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Designer: Isayev. Propellants: Hydrazine Thrust(vac): 5 kgf. Thrust(vac): 0.05 kN. Isp: 229 sec. Burn time: 1,500 sec. Mass Engine: 1 kg. Chambers: 1. Chamber Pressure: 8.00 bar. Area Ratio: 42.00. Country: Russia. Status: In Production. References: 350 . Comments: Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions.
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Last update 12 March 2001.
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© Mark Wade, 2001 .