FIELD ARTILLERY, WORLDWIDE VOLUME 3. FIELD ARTILLERY ROCKET SYSTEMS

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP09-01333R000100330001-7
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 32
• Document Creation Date: December 23, 2016
• Document Release Date: September 11, 2013
• Sequence Number: 1
• Publication Date: May 6, 1986
• Content Type: REPORT

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SECRET
DST-1130S-200-86-VOL 3
6 May
1986
FIELD ARTILLERY, WORLDWIDE (U)
VOLUME 3. FIELD ARTILLERY ROCKET SYSTEMS (U)
?
AUTHOR
DST
3
-1130S -200 -86 -VOL
DIA TASK UNIT PT -1130 -01 -10L
DATE OF PUBLICATION
6 May 1986
Information Cutoff Date
24 October 1985
This
document supersedes ST-CS-07-07-75 (redesignated DST -1130S -007 -75),
dated
November 1974; DST -1130S -200 -82-VOL 3, dated 10 May 1982; and DST-1130S -200 -
82 -VOL 3-SUP 1, dated 29 January 1982.
This is a Department of Defense Intelligence Document
prepared by tie Foreign Science and Technology Center, US
Army-Intelligence Agency, and approved by the Directorate
for Scientific and Technical Intelligence of the Defense
Intelligence Agency.
This document has been processed for CIRC.
NOT RELEASABLE TO FOREIGN NATIONALS
WARNING NOTICE - -INTELLIGENCE
SOURCES OR METHODS INVOLVED
CLASSIFIED BY: MULTIPLE SOURCES
DECLASSIFY ON: OADR
(Reverse Blank)
SECRET
(This page is UNCLASSIFIED)
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it7T-11399-200-Su-VOL 3
9 May 1tA3e
S.VUTINi 11
(o)
Cenettal_(il)
(! ) itat Pelf-plan firm Le,. orats de Zecruytge 9A hae deveioped and is
intradticiri, on the market a new light Mii.LO designated the LA r 97 tfig
Fasically, th13 is a 49-tulto lattraher thdt could he placed on i variety oi
mounts ani fires a 73-fc (2.73-inch) rocket that is a common air-to-ground
munition. Unidentified cuet3mers in the rmr and Middle Last reportedly have
ordered this system.
(1JNCLAS9IFIrdil
Figure II-1.
(UNCLASSIFIED)
(-0) belOau LAU 97 7U-mm HXL
2-1
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DST-1130S-200-86-VOL 3
6 May 1986
2. launcher (11)
The launcher has been shown mounted on a light single-axle trailer, but
it could be mounted on virtually any vehicle with a 1-tonne capacity. The
trailer offered by the rranufac turer as a pin tf orm for the launcher has a
tubular chassis with torsion-bar suspension and a small third wheel near the
front. The trailer, which has a vertically adjustable tow bar on which a
handbrake is mounted , can be adapted to virtually any tow lug vehicle.
24 V, long-life, cadmium-nickel ) battery is mounted in the base of the
mount to provide power to the firing controls and to operate the launcher.
Azimuth and elevation are adjusted using a tic-speed electric ac tor (fast
speed for rapid changes and slow speed for final a dj ustment ) , and manual
backup controls are provided. The trailer weighs 500 kg and is designed to
a 1000-kg payload. UF,t4 from sales brochures are as follows:
Number ci tulbes
Traverse
a
Elevation/traverse power
heng th of mount tasi:
Width of u
height of launcher .......
Weight unloaded .........
40
369'
551'
device
ght
-speed mo tor
1.45 meters
5E5 kg
travelIn mode , the trailer-mounted version of the LA1j-97 :Is 4.115 meters
long, 1.96 me ter
eters high.
ginally, the rockets had a maximum range of 6000 meter but the
current rockets achieve 8000 me.tera, and a new motor that was to be de velbned
in 1983 would extend this to 10 000 meters . The rocket can be armed with any
of several interchangeable warheads (13 or 14, according to two different
) which include HE, smoke, antipersonnel antitank, illumination,
aty antirunway, and f let:he tte. A des trip elan of advertised warheads
FZ-3 2 T d that.
and weighs 2.4 k
FZ-49: Shaped-charge warhead that penetrates 400-rmit
armor, produces 1200 fragments, and weighs kg.
2-2
UNCLASSIFIED
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DST 0 -200-86-VOL 3
6 May 1986
FZ-58 Warhead used against any target that requires
penetration before explosion; it has a base fuze and nose-
mounted antiricochet plug and weighs 4.52 kg.
FZ-63: Warhead loaded with white phosphorus for ncen -
diary and smoke and weighing 4.15 kg.
FZ-71: Antipersonnel warhead producing more than 8000
effective fragments, achieving a 21-meter radius
destruction, and weighing 4.3 kg.
FZ-85: Controlled-fragments tion warhead producing more
than 300 fragments and weighing 4.3 kg.
FZ-86: Smoke round that producesdense smoke for
than 4.5 minutes and weighs 4.3 kg.
EZ-100 : Warhead containing nine shaped-charge submuni-
tiorus and weighing 6.7 kg.
M-257: Warhead that illuminates throughout its trajectory
and weighs 4.9 kg.
4. Firing Characteristics (U)
(U) A ripple of 40 rockets can be fired in 5 85 seconds to cover an area of
200 meters by 300 meters at a range of 8000eters. When tbe rocket with the
HE warhead is fired at an elevation of 40 , the achieved range is
8093 meters, the angle of fall is 64?, the terminal velocity is 197 mis, and
the time of flight is 45 seconds. Also, the circular error probable (CEP) is
170 meters at this firing angle.
2-3
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DST-1130S-200-$6-VOL 3
6 May 1986
(UNCLASSFIlED)
(UNCLASSIFIED)
Figure 111-9. (U) ASTROS-II Reload Operation
3-11
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DST-1130S-200-86-VOL 3
6 May 1986
(UNCLASSIFIED)
Neg. 577505
Figure IX-3. (V) Prototype of French MRL SYRA
9-5
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DST-1131/S-2DO?B6?V01, 3
May le4St;
AS
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UNCLASSIFIED
?
200-S6-VOL 3
IN CLASSIFIED)
(UNCLASSIFIED)
Figure XV-4. (11) Firos-25 Fire-Control Panel
(2) (U) Open source literature states that the Ferranti navigation
system PADS (position- and azimuth-determining system) MK2 and the FIN1111
attitude-reference syster have been selected for use In fire-control system
of the improved Firos-25 system. The new fire-control system will use the
PADS unit to provide position and orientation data to the battery command
vehicle, while the FIN1111 will be offered as an option to allow the indi-
vidual launchers to be aimed more accurately.
15-6
UNCLASSIFIED
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UNCLASSIFIED
e. flescription or the Enci-et (111
(11 The 122-mr rocl:et is available in two versions (fig XV)
which, according En the tyne of warhead, differ in relation tc, the Length!
diameter ratio.
(UNCLASSIFTED)
Figure XV-c. Fam
Rockets of Ffros-2
UNCLASSIFIED
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DST-11305-200 6-VOL
6 May 1986
(2)
provides a max
and performed
submuni tion warhea
The rocket motor with a double-hose solid propellant grain
range of not less than 75 km for conventional warheads (HF
nt--PFF), and a maximum range of not less than 22 km for
Technical data are as follows:
Ca1lber 122 mm
Length:. 22C.5 mm
Weight at f:iring
Weight of propellant: 27 kg
Specific impulse: 22:8 setoit
kg
Maximum pressure: 190 kg/cm2
Avers thrust: 2 kg
Combustion 2.06 second (at 501 maxpressure)
( 3 ) The currently available conventional warheads are identi-
cal
in external configuration and weight and are fitted with the same type of
impact fuze. The two types of warheads are:
An HE natural-fragmentation warhead, which on impact pro-
jects fragments against mixed targets.
A REF warhead, for use mainly against soft targets. The
preformed fragments are spherical and have the optimal
size and weight to obtain maximum antipersonnel effective-
ness.
Technicalthe warheads are as follows:
? Total weight: 17.3 kg
? Weight of fuze: 0.25 kg
? Weight of explosive: 3 kg
? Diameter: 122 mm
a Overall length: 555 mm
? Length of fuze: 50 mm
15-8
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DST-11305-200-86-VGL 3
May I9S6
(UNCLASSIFIED)
Figure XXVIII-13. (U)
Electrical Firing Control
UNCLASSIFIED
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Figure XXVIII-14. (U) Left?Side View of BM-2I fikL
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DST-1 1305-200-86-vol. 3
6 May 1986
UNCLASSIFIED)
(UNCLASSIFIED)
Figure XXVIII-15. (U) Equilibrator
Torsion Bars on BN-71
73-15
UNCLASSIFIED
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DST-1130S-20D-86-VCL 3
6 May 1986
(UNCLASSIFIED)
PNEUMATIC
'TRAVEL
LOCK,
,
(UNCLASSIFIED)
Figure XXV1II-16. (U) BM-21 Launcher Power Section
d. Components(ii).
(1) (U) Electrical system (J). The BM-21 is basically an electri-
cally opera ted launcher with a manual backup system. The power source is a
5-kW, 28-V DC genera tor. The. genera tot, loca ted beneath the vehicle cab, is
driven by a power takeoff from the vehicle's transmission gear box. The
genera tor is engaged, controlled, and regulated from the cab of the vehicle.
It 'oust be opera ted at 3 prescribed revolution-per-minute rate and should
produce 27- to 29-V DC. A tachometer and voltmeter moun ted on the instrument
panel of the vehic Le assist in con troll log and regulating the system. The
genera tor is cooled by forced air during operation. In the upper carriage,
the power is used to elevate and traverse the launcher.
UNCLASSIFIED
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DST- 0 200-86-VOL
6 May 1986
(2) (U) Electrical elevations and traversing mechanisms ( ) .
Both of the mechanisms are essentially the same and will be discussed
together, with di ssimilar i ties no ted Direction and rate of traverse or
elevation are con trolled from the gunner's station by activating the traverse
or elevation potentiometer. When power is received in the Launcher, it is
amplified by an ampl id yne and fed to a slave mo tor (fig XXVII1-16 ) One
ampl id ync , one slave motor, and one potentiometer are provided for each
mechanism. The only difference in the elevating and traversing mechanism is
the manner in which the slave mo tor is geared to perform its function. The
traversing slave mo tor is connected, through a reduction gear assembly, to a
large ring gear attached to the base ring assembly which rotates the upper
carriage. The elevating slave motor, through a reduction gear assembly, is
connected to an arc gear affixed to the bottom of the tube cluster.
Activation of the elevation slave motor elevates and depresses the tube
cluster. The elevating and traversing mechanisms are cons trained by limiting
switches that slow the rate of movement as a limit is approached and break
the circuit when the limit is reached
(3) (U) Mechanical elevating and traversing mechanisms (ii). The
manual elevating and traversing mechanisms are driven by a single handwhee 1
located at the gunner's position (fig X XV111-17 ) . A shifting knob is used to
switch from the elevating to the traversing mode, and vice versa. The
launcher cannot be opera ted manually when the launcher is receiving power
from the power-supply generator. The electric system has automatic magnetic
clu tches that block out the mechanical linkage and a lock for the handwheel
shaft. The manual system is a linkage of hand wheel , shafts, chains, and
gears that can perform the same function as the electrically powered system
in turning the elevation and traverse gears. Actually, the manual system is
an adjunct to the electrical system and provides a backup capability to the
electrical system in case of a malfunction in the electrical components . It
is also used for fine adjustments in orienting the launcher. The manual
system operates in the following manner: When pushed in ( ou tboard) , it
engages Che hand wheel for elevation, and when it is pulled out ( inboard) , it
engages the same hand whee 1 for traversing. The manual system cannot be
opera ted unless the sight mount arm is fully ex tended and locked in the
firing position.
(4) (U) Pneumatic system and locking devices (U) . The B11-2.,1 has
a pneuma tic system with two functions: To operate the launcher travel locks
and to operate two lockout devices that stabilize the launcher during firing.
A belt-driven air compressor mounted in the vehicle's engine compartment
supplies the air. A single control lever mounted in the cab of the vehicle
(fig XXVIII -18 ) has two positions: Travel and combat. In the travel
position, the launcher's upper carriage is rigidly locked to the base and the
lockout devices are deactivated. Upon arrival at the firing position, the
vehicle driver moves the pneuma tic control lever to the combat position. The
system unlocks the launcher ( so it can be elevated and traversed) and acti-
vates the lockouts. The lockouts consist of a pis ton and cylinder device
28-17
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DST-itDOS-2 - 6-VOL 3
6 May 1986
t the cylinder attached to the base of the a uncher and a pis ton attached to
the vehicle a The pis ton floats freely In the cylinder in the travel
nude. When dcttvated by the pneucrla tic system in the coElba t posi lion, a
clamping device locks die pis ton in the cylinder and forms a rigid connec tion
between the base of the launcher and the vehicle axles.
(UNCLASSIFIED)
LLI'VAT I Chi /1:PAVER:SE
SWI
(UNCLASSIFIED)
Figure XXV ill-17. (U) Manual Controls at Gunner's Station
26-19
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DST-1130S-200-86-VOL 3
6 May 1986
(UNCLASSIFIED)
Figure XXVI
(U) Pneumatic Control
Lever
(UNCLASSIFIED)
u, Rocket-Firing Devices (U).
(1) OH The SM-21 has wo firing devices and can be fired from
either the cab of the vehicle or from a remote position nearby. The
principal device is located in the vehicle cab, and the remote device Is
attached to it by an electrical cable. Essentially, the principal device
(fig XXV1.11-19) is an "intervalomener" tint fires a set number of rockets
(1 to 40) in a fixed sequence, at a fixed 0.5-second interval automatically
or at any desired interval. if each successive rocket is triggered manually.
The remote device (fig XXVIIi-20) is basically a component to trigger the
principal firing device, which is located near the center of the vehicle cab
28-19
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DST-1 tJOS-200-86-VOL 3
6 May 1986
(fig XXVI11-21). The vehicle's I2-V eLectrIcal ystera provides the current
to operate the principal firing device and to fire the rockets. Terminals
are located on top of the device to connect an external power source if
required. Tht principal firing device is operated in the following manner;
The power test button is depressed, and the power indicator light comes on to
indicate the receipt of current. The type-of-fire switch is set in one of
the two positions, either automatic or single. The tube-selector handle is
to clockwise until the number on the dial corresponds to the number of
tubes to be fired. The firing key is Inserted in the firing key receptacle
and turned to either the single or automatic position. The safety button is
depressed, and the firing lever is rotated about one-eighth of a turn to the
right. To fire automatically, the lever must be held in this firing position
until the desired number of rockets has been fired. To fire manually or to
fire single shots, the handle must be moved to the right each time a rocket
is to be fired. The number of rockets fired is shown on the round-counter
dial. The dial is illuminated, and the light comes on when the firing key is
turned to one of the fire positions.
(UNCLASSIFIED)
(UNCLASSIFIED)
Figure XXVIII-I9. (U) BM-21 Firing Device
28-20
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UST-1130S-200-86-VOL 3
6 May 1986
(UNCLASSIFIED)
UNCL AS S I 1* I ED
Figure XXVIII-20. (l1) Remote Firinir, Device
28-21
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DST-11JOS-2(10-66-V(31. 3
6 May 1)a6
(UNCLASSIFIED)
(UNCLASSIFIED)
Figure XXVIII-21. (U) Firing-Device Location in Vehicle Cab
(2) (U) The remote device is carried in a storage bin on the
vehicle and operated in the following manner: The cable is attached to the
firing circuit receptacle mounted on the outside rear of the right side of
the vehicle engine compartment, and a few feet of the cable are unrolled.
The principal firing device is programmed for the number of rockets to be
fired and the type of fire, i.e., automatic or manual-single shots. The
power test button on the principal device is depressed, and if power is
received in the remote element, the signal light comes on. The remote firing
device is then moved to the selected position within the limits of the cable
length of 64 meters, When ready to fire, the firing key is inserted and
turned to either the automatic or single-shot position. The firing crank is
28-22
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