Encyclopedia Astronautica

Lox/LH2 propellant rocket stage. Loaded/empty mass 117,000/17,800 kg. Thrust 2,196.00 kN. Vacuum specific impulse 440 seconds. Two-engine version of H-2A-1 used as strap-on booster.

No Engines: 2.

Status: In production.
Gross mass: 117,000 kg (257,000 lb).
Unfuelled mass: 17,800 kg (39,200 lb).
Height: 36.70 m (120.40 ft).
Diameter: 4.00 m (13.10 ft).
Span: 4.00 m (13.10 ft).
Thrust: 2,196.00 kN (493,680 lbf).
Specific impulse: 440 s.
Specific impulse sea level: 338 s.
Burn time: 193 s.

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Associated Countries
Associated Engines
  • LE-7A Mitsubishi lox/lh2 rocket engine. 1098 kN. In production. Isp=438s. Improved model of the original LE-7 for the first stage of the H-II rocket with a two stage combustion cycle system. First flight 2001. More...

Associated Launch Vehicles
  • H-2A 212 Japanese orbital launch vehicle. This version uses two core stages side-by-side in an asymmetric configuration, supplemented by two SRB-A solid rocket boosters. More...

Associated Propellants
  • 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...

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