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RD-802
Part of RD-8 Family
RD-802
RD-802
Credit: Yuzhnoye
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.

Status: Design concept 2007. Thrust: 19.60 kN (4,406 lbf). Specific impulse: 344 s. Burn time: 1,100 s. Height: 1.67 m (5.47 ft).

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.



Country: Ukraine. Propellants: Lox/Kerosene. Agency: Yuzhnoye. Bibliography: 4477.

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