Isayev N2O4/MMH rocket engine. 0.600 kN. Hermes. In Production. Version of DMT-600 using MMH in place of UDMH, adaptation to western market (was discussed for European Hermes space plane project). 6,000 ignitions Isp=305s.
Engine: 4.20 kg (9.20 lb). Chamber Pressure: 9.00 bar. Area Ratio: 46.5. Thrust to Weight Ratio: 14.57. Oxidizer to Fuel Ratio: 1.65.
Status: In Production.
More... - Chronology...
Unfuelled mass: 4.20 kg (9.20 lb).
Thrust: 600 N (130 lbf).
Specific impulse: 306 s.
Burn time: 5,000 s.
Associated Manufacturers and Agencies
N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...
Haeseler, Dietrich, Visit to the museum of Chemical Machining Design Bureau, Kalinin 1998 via Dietrich Haeseler.
Home - Browse - Contact
© / Conditions for Use