Isayev monopropellant rocket engine. 0.050 kN. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions Isp=229s.
Engine: 1.10 kg (2.40 lb). Chamber Pressure: 8.00 bar. Area Ratio: 42. Thrust to Weight Ratio: 4.63.
Status: In Production.
Unfuelled mass: 1.10 kg (2.40 lb).
Thrust: 50 N (11 lbf).
Specific impulse: 229 s.
Burn time: 1,500 s.
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Associated Propellants
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Hydrazine Hydrazine (N2H4) found early use as a fuel, but it was quickly replaced by UDMH. It is still used as a monopropellant for satellite station-keeping motors. Hydrazine (N2H4) found early use as a fuel, but it was quickly replaced by UDMH. It is still used as a monopropellant for satellite station-keeping motors. More...
Bibliography
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Haeseler, Dietrich, Visit to the museum of Chemical Machining Design Bureau, Kalinin 1998 via Dietrich Haeseler.
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