RT-20P / SS-15 SCROOGE
| Specifications | ||
|---|---|---|
| DIA | SS-X-15 (SS-XZ-15) | |
| NATO | Scrooge | |
| Bilateral | ||
| Service | RT-20P RT-20PII - silo version |
|
| OKB/Industry | 8K99 (15II696) | |
| Years of R&D | 1965-1969 | |
| Design Bureau | OKB-586 (Acad. M. K. Yangel) | |
| Approved | 8/24/1965 | |
| Engineering and Testing | 1963-1967/69 | |
| First Flight Test | 10/1967 | |
| IOC | 1969 | |
| Deployment Date | Not deployed 10/__/1969 | |
| Type of Warhead | Single | |
| Warheads | 1 | |
| Yield (Mt) | 0.5 or 1.5 | |
| Payload (t) | 0.545 or 1.410 | |
| Total length (m) | 17.48-17.8 | |
| Total length w/o warhead (m) | 16.2 | |
| Missile Diameter (m) | 1.8 | |
| Launch Weight (t) | 30-30.2 | |
| Fuel Weight (t) | 25.4 | |
| Range (km) | 11000 or 7000-8000 | |
| CEP (m) (Russian Sources) | 2000-4000 | |
| CEP (m) (Western Sources) | 600-1800 | |
| Number of Stages | 2 | |
| Canister length (m) | 18.90 | |
| Canister length w/o front meters (m) | NA | |
| Canister Diameter (m) | 2 | |
| Booster guidance system |
| 1st stage | 2nd stage | |||
| Length (m) | 6.12 | 8.4 | ||
| Body diameter (m) | 1.8 | 1.8 | ||
| Fueled weight (t) | 16.7 | 8.9 | ||
| Dry weight (t) | ||||
| Liquid Engine Designation | N/A | RD-857 (15D12) (8K94) | ||
| Solid Motor Designation | RDTT 15D15 | N/A | ||
| Design Bureau | Acad. M. K. Yangel | |||
| Years of R&D | 1963-1967 terminated | |||
| Propellants | Solid | Liquid Storable | ||
| Fuel | N/A | UDMH | ||
| Oxidizer | N/A | AT=AK-27P, N204, Nitrogen Tetrioxide | ||
| Burning time (sec.) | 210 + 5 | |||
| Thrust Sea Level / Vacuum (Tonnes) |
60 | 114-115 | ||
| Specific Impulse Sea Level/Vacuum (sec.) | ? | 329.5 vacuum |
| Basing Mode | Ground mobile & silo concept (SLBM?) | |
| Hardness | ||
| Launching Technique | Cold | |
| Deployed Boosters | 0 | |
| Test Boosters | ||
| Warheads Deployed | 0 | |
| Deployment Sites | ||
| Training Launchers | ||
| Space Booster Variant | NA |
|
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