Encyclopedia Astronautica
HOTOL



hotol2.jpg
Hotol 2
Hotol 2 is launched from the back of an Antonov 225
Credit: British Aerospace
Liquid Air/Lox/LH2 propellant rocket stage. Loaded/empty mass 250,000/50,000 kg. Thrust 1,103.20 kN. Vacuum specific impulse 700 seconds.

Cost $ : 10.000 million. No Engines: 3.

AKA: Horizontal Takeoff and Landing.
Status: Development ended 1985.
Gross mass: 250,000 kg (550,000 lb).
Unfuelled mass: 50,000 kg (110,000 lb).
Height: 62.80 m (206.00 ft).
Diameter: 7.00 m (22.90 ft).
Span: 28.30 m (92.80 ft).
Thrust: 1,103.20 kN (248,009 lbf).
Specific impulse: 700 s.
Specific impulse sea level: 2,000 s.
Burn time: 730 s.

More... - Chronology...


Associated Countries
Associated Engines
  • RB545 Rolls Royce air augmented rocket engine. 367.7 kN. Used Liquid Air/Lox/LH2. Development ended 1985. Isp=700s. Used on HOTOL launch vehicle. More...

Associated Launch Vehicles
  • HOTOL This single-stage-to-orbit winged horizontal takeoff/horizontal landing launch vehicle concept was powered by the unique Rolls-Royce RB545 air / liquid hydrogen / liquid oxygen rocket engine. HOTOL development was conducted from 1982 to 1986 before the British government withdrew funding. It was superseded by the Interim HOTOL design which sought to reduce development cost through use of existing Lox/LH2 engines. More...

Associated Propellants
  • Liquid Air/Lox/LH2 Liquid air has no advantage as a stored propellant, but in a Liquid Air Cycle Engine (LACE) relatively freely available atmospheric air is scooped up, liquefied, and burned with a fuel in a conventional rocket engine. More...

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