Encyclopedia Astronautica
LE-7

LE-7

Thrust (sl): 843.500 kN (189,626 lbf). Thrust (sl): 86,018 kgf. Engine: 1,714 kg (3,778 lb). Chamber Pressure: 127.00 bar. Area Ratio: 52. Thrust to Weight Ratio: 64.1338435000121. Oxidizer to Fuel Ratio: 5.9. Coefficient of Thrust vacuum: 1.73739021790307. Coefficient of Thrust sea level: 1.32200560251845.

Unfuelled mass: 1,714 kg (3,778 lb).
Height: 3.40 m (11.10 ft).
Diameter: 4.00 m (13.10 ft).
Thrust: 1,078.00 kN (242,344 lbf).
Specific impulse: 446 s.
Specific impulse sea level: 349 s.
Burn time: 346 s.
Number: 7 .

• Japan Japan More...

• First Stages Category of engines. More...

• Lox/LH2 Category of engines. More...

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• 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...

• Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.

• H-2-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 98,100/11,900 kg. Thrust 1,078.00 kN. Vacuum specific impulse 446 seconds. More...