Encyclopedia Astronautica

Lox/Solid propellant rocket stage. Loaded/empty mass 31,000/5,900 kg. Thrust 931.33 kN. Vacuum specific impulse 284 seconds.

Cost $ : 1.000 million.

AKA: Aquila.
Status: Design 1988.
Gross mass: 31,000 kg (68,000 lb).
Unfuelled mass: 5,900 kg (13,000 lb).
Height: 19.50 m (63.90 ft).
Diameter: 1.83 m (6.00 ft).
Span: 1.83 m (6.00 ft).
Thrust: 931.33 kN (209,371 lbf).
Specific impulse: 284 s.
Specific impulse sea level: 283 s.
Burn time: 75 s.

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Associated Countries
Associated Engines
  • H1500 Notional Lox/Solid hybrid rocket engine. 931.3 kN. Design 1988. Isp=284s. Used on Industrial Launch Vehicle launch vehicle. More...

Associated Launch Vehicles
Associated Propellants
  • Lox/Solid 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. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...

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