MainРroductsAerospace equipment

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.


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


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


Engine thrust in vacuum, tf:


I stage


II stage


III stage (main/partial power operation mode)


Accuracy of spacecraft launching to orbit at 300 km altitude:


orbit altitude, km


orbital rotation period, s


inclination, arc min


ascending node right ascension, deg