Isayev monopropellant rocket engine. 0.025 kN. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 60,000 ignitions Isp=234s.
Engine: 1.30 kg (2.80 lb). Chamber Pressure: 4.50 bar. Area Ratio: 55. Thrust to Weight Ratio: 1.96.
Status: In Production.
Unfuelled mass: 1.30 kg (2.80 lb).
Thrust: 25 N (5 lbf).
Specific impulse: 235 s.
Burn time: 25,000 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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