Isayev monopropellant rocket engine. 5 N. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 550,000 ignitions Isp=230s.
Engine: 0.90 kg (1.98 lb). Chamber Pressure: 3.80 bar. Area Ratio: 60. Thrust to Weight Ratio: .56.
Status: In Production.
Unfuelled mass: 0.90 kg (1.98 lb).
Thrust: 5.00 N (1.10 lbf).
Specific impulse: 230 s.
Burn time: 120,000 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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