Specifications | ||||
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DIA |
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NATO |
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Bilateral |
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Service |
RT-1 |
RT-1-63 |
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OKB/Industry |
(8k95-63) |
(8K95-1963) |
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Design Bureau |
OKB-1, Acad. S. P. Korolev |
OKB-1, Acad. S. P. Korolev |
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Approved |
11-20-59 |
11-20-59 |
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Years of R&D |
1958/59 -1962 |
1962,-1963/1964 |
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Engineering and Testing |
1960 –1963 |
1962 -1963 |
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First Flight Test |
04/28/1962 failure 3/18/1963 success cancelled |
9-11/ /1965, 2 failures one success cancelled |
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IOC |
N/A |
N/A |
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Deployment Date |
N/A |
N/A |
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Type of Warhead |
Single |
Single |
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Warheads |
1 |
1 |
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Yield (Mt) |
0.5 -1.0 |
0.6 -1.0 |
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Payload (t) |
0.5 - 0.8 |
0.8 |
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Total length (m) |
18.0 |
18.3 |
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Total length w/o warhead (m) |
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Missile Diameter (m) |
2.0 |
2.0 |
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Launch Weight (t) |
35.5-36.0 (34) |
34 –35.5 |
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Fuel Weight (t) |
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Range (km) |
1,850-2,000 |
2,400-2,500 |
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CEP (m) (Russian Sources) |
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CEP (m) Western Sources) |
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Number of Stages |
3 |
3 |
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Canister length (m) |
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Canister length w/o front meters (m) |
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Canister diameter (m) |
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Booster guidance system |
Inertial |
Inertial |
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1st stage |
2nd stage |
3rd Stage |
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Length (m) |
4.6-4.8 |
3.9-4.0 |
2.8 |
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Body diameter (m) |
1.6 x 4 |
1.5 x 4 |
1.4 |
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Fueled weight (t) |
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Dry weight (t) |
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Engine Designation |
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configuration |
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Design Bureau |
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Years of R & D |
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Propellants |
Solid Propellant |
Solid Propellant |
Solid Propellant |
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Fuel |
Solid Propellant |
Solid Propellant |
Solid Propellant |
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Oxidizer |
Solid Propellant |
Solid Propellant |
Solid Propellant |
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Burning time (sec.) |
30 -32 |
17.5 -30 |
30 - 42 |
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Thrust Sea Level/Vacuum (Tonnes) |
100 |
51 |
25 |
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Specific Impulse Sea Level/Vacuum (sec.) |
204 |
223 |
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Basing Mode |
N/A |
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Hardness |
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Launching Technique |
Hot Launch |
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Deployed boosters |
0 |
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Test Boosters |
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Warheads Deployed |
0 |
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Deployment Sites |
0 |
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Training Launchers |
0 |
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Space Booster Variant |
N/A |
