UR-100N / SS-19 STILLETO
| Specifications | ||||||
|---|---|---|---|---|---|---|
| Mod-1 | Mod-2 | Mod-3 | ||||
| DIA | SS-19 | SS-19 | SS-19 | |||
| NATO | Stiletto | Stiletto | Stiletto | |||
| Bilateral | RS-18A | RS-18A UTTKh | RS-18B | |||
| Service | UR-100N | UR-100N | UR-100NU | |||
| OKB/Industry | 15A30 | 15A30 | 15A35 | |||
| Design Bureau | OKB-52, KB Salyut, Acad. V. N. Chelomey |
OKB-52, KB Salyut, Acad. V. N. Chelomey |
OKB-52, KB Salyut, Acad. V. N. Chelomey |
|||
| Approved | 8/19/1970 | 8/19/1970 | 8/16/1976 | |||
| Years of R&D | 1964-73 | 1964-1973 | ||||
| Engineering and Testing |
1973-75 | 1973-75 | 1977-79 | |||
| First Flight Test | 9/15/1972 failure & 12/28/1973 success | 4/9/1973 | 10/26/1977 | |||
| IOC | 4/26/1975 | 1975 | 1979 | |||
| Deployment Date | 12/301975 | 12/30/1975 | 11/5/1979 | |||
| Type of Warhead | MIRV | Single | MIRV | |||
| Warheads | 6 | 1 | 6 | |||
| Yield per Warhead (Mt) | 0.5 0.55 0.750 | 2.5 - 5.0 | 0.5-0.75 | |||
| Payload (t) | 4.350 | 4.350 | 4.350 | |||
| Total length (m) | 24.0 | 24.0 | 24.3 | |||
| Total length w/o Warhead (m) |
21.1 | 21.1 | 21.1 | |||
| Missile Diameter (m) | 2.50 | 2.50 | 2.50 | |||
| Launch Weight (t) | 103 - 105.6 | 105.6 | 103.4 - 105.6 | |||
| Fuel Weight (t) | 93.1 | 93.1 | 93.1 | |||
| Range (km) | 9,650 | 10,000 | 10,000 | |||
| CEP (m) (Russian Sources) |
? | ? | 920 | |||
| CEP (m) (Western Sources) |
350-550 | 250-400 | 220-380 | |||
| Number of Stages | 2 |
| Canister length (m) | 19.4 |
| Canister length w/o front meters (m) |
|
| Canister diameter (m) | 2.9 |
| Booster guidance system | Inertial |
| 1st stage | 2nd stage | 3rd. Stage | |
|---|---|---|---|
| Length (m) | 17.2 | 2.8 | |
| Body diameter (m) | 2.5 | 2.5 | 2.5 |
| Fueled weight (t) | 86.3 | 86.3 | |
| Dry weight (t) | |||
| Engine Designation | RD-0233 / RD-0234 | RD-0235 (14/15D113) | N/A |
| Vernier Engine Designation | N/A | RD-0236 (15D114) | N/A |
| Bus Engine Designation Third Stage | N/A | N/A | RD-0237 |
| Design Bureau Main Engines | OKB-154, Acad. S. A. Kosberg | OKB-154, Acad. S. A. Kosberg | N/A |
| Design Bureau Vernier Engine | N/A | OKB-154, Acad. S. A. Kosberg | N/A |
| Design Bureau Bus Engine Third Stage | N/A | N/A | OKB-154, Acad. S. A. Kosberg |
| Configuration | Cluster of four engines | One engine | N/A |
| Configuration Vernier Engine | N/A | Four vernier chambers | N/A |
| Configuration Bus engine Third Stage | N/A | N/A | Four chambers |
| Years of R & D | 1969 1974 | 1969 - 1974 | N/A |
| Years of R & D Vernier Engine | N/A | 1969 - 1974 | N/A |
| Years of R & D Bus Engine Third Stage | N/A | N/A | 1969 - 1974 |
| Propellants | Liquid | Liquid | Liquid |
| Fuel | UHMH | UDMH | UDMH |
| Oxidizer | Nitrogen Tetroxide | Nitrogen Tetroxide | Nitrogen Tetroxide |
| Burning time (sec.) | |||
| Main Engine Thrust Sea Level/Vacuum (Tonnes) | 46.961/52.958 - 53.1 | 24.5 Vacuum | N/A |
| Verniers Thrust Sea Level/Vacuum (Tonnes) | N/A | 1.6 Vacuum | N/A |
| Third Stage Bus Engine Thrust Vacuum (Tonnes) | N/A | N/A | 0.5 Vacuum |
| Total Thrust Sea Level/Vacuum (Tonnes) | 187.8442/207.8319 | 30.9 Vacuum | 2.0 Vacuum |
| Main Engine Specific Impulse Sea Level/ Vacuum (sec.) | 291 / 310 | 320 Vacuum | N/A |
| Vernier Engine Specific Impulse Sea Level/Vacuum (sec.) | N/A | 293 Vacuum | N/A |
| Bus Third Stage Engine Specific Impulse Vacuum (sec.) | N/A | N/A | ? |
| Basing Mode | Silo |
| Hardness | |
| Launching Technique | Hot |
| Deployed Boosters | |
| Test Boosters | |
| Warheads Deployed | |
| Training Launchers | |
| Space Booster Variant | Yes SL-X- ? , Rockot |
|
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