Encyclopedia Astronautica

Credit: Aerojet Redmond
HiPAT Dual Thrust
Credit: Aerojet Redmond
Redmond N2O4/MMH rocket engine. 0.445 kN. In Production. High performance liquid apogee thruster. Isp=323s.

Engine: 5.20 kg (11.40 lb). Chamber Pressure: 9.40 bar. Area Ratio: 375. Restarts: 500.

Status: In Production.
Unfuelled mass: 5.20 kg (11.40 lb).
Height: 0.72 m (2.36 ft).
Diameter: 0.36 m (1.19 ft).
Thrust: 445 N (100 lbf).
Specific impulse: 323 s.
Burn time: 3,600 s.

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Associated Countries
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Associated Manufacturers and Agencies
  • Redmond American manufacturer of rocket engines. Redmond, USA. 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...

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