Mitsubishi lox/lh2 rocket engine. 121.5 kN. Isp=452s. Used on H-2 launch vehicle. First flight 1994.
Engine: 242 kg (533 lb). Chamber Pressure: 40.00 bar. Area Ratio: 130. Thrust to Weight Ratio: 51.1964958168671. Oxidizer to Fuel Ratio: 5. Coefficient of Thrust vacuum: 1.87986266248807.
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Unfuelled mass: 242 kg (533 lb).
Height: 2.67 m (8.75 ft).
Diameter: 4.00 m (13.10 ft).
Thrust: 121.50 kN (27,314 lbf).
Specific impulse: 452 s.
Burn time: 609 s.
Number: 7 .
Associated Launch Vehicles
H-2 Heavy lift Japanese indigenous launch vehicle. The original H-2 version was cancelled due to high costs and poor reliability and replaced by the substantially redesigned H-2A. More...
Associated Manufacturers and Agencies
Mitsubishi Japanese manufacturer of rockets, spacecraft, and rocket engines. Mitsubishi Electric Corp, Japan. More...
Lox/LH2 Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Liquid hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. The technology was transferred to the Centaur rocket stage program, and by the mid-1960's the United States was flying the Centaur and Saturn upper stages using the fuel. It was adopted for the core of the space shuttle, and Centaur stages still fly today. More...
LE-5EC Lox/LH2 propellant rocket stage. Loaded/empty mass 16,700/2,700 kg. Thrust 121.50 kN. Vacuum specific impulse 452 seconds. More...
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