This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Designer: Isayev. Propellants: N2O4/UDMH Thrust(vac): 3 kgf. Thrust(vac): 0.03 kN. Isp: 285 sec. Burn time: 25,000 sec. Mass Engine: 1 kg. Chambers: 1. Chamber Pressure: 8.00 bar. Area Ratio: 45.00. Oxidizer to Fuel Ratio: 1.85. Country: Russia. Status: In Production. References: 350 . Comments: Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 300,000 ignitions.
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Last update 12 March 2001.
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© Mark Wade, 2001 .