BUILDER(S)
Shahid Hemat Industrial Group, Tehran, Iran (design bureau)
Shahid Bagheri Industrial Group, Tehran, Iran (design bureau)
Acad. V.P. Makeyev OKB, Russia (original Scud-B design bureau)
Isayev OKB, Russia (original engine design)
Great Wall Industries Corp., China (guidance control, solid-propellant
motor technology, telemetry equipment)
State factories, North Korea (imported rocket motors)
USERS/PLATFORMS
Iran
CHARACTERISTICS
WEIGHTS
Launch mass 34,948-35,825 lb (15,852-16,250 kg)
Dry mass 3,924- 4,806 lb ( 1,780- 2,180 kg)
Stage mass 33,272 lb (15,092 kg)
Warhead 1,676 lb ( 760 kg)
or 2,176 lb ( 987 kg)
or 2,553 lb ( 1,158 kg)
DIMENSIONS
Length 52 ft 6 in (16.00 m)
Diameter 4 ft 5 in ( 1.35 m)
Configuration cylinder with tapered nosecone, slightly
smaller diameter cylinder at rear of
missile, four clipped delta tail fins
PROPULSION
Engine single-stage one-chamber liquid-propellant
rocket
Thrust
effective 57,433 lb (26,051 kg)
actual 58,996 lb (26,760 kg)
Fuel TM-185 (20/80 gasoline/kerosene)
Oxidizer AK-27I (27/73 dinotrogen tetroxide/nitric
acid with imodium inhibitor
Propellant mass 28,466 mi (12,912 kg)
GUIDANCE
Type inertial
PERFORMANCE
Range 810 nm (932 mi, 1,500 km) max est.
CEP 208 yd (190 m)
Launch preparation unknown, probably around 60 min
Burn time 110 sec
Deployment mobile
TEL speed 44 mph (70 kmh)
TEL range 342 mi (550 km)
WARHEAD
Nuclear possible, though no known warheads in Iran
Chemical capable of carrying chemical warheads
Conventional 2,553 lb (1,158 kg) HE
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