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Designer: Isayev. Propellants: Hydrazine Thrust(vac): 3 kgf. Thrust(vac): 0.03 kN. Isp: 235 sec. Burn time: 25,000 sec. Mass Engine: 1 kg. Chambers: 1. Chamber Pressure: 4.50 bar. Area Ratio: 55.00. Country: Russia. Status: In Production. References: 350 . Comments: Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 60,000 ignitions.
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Last update 12 March 2001.
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