UR-200 / SS-X-10 SCRAG
| Specifications | ||||||
|---|---|---|---|---|---|---|
| DIA | SS-X-10 | |||||
| NATO | N/A | |||||
| Bilateral | N/A | |||||
| Service | UR-200/UR-200B | |||||
| OKB/Industry | 8K81/8K83 | |||||
| Design Bureau | OKB-52 , KB Salyut, Acad V. N. Chelomey | |||||
| Approved | 3/16/1961 & 8/1/1961 | |||||
| Years of R&D | 1961-1964 | |||||
| Engineering and Testing | 1963-1964 | |||||
| First Flight Test | 11/4/1963 | |||||
| IOC | Not operational | |||||
| Deployment Date | Not deployed, terminated 1964/1965 | |||||
| Type of Warhead | 1 | |||||
| Warheads | Single | |||||
| Yield (Mt) | 5 & 15 | |||||
| Payload (t) | 2.690 - 3.9 - 4.0 | |||||
| Total length | 34.65 | |||||
| Total length w/o warhead | 30 - 32 | |||||
| Missile Diameter | 3 | |||||
| Diameter of Stabilizers | 4.2 | |||||
| Launch Weight (t) | 136 -138 | |||||
| Fuel Weight (t) | ||||||
| Range (km) | 12000 & 14000 | |||||
| CEP (m) (Russian Sources) | ||||||
| CEP (m) (Western Sources) | 1800-5500 | |||||
| Number of Stages | 2 | |||||
| Canister length (m) | ||||||
| Canister length w/o Front meters (m) |
||||||
| Canister diameter (m) | ||||||
| Booster guidance system | Inertial autonomous with radio correction | |||||
| 1st stage | 2nd stage | |||
|---|---|---|---|---|
| Length (m) | 16.9 - 19.4 | 12.9 | ||
| Body diameter (m) | 3 | 2.2 | ||
| Fueled weight (t) | ||||
| Dry weight (t) | ||||
| Engine Designation Main Engines | RD-0203/RD-0204 (8D44/8D45) |
RD-0206/RD-0207 (8D46) | ||
| Vernier Engine Designation | N/A | Four Verniers | ||
| Design Bureau | OKB-154, Acad. S, A, Kosberg | OKB-154, Acad. S, A, Kosberg | ||
| Configuration | Cluster of Four Engine | One Main Engine and Four Verniers | ||
| Years Of R & D | 1961-1964 | 1961-1964 | ||
| Propellants | Liquid | Liquid | ||
| Fuel | UDMH | UDMH | ||
| Oxidizer | (AT) Nitrogen Tetroxide | (AT) Nitrogen Tetroxide | ||
| Burning time (sec.) | ||||
| Main Engine Thrust Sea Level/Vacuum (Tonnes) | 50.0/57.0 | 58.7 Vacuum | ||
| Vernier Engine Thrust Sea Level/Vacuum (Tonnes) | N/A | 3.1 Vacuum | ||
| Total Thrust Sea Level/Vacuum (Tonnes) | 200 | 62.5 - 71.1 Vacuum | ||
| Specific Impulse Main Engines (sec.) | 278/311 | 297 | ||
| Specific Impulse Vernier engine (sec.) | N/A | 322 - 326 |
| Basing Mode | Soft Site Land Based | |
| Hardness | N/.A | |
| Launching Technique | Hot | |
| Deployed Boosters | N/A | |
| Test Boosters | ||
| Warheads Deployed | ||
| Deployment Sites | N/A | |
| Training Launchers | N/A | |
| Space Booster Variant | No |
|
NEWSLETTER
|
| Join the GlobalSecurity.org mailing list |
|
|
|
