Dnepr (rocket)

Dnepr

Function	Orbital carrier rocket
Manufacturer	Yuzhnoye Design Bureau (design) Yuzhmash (manufacturing) Khartron (control system)
Country of origin	Soviet Union (original build), Ukraine (commercial launches after 1999)
Cost per launch	US$29 million [1]
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	R-36M
Launch history
Status	Retired[1]
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
[edit on Wikidata]

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.^[2][3]