RD-802

Yuzhnoye LOx/Kerosene rocket engine. Upper stages. Design concept 2007. Derivative of the RD-8 Zenit-2 second stage vernier thrust engine combustion chamber for use in launch vehicle upper stages.

The multi-start pump-fed single-chamber engine featured:

• Thrust and mixture ratio regulation to an accuracy of ±1%;
• Total operation time up to 1100seconds
• Generator gas afterburning scheme
• Thrust vector control by gimbaling the chamber in two orthogonal planes; gimbal angle, ±8 deg. Roll control provided by roll nozzles tapping off the gas generator.
• Spin-up of booster turbopump and operation of solenoid valves for engine start and restart performed by gas from an autonomous pneumatic unit
• Turbine powered by oxidizer-rich gas.
• Propellants ignited in the gas generator and combustion chamber by use of a starting fuel.

Chamber Pressure: 78.00 bar. Oxidizer to Fuel Ratio: 2.5. Restarts: 6.