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RD-860
RD-860
RD-860
Credit: Yuzhnoye
Yuzhnoye N2O4/UDMH rocket engine. Upper stages. Developed 1972. Engine used a novel scheme combining an existing proven combustion chamber but using a pneumatic pump for propellant supply.

Status: Developed 1972. Date: Developed late 1960's. Thrust: 5.90 kN (1,326 lbf). Specific impulse: 320 s. Burn time: 1,500 s.

This allowed:

Throttled thrust(vac): 1.960 kN (441 lbf). Engine: 30 kg (66 lb). Oxidizer to Fuel Ratio: 2. Restarts: 15.



Subtopics

RD-869 Yuzhnoye N2O4/UDMH rocket engine. R-36M2 vehicle bus. Based on RD-864. Two thrust levels. The four thrusters swing out of the stage housing before use. Chamber pressure 41 / 17 bar. Diameter 3,0 / 4,02 m. First flight 1986.

Family: Storable liquid. Country: Ukraine. Propellants: N2O4/UDMH. Agency: Yuzhnoye. Bibliography: 4477.

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