UR-100 / SS-11 SEGO
| Specifications | ||||||
|---|---|---|---|---|---|---|
| Mod-1 | Mod-2 | Mod-3 | Mod-4 | |||
| DIA | SS-11 | SS-11 | SS-11 | SS-11 | ||
| NATO | Sego | Sego | Sego | Sego | ||
| Bilateral | RS-10 | RS-10 | RS-10M | RS-10M | ||
| Service | UR-100/ UR-100M |
UR-100K | UR-100U | |||
| OKB/Industry | 8K84 8K84UTTkh |
8K84K | 8K84UTTkh 8K84M 15A20U | |||
| Design Bureau | OKB-52 Chelomey |
OKB-52 Chelomey |
OKB-52 Chelomey |
OKB-52 Chelomey |
||
| Approved | 3/30/1963 | |||||
| Years of R&D | 1951-66 | |||||
| Engineering and Testing | 1962-66 | 1969-1971 | 1971-1973 | 1971-1973 | ||
| First Flight Test | 4/19/65 | 7/23/1969 | 2/2/71 & 9/2/69 | 6/16/71 | ||
| IOC | 11/24/966 | 3/1/1970 | 1973 - 74 | [not deployed] | ||
| Deployment Date | 7/21/1967 | 12/28/72 | 9/26/1974 | [not deployed] | ||
| Type of Warhead | Single | Single | MRV | MRV | ||
| Warheads | 1 | 1 | 3 | 6 | ||
| Yield per Warhead (Mt) (Russian Sources) |
0.5 or 1.0 -1.1 |
1.2 | 0.35 | 0.35-1.3 | ||
| Yield per Warhead (Mt) (Western Sources) |
0.6 to 1.2 | 0.6 to 1.2 | 0.2 to 0.8 | |||
| Payload (t) | 0.76 - .08 | 0.9-1.2 | 1.208 | 1.2 | ||
| Total length (m) | 16.925 | 18.9 - 19.0 | 18.9 | 19.1 - 19.8 | ||
| Total length w/o Warhead (m) |
16.45-16.69 | 16.5 | 17 | 17 | ||
| Missile Diameter (m) | 2 | 2. | 2 | 2 | ||
| Launch Weight (t) | 39.4 - 42.3 | 50.1 | 50.09 - 50.1 | 50.1 - 51.24 | ||
| Fuel Weight (t) | 40.4? | 45.3 | 45.3 | 45.3 | ||
| Range (km) | 11,000-12,000 or 5,000 |
11,000-13,000 | 10,600-12,000 | 10,600-12,000 | ||
| CEP (m) (Russian Sources) |
1,400 | 1,400 | 900-1,350 | 900-1,350 | ||
| CEP (m) (Western Sources) |
1,400-1,500 | 1,100-1,400 | 1,000-1,100 | |||
| Number of Stages | 2 |
| Canister length (m) | 19.5 |
| Canister length w/o Front meters (m) |
|
| Canister diameter (m) | 2.9 |
| Booster guidance system | Inertial, autonomous |
| 1st stage (8S816) | 2nd stage (8S817) | |||||
|---|---|---|---|---|---|---|
| Mod-1 | Mod-2 | Mod-3/4 | Mod-1 | Mod-2 | Mod-3/4 | |
| Length (m) | 12.5 | 13.3 | 13.4 | 2.9 | 3.2 | 3.8 |
| Body diameter (m) | 2 | 2 | ||||
| Fueled weight (t) | 34 | 38-40 | 40 | |||
| Dry weight (t) | ||||||
| Engine Designation |
RD-0216 / RD-0217 (15D2) |
RD-0235 / RD-0236 (8D13, 8D419, 15D14) |
||||
| Design Bureau | OKB-154, Acad. S. A. Kosberg | OKB-117, Acad. V. Klimov | ||||
| Configuration | Cluster of four engines | One engine | ||||
| Years of R & D | 1963-1966 | |||||
| Propellants | Liquid | Liquid | ||||
| Fuel | UDMH | UDMH | ||||
| Oxidizer | Nitrogen Tetroxide | Nitrogen Tetroxide | ||||
| Burning time (sec) | 103? | 164? | ||||
| Verniers Thrust Sea Level/ Vacuum (Tonnes) | N/A | 1.565 ? 1.6 | ||||
| Main Engines Thrust Sea Level/Vacuum (Tonnes) | 79.95/86.275 - 89.33 | 13.665 - 15.195 - 24.5 Vacuum | ||||
| Total Thrust Sea Level/Vacuum (Tonnes) | 319.8/357.6 | 20.0651 - 22.3 - 30.9 Vacuum | ||||
| Main engine Specific Impulse Sea Level/Vacuum (sec.) | 262/313 Vacuum | 320 Vacuum | ||||
| Verniers Specific Impulse Sera Level/Vacuum (sec.) | N/A | 293 Vacuum | ||||
| Basing Mode | Silo |
| Hardness | Silo at 700-750 psi LCC at 360-400 psi |
| Launching Technique | Hot |
| Deployed Boosters | |
| Test Boosters | |
| Deployment Sites | |
| Training Launchers | |
| Space Booster Variant | No |
|
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