The Pershing Guided Missile System

7/21/2019 The Pershing Guided Missile System

1/47

THE

PERSHI~

.

GUI E

I

,

MISSILE

M

U S ARMY

ARTILLERY

AND

MISSILE

SCHOOL

Guided

Missile epartment

Fort Sill, Oklahoma


2/47


3/47

U S

RMY

RTILLERY

ND

MISSILE

SCHOOL

Guided Missile Department

ort

Sill Oklahoma

Reference Note

THE

PERSHING GUIDE];) MISSILE SYSTEM

PART ONE

INTRODUCTION

l . REFERENCES

*GM 3000

Feb 65

TM

5 -

1450-202-12,

TM 9 -

1400

-

375 -1 0/1, TM 9-1400-375-10/2

/

l ,

TM 9 -1 400-375 -1 0/2/2,

TM

9

-11

00 -

375 -12.,

TM 9 - 1410-375-12,

TM

9 -

1430-376-14

, TM

11- 5820-469

- 10 , TM 9- 1450 - 375 - 14, TM 9 - 8140 - 375-

24, TOE 6-6

15T, TOE 6 - 6 1

6T

,

TOE

6 -

617T

and TOE 6 - 6 19T.

2. INTRODUCTION

The Persh ing is

the U.

S . Army's longest range field a r t i l l

ery

guided

m

iss i le .

In

1958, after the deve

lop

ment of the f i rs t generat ion of

m i s

siles ,

which

i

ncluded

the

Redstone

miss i le

system

,

the Army

deter

mined

that

sufficient advances had been made

in

missi le technology to

warran t

the development

of a completely new

miss i

l e sys tem to replace

the Redstone. This

new system ,

named in honor of

General

John

J .

Persh ing and developed with the M ar t in Company as

the

.pr ime c

ontractor,

uti l izes

many state of the

a

r t

advances

which

provide

great ly

increased

mobility

and ran ge and al low a significant reduction in size, weight and

reaction

t ime

.

Other outstanding improvements include

ground

support

equipment designed

fo

r

maximum

t ac tic a l and s trategic mobility, elec

t roni

c

computation of

f ir ing

data

,

and automatic tes t

and

checkout equip

ment.

The

Persh ing

sys tem also

includes

a

sp

ecially

designed

commun

i -

ca

tion set wh ich is unique within

the

a r

t i l l

ery

and al lows

extremely

re l i

able

communicat ions

over

great dis tances

(99.

9 pe r

cent

r

el

i

abili ty at

160 kilomete r s) . The

Pe r

shing is normal ly employed in gener a l support

of a

field Army.

3 . OBJECTIVE

The obje

c

t ive of this referen

c e

note is

t o

provide students

a t t

he

U.

S,

Army Arti l lery and Mi ssi le School with

an

unclassif ied

re feren

ce which

outlines the sal ient features of the

Pe r

s

hi

ng

m

is

s i le system.

Since

the

Persh ing is

re l

a

t ively

ne

w, this mater ia l

is base d on

doctrine,

concepts ,

,~supersedes

GM 3000

, Apr

64

.


4/47

and equipment

configuration

which

are subject to

change

.

The Pe

r

shing

is a nuclear del ivery

system;

therefore , in the discussion of tact ical

concepts

,

t

is

assumed

that

the field

a rmy is

deployed for

nuclear

com

bat .

PAR

T

TWO

EXPLANATION

4 .

CHARACTERISTICS

a .

The Pershing

field ar t i l le ry bal l is t ic

missi le

has the following

t

ec

h

nical

cha r t er is t ics :

1)

Length

- - 34 . 6

feet 10

.

38

meters .

2) Diamete r

- -

40 inches 1. 02 meters .

\

'

3)

Weight - - 10

1

275

pounds

.

) .

r ~

4) Range - - 185 - 740 ki lomete r

s .

e~ .

. .u;.

S f f itM )

- -

r I

: ~

5)

Propuls

i on - - so l id p r

opellan

t, two - stage.

6) G ui danc e - -

ine

r t i a

l .

7)

Warhead

- - n u

c lear

.

b . Tactical cha r ac ter is t ics

of the Pershing

a re

as follows

:

1)

The sys tem

is

mounted on t racked

vehicles .

2)

All

elements are

t ranspor table

by phase

II a ircraf t

.

3) All elements necessary for

firing

a re

t ransportable

by

hel i -

copter

.

4)

The guidance sys tem and fuzing sys tem

a re immune

to

e l

ectronic

countermeasures .

5)

The

communicat ion sys t em

allows

separat ion

up

to 160 kilo-

m

et

e r s be t ween t he

bat tery

and the battal ion headquar ters .

5 . GROUND

SUPPORT EQUIPMENT

The

Pershing sys tem is

designed

to

achieve minimum

react ion t ime

wi th

maximum

mobili ty

and rel iabil i ty

.

Mobility

is provided

the firing

bat tery by mounting al l Pershing-pecul iar equipment, including commu

n i cat i on

equ

ipment , on four t racked vehicles , designated the XM474E2

2


5/47

missi le equipment ca r r i e r . The XM474E2

is

a modification

of

the Mll3

armored

personnel

ca r r i e r and is specif ical ly designed to t ranspor t

the

Pershing

system.

Mounting

kits

permi t in terchange of any of

the

four

Pershing

loads

from vehicle to vehicle without modification of the basic

vehicle

s t ructure

. The XM474E2

is l ightweight

and una rmored . t is

capable

of sp

eeds

up to 35 miles

per hour and has a cruising

range

of 3 20

ki lometers .

t

can

t ravel

i n swamps

and

s t reams to a depth of l . 3

meters

and cl imb

60

perc ent inclines.

t

is powered by a 215 - horsepower ,

V

engine .

a . Warhead Vehicle . One XM474E2 ca r r i e s the warhead sect ion

fig 1 ,

two ches ts containing

the azimuth laying equipment , and a

con

tainer

ca rryin g the missi le a ir

fins

. This

vehicle

also

mounts

a

collapsi

ble -davit

assembly

which is used to

mate the

wa r head section to

the

m is

sil e a t the firing

position

.

Figure

1. Warhead vehicle .

b. The Erector Launcher .

1) The erec tor

launcher

fig

2 i s normal ly t ranspor ted on an

XM474E2 t racked vehicle; however,

i t

may be t ranspor ted

by

hel icopter .

The

erec t

o r

-

launcher

performs the

following

functions:

3


6/47

(~) Serves as a

platfo

r m for assembly

of

the missi le

body

sections.

(~)

Supports

the assembled

miss i le ,

les s w ar

he ad sec

ti

on

,

during t ransi t

on

the XM4

7

4E2 car r i e r

.

(~) Provid e s a plat form fo r warhead

m a

t ing to the m i ss i le

body section, for

horizont a l

t es t and checkout

of the

missi le , and for

azimuth l aying ope.r

ations

while

th

e

miss i le is horizontal .

t,,

....

(~)

Erec t s the missi le

and, if

ne

cessa r

y,

recaptures

i t and

r e tu rns i t to a horizontal

posit ion.

(~) Rotates

the miss i le to the he

ad

in

g of

the

gui

dance plat form

af

te r

erect ion.

(i,)

Delivers electr ical

power

,

conditioned

a i r , high -

pressu re

a i r ,

tes t

a n d chec k

ou

t s~gnals, and control

signals

to the

m issi l e

through

the cabl e mast .

, ,

V

;

f

e L

.g) Provides a level , s table pla t form for firing the miss i le . < }

0

JY

1

,L

p l.. '

N IC ~~

yl

(2) The erector - launcher has fou

r

major

assembl ies : the t r ans -

por te

r ,

the erec

tor , the launcher

, and

the

cable

m as

t .

(~)

Transpor ter .

The t ranspor ter i s a fou r - w

he

eled , t r ai le r

typ

e vehicle that

can be

towed

or can be

ca

r r i ed

on the

XM474E2 car r i e r .

The

e r

ector and

the launcher a r e

mo u

nted

on

t

he

t ransporter . The t r a n

spo r ter

furnishes

elect r ica l and

m echanical

control for erector and

~)

launcher

functi ons . During the

fi r in

g se quence , signa ls

f rom

the

p ro g r ammer t es t

station

cont r

ol

the funct i ons {

the

e r ec tor -

launcher .

Hand cranks can be used to

manual ly oper a t e equipment

on

the t r anspo r t e r when

power

is

not

avai

l a

ble

or

for

m ai

nt

enance

purposes

.

Erector . The

erector supports

the

miss i le

du

r in

g

assem

bl y

operat ions, during

t ra~e l

whi

le assembl ed (less th e

warhead section),

during

t es t and

checkout in

the hor izon -

. t a l position, and ur

ing

erec

t i

on o r lowering . Ramps

along th

e

s ides

of th e erec

tor boom

suppo

r t

the

body sec

t ion t rucks and

provide

a wo r king platform for personnel

during assembly operations.

The e re

cto r is

raised

1

or )-

l owered by actuators mounted

on

the t r ansporte r .

(~)

Launcher .

After

the

miss i l e

is

e r ected

and the

erecto r

is

low

e re d , the launcher supports the miss i le and ro tates

i t to t

he f i r ing azimut

h . A

blast deflecto

r under t

he

l a uncher deflects the rp i ss i le exhaust away f rom the

4

>

-

~

>

.

t > '


7/47

erector - launcher . The

launcher is leveled

by automat ical ly

operated jacks;

however, the

launcher can

also be le

veled

manually

when

necessa ry

.

.~)

Cable

mast .

With

the

exception

of the cable connected to

the

missi le

tai l

plug,

a

l l

connect

io

ns

to the

miss i le

during

;i :; .

the

~ref ir ing

sequence

a re

made through the cable mast .

Cables conduct

guidance and burs t select ion signals to the

missi le ,

t es t and

checkout

signals to and

from

the miss i le

and elect r ica l

power

to the

missi le unti l i ts

own power

system is

energized.

Conditioned a i r and

high-pressure

ai r

a re

routed through ai r

hoses .

The

cable

mast i s

automatica

lly

separated f rom

the miss i le an instant

before

n

1

) l..,

t1..

.1 .c.. ignition of the f i rs t -s tage motor

section.

- /> ~p" c .

t

1

TI

D

r

I I , f

f:

l .

Figure

2 . Erec to r - launchE t

(mounted on XM474E2).

~- Progra m m e r -Te s t Station

and

Power Station Vehicle

. A th i rd

XM474E2 (fig 3) ca r r i e s the programmer t es t s tation and power

station

.

1) Power stat ion . The power

station

(PS)

produces

both elect r ical

and pneumatic

outputs for

the Persh ing

system.

The e l

ectr i

ca l

outputs

a re DC

and

AC

power.

The pneumat ic

outputs

a re

high

pressu re a

i r

and conditioned a ir .

The

power outputs

a re used

a t the f i r ing posi t ion to opera te the m i

ss i le

and i ts ground sup

port equipment and a t the

battery

assembly a

rea

to tes t the

5


8/47

.

.

,-

,,

.

,

t l

f ti

f .,.

F

igur

e 3 .

P r o g r amme

r - test

station and pow

e r s t a t

ion vehicle.

2)

sys tem equipment . The

power

s tat ion

ca

n operat e a pproxi

mately 2 hours with a full t a nk of fuel.

Prog

r

amme

r

t es t

station. The

P e

rshing s

fas t react ion

t im e

is made possible to

a g r eat extent by

the

automat i c features

in

c

orpora ted in

the

programmer t es t station

(PTS).

The

PTS

contains c omplete ly automat ic, t ransistor ized , se lf-ve r

ify

ing

equipment

with a m alfunction

detect

i

on

a n d

isolat ion

capab

i l i t

y .

> h e pu

LP

ose of the

PTS is

to det

ermine

whether the

miss ile is

flightworth y , to compte the

firing data,

and t o

inser t

the re

quired

presets

into the

miss

i le and energize i t for

flight.

Withi n the P'IS a re

three

func t iona l groups

of

equipment -

- t

he

f i re data c

omputer ,

the

pe

r

~er l equipment

,

and the

t es t

and

che

d

out equipment

.

The

oper

a

to r

s

conso

l e

provides

count

down

c

ontro

l a nd monitoring as

we l l as

c

ontrol

and

moni tor in

g

of

the f i re

da ta c o m puter .

6


9/47

-

1-=> ' ~ - L

~)

Fi re data

computer

.

The f i re data

computer

is

a general

purpose ,

digital computer

. I ts purpose

is to solve the

Persh ing

gunnery

problem . Using the desi r ed height of

burs t and

the ant ic ipated weather conditions at

the

ta

r get

area , the computer solves the gunnery problem

in

about 40

seconds

.

This

gunnery data,

which

will

cause

the

wa

r

head

to detonate

a t

the t a rge t

,

is produced in the

form

of t es t

and prese t

val

ues which

a re u&ed

to

tes t

the guidance

and

control

sect ions

; to select

slant

al t i tude

and

pitch

pro

-

g r ams;

to

prese t velocity,

disp

l acement ,

and

t ime into

the

guidance computer ;

and

to

prese t

the warhead

. These

values

a r e

s tored

in t

he computer ' s

memory and a re

made

avai lable

to

the

peripheral

equipment

when

cal led

for .

Al though the f i re data computer is

normal ly used

to solve

the

gunnery

problem ,

i t can

be programmed to isolate

malfunct ions to

a

computer

chass is

.

The PTS

opera tor

can

then replace

the

maliunctioning chass is

and

con -

tinue

operat ions . f a replacement chassis

is

not avai l -

able , a f i re data computer in another bat tery

can be used

to solve

the

gunnery problem for the tes t and prese t

values

.

These values can

the

be manually

entered

into

the

programmer tes t stat ion

by

use

of the periphera l

equipment .

h / . , +;P

Periphera l

equipment

.

The purpose

of

the

peripheral

eg

ui

p E1

e~

is

to

prese t

and

test

the

missi le

guidance com

-

ponents

and to d ~ mine

whether

they ~ re fli gh wo r y .

The

pe r iphe

r

al

c ~

ui

pment

will

then prese t the

miss i le

guida

_ l

e

components

and warhead for f ls

ht

.

The per i

-

phera l eci_u

iil.m,

ent

functions as the electr ical

l ink

between

the f i re data computer and

the

miss i le

. The so l

ution

t o

t

he

gunne r y p r

oblem that

i s

s tored in computer

memory

contains

, i n binary

form,

the

va

r iable data

used

t o prese t

guidance components for t es t

and flight

. During the count -

down

, the

per iphe

r

al equipment

will

automatical ly

extract

th

i s

info

r m a t

ion

f rom

the

computer

,

conver t

i t

to

analog

info

r

mation, and inser t i t

into

the miss i le

. In

the event

of

computer

fai lure

i t is

possible to

use an operable com

-

puter in

another

fir ing battery to solve

the gunnery

prob -

lem . The solutions to the

problem

a re

then

recorded on

a

f i re

mission

data

sheet which is given to the PTS

operator whose

computer is malfunctioning

.

The per i

-

phera l equipment then provides the

opera tor with

the

manual capabi l ity

of

preset t ing and test ing the miss i le

guidance components

.

7


10/47

J

' ,.

\

t

:

(~) Test

and checkout equipment. The

t es t

and checkout

(T CO) equipment is located inside the

PTS

to

the

r i

ght

of the contro l console . I ts purpose is to sequentia l ly

energize, test , and launch the

miss i le . It also

displays

the

status

of the

countdown .

When

tes ts a re completed

s a

t isfactori ly,

the

T CO

equipment

will

indicate

that

con

t ro l may be t rans fe r red to the remote firing panel

,

which

may

be emplaced up to

152

m et e rs

f rom the

base

of the

l aunche r .

When the

command

to f i re

is given, the T C O

equipment

ini t iates and controls the automatic l aunch

sequence through missi le l

iftoff.

Should a faulty compo

nent be

detected

or the resul ts of

a

t es t

become

invalid

pr ior to th

e

command to

fire, the

T CO stops th

e

count

down

, initiates a

malfunction search

to d

etec

t the fault, and,

in most cases , ini t ia t es a power

shutdown

.

Malfunction

isolat ion

equipment

is

located

in the

T CO

assemblies .

The malfunction equ

i

pment will check

various

points for

the

presence of 28 volts .

The

absence of 28 volts a t

any

monitor point

will

cause a malfunction

indication

to be

displayed,

indicating

that

the

fault

l ies within the miss i le

o r the

ground

support equipm ent, and will fur ther

isolate

the

t rouble to a par t icular

component.

(~) Radio Termina l

Set AN/TRC

- 80 . A

fourth XM474E2

car r i es

the radio te rminal set which houses the AN/TRC -

80

t ropospheric

scat ter

radio

(fig

4)

.

The unit

is

com

pletely self -contai

ned and includes

a 10-kw

gene

ra tor

lo

cated

in a

compar tment a t the

rea r

of

the

hutment

.

The

pack mounts a 2 . 4 -

meter

inflatab le, parabolic dish

antenna . The AN/TRC-80 has the capabil i ty for

one

duplex

voice

channel and one half-duplex teletype channel

for

point

-

to

-

poin

t

communications over

a

range

o f

160 ki lo

meters .

The radio

te rmin a l set is normal ly

emplaced

a t

some dis tance f rom

the

tact ical

f ir ing

position - -up to a

maximum of 3.

2 ki lometers . A

th ree man

crew

ca

n

put

the

set

into

operation

within

10

minutes af

te r

.

moving into

position.

Tropospheric scatter radio uses a technique

whereby

SHF radio waves a re scat tered in th e

t roposphere

and

a re

th en picked up by

a

receiving station

using a

direct ional

antenna pointed

a t that par t icu lar spot in the

sky. The t roposcat ter process is

very

directional and,

as

such, p

ro vides

a high

degree of immuni ty

to jamming

and

interception .

6. MISSILE

PROPULSION AND STRUCTURE

The Pershing miss i le is designed to lift

the warhead

from the surface

of

the earth , t ranspor t the

warhead

to

a

point

in space,

and

impart

suf

f icient velocity to

the

warhead a t a des i red angle

and

direct ion so that

the

warhead

, when re leased, w

i l l follow

a

t rue ball ist ic t ra jec tory to

a

8


11/47

Figure

4 .

Rad io t e rmin

a l

set AN/T

R C- 80

.

se

l ected t arge t .

To

do

this, the P e r s

hing

miss i le

uses

two solid

propel lant rocket mot o rs and

a

guidance and control sec t ion. One m otor

provides the

thrust

fo

r

each s tage

.

The

warhead i s

the fourth sec t ion

of the miss i le fi g 5) . The fou r

sect ions

a re secured w

i th

th ree

spl ice

bands

.

Each

spl ice

band has four segments

A ,

fig 5)

. The

f i r s t

stage

and the warhead spl ice band

segments

a re fastened with two ex

plosive bolts to facil i tate inflight separat ion

.

a .

Const

r

uction

.

The f i r s t

-

stage

sect ion

houses the rocket moto

r

whGh provides

the

ini t ia l th r u

s t fo

r m o r e

than

one - ha l f of

the

t o t

al ac

celera t ion

t ime

B ,

fig

5) .

The rocket motor cons is t s of

a

combus

t ion

chambe

r

part ia l ly

f i l led

with

a

propel lant

, a

throat

with a

diam

e ter so

designed

tha t i t will

main ta in

th e de s i r ed

combust ion

chamber p r essure ,

and

a

nozzle desig

n

ed

to accele r

ate

the

pres su r ized gas

to am

bien t pres

sure a t the

exit

end of the nozzle. At the forward

end

of the combust ion

chambe

r

is

a p y r ogen

unit igni ter . The pyrogen uni t is

used

to ignite

the so

l

id propel lant within the rocket m o

t o r .

9


12/47

, SPLICE

IIAIIID

J

A

tL..

....

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...

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PROPELLANT

,: J P I

p

.,..J,.,.

d

Figure 5 . Mi ss i l e

st

r uctur es .

10


13/47

b. Oper ation . The functioning

of

the rocket

motor is

based on

Ne;-ton s third law of

motion :

For

e

ach

action

there is an equal

and op

posite r eaction . ~hen the propellant

of

the rocket motor is ignited, the

forward

thrus t

F) is

equal to

the

mass

M)

of the

gas

that is exhaused,

multiplied by the

accelerat ion

A)

of

the gas through the nozzle

of

the

rocket motor

F MA). The design

of

the nozzle and throat provide for

the maximum

accelerat ion

possible .

Constant

chamber pressure , and

therefore constant thrust ,

is

maintained

by

design

of

the

propel lant con

f iguration and

throat and nozzle

opening

.

c , Control

Surfaces.

Another integral par t of the

motor

section

is

three

sets of air fins and je t vanes displaced 120 apart around the aft

end

of

each

motor . Each

set

of

fins and vanes have a common mechani

cal

connection

to an electr ical-mechanical

hydraulic actuator. The a ir

fins

provide

a

control surface

when

the

missi le

has

sufficient

velocity

and is passing

through

re la t ively

dense

atmosphere . The

je t vanes a re

mounted so

that

they

extend

into

the rocket mo tor s exhaust gas . The

j e t vanes

ass i s t

the

ai r

fins

by

providing an additional control surface

to

deflect

the

high

velocity exhaust gas when the missi le has l ow velocity

as at liftoff. The

second

- stage

rocket

motor ( C , fig 5)

util izes

je t

vanes to provide control of the missi le

when

the

missi le is

passing

through

rari f ied o r low density a tmosphere . The fins

of

the second st

age

have a much l a rge r surface

area

than do those of

the f irs t

stage; this

helps compensate for the lower a ir

density.

7)

d, Exploding

Bridgewire.

Within each ini t ia tor

for the rocket motor

pyr7igen unit, the th rus t terminat ion por ts , and the miss i le

splice

bands

is

an exploding

bridgewire EBW)

device

. An

EBW device conta

ins a

piece of platinum wire and a pentaephyri te trani t ra te

PETN) charge

, a

standard ordnance explosive. When 2,

500 volts of

direct

current a re

applied ac ross the platinum wire , the wire vaporizes and the energy is

used to

set off the PETN charge. The PETN

charge,

in turn, will

ignite

the

pyrogen

units , t r igger open the th rus t terminat ion ports ,

or cause

a splice

band

bolt

to

exp

lode.

The 2, 500-volt direct c

urrent i s

s tored

across

a capaci tor

until

a

signal is

received from the

guidance

and

con

t ro l section

to

discharge the voltage across the platinum wire .

7. TRAJECTORY

THEORY

When

a howitzer

is

f ired , the t rajectory that the project i le w

ill follow

is governed by the angle

of

launch elevation), init ial velocity

powder

cha

r ge), gravity, aerodynamic drag, and a tmospher ic conditions . The

path that the p r ojectile

follows

is a ballist ic t ra jec tory and is

parabol ic

in shape. The Pershing missi le

is

f i red from a

position

inside under)

the parabol ic

path

which

a

ballist ic project i le

no

r

mally

follows fig

6) .

After

liftoff, the Pershing s center of gravity

is

guided

to

a point in

space

on

th

e

desired

ballist ic

t rajectory.

At

that

point the warhead

is

re leased with a

velocity

vector that will be the

same

as the velocity

vector

of

a project i le f i red f rom a howitzer.


14/47

jO

1

VENTING

c,

;~

~t

GOOD

GUIDANCE SIGNAL

. END OF COAST :II ,

c { 1. IGNITE Sf:COND ST

AGE

-

~ f Slf ARATr P'I

R:\T S

TACI

E

_ f fl'lltST-STACII BUIINOUT

7

BECIIN COAST

)poP S

,,.

IGNITE 11 STA:0

. ..

Figure

6.

Pershing t ra jec tory .

8 . GUIDAN

CE

AN D CONTROL

SYSTEM

The P e r shing miss i le

uses an

iner t ia l guidance s y

s tem

to solve the

basic

requirements of

navigation

- -guidance

and

atti tude control ( D ,

fig 5 .

The guidan

c e a nd control sect ion moni tors the position a nd the

velocity

of

th

e miss i l e s cen t e r of gravi ty with respe c t to the des i red cut

off velocity alon g the t rajectory. Atti tude control devic

es

m onitor the

position of the miss i le

about

i ts center of

gravi ty

to maintain c or rec t

o r i

entation

with respect to

the direction

of t ravel .

~ - Inert ia l

Guidance

. The ine r t ia l

guidance

system uses on - board

gyroscop e s and accele r omete r s to detect and meas u r e the a

t t i tude

e r r o r s

and

accelera t ions that

the

miss i le may encounter .

b . Bas ic P

r i

nciples ,

Any

unbalanced fo r c e a

cting on

the miss i l e re

sults

in

a

cce le r

a tion of the m i

ssi le . Accelerat ion

is the r a t e of

change

of

velocity.

The device c apable of

measur ing

a c c elera t ion is known

as

an

acce le romete r .

By

design ,

an

acce le romete r c

an

m e a

su re ei ther

posi t i v e o r nega

t i

v e acce l

e r

a t ions . When

an

acce le rom e

t e r is

coupled

with a d e vic e

capab

l e of performing

the

mathemat i c a l oper a

t ion known

a s

in tegr a

tion,

an output equivalent to velocity

can be obt

a ined . Velocity

m a y be

ei ther

posi t ive or negative

in

di rec t ion . When veloci ty i s routed

into

an in tegrator ,

the

output of

the

in tegra tor

will

be

displ

a cemen t .

Therefore, if

an accele

r

om e

t er

is or iented

to meas u r e

acce

l erat ions to

the lef t and r ight of the flight path , that a c e

elera t i

on can be in tegrated

once to provide ve l o c i ty i

nforma

t

ion

and a second t ime

to

d

e te rmine

the

dis t ance the miss i l e has moved away f rom the prese l

ec

ted flight pat h

12


15/47

(displacement). This

velocity

and

di sp lacement informat ion is used

to

cor rec t the

miss i l e to

the des i red flight

path

.

~ Theory of Operat ion. Before f l ight, the firin g azimuth ,

velo

ci ty

and d

i spl

acemen t a re c

omputed

and

prese t

into the

Persh ing

guidance

s y

s te

m .

The

p~ s e t

values

a

re

re fe rence

d to

t

he

Pe r sh i

;g

's

Z~

r

dinate

a t the

firing posit ion

(fig 7) . During

flight

, acce lerat ions of the

miss i le ' s

cente

r of g

ravi ty

along these coordinates a re integr

a t

ed t o

obtain ac tua l velocity. The

velocity

i s

then in tegra ted

to

obtain the dis -

placement

of the miss i l e ' s cent e r of

gravi ty

, which is then com

par

ed to

the

prese t

values . The difference between the prese t and the ac tual

values

is used to determine the commands

nece

s s a r y to bring

~is ;

s i le

' s

cen

te r

of

gra::d,ty 1:iack_ :o'"'fue

f ra

j

ec

to r

.

The th r

us t t e

rmination

sign3 I will be t r a nsmi t ted when the pres e t va lues a re

equ

a l

and

~pposi _:

to

the actua

l vaha..e s .

42.5

_____

l

_________

_ _

SL N

T

LTIT

UDE

COORDIN TE

FIRING

POSITION

I I

I

/

SLANT

R NGE

COORDIN TE

42.5

I

I

I , CROSS R NGE

/ 1 COORD

IN TE

S

>

-

DIRECTION

OF

FIRE

LOC L HORIZONT L

E RTH SURF CE

Figur

e

7. Pe r shing coordinate sys tem

.

~ . ?e rsh ing Guidance Components . The Pe rsh ing g

uid

ance and c on-

t r o l sect ion components (fi

g

8)

cons is t

of:

(1) a s tabi l ized p la t form which

is the reference for sensing devices to measu r e att i tude e r ro r s and

ca r r i e s

the acce

l e r

omete

r s

which

detect

and

measu

re

th

e

acc

elerat ion

of t

he miss i le

' s cent e r of

grav

i ty , (2) a guid

ance

computer

which gen-

era tes the necessa ry signals to keep the

m

i ss i le

's

cente

r

of gravi

t y

on

the des i red t ra jec tory and which a lso solves fo r thru s t

terminat ion

,

3)

a con t ro l compute r to sum both a t t i t

ude

and guidance e r ro r s and to gen -

13


16/47

~

~

, / '

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f

S/R

VEL

ATT I TUDE ERRORS

VEL

CIR

VE

L

GU

IDANCE

COMPUTOR

CONTROL

COMPUTER

s

I

u

PITCH

M

M

I

ROLL

I

. ,

,Ill~ ,. ,

TH .. UST

Tt: MINAT I

S QU[

N IHe MDS

"

NV T R

~

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- - ---+ ASE

V

ENTIN

G

PUMP

POWER

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I

YAW

I I I

) ACTUATOR

3f-

---

~

T'

\

1:/

0 . .

,.) .)

/. J.

. /7

" .

Figure

8 . Guidance and control

section

components .

e rat e signa l s to m o

ve

the appropriate

control

surface,

(4)

three

e l

ect

r ical -

mechan

i cal -

hydrau

l

ic

actuators

to

turn

control

sur faces

for

th

e purpose

of

maneuver ing t he miss i l e

to

a

posi t ion that

will

reduce

the

e r r o r s s ensed by the at t i tude sensors and accelerometers

to

zero, and

(5)

an

e l

ect

r ical power

supply system

.

(1) Stabi l ized plat

form

. The hear t of the Persh ing inert ial

guid

ance sys tem is the

stabil ized platform

, Model 120, known

as

the

ST

- 120 (fig 8

and

9) . Stabil ized with

gyroscopes

,

the

ine r

t ia

l

platfo

r m p r ovides a

space fixed

r

eference for at t i tude

contro l

and car r i es and orients

th ree acce le romete r s to detect

and

measure

the

accelerat ion

of

the

miss i le s

center

of

g r

avity

along

the

Pe

r shing

coordinates

.

Before f i r ing, the

ST

- 120

is

automat ical ly leveled to the

local

horizontal

and

pointed along

the firing azimuth.

Pla t form orientation

is maintained wi t h

the

use of

the

gyroscopes

until

warhead separat ion.

(2) Guidance computer . The flight data (velocity and position of

the

miss i le s center of gravi ty along

the

t ra jectory)

is

prese t

i

nto

t

he

gu i dance

computer

pr ior

to

flight . The guidance com

puter has three channels - -

slant

range, s l ant

alt i tude

, and

c ross

range

.

The

acce l

erometers

on

the ST

-

120

a r e

in

t

eg

r

al pa

r

t s

of

the guidance channels and

supply

the

inflight info

r mation re -

quired

by the guidance

computer

.

14


17/47

,

..

I A~e.

0

p~

r ' Al l i ~

J ..


18/47

3)

4)

E_)

Slant

alt i

tude SA). The s l

ant

al

titu

de

program

gene r

ato

r

of the guidance

compute

r represents a des i red

slant

a l t i -

tude velocity . The

slant

alti tude acce le romete r on the

S T-1 20 measures the actual

velocity

of

the

miss i le s c

enler

of g r a vit y a l ong the slant a l t i tude c oordinate for compa.ri

son

with

the

desi red

programmed

velocity. The differen

c e

r ep resen t s a slan t a l t

i tud

e

velocity

e r r o r

,

which is inte-

g r ated to p1ovide s l ant alt i tude displac ement

e r ro r

information . Th ese two e r ro r signals , s lant a l t i tude

velocity

and d is placement , a re c

hanneled

into the cont r

ol

computer to cause the control surfaces lo maneuver the

miss i le , cane eling the s lant a l t itude

e r ror .

~) C r oss r

ange CR). The

c ro s s range a c ce le romete r

detects ,

measures , and in tegra tes

lhe

ac c elerat ion of the

miss i l e s

ce

nt

e r

of

gravi ty

along the

c ro s s

range

coordi -

nate,

which

is pe rpendicular to the plane of l he t r a jec tory .

The velocity information is routed

into

the

c ro s s range

channel and in tegrated

to

yield cl isplacement .

The

veloc i ty

and displacement information a re routed to the cont r ol

compu

t e r to

cause the cont

r

ol surfaces

to

maneuver the

miss i l e s cente r of g r av it y back to the flight

path

. Any

input t o the c r oss r ange channe l will be

interp

r eted

as

an

e r r o r and will be

co r

r

ected

.

Control

compu

t e

r .

Th

e

cont

r

ol

computer

receives

a

t t i tu

de

e r r o r s

roll

,

pitch

, and

yaw signals)

f rom the

stabi l iz ed

plat

fo rm and guidance e r ro r s (cross range, s lant a lt

i

tude

,

ve

l oc

i t

y ,

and

displacement

signals) f rom the guidance

computer .

The

signals

rece ived

a

re then summed, amplif ied

,

and

routed

t o

the appro pr ia te contro l

surfaces .

Powe r

sys tem.

Inflight power is suppl

ie

d by two 28 - volt ba t -

t e r ies

.

The

ba

t t e r i e s

a re automat ica ll y

act ivated jus t pr ior

t o

flight. One

ba t te ry

supplies

the necessa ry DC power for the

si

x

hydraul ic

ac tua

tor

packages.

The

seco nd

bat tery drives

a

11 5

- vo lt ,

AC,

400 -

cycl

e

inver ter

w

h ich supplies

all necessa r y

AC

powe r to

the guidance compone

nts .

9. FIRING O PE RA TIONS

a .

Battal ion Employment . The

Pershing

bat ta l ion

is o rganized with

a

h ;adquar te r s

and headquar te rs bat tery , a se rv ice

bat tery, and

four

f i r -

ing

bat ter ies . Prop; ; ,

pos ition

ing

of the f i r ing bat ter ies will

permi t

an

over lap with weapons of shorter r

ange

and will al low c overag e of any

t a rg

e t

of

in teres t

to

the

field

a r m y

by

m o r e

than one firing

b a

t tery.

The

tac t ica

l si tua t ion

may

frequently

dic ta te

re la t ively long

dis tances between

the ba tt e ry

and the

battalion

posi t ions.

16


19/47

b.

Normal Means of Movement

. Although

the Persh ing

sys tem i s

t ra~spor table

by fixed-wing

a i r c ra ft or by

hel icopter

,

the

normal method

of displac ing is by t racked and

wheeled

vehicles . A ground movement by

organic

vehicles

al lows the shor tes t react ion t ime

.

In

order to

move the

equipment and personnel of the fir ing

element ,

the

following

vehicles a re

used:

1)

Four

XM474E2 t racked

vehic les

.

2) Two

1/4- ton t rucks with t ra i le rs - -

one for the bat tery com

mander

and

the other for the

fir ing

platoon l eader .

3) One 3 /4 -

ton

t ruck with t ra i le r - - to c a r ry

communicat ion

and

cryptographic

equipment

.

4)

One

z f

-

ton

t

ru

ck

with

t ra i le r - - to

ca

r r

y

spare par ts

and

winter izat ion

equipment, when

required.

5) One 5

- t

on wrecker .

(6) Three 5 - ton t rucks- - wh en a disassembled

miss i l e

is to

be

t ranspor ted in

containers .

c. Typical

Fire Mission .

To execute

a

f i re mission, the four

t racked vehicles move

into the

p r esu r veyed firing position in a pre a r

r

anged

order

to

minimize

vehicula

r

movement .

The

warhead vehicle

enters the f ir ing position f i rs t , passing over

the f ir ing

stake

in

the gen

e ra l

di

r

ect ion of

f i re .

The erec to r - l

auncher

vehicle

follows

the warhead

vehicle

and

stops when

the

r ea r of

the vehic le

is

appro>.-ima

t ely

ove

r the

f ir ing

stake . When

these

vehicles a re

positioned, they

should be

point

ing vithin 71 mils of the

ta rget

azimuth to faci l i ta te

laying ope

r at ions with

the miss i le horizontal . The vehic le car ry ing the p r o g r ammer

tes t

s ta

t ion

and the power

stat ion is positioned immedia te ly

to the

right of

the

erector - launcher vehic le and about 6 feet fo

r ward

of i t

.

The vehicle

car ry ing the

radio t

ermina

l se t is

emplaced in

an

a re a

consistent with

the

tac t ical

situation and sui table

for

communicat ion

requi rements .

The

countdown

sequence,

consist ing of phases , each

logically

named,

may

then

be

s tar ted

l)

P r e l

iminary phase. The prel iminary phase includes the

a r r iva l and positio ning of the vehicles a t the f ir ing position .

System

cables a re

connected

,

the power station is s tar ted and

AC

and

DC

power

a re appl ied to the p

rogr

ammer tes t station

and the e rec to r - launche

r .

The wa rh ead is

e l

ec tr ica l l

y

mated

to the G C

sect ion

and the

erector - launche r is prepared for

firing

.

17


20/47

2)

s

Power

ph

ase . During

the power

ph ase DC

power

is

applied

to

the miss i le and the inver ter , the

guidance computer ,

and the

cont ro l compute r

a re

energized.

The ST

-1

20 is

condit ioned

and

uncaged. Fir ing data is

entered

intt> the f i re data

com

puter which then

computes

the

guidance

presets and solves

3)

the

gunnery

problem

.

J

f

Preset t ing

phase.

Miss i le guidance sys tem t es t and

prese t

functions for

simula ted

fligh t a re pe r formed dur ing the

p re

se t t ing phase

.

Alinement

of the

ST-120 to

the

f ir ing azimuth

is s ta

r te

d .

....

4)

Test ing

phase .

Simu

lated

launch sequence and flight sequence

a r e pe r fo rmed

dur ing

the tes t ing

phase . All on-board miss i le

components

a re exerc ised

to

insure

proper opera t ion

during

flight

.

5)

Reset t ing phase

,.

During the

rese t t ing

phase the miss i l e

g

ui

d

ance

sys tem is preset fo r f l ight , the erec to r - launcher is

read ied for erec

ti

on , and

hor izonta l

laying is completed.

See

page

19),

~

6)

Erec t ing

phase . The miss i l e is erec ted vertical) on the

l

auncher during the

erect ing

phase

.

7)

Laying

phase

.

The

miss i le

is

automatica l ly leve

l

ed and

al ined

to the ST -12 0

du

r ing the

lay ing phase

.

8) Monitoring

phase .

A

40

-

second

tes t

of the acce le romete r s

and

check on the al inement

of the

ST-120 is

pe r fo rmed

dur ing

the monitor ing phase

.

..\ 9) Second laying

phase .

A

l i

gnment

of the ST

-

120 to the f ir ing

az imu

th is veri f ied during the second

laying

phase

.

See page

19).

10)

Remote

phase

.

During the

remo t e

phase,

cont

r

ol

of the m is

si le

fo r f i r ing is t ransfe r r ed to the r emote firing panel

approxima

t e l y

152 mete r s away

.

11)

Fir ing phase

.

The f i r ing phase begins with the

press ing of

the

firing

buttons

.

This in i t ia tes the

l

aunch sequence, t e r mi

n

ating

with

f i r s t - s tage ignit ion

and lif toff .

Note : f a t rouble

which

may be co r rec

ted

occurs dur ing

the

count

down

,

the

sys tem

may

be

placed

in

a

shor t

hold condi tion eithe

r

ma nuall

y

by the PTS

opera tor or

automat

i

cal ly by

th e

t es t and checkout equipment .

When the

t rouble

i s co r r

ected ,

the cou

ntdown

w i l l continue f rom the

poi n t

of th

e

ho

l

d.

18


21/47

10. PERSHING LAYING PROCEDURES

Pershing

presents the a r t i l lery with a new challenge in laying accuracy

by vir tue of being the A r my s longest r ange

miss i l e

.

Therefo

r e, g r eater

accuracy in

laying

is

necessary

than heretofore required for any other

ar t i l le ry

wea:pon

.

Ful l

utilization

of the

Pershing s

inherent capabi l i t ies

depends on the ar t i l le ryman s skil l in

laying

the miss i l e

:

The

system

used to lay the Pershing

miss i l e

on i ts

firing

azimuth

is relat ively

simple .

The Pershing laying

method

pe rmi t s the ST -1 20

guidance platform to be alined

to

the fi r ing azimuth

before

erect ion

of

the

miss i le and

al lows

veri f icat ion of this al inemement aft e r erect ion, jus t

pr ior

to f ir ing.

The l ay ing

sys tem

also permi t s the f ir ing

azimuth to be

changed af ter the m is s il e is ver t ica l

in

the

event

anothe r ta rget is

selected .

b . Pre l iminary

firing

posit ion sur

vey

includes

the

e s tabl ishment

of

an

orient ing l ine OL)

and a firing stake . f the location of the

ta rget

is

known pr ior to occupation

of

the

firing

posit ion, a l ine denot ing the

app r

oximate ta rget

azimuth is establ ished for use

in

po s i t ioning the

erec to r - launcher

EL)

v e hicle .

~ The

equipment

us e d t o

lay

the P e r shin~

m i s s i ~

con_tists of thr.

ee

Wild T2

theodolites

i o n ~ o u n t e d on a stan.p.ard

t r ipod

and two mounted on

specia l t r ipods with t rans la t ion

devices

to a l low l a t e ra l t ranslat ion of

the

i

nst rument

without

reposi t ioning

the

t r ipod

fi

g 10) ;

an

M2

aim ing

c i

r

cle;

~ n d a the odol i t e

cont

rol box fig 11),

which

is used

to

posi t ion the ST - 120

on th e des i red azimu

th.

The normal ar rangement of the equipment dur

ing laying is

i l lust

r ated in f igure 12 rf

1) The theodoli te on the s tandard t r ipod is em pl

aced

over the

stake marking th

e nea r

end of the

or ient ing

line. This ins t

r u

ment is

cal led the

orient ing

sta t ion theodoli te OST) and

provides

di r ect ional

cont

r

ol

.o r the other ins t

ru

ments .

2)

A

second

theodoli t

e ,

cal led the hor izontal

l

aying theodoli te

HLT). is

mounted

on

a specia l

metal t r ipod and t rans la t ion

device ,

which

a l l

ows

la tera l t ranslat ion . The

horizontal

laying

theodoli te

is emplaced near the window of the guidance and

control sec ti

on for opt

i

ca

l

viewing of the po r ro

pr ism . The

Po

r r o pr i sm

is

a m i

r r o r - l i

ke

device

whic h

is mou

nted on the

ST -

120

so tha t i ts re

flec

tin g su r

face

faces a t a r ight

ang

le

to,

1600 mils less than, th e ST - 120 heading . Afte r the HLT has

been orien ted by the

OST,

the

HL T

opera t o r ro ta tes the ins tr u -

ment

until

the

scales of

the ins t rument indicate the value

of

the

f ir ing

az

i

muth

.

The ope

r

ato

r

th

en

moves

the theodoli te along

the t ranslat ion device, if necessary , until th is ins t rument

poin t s to the window on the side

of

the guidance

and control

sect ion . To

in su re

accuracy

, the HL T operator reor ien ts

his

ins t rument

on the OST befo r e

proceeding

to

lay

the ST-120.

19


22/47

i g

ure

10 .

Th

e

odoli te

t r a

ns l

a t i

on

dev i

ce

a n d me t a l

t r i

p o d .

2


23/47

12

5

6

OR

H44820

Figure 1 1. Theodol

i te

control

box

.

He then

uses the

theodolite cont ro l box to adjust

the head

i ng of

the ST-120 unti l the l ine

of

sight of the

ins t rument

coincides

exactly with

i t s

ref lect ion

from the

P o r ro

pr ism . The ST -

120

is now l ayed on

the fi r ing azimuth

.

3)

The

launcher aiming c i rc le (LAC)

is

emplaced over

the cente r

of the launch pad .

The pur

pos e o the l auncher

aiming c i rc le

is to dete r

mine

~

on

which to

emp Jl,c.e

the th i rd theodoli te ,

known a s t h e

ver

_ ig l . la

ying

theodoli te (VLT) .

4)

The

ver t i cal

laying

t

heodo

l i te , which

is

also provided with a

t rans la t ion

device

,

is

used

to

veri fy

the

heading of the

ST

-

120

af

t e r th e m i ss i le h

as been

e r

ected

. The theodo l i t e co nt r ol

box w h ich

was

us e d a t t he

LT is

moved

to

the VLT w

hil

e the

miss

i l e i s b eing e r ec ted.

Afte

r t he

miss

i l e is ve

r t

ic al , t

automat ical ly r o t a t

es

until i t is a l i ned

wi

th t h e ST - 120 .

Us

i

ng

21


24/47

the contro

l

box

the

VLT

o

per

a t

or

can

i necessary cor

r

ect

the ST-120 heading by rota t ing the

erected

miss i le and the

ST -

120

which have been slaved

t

ogether . The VLT opera

to_r

continues to

monitor

t

he

ST -12

0

headi

ng

until th

e

immedia te

f ir ing a rea is

evacuated

jus t

pr ior to

firing t ime.

During th is

t i

me

fina

l

adjustments

can be

made

to keep

the

miss i le

and

ST-

1

20 alined to the

fi ring

azimuth.

AZIMUTH

OF FIRE

ST-120 HEADING

HLT

6

METERS

30-50

METERS

TOOLT

Figure 12 D

.

Installation of

ins t ruments .

MISSILE

HORIZONTAL

MISSILE VERTICAL

Step

I

Orientation

of th e

gu id ance platfo rm

on the f ir ing

azim uth

Step 2

issile

rotated

until

olined

with

guidance

pla tform

issi

le and

guidance

platform

maintained on

the f i r ing

azimuth

Figure 12 . @ . Major s teps in az imu th lay

in

g.

22

i


25/47

l l . MISSILE FLIGHT SEQUENCE

At

a specif ic point in the

countdown,

control

is

t rans fe r red to a re

mote f ir ing panel (fig

13),

and a t T-0 the command to

f i re

is

given.

~ F i r s t -

Stage Ignition. When

the f i rs t - stage rocket motor is ignited,

the Persh ing l i f ts off the launcher (fig 14)

. Milliseconds

after l iftoff

,

the missi le begins

to pitch,

or t i l t ,

away

f rom the

ver t i

c a l and toward the

target a t

a prede termined

ra te .

Init ial th rus t is

provided

by

the f i r s t

s tage rocket motor ,

which

burns out completely

regard less

of ta rget

range

.

b. Coas t Period.

After

f i rs t -s tage burnout, the

miss i le

ente rs

a

coas t period (fig

15)

. The t ime length of th is coas t period depends on the

range

f rom

the launcher

to the

target .

The

coast

period

is

determined

by the f i re data computer and is p re se t into the missi le pr ior

to

firing.

~ Fi r st - Stage Separat ion, Second-Stage Ignition.

At

the end

of

the

coas t

period, the f i rs t inflight separat ion occurs

between

the f i rs t

and

second s tages . The explosive bol ts on the f i r s t - s tage

splice

bands a re

detonated,

and

the f i rs t

s tage

is separa ted

(fig

16). The

second s tage is

ignited, accelera t ing the remaining miss i le

sect ions

a long the flight path.

During second-s tage burning the

guidance

computer in the

miss i le

con

stantly

moni to rs

the velocity

and position

of

the

m iss i le s

center

of

gravity. When the

proper

values a re sensed

by

the

guidance computer -

when the miss i le i s tangent

to

the bal l is t ic t ra jec tory and

has

gained the

proper veloci ty- - the cutoff signal is generated . At this t ime, the

second

and la s t inflight separat ion takes place . Explos ive bol ts between the

w ar

head

and

guidance

and control section are detonated and the warhead is

separa ted f rom the

guidance

and

control

section (fig 17)

. Simultaneously

three thrus t t e rmina t ion por t s in the forward end

of

the second-s tage

rocket motor

blow open,

terminat ing

the

second -

s tage

th rus t .

Mill i

seconds af ter

warhead separat ion, a shaped charge on

each

side

of

the

second

- st

age

motor

is

detonated

(fig 18)

.

Detonation of

the shaped

charges insures a clean warhead separat ion. At separation, the warhead

section ( reentry body) is spin

stabil ized

to

ass i s t

i t

on i ts t rue ballist ic

t ra jec tory to

the ta rge t .

d . Reentry. As the warhead section reen te rs the

ear th

s a tmosphere

(fig

-

19) i t is

subjected

to

ext reme

t empera tures

f rom

aerodynamic

hea t

ing

. Pro tec tion f rom these high t empera tures is achieved

by

an ablat ive

coating which burns or mel t s away during

reen t ry

,

thus shielding

the war

head

section

f rom

the

in tense heat

encountered.


26/47

igure

13 Remote fi re

panel

4


27/47

igure 4 . i r s t stage

ignition

.

25


28/47

_

Figure

15

Coast per iod


29/47

Figur

16. i r s t

stage

separation and

second s tage

ignition.

27


30/47

Figure 7 Thrust terminat ion

8


31/47

Figu r e 18 ase venting

29


32/47

Figur.e

19. Warhead

reen t ry

12.

ENVIRONMENT

CAPABILITIES

The Persh ing can be employed within a wide range of environmental

ext remes including high

winds,

high humidity, high or low t empera tures

fig

20)

sal t

spray,

and darkness or low

visibili ty.

Figure 20 Environmental capab ility.

30


33/47

~

Winterization

Equipment

. Winterizat ion equipment is

necessa ry

in ex t remely

cold

c

l im

a tes to maintain cer ta in

Persh ing

equipmen t

a t

an

operat ional

temperature . The winte r ization

equipment

consis ts

of

gaso

lin e

operated heaters

and e lectr ic blankets . This equipment

is

effective

in

t empera ture

ranges

of -65

to

+50

F

and

i s util ized as determined

by

the commander .

1) A 15, 000

-B T

U

pe r h

our, gasol ine -

f ired heater is

mounted

in

side the p r o g r a m m e r tes t station fig 21) for use during

ext reme

co ld. The

heate

r opera tes on fuel which is pumped

fron:i the ca r r ie r fuel tank

or f rom an external

source

.

Figure

21. P r o g r a m m e r tes t s tat ion winterizat ion equipment .

2) Two 150,

000

- BTU -pe r h ou r

heaters

a re used du r in g ext reme

cold

to heat the

radio

terminal

set

and

the power

s tat ion

f igs

22 and 23). The heater for the radio terminal set is used to

preheat

the inflatable antenna during erect ion and preparat ion

for

s torage in order to prevent cracking of the antenna .

The

heater for the

power

station is

used

to preheat the

power

s ta -

t ion

before i t s

turbine engine

is

star ted.

31


34/47

Figure

22. Radio

terminal set

winterization equipment.

b.

Missile

Blankets.

Four

thermostat ical ly

controlled blankets are

supplied

to

maintain the missi le sections at the

required temperatures .

Firs t and

second-stage body section

blankets

maintain

the

respective

section

skin temperatures a t 8 C 35 15 F), the guidance and

control section blanket maintain;-the temperature of the guidance and

control

section

skin

at approximately

28

8

C 82

15 F), and the

warhead

blanket

maintains the warhead se; t ion at

an operational t em

perature

of

-32

C

-25

F)

or

above.

All

the

blankets operate

on

120/208-volt, 3-phase, 60- or 400-cps power. The warhead blanket uses

a

28-volt

DC circuit to heat the blanket when

the warhead

section is

mounted on the carr ie r M474. Conditions

under

which the blankets

are

used

vary, depending on the length of t ime the sections are to be exposed

to specific

t empera tures

and

wind

velocit ies. When

used,

the second

stage and the

guidance

and control section blankets

are

removed pr ior

to

erection of

the

missi le ,

but

the f i rs t -s tage and

the

warhead

section

blankets

may

be removed after erection. The blankets

are held

in place

on the missi le by hook and

pile

tape fasteners to permi t

rapid

installation

and removal.

32


35/47

OPCR,i, TE 1-lEATI:R

l OR lO

MINUTES.

DISCONNECT DUCTING, CLOSE

WINTE~IZAT ON OOOR

igu

re

23

Power

sta

t ion

winter izat ion

equipment.

c Theodo l i te Sun

and

Wind Shi eld. During

operat ions

unde r normal

weather

condi

tions an umbre l la device is used to shield the theodoli tes

However

under ex

t r

eme weathe r

c on ditions

specia

l canvas tents with

zipper opening sides a re used

to

shield

the

theodoli tes f rom

the sun and

wind

33


36/47

d. Pr i sm Shield. An awning type

device

is used on

the

guidance and

contro l

section

to

shield the

Por ro

pr i sm

f rom

the

sun . This

device,

which is

detached

from

the

missi le short ly before liftoff, prevents the

ref le

ct ion

of sunlight f rom the window in

the

missi le into the eyes of

the

VLT

operator .

13 . AIR TRANSPORTABILITY

Tact ical mobili ty

is

fu

r

ther enhanced

by

the

ability

to move

all

the

necessary firing equipment by he licopter

.

In adc . 1 the Persh ing was

specifically designed for t ranspor t by fixed-wing a i rc ra f t to achieve

strategic mobili ty .

a .

n

order to

t ranspor t the

Pershing

sys tem by f ixed

-

wing a i rc ra f t

o r by helicopter , several pieces of special handling equipment a re pro-

vided .

1)

Rack

bar

j acks

.

our

rack bar jacks

fig 24) a re used

to load

the var ious

equipment

packages

on

the

XM4

74

1

s . The

jacks

a re

operated

by

four

men

working

in

unison

.

The

rack bar jacks

a re

used

only in the

absence of a

5-

ton

wrecke

r .

igure 24 .

Rack

bar j acks .

34


37/47

(2)

Dolly sets .

Wheel

and axle

ar rangements (fig

25) a re

at tached

to the

equipment packs to

allow them to

be

towed

on

the

ground

and

to provide l imited mobili ty when the equipment is

not

loaded

on the

t racked vehicles

.

3) Body

section

l

ift t rucks .

Body

section l if t truck ' (fig 25) a re

used to t ranspor t the

missi le

sections when the firing elements

a re moved

by

fixed wing

airc

r aft or helicopter . These

t rucks

a r e equipped

with

tow ba r

s.

b. All

elements

of the weapon sys t

em

except the 5 - ton

wrecker

can

be

t ranspor ted by .L4 C -1..f3 aircraf t . A ele~ s

includ

i

ng

the wrecker

can

be t r ans p o r ted in 11 Cl30B ai rcraf t . n

a i rc ra f t

operat ions , the

programme r test

station,

power

station,

and

radio

termina l set are

mounted on dolly sets ,

and

t he missi le sect ions are loaded

on body

sec-

t ion

l ift t rucks .

However, the

equipment

mount

ed on

the warhead

vehicle

is no

t

un

l

oaded

. All four t r

acked vehicles

a r e t

ranspor ted to

the fo r

ward

a i rs t r ip by

a i rc ra f t

.

When the a i rc ra f t

a r

r ive

at

the

prescr ibed

des t ina-

tion,

the

equipment is unloaded, demobil ized,

and

mounted

on the

t racked

vehicles

with the rack

bar jacks,

if

no

wr

ecker is available

. Miss i le

assembly is conducted as in no

r mal

ground operat ions i f the wrecke

r

i s

available o r as in

helicopter

operat ions, using

a

modif ied 3 /

4 -

ton

t r

uck

.

~

Four teen

f H -

47

(Chin

o

ok)

c~

go

he

l i

copters

are

requi

r

ed to

t

rans-

port the

necessary

equipment

for

firing . Two helicopters

t ransport

the

advance party and then re turn to ass is t in

bringing

the main body fo r

ward

.

The

CH

- 47 helicop t e r

has

a r

ange

o f 200

miles

When t r ansport ing 6, 600

poun~ ca r

go

. The Chinook

normal ly

req ui r e s

a t

l eas t a 200 - foot

clear ing in which

to land

. All

of

the

equipment

no r

mally car r ied on

t

he

t racked vehicles

i s needed a t

the firing position;

however, because

of

the

load

l imitat ions of t

he helicopte

r

s,

t

he

fou r t racked

vehicles cannot

be

t ransported.

The pr ogr amme

r t est station ,

power station

, and

radio

terminal set

are mounted on

dolly sets .

The azimuth laying equipment

must

be man

-

hand

l

ed

. Afte r i t

i s removed from i ts ca r

r

ier the

erec tor

l auncher is maneuvered on

i ts

own whee

l s . One

body section

l

ift

t ruck

is

used to

t ransport

the f i r s t

-

stage motor section

,

and

a

second body section

l if

t t ru

ck

ca r r i

es the second

-

s tage

motor

and

the guidance control sec

-

tion. A warhead t rai le r is

used

to t r anspor t the wa r head

section

. A 3/ 4 -

t

on

t ruck

M37Bl)

equipped

with

a

davit (fig 25) is requi

r ed

to move the

mobil ized equipment at the f ir ing position and to mate the warhead sec-

tion.

35


38/47

BlCTOI-UUNCHB

C

AHIB

AOAl TB

KIT

S

PIIOGUMMB-TIST

STAOON. POWB

AOON CAIIIB

ADAPTII

KITS

OOY 5lCT10H CIADLH IODY

SKTION

SUNG

BODY SfCTION

YIUCl S

CAIIIU IOAIDING

U.DDB

DOU

Y

TltUCI SET

R H 89.5.5

Figu r e 25 . Special handling equipment .

36


39/47

14 . CONTAINERS

T

he containers for the fou

r

sect ions

of the Pe r shing

missi le fig

26)

a re of welded steel cons truc t ion and a re designed to

pr

otect the

miss i

l e

sect ions f rom

shock,

vibration and

weather

during t rans i t and

sto

r age .

T hey a re also

designed

t o

perm

i t a

comp

l e t e el ec tr ica l

checkout of the

miss i l e sections withou t

being

opened . The warhead section conta iner is

t o p open ing whe r eas th e gu

idance

and contr o l sect ion containe r and the

two

motor section conta iners a re

end

open i ng . All

four

of th e

containe

r s

a re

reusab

l e .

F I R S T S T A G E CONTA INER

2 GU IDANCE

A N D

CONTROL-

S E C T

ION

CONTAtNEH

igure 26 .

Miss i le

section containers .

37


40/47

a. Descr i ption. The

con

t aine rs a re sealed at

a tmospher ic

pressu r e

and-

the humidity is

controlled

by

a prescr i bed

amoun

t

of

d_esiccant

s tored

inside

the

cont

ainers

. The pe r cen t of humidity is

co

ntinuous l y monito r

ed

by

a humidity

indicator in

each conta ine r .

Strip

heaters inside the

motor

s

ect ion

c

ontainers protect the

moto r

sections

f rom

damaging

cold

.

Each

motor sec t ion container

has

a

te

mpe

ra

ture

monitor assembly

for

detecting

whether

the motor

section has been

subject

ed to excessive

l y co l d

or

hot

t empera t ures .

The guidance and contro

l

section is maintained at i ts

operationa l t empera ture

by an

elect r ic heating blan

ket wh

i c h i s i ssued

with the

m i ss il e.

Shear mounts and hydraulic shock abso

r bers

inside the

containers

p r otect the miss i l e body sect ions f rom shock and vibration .

T

he motor sect ions an

d guidance

and control section

containers a

re

equipped

with

monito r

assembl ies for detecting whether the

missi le

sec

t ions have been

subjected

to e xce ss ive amounts of s

hock.

b.

T r

ansportation. Th

e

miss i l e sect ions are norma

l ly t ransported

in

the

containers

on

extra - long whee

lb

ase 5 -

ton

t rucks. Three t rucks

a re

requir

ed to

t ransport

one

complete

miss il e.

15.

PERSHING

MISSILE TRAINER

a . General .

One

Pershing miss i le t ra iner is authorized

each

TOE

P e ; shing

f ir ing bat tery.

t

is used

t o develop a

nd m a

intai n individual and

t eam proficiency

in a l l

operat ions

a

nd procedures for

which

the bat te ry is

responsible .

The missi le

t ra iner

cons is ts

of

1 bal lasted f ir s t s ta

ge

motor

section

with a i r fins and je t

vanes

and associated

hyd

r aulic

packages.

2 ) ballasted

second

- stage motor section with a i r fins and

j e t

vanes

a

nd associated hydraulic packages.

3) An elect r ical ly and mechanical ly

operable

guidance and

contro

l

section.

4) type X

nucle

a r warhead section .

b. Character i s t ics .

1)

The miss i

l e t r

aine

r

duplicates all handling, tes t and checkout,

maintenance

, and

prefir ing

c haracter i s t ics and responses of

the

tact ical miss il e

when

used

in conjunctio

n

with

the tact ica l

ground support equipment

.

t is suff iciently rugged

to

with-

stand

repeated

handling

and sufficientl

y

re l i

able

to

permi t

ex-

tended

periods of

ope

r

ation.

2)

The

missi le t ra ine r and components have

the same

external

configurat

i

on

and

th

e same size ,

weight,

and center of

gravi ty

as the tact ical sections

a nd

components

.

38


41/47

(3)

Internal

assem bl ies ins ta l led in

the

missi le t ra iner are

mounted in

the

same locations and in

t h e

same manne

r

as the

tact ical assemblies and a r e such that the

handling

charac te r i s

t

ics are the same.

4)

All

assembl ie s

or

components

in

the

tact ica

l

sys tem

which

are

removable,

r

eplaceab

l

e, or adjustable a t

the

organizat ional

level are also

removable, replaceable

, o r

adjustable

i n the

missi le

t ra iner

.

(5)

The t ra ine

r i s

compatible with the tac

t

ical

w inter iza

t ion kit

.

(6) The miss i l e sections of the t ra ine r are

compatible with

the

ope

r

a t

i

ona

l

shipping conta

iners

so tha

t t he missi le

sect ions

can

be

e lec t r ica l ly

checked

out without being

removed from

their

shipping

containers .

c .

Maintenance Requirements.

( l)

The

miss i l e t ra iner

requi

r

es norma

l o r dnance maintertanc e and

supply support.

(2)

The miss i le

t raine r

is compatible with

the

too

l

sets

and th e

tes t equipment is sued with ope

r

ational

equipment a t the organi

zational maintenance level . No special tools or auxi

l

ia

r y

tes t

equipment is requir e d .

16 . PERSHING

ORGANIZATION

The Pe r shing

battal ion

(

fig

27) cons is ts

of

a

headquar ters

and

head

quar te rs bat tery

with

an organic signal

maintenance

section,

a

service

batte

r y

wi

t h

organi

c o r

dna

: e and

engineer

e l

emen

t

s ; and four f i r ing

bat te r ies

FA BN

PERSHING

OFF

w 0 EM

36

I 3

587

r

3 6>

I

HQ HQ

BTRY

SVC BTRY

15

f

3

120 q

5 6

175

4

NOTE:

SECURITY PLATOON AUGME

,

NTATION

-

N SVC BTR Y - I

OFF

AND 50

EM NOT INCLUDED

IN TOTALS.

I

FA BTRY

I

I

I

Figure 27. Field a r t i l lery

batt

a lion, Pershing.

39

'

'

73

To A

8


42/47

~

Headquar ters

and Headquar ters

Battery. The headquar ters

and

h

eadquar ters batte

r y (fig 28) provides nor m a l support , including re

con

-

na i ssance and survey communica tions,

operational

control ,

and

admin is

t rat ion for

all

e lements of

the battalion

.

Communicat ion between

the

headquar ters bat tery and t

he

four f ir ing

bat ter ies

fig 30)

is

p r ovided y

the AN TRC-80

r a

dio

te rminal

se t

. T

his pow

e

r ful and highl

y directiona l

radio

in su

re s

an extreme

l y

rel i

a ble and vi r tual ly

j am-proof commun

ica -

t ion

link to distances up to 160

ki lometers

.

0

.,,/o Fl

0

'D

~

w

5

,

2

BN HO

HO

I

BTR

Y

I I I

I I

1

0 19 1

0

3

1 0 9 1

3

0 0

9

BTRY HO

0

ij P

LAT

HQ COMM

IPLAT

HQ

AVN SEC

MEO SEC

0

0

2 0 0

9

LN

ISEC WRE I SEC

0 0

4

0

0

9

SIC

RAD

I EC

0 0 4

SIG

MANT

Figure 28. Headquarte r s

and

headquar ters batte ry , Per sh i

ng

.

b. Service Battery . Service

bat te ry

is organized to provide logist ic -

a l , motor

maintenance

, and

personnel administrat ive

suppor t to

the

battalion . T h e bat t

ery

s m is s ion

is

to procure ,

break

down , a

nd

d i s -

t r ibute a l l c l

asses

of

supplies

to units

of

the battalion , to m a

in

ta i n ap -

p ropr i

ate

supply and pe r

sonnel records

a nd to

per form

a

por t

ion

of

equipment

maintenance

functions

. The

ammunit ion

platoon

performs

bat ta lion miss i le resupply and

s tores

a por ti on of the battalion bas i c

load

of

missi les .

~ Persh ing Missi le Bat tery . Each

of

th e four miss i l e bat te r ies

fig

30 )

const i tutes

a fi

re unit

and contains

th

e

necessa ry

personne l and

equipment

for proc es s in g f i re data for

assemb

l ing, te s ting , e recting , and

f ir ing

miss i l es

and for o rganiza tiona l maintenance of the

miss i l es

and

ground

support

equ ipment.

The

miss i l e

batte

r i es

provide

their

own

40


43/47

m

r

l

?

n

31

1

n

3 1

n 7

BTRY HQ

AMM O

I

PLAT HQ

OR

O EQUIP

MAIHT PLAT H

SECURITY PLAT

n

0

6

0 1

0

7

-

.....

11

1

0

1 22

I

I

PROP

I

S

TRUC

I

PER S

EC

BH

MA IHT

:J

-

r

2

~

.

AMMO SEC

,

.

-

..

,

0

1 19

n

1 lR

n 1

17

I

I I

ELEC CONTR

SUPPLY

E

NG MA

INT

I

11

1

~ D 12

Documents

The Pershing Guided Missile System