Rokot
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; The contract with European Space Agency (ESA) for launching Swarm in September 2013 was worth €27.1 million (US$36 million).
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) |
| Maximum thrust | 2,080 kN (470,000 lbf) |
| 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) |
| Maximum thrust | 255.76 kN (57,500 lbf) |
| 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 | 325 seconds |
| Burn time | 3000 seconds |
| Propellant | N2O4 / UDMH |