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astronautix.com RD-868


Manufacturer Name: RD-868. Designer: Yangel. Developed in: 1983-. Application: Apogee stage. Propellants: N2O4/UDMH Thrust(vac): 2,371 kgf. Thrust(vac): 23.25 kN. Isp: 325 sec. Burn time: 1,600 sec. Mass Engine: 203 kg. Diameter: 2.4 m. Length: 1.1 m. Chambers: 1 + x. Chamber Pressure: 91.50 bar. Oxidizer to Fuel Ratio: 2.20. Country: Ukraine. Status: Developed 1983-. References: 348 . Comments: Still 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. Burn time 1600 / 7200 sec. Oxidizer to fuel ratio 2,2 / 1,6.
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Last update 12 March 2001.
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