Dnepr (rocket)
| Function | Orbital carrier rocket |
|---|---|
| Manufacturer |
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| Country of origin | Soviet Union (original build), Ukraine (commercial launches after 1999) |
| Cost per launch | US$29 million |
| Size | |
| Height | 34.3 m (113 ft) |
| Diameter | 3 m (9.8 ft) |
| Mass | 211,000 kg (465,000 lb) |
| Stages | 3 |
| Capacity | |
| Payload to LEO | |
| Mass | 4,500 kilograms (9,900 lb) |
| Payload to the ISS | |
| Mass | 3,200 kilograms (7,100 lb) |
| Payload to SSO | |
| Mass | 2,300 kilograms (5,100 lb) |
| Payload to TLI | |
| Mass | 550 kilograms (1,210 lb) (with ST-1) |
| Associated rockets | |
| Based on |
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| Launch history | |
| Status | Retired |
| Launch sites | Site 109/95, Baikonur LC-13, Yasny |
| Total launches | 22 |
| Success(es) | 21 |
| Failure(s) | 1 |
| First flight | 21 April 1999 |
| Last flight | 25 March 2015 |
| First stage | |
| Powered by | 1 RD-264 module (four RD-263 engines) |
| Maximum thrust | 4,520 kN (1,020,000 lbf) |
| Specific impulse | 318 s (3.12 km/s) |
| Burn time | 130 seconds |
| Propellant | N2O4 / UDMH |
| Second stage | |
| Powered by | 1 RD-0255 module (one RD-0256 main engine and one RD-0257 vernier) |
| Maximum thrust | 755 kN (170,000 lbf) |
| Specific impulse | 340 s (3.3 km/s) |
| Burn time | 190 seconds |
| Propellant | N2O4 / UDMH |
| Third stage | |
| Powered by | 1 RD-864 |
| Maximum thrust | 20.2 kN (4,500 lbf) |
| Specific impulse | 309 s (3.03 km/s) |
| Burn time | 1,000 seconds |
| Propellant | N2O4 / UDMH |
The Dnepr rocket (Russian: Днепр, romanized: Dnepr; Ukrainian: Дніпро, romanized: Dnipró) was a space launch vehicle named after the Dnieper River. It was a converted ICBM used for launching artificial satellites into orbit, operated by launch service provider ISC Kosmotras. The first launch, on April 21, 1999, successfully placed UoSAT-12, a 350 kg demonstration mini-satellite, into a 650 km circular Low Earth orbit.