Encyclopedia Astronautica

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.
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.

More... - Chronology...

Associated Countries
Associated Engines
  • 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...

Associated Launch Vehicles
  • Jarvis American orbital launch vehicle. Launch vehicle planned for Pacific launch based on Saturn V engines, tooling. Masses, payload estimated. More...

Associated Propellants
  • 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...

Home - Browse - Contact
© / Conditions for Use