N2O4/MMH propellant rocket stage. Loaded/empty mass 13,400/2,000 kg. Thrust 3.92 kN. Vacuum specific impulse 312 seconds.
Cost $ : 10.000 million. No Engines: 8.
Status: Study 1985.
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Gross mass: 13,400 kg (29,500 lb).
Unfuelled mass: 2,000 kg (4,400 lb).
Height: 3.00 m (9.80 ft).
Diameter: 5.18 m (16.99 ft).
Span: 5.18 m (16.99 ft).
Thrust: 3.92 kN (881 lbf).
Specific impulse: 312 s.
Burn time: 8,100 s.
R-4D Marquardt N2O4/MMH rocket engine. 0.490 kN. Isp=312s. Developed as attitude control thruster for the Apollo Service and Lunar Modules in 1960s. In production for numerous satellites for apogee / perigee maneuvers, orbit adjustment, and attitude control. More...
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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...
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