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RD-868

RD-868

RD-868
Credit: Yuzhnoye

Yuzhnoye N2O4/UDMH rocket engine. Apogee stage. Developed 1983-. In development in 1996. One main and an unknown number of control thrusters. 23.25 + 0.03 kN. Chamber pressure 91.5 / 6.9 bar. Specific impulse 325 / 230 sec.

Status: Developed 1983-. Date: 1983-. Thrust: 23.25 kN (5,227 lbf). Unfuelled mass: 203 kg (447 lb). Specific impulse: 325 s. Burn time: 1,600 s. Height: 1.10 m (3.60 ft). Diameter: 2.35 m (7.70 ft).

Burn time 1600 / 7200 sec. Oxidizer to fuel ratio 2.2 / 1.6.

Chambers: 1 + x. Engine: 203 kg (447 lb). Chamber Pressure: 91.50 bar. Thrust to Weight Ratio: 11.67. Oxidizer to Fuel Ratio: 2.2.



Family: Storable liquid. Country: Ukraine. Propellants: N2O4/UDMH. Agency: Yuzhnoye. Bibliography: 348.

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