n a l Sox, i n p u t p o w e r f o r the a i r conditionerh e a t e r s e n t e r s the forward s t o r a g e c o m p a r t m e n t t h a t e r m i n a l box, into e l e c t r i c a l nduit, and t o t h r e e c i r c u i t b r e a k e r s that supply t o the a i r c o n d i t i o n e r - h e a t e r s . s e l e c t o r switch c o n t r o l s the operation of the a i r i t i o n e r - h e a t e r s , s o that cooling o r heating can be provided, depending u on w e a t h e r conditions, T h r e e t h e r m o s t a t s r e gulate the t e m p e r a t u r e of t h e a i r and maintain the conditioned air between 7 I 5 F and 83'F, T h r e e r e t u r n - a i r r e g i s t e r s f o r the a i r c o n d i t i o n e r - h e a t e r s a r e attached t o the i n s i d e w a l l of the SCTS van, They e a c h contain an indoor r e t u r n - a i r d a m p e r c o n t r o l and o u t d o o r - a i r d a m p e r c o n t r o l , A c c e s s to the o u t s i d e - a i r d a m p e r c o n t r o l is gained by opening the r e t u r n - a i r r e g i s t e r f a s t e n e r . T h r e e 3 , -waxt portable e l e c t r i c h e a t e r s a r e s t o r e d in the forward s t o r a g e c o m p a r t m e n t .

A s t o r a g e box mounted i n the lower right-hand c o r n e r of the forward s t o r a g e c o m p a r t ment contains 14 eye-bolts that s e r v e a s tiedown r i n g s when s e c u r i n g the van f o r t r a n s portation, T h e s t o r a g e c o m p a r t m e n t contains guidance section t e s t c a b l e s , A r o t a r y inm o t o r g e n e r a t o r ) s u p p l i e s 115V, 3 o w e r to the a s s e m b l y t e s t e r f o r p u r p o s e s of UUT t e s t i n g and a l s o a s p r i m a r y power t o c e r t a i n a s s e m b l i e s of the a s s e m bly t e s t e r , A c c e s s t o the r o t a r y i n v e r t e r I s gained by removing the r o t a r y i n v e r t e r c a s e . When an i n v e r t e r is tested a s a UUT on the a s s e m b l y t e s t e r , t h e i n v e r t e r fixture s u p p o r t s and e s t a b l i s h e s a s t a b l e platfdrm f o r the i n v e r t e r . The irrterior of the f o r w a r d s t o r a g e c o m p a r t m e n t is illuminated by f l u o r e s c e n t light, T h e ;eve1 s e n s o r leveling fixt u r e , which i s used i n testing the level s e n s o r a s a U U T , i s a l s o located in the forward storage compartment,

T h e r e a r i n t e r i o r of the SCTS van contains equipment such a s a hand l a n t e r n , a d o o r post with a s s o c i a t e d h a r d w a r e , two c o v e r p l a t e s , and two equipment d o o r s with a s s o c i ated i n t e r l o c k switches. Equipment d o o r s provide a m e a n s of x c e s s f o r a l l equipment that is tested i n s i d e the SCTS van, When ihe guidance section is t a ~ e ninto the SCTS van f o r c h e c k c ~ l to r r e p a i r , the equipment d o o r s a r e opened and the doo:yost is r e m o v e d , Two i n t e r l o c k switches above the equipment d o o r s t u r n off the eight white f l u o r e s c e n t Light a s s e m b l i e s whenever the eqwipment d o o r s a r e opened, A hand l a n t e r n , which is used at night in the a s s e m b l y a r e a , is rnoanted on the s t o r a g e shelf on the r i g h t r e a r wall of the SGTS v a n ,

T h e a c / d c d i f f e r e n t i a l v o l t m e t e r ( F i g u r e 10-10) is a p r e c i s i o n voltmeter used during LUT t e s t i n g and during troubleshooting of the equipment within the SCTS. During a UUT t e s t , if the p r o g r a m m a b l e voltage c o m p a r a t o r ( P V C of the a d a p t e r cannot m e a s u r e a criticalrvoltage, the a c l d c d i f f e r e n t i a l v o l t m e t e r can be used s i n c e i t s s e n s i t i v i t y 1s g r e a t e r than that of the PVC. M e a s u r e m e n t jacks on the m a s t e r c o n t r o l panel of the a s s e m b l y t e s t e r a r e provided f o r this p u r p o s e , Convenience o u t l e t s , on the a s s e m b l y t e s t e r , supply s o u r c e power t o the t e s t equipment. An isolation t r a n s f o r m e r provides the m e a n s f o r making floating a c m e a s u r e m e n t s . T h e o s c i l l o s c o p e ( F i g u r e 10-11) displdys waveshapes of a d j u s t m e n t s m a d e during

UUT t e s t i n g and i s a l s o used during troublesiiooting of the equipment in the SCTS. It i s equipped with an attenuatoi probe that i s s t o r e d in the oscilloscope c o v e r .

RS) and t h e s e q u e n t i a l launch a d a p t e r (SLA) a r e The automatic reference s y s t e m ment f o r t h e P I a Weapon S y s t e m , Under e n g i n e e r i m p r o v e m e n t s i n ground s u p p o r t eq ing development a t t h i s writing, t h i s i m p r o v e d equipment will e l i m i n a t e s u r v e y r e q u i r e m e n t s and r e d u c e p e r s o n n e l functions d u r i n g countdowns t h u s i m p r o v i n g P f a launch reaction time. T h e ARS concept o f f e r s a n u m b e r of d i s t i n c t advantages t o t h e P I a Weapon System. It e m p l o y s a n a z i m u t h r e f e r e n c e unit (ARU) which i n t e r f a c e s e l e c t r i c a l l y with t h e PTS and optically with t h e p o r r o p r i s m on t h e ST-120 i n e r t i a l platform, T h e PTS c o n t r o l s p l a t f o r m slewing t o f o r m t h e complete s>-stem. T h e ARTS contains a n o r t h s e e k i n g g y r o which e s t a b l i s h e s t h e a z i m u t h r e f e r e n c e l i n e t r u e n o r t h ) n e c e s s a r y t o align t h e ST-120 p l a t f o r m t o t h e f i r i n g a z i m u t h and e l i m i n a t e s t h e need f o r p r e s u r v e y e d a z i m u t h lines. Also contained i n t h e ARU is a n a u t o m a t i c o p t i c a l link (AOL) which u s e s a low-level helium-neon l a s e r t o m a i n t a i n t h e optical i n t e r f a c e with t h e p o r r o p r i s m , E r r o r s i g n a i s n e c e s s a r y t o c a u s e PTS-controlled slewing of t h e p l a t f o r m a r e developed in t h e AOL, After initial m a n u a l optical acquisition of t h e p l a t f o r m by t h e AOL, t h e countdown i s a u t o m a t i c a l l y controlied by t h e PTS. Deployment of tile i i R S will e l i m i n a t e t h e need f o r t h e p r e s e n t a z i m u t h equipment laying s e t .

T h e S L A will p r o v i d e t h e P I a platoon c o m m a n d e r with a capability t o sequentially c o u n t d o w n and l a u n c h up t o t h r e e m i s s i l e s with a s i n g l e P T S and PS without r e c a b l i n g between individuai f i r i n g s ( F i g u r e I l - 1 ) . T h e SLA c o n s i s t s of t h e S L A box; c a b l e s , a i r d u c t s , and a i r h o s e s ; and a t r a n s p o r t vehicle, One p o r t i o n of t h e S L A box h o u s e s t h e s y s t e m s i g n a l i n t e r f a c e e l e c t r i c a l c o n n e c t o r s , e l e c t r i c a l switches, relab-s, and n e c e s s a r y c i r c u i t s . T h e o t h e r p a r t of the b6x h o u s e s t h e high p r e s s u r e and conditioned a i r i n t e r f a c e couplings, v a l v e s , and d u c t s a s well a s t h e s y s t e m power i n t e r f a c e c o n n e c t o r s and r e l a y s . P a n e l s on both s i d e s of t h e box c a n be r e m o v e d t o p e r f o r m m a i n t e n a n c e on the internal parts.

#

T h e ARS is co:mprised of t h e ARU, t h e P r o g r a m m e r - T e s t Station, and t h e ST-120 p l a t f o r m . Thi- .!lL%U i n t e r f a c e s ~ l e c t r i c a l l ywith t h e P T S and optically with tiie ST-129 i n e r t i a l p l a t f o r m . T h e P T S c o n t r o l s p l a t f o r m motion t o f o r m t h e c o m p l e t e s y s t e m . After s e t u p and initial m a n u a l a l i g n r n c n t c f t h e ARU, t h e s y s t e m is controlled by t h e PTS c o m p u t e r f o r fully-automatic s y s t e m o p e r a t i o n through completion of p l a t f o r m alignment.

AL -_, L

T h e ARU is composed of a r e f e r r n c c a s s e m b l y i R A j , a n e l e c t r o n i c s unit ( E U ) , a a n s l a t i n g a s s e m b l y ( T A J , a t r i p o d , a i n a ~ ~ u corrtrol a? unit, and f o u r fntra-connecting

c a b l e s ( F i g u r e 11-21. T h r e e t r a n s p o r t a t i o n containers a r e r e q u i r e d - one f o r t h e RA, .one f o r t h e T A and t r i p o d , and t h e t h i r d f o r t h e ELJ, manual c o n t r o l unit, and i n t r a connecting cables. In t h e R A a n o r t h s e e k i n g g y r o e s t a b l i s h e s geographic n o r t h (true n o r t h ) t o r e q u i r e d s y s t e m a c c u r a c y , an a u t o m a t i c o p t i c a l link containing a low-outputhhelium-neon l a s e r and d e t e c t o r s optically z c q u i r e s and t r a c k s a p o r r o p r i s m located on t h e STf o r m , and a digital e n c o d e r p r o v i d e s a b i n a r y indication t o t h e PTS c o m p u t e r cf t h e a z i m u t h angle between geographic n o r t h and tiie AOL optical a x i s , Under p r o g r a m c o n t r o l t h e PTS d r i v e s t h e o p t i c a l a x i s of t h e A O L t o w a r d the f i r i n g a z i m u t h p e r p e n d i c u l a r , causing e r r o r s i g n a l s t o be g e n e r a t e d in t h e A0L. T h e s e e r r o r s i g n a l s a r e used t o c o n t r o l the s l e w i n g of t h e i n e r t i a l p l a t f o r m towu-d t h e f i r i n g azimuth

and t o t r a n s l a t e t h e A O L a s n e c e s s a r y t o m a i n t a i n acquisition of "ce p l a t f o r m p o r r o p r i s m . Thus, t h e i n e r t i a l p l a t f o r m t r a c k s t h e A O L until it is aligned along t h e f i r i n g azimuth, w h e r e i t s o r i e n t a t i o n i s maintained a u t o m a t i c a l l y until t h e PTS inhibits f u r t h e r ST-120 p l a t f o r m slewing just p r i o r t o m i s s i l e e r e c t i o n ,

In a t y p i c a l p l a b o n deployment configuration, t h e ARU ( F i g u r e 11- 3) is positioned opposite t b c e r e c t o r - l a u n c h e r and the m i s s i l e c e n t e r l i n e . P r e c i s e e m p l a c e m e n t is achieved Sy u s i n g a tripod-locating roc! a t t a c h e d t o t h e e r e c t o r - l a u n c h e r ( a n ARSr e q u i r e d E L modification).

T h e ARU is connected b>-a s i n g l e 61-conducter c a b l e t o the PTS t h r o u g h t h e sequ-ent i a l launch a d a p t e r (SL,?) i n a t y p i c a l t h r e e - m i s s i l e launch configuration, o r it m a y be t o t h e PTS f o r a s i n g l e - m i s s i l e configuration. connected d i r e c t l y (with t h e s a m e c t h e A R U and t h e ST-120 i n e r t i a l p l a t f o r m by Initial optical i n t e r f a c e i s m a d e bet v a r y i n g t h e AOL9s heading/position t o c a u s e t h e l a s e r b e a m t r a n s m i t t e d t h r o u g h t h e t u r e t o r e f l e c t d i r e c t l y b a c k into t h e AOL t e l e s c o p e f r o m t h e p o r r o p r i s m p l a t f o r m . T h e low-level l a s e r light r e t u r n e d through t h e 30): AOL t e l c s c o p e i s c e n t e r e d on t h e t e l e s c o p e r e t i c l e when p r o p e r alignment i s a c h i w c d , A f k r initial alignment, both t h e ARU and t h e i n e r t i a l p l a t f o r m a r e automatically c o n t r o l l e d by t h e PTS d u r i n g a z i m u t h laying. T h e m i s s i l e c e n t e r l i n e m u s t be o r i e n t e d within 7 112 d e g r e e s of t h e f i r i n g a z i m u t h d u r i n g horizontal laying b e c a u s e of t h e p h y s i c a l l i m i t a t i o n on t h e angle through which t ! ~ ei n e r t i a l p l a t f o r m m a y be slewed. When t h e ARU has been e m p l a c e d and leveled t o a n a c c u r a c y of o p t i c a l acquisition of t h e p l a t f o r m p o r r o p r i s m begins ( r e f e r t o F i g to t h e application of ARU power, t h e ARU o p e r a t o r manually r o t a t e s t h e AOL and t r a n s l a t e s t h e r e f e r e n c e a s s e m b l y t o a c h i e v e a p p r o x i m a t e o p t i c a l alignment of "ce

At the time of a plication of ARU power, the AOL is enabled, turning on the helium-neon laser, and automatic AOL leveling begins. After AOL leveling, the ARU operator, using the remote control unit, completes the optical acquisition of the porro prism b:.- rotating tkle -4Oiand translating the RA as

4 O L on the ezged ST-12 porro prism.

necessari-to center the low-level laser light returned from the porro prisni through the AOL telescope on the teles,coperrticie, .Lit the beginning of the coarse nortii deterrr~inationinterirall the countdoivn program disables the manual control capabilitj-,permitti~gno further operator movement of the AOL and RA unless a recycle m o d e is initiated, All remaining ,4125 functions a r e automatic.

RRU

PZ ROTAi!Ol

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The. ri>f- t h e PTS, t h e load r e s e t command is given t o t h e cont r o l logic. At e a c h clock p u l s e t h e m u l t i p l e x e r p r o v i d e s a n output based on t h e condit i o n of t h e a p p r o p r i a t e r e l a y . T h e word is clocked out s e r i a l l y t o t h e P T S and is used f o r modification of the f i r i n g a z i m u t h p e r p r n d i c u l a r by tile PTS.

T h e e l e c t r o n i c s unit (E"J), F i g u r e 11-8, is t h e s o l e i n t e r f a c e point between t h e A130 and t h e PTS. During s>-stcm o p e r a t i o n s it i s placed upon t h e ground a d j a c c n t t o the ARU, f o r interconnection betxveen t h e ARU and t h e SLA/PTS. In t h e S L 4 configuration e a c h of t h r e e A R U 1 s , v i a t h e i r r e s p e c t i v e E U Ps, m a y be connected 57; a s i n g l e 130-foot cable t o t h e SLA, T h e SLA, i n t u r n , is connected to t h e I T S by one 30-foot cable. In a s i n g l e - m i s s i l e launch s i t e configuration, o r in t h e e v e & of SLA malfunction, t h e E U m a y be connected d i r e c t l y t o t h e P T S with t h e 130-foot cable.

VOTES:

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T h e s y s t e m corn-pocents t e s t station (SCTS) is used in p e r f o r m i n g r e a r a r e a m a i n tenance of the P l a s y s t e m . A'is a housed mobile c e n t e r , the SCTS utilizes a c o m p u t e r and tape p r o g r a m s f o r testing m i s s i l e s e c t i o n s , together with a s s e m b l i e s , c a r d s , r e l a y s , and m o d u l e s f r o m the guided m i s s i l e and a s s o c i a t e d ground support equipment. Diagnostic tape p r o g r a m s a r e a l s o provided f o r verification and troubleshooting of m a j o r SCTS a s s e m b l i e s . T h e SCTS contains a dismounted P T S and h a s facilities w h e r e by one m i s s i l e guidance section can be tested and another r e p a i r e d simultaneously under controlled t e m p e r a t u r e conditions. P o w e r f o r the SCTS o r i g i n a t e s f r o m the power s t a tion equivalent ( P S E ) .

T h e SCTS equipment i s housed in a modified s e m i t r a i l e r van M373A2 The significant e x t e r i o r f e a t u r e s a r e d e s c r i b e d below. p e r s o n n e l d o o r , located on the right s i d e , is the m'ain a c c e s s to the i n t e r i o r of the SCTS van. T h r e e a i r c o n d i t i o n e r - h e a t e r s mounted on the front of the SCTS van e s t a b l i s h the i n t e r n a l e n v i r o n m e n t a l conditions. A t e m p e r a t u r e of 77' rt F ° F is n e c e s s a r y f o r optimum operation of the SCTS equipment within the SCTS va.11. E a c h a i r conditioner-heater i s shock mounted and attached t o the front wall of the SCTS van by c o r r u g a t e d neoprene bellows, t o e n s u r e a minimum amount of vibration and shock during t r a v e l . Canvas c o v e r s a r e lowered and s e c u r e d when the a i r c o n d i t i o n e r - h e a t e r s a r e not in use. T h r e e connector panels, located d i r e c t l y below e a c h air c o n d i t i o n e r - h e a t e r , a r e attached to the front wall of the SCTS van. Input power is supplied to the a i r conditioner heater controls.

- Personnel door - Identification plate

1 1.1 2 3 4

-

7

-

5 6 8 9 -

20 11 12 -

A i r conditioner-heater p r o t e c t i v e cover ( 3 ) A i r conditioner-heater Power c a b l e ( 3 ) A i r conditioner-heater connector panel (3) A i r conditioner-heater A i r condi t i o n e r - h e a t e r A i r c o n d i t i o n e r - h e a t e r m o u n t i n g frame Access l a d d e r Sand pad ( 2 ) Landing g e a r ( 2 ) Personnel ladder (2)

13 14 15 16 17 18 18.1 19 20 21 22 23 24

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-

-

-

-

M o d i f i c a t i o n mounting panel SCTS c a b l e e n t r y p a n e l p r o t e c t i v e c o v e r Dooroost ~ ~ u i b m e en nt t r a n c e d o o r ( 2 ) A i r vent f i l t e r Humidity i n d i c a t o r Evebolt (3) ieveling'jack (2) T a r p a u l i n s t o r a g e compartment PTS c a b l e e n t r y p a n e l p r o t e c t i v e c o v e r PTS power c a b l e e n t r y p a n e l S a f e t y 1anya.rd SCTS m a i n c a b l e e n t r y p a n e l

T h e SCTS n ~ a i ncable e n t r y panel c o n s i s t s of four c a b l e entr.y panels: t a c t i c a l cable e n t r y , t e s t cable e n t r y , SCTS power e n t r y , and communications c a b l e e n t r y . T h e t a c t i c a l and t e s t cable e n t r y panels connect t e s t and r e s p o n s e s i g n a l s between the SCTS and the m i s s i l e s e c t i o n s when the m i s s i l e s e c t i o n s a r e installed in c o n t a i n e r s , T h e SCTS power e n t r y panel connects power t o all a s s e m b l i e s in the SCTS, except the PTS a s s e m b l i e s . T h e c o m m u n i c a t i o n s cable e n t r y panel contains the following: two phone jacks that provide communication between p e r s o n n e l inside and outside the van; one phone jack and switch f o r u s e with the i n s t r u m e n t a t i o n m o n i t o r ; SCTS grounding t e r m i n a l s and a pneumatic quick-disconnect c o n n e c t o r . H i g h - p r e s s u r e a i r i s supplied to the SCTS through the pneumatic quick-disconnect connector.

; i . i a c c e s s l a d d e r is used to gain a c c e s s to the top of the SCTS van and to gain a c c e s s t o the a i r c o n d i t i o n e r - h e a t e r s for maintenance.

T h e sand pads a r e used to e m p l a c e the SCTS van and a r e placed under the landing g e a r t o s t a b i l i z e the van on soft t e r r a i n , The larding g e a r s a r e ioivered when emplacing the SCTS van 2nd a r e adjusted along with tile leveling jacks t o level the v a n . Two p e r s o n n e l l a d d e r s a r e used t o gain a c c e s s t o the i n t e r i o r of the SCTS v a through e i t h e r the p e r s o n n e l d o o r o r the equipment d o o r s . -4 humidity i n d i c a t o r displays the r e l a t i v e humidity of the SCTS van through an o b s e r v a t i o n port. ?%G

leveling jacks a r e used f o r leveling the SCTS van at an attitude of not m o r e than

G d e g r e e s (106 m i l s ) f r o m the horizontal position. T h e y a r e lowered during van e rnent i n the field maintenance a r e a . The SCTS van m u s t be guidance seciion testing f o r optimum checkout of tile ST-12

T h e PTS power cable en-try pane? connects power f r o m the power station equivalent to t!le P T S a s s e m b l i e s of the SCTS v a n .

T h e m a j o r a s s e m b l i e s of the SCTS a r e divided into two c a t e g o r i e s : P T S a s s e m b l i e s and SCTS a s s e m b l i e s ( F i g u r e 10-2)'

T h e ma,ior P T S a s s e m b l i e s a r e the adapter-, card and m-odule t e s t s e t , power. d i s t r i bution cabinet, console, c o m p u t e r , utility c i r c u i t b r e a k e r panel a s s e m b l y , and s i g n a l distribution box. The a d a p t e r , console and c o m p u t e r a r e d i s c u s s e d in C h a p t e r F o u r , T!ie m a j o r PTS a s s e m b l i e s a r e used when testing m i s s i l e s e c t i o n s , PTS c i r c u i t c a r d s , and P'rS modules. The m a j o r P T S assemblies of the SCTS van a r e d e s c r i b e d below. T h e c a r d and module t e s t s e t functioinally t e s t s the printed c i r c u i t c a r d s , m o d u l e s , and c i r c u i t network modules used i n the a d a p t e r and tile c o m p u t e r . It a l s o t e s t s i t s own c a r d s and modules. T h e power distribution cabinet contains the c.ircuits that c o n t r o l the distribution of p r i m a r y power t o the console, a d a p t e r , c o m p u t e r , s i g n a l distribution box, and c a r d and module t e s t s e t . An i n t e r l o c k switch actuated by the cabinet d o o r r e m o v e s p r i m a r y power f r o m a l l the P T S a s s e m b l i e s whenever the door- i s opened. T h e utility c i r c u i t b r e a k e r panel a s s e m b l y c o n t r o l s power to the console and adapter blowers. T h e signal distribution box i s the distribution c e n t e r f o r the s i g n a l s e n t e r i n g and leaving the SCTS, which a r e gener,ated ciuring m i s s i l e section in-container t e s t s . It is a l s o 3 convenient s o u r c e of eleetricril t e s t points. Tile t e s t points a r e a c c e s s i b l e througih a hinged maintenance a c c e s s panel. An i n t e r l o c k switch activated by the a c c e s s panel r e m o v e s power f r o m a l l PTS a s s e m b l i e s whenever the panel i s opened.

PiGHT

TAPE STORAGE CABINET b N C 7 4 3 P k I A B L E

SIDE

AC,DC DICFFRFNiIAL VCLTMEIER

AIR CO?J3'TiONiNG UNIT 3! 20 000 KTU EACH

LEFT SIDE

C:RCUII BREAKER AREA

POWER DiSTRtBUilCN

7

C

CARD AND r/i3 P ~ ~ ~ M TES A T ~ c

ZE!AY PANi! AND R F I FlilER i S 5 E ~ a i Y

S c o n s o l e s and a s s e m b l i e s a r e the d i s t r i b u t i o n cor%ole, p n e - ~ ~ a t i c t e s t c o n s o l e , and a s s e m b l y t e s t e r . Significant a s s e m b l i e s of the SCTS :iiso c o n s i s t of the c a b l e and xape s;o:-:ige.cabir!eis, o s c i i l o s c o p e , ant! ac/cic d i f f e r e r t i a l vojlrnete:,. T h e m a j o r SCTS :tsserni'?fes anu other- sigi~ificaiira s s e m b l i e s of ;he SCrS van a r e d s s c r i b e d below. The disrribution console d i s t i . i b u t e s p r i m a r y porzier. to all SCTS rnajor c o n s o l e s aiid - a s s ~ r n . b ! i e s ~ ~ w i 5ti16 ! ~ hSCTS 17a!i, 111 addition, i t r o u t e s t e s t s i g n a l s to and f r o m t h e l n i s s i i e s e c t i o n s u n d e. r. t e s t . T h e d i s t r i b u t i o n console contains 25 patchboard recepttzcle, ::, circu'it b r e a k e r panel, a r e l a y panel, r a d i o frequency i n t e r f e r e n c e ( R F I fflters, apd s t o r a g e a r e a f o r technics! m a n u a k .

T h e pneumatic t e s t c o n s o l e i s used t o t e s t and fault i s o l a t e the m i s s i l e guidance s e c o n e n t s and t o check guidance s e c t i o n c o m p a r t m e n t

assembly tester uses ograrnrned t a p e s t l i e s b y applying stirnu to the unit under t A work-table i s provided on the a s s e m b

m i s s i l e , P T S , EL, and SCTS and routing r e s p o n s e s to the o s u p p o r t the UUT,

T h e r o t a r y i n v e r t e r s u p p l i e s 115 volt, 3-pnase, 401)Hz power to the a s s e m b l y t e s t e r and t o the applicable U U T ' s on the a s s e m b l y t e s t e r . T h e air c o n d i t i o n e r - h e a t e r c o n t r o l panel i s used to s e t the a i r t e m p e r a t u r e output of t h e zir c o n d i t i o n e r - h e a t e r s , which a r e r a t e d ax 20,00 Btu e a c h f o r cooling and 1 2 , 0 0 0 Btu e a c h f o r heating, T h e a i r c o n d i t i o n e r - h e a t e r s s u ly e i t h e r cool o r w a r m a i r , d e pending upon the outside tern T h e ULJrI" c a b l e s and p r o g r a m m e d t a p e s used during a s s e m b l y t e s t e r checkout of a TiUT a r e s t o r e d in the s t o r a g e cabiriets. A worktable i s mounted on top of the tape s t o r age cabinet, When not in u s e , the o s c i l l o s c o p e i s s t o r e d on top of the worktable. T h e o s c i i i o s c o p e and ac!dc differentia! voltmeter a r e s u p p l e m e n t a l pieces of t e s t equipment used during U U T t e s t i n g when a d j u s t m e n t s and c r i t i c a l voltage rrieasurernents a r e r e q u i r e d . T h e y a r e a l s o used f o r fault isolating and troubleshooting the a s s e m b l i e s within the SCTS.

A Tile a s s e m b l y tester. ( F i g u r e 10-3) p r o v i d e s the n e c e s s a r y s t i m u l i , loads, and s w i t c h ing o p e r a t i o n s for. functional testing of c e r t a i n a s s e m b l i e s , printed c;--e A L L u ict a r d s , and r e l a y s of the ? l a s - s t e r n . P r o g r a m m e d by row s e l e c t and column d ~ i t as i g n a l s fr,orn the a d a p t e r , the c ~ s s e m b i yt e s t e r p e r f o r m s e s s e n t i a l l y t h r e e fnnctions ihrough LI r e l a y r n 3 t r . i ~ : g e n e r a t i o n 3 f xhe r e q u i r e d s t i m u l i and l o a d s , routing of the s t i m u l i and loads to n iiii'r, and routing of CUT r e s p o n s e s for m e a s u r e m e n t by the a d a p t e r . Tile zssernbly t e s t e r b a s i c f r a m e c o n s i s t s of welded s t r u c t u r a ! alumirium ext:usions c o v e r e d with outside s k i n s of aluminum s h e e t . .A s t e p in the f r a m e and a hinged w o r k table f o r m a workbench s u r f a c e on which LTUT's a r e placed for testing. T h e rna