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| UR-200 SS-10 Scrag | |
|---|---|
 | |
| Type | Intercontinental ballistic missile |
| Place of origin | Soviet Union |
| Service history | |
| In service | 1963-1964 |
| Production history | |
| Designer | OKB-52 |
| Designed | 1962 |
| Specifications (8K81[3]) | |
| Mass | 135,710 kg (299,190 lb) |
| Height | 34.65 m (113.7 ft) |
| Diameter | 3 m (9.8 ft) |
| Wingspan | 4.2 m (14 ft) |
| Warhead | Nuclear warhead |
| Engine | First stage, RD-0202 liquid-fuel rocket Second stage, RD-0205 liquid-fuel rocket First stage, 2,236 kN (503,000 lbf)[1] Second stage, 606.4 kN (136,300 lbf)[2] |
| Propellant | N2O4 / UDMH |
Operational range | 12,000 kilometres (7,500 mi) |
| Flight ceiling | 185 km (115 mi) apogee |
| Maximum speed | Mach 20 (24,500 km/h; 15,200 mph; 6.81 km/s) |
Guidance system | Inertial |
The UR-200 was an intercontinental ballistic missile (ICBM) developed by Vladimir Chelomey's OKB-52 in the Soviet Union. It was known during the Cold War by the NATO reporting name SS-10 Scrag and internally by the GRAU index 8K81. The design was authorized by the Decisions of the Central Committee of the CPSU of March 16 and August 1, 1961, and the draft project was finished in July[clarification needed] 1962. It first flew on November 4, 1963, from the Baikonur Cosmodrome. The ninth and final flight was conducted on October 20, 1964.