R-9
| R-9 | |
|---|---|
|
|
|
| General Information | |
| Type | ICBM |
| Local name | R-9, 8K75 |
| NATO designation | SS-8 Sasin |
| Country of origin |
 Soviet Union
|
| Manufacturer | OKB-1 (Korolev) |
| development | 1959 |
| Commissioning | 1964 |
| Working time | 1976 |
| Technical specifications | |
| length | 26.50 m |
| diameter | 2,680 mm |
| Combat weight | 80,500 kg |
| Drive First stage Second stage |
Liquid rocket engine. Liquid rocket engine |
| Range | 11,000 km |
| Furnishing | |
| steering | Inertial navigation system |
| Warhead | 1 nuclear warhead of 1.65 or 5.0 MT |
| Detonator | Programmed detonator |
| Weapon platforms | Missile silo |
| CEP |
2,000 - 5,000 m |
| Lists on the subject | |
The R-9 ( NATO reporting name SS-8 Sasin , GRAY index 8K75 ) was a Soviet intercontinental ballistic missile from the time of the Cold War .
The first test flight of the two-stage rocket took place in 1961. Both stages, which were connected with a grid structure, used liquid oxygen and the kerosene type RP-1 as fuel. Commissioning began in 1964. The last missile was retired in 1976.
The NATO code name SS-8 Sasin was mistakenly given to the R-26 , of which a dummy was shown at a military parade in 1964. When the error was noticed, however, the R-26 program had already been discontinued, so no new naming took place.
1st generation ICBM in comparison
| Country | USSR | United States | |||
| rocket | R-7 / R-7A | R-16 / R-16U | R-9A | SM-65 Atlas (-D / -E / -F) | SM-68 Titan I |
| developer | OKB-1 ( Korolev ) | OKB-586 ( Jangel ) | OKB-1 (Korolev) | Convair | Glenn L. Martin Company |
| Start of development | 1954/1958 | 1956/1960 | 1959 | 1954 | 1958 |
| first operational readiness | 1959/1960 | 1961/1963 | 1964/1964 | 1959/1961/1962 | 1962 |
| Retirement until | 1968 | 1976/1976 | 1976 | 1964/1965/1965 | 1965 |
| Range (km) | 8,000 / 9,500-12,000 | 11,000-13,000 | 12,500 | n / A | 10,000 |
| control | radio-inertial | inertial | radio-inertial | radio-inertial / inertial | radio-inertial / inertial |
| Scattering circle radius (km) | 10 | 4.3 | 8-10 | n / A | <1.8 |
| Takeoff mass (t) | 280/276 | 141/147 | 80 | 118/122/122 | 103 |
| stages | 1.5 | 2 | 2 | 1.5 | 2 |
| Fuel combination | Kerosene / LOX | UDMH / nitric acid | Kerosene / LOX | Kerosene / LOX | Kerosene / LOX |
| Stationing type | launch pad | Launch ramp / silo | Launch ramp / silo | Launch ramp / bunker / silo | silo |
| maximum overpressure ( psi ; protection of the starting system in the event of an explosion) | n / a | n / a / 28 | n / a / 28 | kA / 25/100 | 100 |
| reaction time | about 24 h | 10 min - several hours | 20 min / 8-10 min | 15-20 min | 15-20 min |
| Warranty period (years with highest alert) | n / a | 30 days (fueled) | 1 | n / a | 5 |
| Explosive strength of the warhead ( MT ) | 3-5 | 3-6 | 5 | 1.44 / 3.75 / 3.75 | 3.75 |
| Max. stationed number | 6th | 186 | 23 | 30/27/72 | 54 |
Web links
- R-9 in the Encyclopedia Astronautica (English)
Individual evidence
- ↑ a b c d e P. Podvig (Ed.): Russian Strategic Nuclear Forces. MIT Press, 2004, ISBN 978-0-262-16202-9 .
- ↑ a b c S. J. Zaloga : The Kremlin's Nuclear Sword - The Rise and Fall of Russia's Strategic Nuclear Forces, 1945-2000. Smithsonian Institution Press, 2001, ISBN 1-58834-007-4 .
- ↑ a b c d e Nuclear Notebook: US and Soviet / Russian intercontinental ballistic missiles, 1959–2008
- ^ A b David Stumpf Titan II - A History of a Cold War Missile Program . University of Arkansas Press, 2000. ISBN 1-55728-601-9