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Launch vehicle DNEPR

It is designed for spacecraft launching to circular and elliptic near Earth orbit with inclination of 65.50 deg, 87.30 deg and 98.0 deg. The launch vehicle is a three-stage type developed on base of the most powerful RS-20 (SS-18 Satan) intercontinental ballistic missile. Fuel components are: diazote tetraoxide and asymmetric dimethyl hydrazine. The LV is capable to fulfill up to 25 rocket carriers launching per year.

Specifications

Launching weight (at spacecraft mass of 2 t), t

208.9

Mass of payload which is launched to circular orbit (altitude is 400 km), t

3.3

Engine thrust in vacuum, tf:

 

I stage

461.2

II stage

77.5

III stage (main/partial power operation mode)

1.9/0.8

Accuracy of spacecraft launching to orbit at 300 km altitude:

 

orbit altitude, km

±4

orbital rotation period, s

±3

inclination, arc min

±0.04

ascending node right ascension, deg

±0.05