Engine Model: RD-802. Manufacturer Name: RD-802. Designer: Yuzhnoye. Application: Upper stages. Propellants: Lox/Kerosene. Thrust(vac): 19.600 kN (4,406 lbf). Isp: 344 sec. Burn time: 1,100 sec. Length: 1.67 m (5.47 ft). Chambers: 1. Chamber Pressure: 78.00 bar. Oxidizer to Fuel Ratio: 2.50. Country: Ukraine. Status: 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.
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