Encyclopedia Astronautica

ISRO N2O4/MMH rocket engine. 7 kN. Isp=308s. Used on PSLV launch vehicle. First flight 1993.

Chamber Pressure: 8.40 bar. Area Ratio: 60. Thrust to Weight Ratio: 0. Coefficient of Thrust vacuum: 1.74598584050247.

Diameter: 0.67 m (2.19 ft).
Thrust: 7.00 kN (1,574 lbf).
Specific impulse: 308 s.
Burn time: 425 s.
Number: 16 .

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Associated Countries
See also
Associated Launch Vehicles
  • PSLV Indian third-generation launch vehicle, large enough to carry polar-orbiting earth resources satellites. More...

Associated Manufacturers and Agencies
  • ISRO Indian manufacturer of rockets, spacecraft, and rocket engines. Indian Space Research Organization, India. 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...

Associated Stages
  • PSLV-4 N2O4/MMH propellant rocket stage. Loaded/empty mass 2,920/920 kg. Thrust 14.00 kN. Vacuum specific impulse 308 seconds. More...

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