Lox/LH2 propellant rocket stage. Loaded/empty mass 23,300/3,500 kg. Thrust 73.50 kN. Vacuum specific impulse 461 seconds. Planned version for Angara. 5 restarts.
Status: In development.
More... - Chronology...
Gross mass: 23,300 kg (51,300 lb).
Unfuelled mass: 3,500 kg (7,700 lb).
Height: 8.60 m (28.20 ft).
Diameter: 4.10 m (13.40 ft).
Span: 4.10 m (13.40 ft).
Thrust: 73.50 kN (16,523 lbf).
Specific impulse: 461 s.
RD-56M Isayev lox/lh2 rocket engine. 73.580 kN. Proton and Angara upper stage KVRB, 12KRB upper stage for GSLV (India). In development. Isp=461s. First flight 2001. More...
Associated Launch Vehicles
Angara 5A Russian orbital launch vehicle. The Angara 5A was a proposed variant of the modular launch vehicle that would use four universal rocket modules (URM's) as boosters surrounding one URM in the core, with a Lox/LH2 upper stage. It could put 5.0 tonnes into geosynchronous orbit, or 8.0 tonnes into geosynchronous transfer orbit. 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...
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