Engine is intended to control flight of the Zenit LV second stage in all stabilizing channels. Sustainer and steering engine operate simultaneously after engine RD-120 disconnects during the flight. The single mode engine provides maintenance of specified thrust and propellants mixture ratio.

The RD-8 is designed for the first time in the world practice under the scheme of power gas combustion.

The engine’s pressure indicators issue shutdown commands at propellants depletion in LV tanks.

The engine may stay in the rocket filled with propellants within 24 hours.


Technical characteristics Value
Propellant components liquid oxygen + kerosene
Propellant ignition in the chamber starting fuel
Vacuum thrust, tf 8,0
Vacuum specific propulsive burn, s 342,0
Combustion chamber absolute pressure, kgf/cm2 78
Nozzle exit absolute pressure, kgf/cm2 0,05
Propellant mixture ratio 2,4
Number of restarts 1 and more
Gimbal angle of chambers, deg. ± 33
Firing time, s up to 1100