R-36 / SS-9 SCARP
| Specifications | ||||
|---|---|---|---|---|
| Mod-1 | Mod-2 | Mod-3 | Mod-4 | |
| DIA | SS-9 | SS-9 | SS-9 | SS-9 |
| NATO | Scarp | Scarp | Scarp/ FOBS | Scarp/ MRV |
| Bilateral | ||||
| Service | R-36 | R-36 | R-36O | R-36P |
| OKB/Industry | 8K67 | 8K67 | 8K69 | 8K67P |
| Design Bureau | OKB-586 (Acad. M. K. Yangel) | OKB-586 (Acad. M. K. Yangel) | OKB-586 (Acad. M. K. Yangel) | OKB-586 (Acad. M. K. Yangel) |
| Approved | 4/16/1962 | 4/16/1962 | 1/12/1965 | |
| Years of R&D | 1962-1966 | 1967- 1968 | ||
| Engineering and Testing | 1963-1966 | 1963-1966 | 1965-1969 | 1968-1970 |
| First Flight Test | 9/23/1963 | 10/10/1964 | 12/16/65 | 8/23/1968 |
| IOC | 11/05/1966 | 1966 | 08/25/66 | 1970 |
| Deployment Date | 7/21/1967 & | 7/21/1967 | 11/19/68 | 10/26/1970 |
| Type of Warhead | Single | Single | Orbital | Multiple |
| Warheads | 1 | 1 | 1 | 3 |
| Yield (Mt) (Russian Sources) |
5 | 10 | 5 | 2.0-3.5 |
| Yield (Mt) (Western Sources) |
12-18 | 18-25 | 1-3 | |
| Payload (t) | 5.825 | 3.95 | 1.7 | 6 |
| Total length (m) | 32.2 | 31.7 | 32.6-34.5 | 32.2 |
| Total length w/o warhead (m) | ||||
| Missile Diameter (m) | 3.0 | 3.0 | 3.0 | 3.0 |
| Launch Weight (t) | 183.9 | 179 -183.89 | 180 | 183.9 |
| Fuel Weight (t) | 166.9-170.2 | 166.2 | 166.2 | 166.2 |
| Range(km) | 10,200 | 15,200-15,500 | 40,000 | 10,200-12,000 |
| CEP (m) (Russian Sources) |
1,300-1,900 | 1,300-1,900 | 1,100 | 1,340-1,970 |
| CEP (m) (Western Sources) |
900-920 | 920 | 1,800-5,500 | 1,850 |
| Number of Stages | 2 |
| Canister length (m) | |
| Canister length w/o front meters (m) |
|
| Canister diameter (m) | |
| Booster guidance system | Inertial, autonomous |
| 1st stage | 2nd stage | |
|---|---|---|
| Length (m) | 18.9 | 9.4 |
| Body diameter (m) | 3 | 3 |
| Fueled weight (t) | 121.7 -122.3 (118.7) | 48.5 - 49.3 |
| Dry weight (t) | 6.4 | 3.7 Total =17.737 |
| Engine Designation | RD-251 (8D723) | RD-252 |
| Design Bureau | Acad. V. P.Glushko (OKB-456) | Acad. V. P. Glushko (OKB-456) |
| Configuration | Cluster of three main engines, 6 chambers | One engine 2 chambers |
| Configuration | Yuzhnoy | Yuzhnoy |
| RD-68M / RD-855 | RD-854 | |
| One engine 4 chambers | One engine 4 chambers | |
| Propellants | Liquid Storable | Liquid Storable |
| Fuel | UDMH | UDMH |
| Oxidizer | AT =Nitrogen tetroxide | AT=Nitrogen tetroxide = NTO |
| Main Engines Burning time (sec.) | 120, | 160 |
| Verniers Burning time (sec.) | 127 | 163 |
| Verniers Thrust Sea Level/Vacuum (Tonnes) | Yuzhnoy RD-68M / | Yuzhnoy RD-69M / |
| RD-855 | RD-856 | |
| 29.1 | 5.53 | |
| Main engines Thrust Sea Level/Vacuum (Tonnes) | 241 / 270.4 | 96 Vacuum |
| Total Thrust Sea Level/Vacuum (Tonnes) | 270.1 / 303 | 101.53 B 102.9982 |
| Vernier Engine Specific Impulse Sea Level/Vacuum (sec.) | Vernier Engine | Vernier Engine |
| 254 / 292 | 280.5 Vacuum | |
| Main Engines Specific Impulse Sea Level/Vacuum (sec.) | Main Engines | Main Engine |
| 269 -270 /301 | 317.6 Vacuum |
| Basing Mode | Silo |
| Hardness | |
| Launching Technique | Hot launch |
| Deployed boosters | 0 |
| Test Boosters | |
| Warheads Deployed | 0 |
| Training Launchers | |
| Space Booster Variant | Yes - SL-10 / F-1-r, Mod-3, FOBS SL-11 / F-1-m, Tsyklon - 2 SL-14 / F-2, Tsyklon - 3 |
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