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Rokot
Russian space launch vehicle / From Wikipedia, the free encyclopedia
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Rokot (Russian: Рокот meaning Rumble or Boom), also transliterated Rockot, was a Soviet Union (later Russian) space launch vehicle that was capable of launching a payload of 1,950 kilograms (4,300 lb) into a 200-kilometre (120 mi) Earth orbit with 63° inclination. It was based on the UR-100N (SS-19 Stiletto) intercontinental ballistic missile (ICBM), supplied and operated by Khrunichev State Research and Production Space Center. The first launches started in the 1990s from Baikonur Cosmodrome out of a silo. Later commercial launches commenced from Plesetsk Cosmodrome using a launch ramp specially rebuilt from one for the Kosmos-3M launch vehicle. The cost of the launcher itself was about US$15 million in 1999;[6][7] The contract with European Space Agency (ESA) for launching Swarm in September 2013 was worth €27.1 million (US$36 million).[8]
![]() Rokot launch vehicle | |
Function | Orbital launch vehicle |
---|---|
Manufacturer | Khrunichev State Research and Production Space Center |
Country of origin | Soviet Union |
Cost per launch | US$41.8 million |
Size | |
Height | 29 m (95 ft) |
Diameter | 2.5 m (8 ft 2 in) |
Mass | 107,000 kg (236,000 lb) |
Stages | 3 |
Capacity | |
Payload to Low Earth orbit | |
Mass | 1,950 kg (4,300 lb) |
Payload to Sun-synchronous orbit | |
Mass | 1,200 kg (2,600 lb) |
Launch history | |
Status | Retired |
Launch sites | Baikonur 175/1 Plesetsk 133/3 |
Total launches | 34 |
Success(es) | 31 |
Failure(s) | 2 |
Partial failure(s) | 1 |
First flight | 20 November 1990 26 December 1994 (orbital) |
Last flight | 26 December 2019 |
First stage | |
Diameter | 2.5 m (8 ft 2 in) |
Powered by | 3 RD-0233 (15D95) 1 RD-0234 (15D96) [1][2] |
Maximum thrust | 2,080 kN (470,000 lbf) [3] |
Specific impulse | 310 seconds |
Burn time | 120 seconds |
Propellant | N2O4 / UDMH |
Second stage | |
Diameter | 2.5 m (8 ft 2 in) |
Powered by | 1 RD-0235 (15D113) 1 RD-0236 (15D114) [1][2] |
Maximum thrust | 255.76 kN (57,500 lbf) [4][5] |
Specific impulse | 310 seconds |
Burn time | 180 seconds |
Propellant | N2O4 / UDMH |
Third stage – Briz-KM | |
Powered by | 1 S5.98M |
Maximum thrust | 19.6 kN (4,400 lbf) |
Specific impulse | 326 seconds |
Burn time | 3000 seconds |
Propellant | N2O4 / UDMH |