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Weapons of Mass Destruction (WMD)


GR-1 / SS-X-10 SCRAG


Specifications
DIA  
NATO Scrag
Bilateral  
Service GR-1
OKB/Industry 8K713
Design Bureau OKB-1 (Acad. S. P. Korolev)
Approved 9/24/1962
Years of R&D  
Engineering and Testing  
First Flight Test 10/20/64 One to eight flights suggested. All missed through 1967 by U.S. Intelligence.
IOC Canceled 11/19/68
Deployment Date Not deployed
Type of Warhead Single/Orbital
Warheads 1
Yield 2.2
Payload 2.5
Total length 35.305
Total length w/o warhead 33.9
Missile Diameter (m) 2.85
Launch Weight (t) 116
Fuel Weight (t) 1st 116 -38.94, = 77.06
2nd 30.76 -10.24,= 20.52
3rd 7.44 -3.84 = 3.6
Total 101.18
Dry weight total (t) 14.82 - 2.5 payload mass = 12.32
Range (km) 12,000/40,000
CEP (m) (Russian Sources) 5,000/3,000
CEP (m) (Western Sources)  


Number of Stages 3
Canister length (m) N/A
Canister length w/o
front meters (m)
N/A
Canister diameter (m) N/A
Booster Guidance System Inertial autonomous


  1st stage 2nd stage 3rdstage
Length (m) 18.0 7.7 6.4
Body diameter (m) 2.85 2.7 2.35
Fueled weight (t) 77.06 20.52 3.6
Dry weight (t) 8.18 2.8 1.34
Engine Designation NK-9 (8D717) NK-9V /
(NK-19)
Derivation of the
S1.5400, 8D726
Design Bureau Acad. N. D. Kuznetsov, OKB-276 Acad. N. D. Kuznetsov, OKB-276 Acad. A.M.
Isayev,
OKB-2


Years of R&D 1959-1965 1959-1965 1962-1965
Propellants Liquid Liquid Liquid
Liquid Fuel RG-1, Kerosene RG-1, Kerosene RG-1,
Kerosene
Oxidizer Oxygen Oxygen Oxygen
Burning time (sec.)      
Thrust Sea Level/Vacuum (tonnes) 4 x 36.5=147/ 4 x 38=152 44.6-45-46.1 6.87-8.5
Specific Impulse Level/Vacuum (sec.) 285 - 327 330 - 341 344


Basing Mode Silo
Hardness  
Launching Technique Hot Launch
Deployed Boosters 0
Test Boosters 1-8?
Warheads Deployed 0
Deployment Sites 0
Training Launchers 0
Space Booster Variant Yes GR-1



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