Encyclopedia Astronautica

Lox/Solid propellant rocket stage. Loaded mass 12,200 kg. Thrust 315.00 kN.

Status: Retired 1989.
Gross mass: 12,200 kg (26,800 lb).
Height: 17.70 m (58.00 ft).
Diameter: 1.29 m (4.23 ft).
Thrust: 315.00 kN (70,814 lbf).
Burn time: 70 s.
Number: 1 .

More... - Chronology...

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
  • AMROC IRR American low cost orbital launch vehicle. Single stage vehicle. More...

Associated Manufacturers and Agencies
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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