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