R-5 / SS-3 SHYSTER
| Specifications | ||
|---|---|---|
| DIA | SS-3m | |
| NATO | Shyster | |
| Bilateral | R-5 | |
| Service | R-5M | |
| OKB/Industry | 8K51 (8A62M) | |
| Design Bureau | (OKB-I), NII-88, (Acad. S. P. Korolev) | |
| Approved | 4/10/1954 | |
| Years of R&D | ||
| Engineering and Testing | 1955-1956 | |
| First Flight Test | 1/21/1955 | |
| IOC | 1956 | |
| Deployment Date | 6/2/1956 | |
| First public display | November 1957 | |
| Phase-out completed | 1967 | |
| Type of Warhead | Single | |
| Warheads | 1 | |
| Yield (Mt) | 1x0.08 - 0.3 MT. | |
| Payload (t) | 1.350 | |
| Total length (m) | 20.747 - 20.8 | |
| Missile Diameter (m) | 1,652 | |
| Diameter of Stabilizers (m) | 3.452 | |
| Launch Weight (t) | 28.9-29.1 | |
| Fuel Weight (t) | 24.4 | |
| Dry weight (t) | 4,39 | |
| Range(km) | 1200 | |
| CEP (m) (Russian Sources) | 1500 m downrange and 1250 m cross range | |
| CEP (m) (Western Sources) | 2500-5000 | |
| Number of Stages | 1 | |
| Booster guidance system | Autonomous/inertial plus radio-control | |
| Engine Designation | RD-103M, 8D52 | |
| Design Bureau | Acad. V. P. Glushko OKB-456 | |
| Years of R & D | 1952-53 | |
| Propellant | Liquid | |
| Fuel | 92% Ethyl Alcohol/water solution | |
| Oxidizer | Liquid Oxygen | |
| Burning time (sec.) | 115.4 | |
| Thrust Sea Level/Vacuum (Tonnes) | 43.86 - 44 / 50.9892 - 51 | |
| Specific Impulse (sec.) Sea Level/Vacuum |
219 -220 / 243 -248 | |
| Basing Mode | Ground-Based | |
| Launching Technique | Hot Launch | |
| Deployed boosters | 0 | |
| Test Boosters | ||
| Warheads Deployed | 0 | |
| Deployment Sites | ||
| Training Launchers | ||
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