Cyclone-4 LV second stage sustainer engine is intended for creation of the main propulsive burn and ensuring LV launching and passing hard air layers.

The double-chamber turbo pump-fed rocket RD-262 is designed according to the scheme without afterburning of a turbine operating body. Combustion products of main propellant components are used as a turbine operating body.


Technical characteristics Value
Propellant components NTO (N2O4) + UDMH ((CH3)2N2H2)
Combustor pressure, kgs/ 91,0
Vacuum specific propulsive burn, s 315,7
Vacuum thrust, kgs 95970
Propellant mixture ratio 2,6
Firing time, s 160