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HiPAT
HiPAT

HiPAT
Credit: Aerojet Redmond
Redmond N2O4/MMH rocket engine. In Production. High performance liquid apogee thruster.

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

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

Family: Storable liquid. Country: USA. Propellants: N2O4/MMH. Agency: Redmond.
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HiPAT Dual ThrustHiPAT Dual Thrust
Credit: Aerojet Redmond
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