Encyclopedia Astronautica

Rolls Royce turbofan engine. 29.4 kN. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=9900s. Used on L1011 launch aircraft for Pegasus, Pegasus XL. First flight 1990.

Thrust (sl): 26.700 kN (6,002 lbf). Thrust (sl): 2,727 kgf. Engine: 4,180 kg (9,210 lb). Thrust to Weight Ratio: .71.

Unfuelled mass: 4,180 kg (9,210 lb).
Thrust: 29.40 kN (6,609 lbf).
Specific impulse: 9,900 s.
Burn time: 4,590 s.
Number: 117 .

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Associated Countries
See also
Associated Launch Vehicles
  • Pegasus American air-launched orbital launch vehicle. Privately-funded, air-launched winged light satellite launcher. More...
  • Pegasus XL American air-launched orbital launch vehicle. Uprated version of Pegasus air-launched winged light satellite launcher. 4 stage vehicle consisting of 1 x L-1011 + 1 x Pegasus XL stage 1 + 1 x Orion 50XL + 1 x Orion 38. More...

Associated Manufacturers and Agencies
Associated Propellants
  • Air/Kerosene Ambient air (78 % nitrogen, 21% oxygen, etc.) is scooped up by air intakes and used in turbojet, turbofan, ramjet, scramjet, or other airbreathing engines. It is used to burn aviation-grade kerosene, commercial grade JP-4 or JP-5, their military equivalents, or special high-temperature blends such as those used in the SR-71. More...

Associated Stages
  • L-1011 Subsonic rocket launch aircraft. Loaded/empty mass 156,000/109,629 kg. Thrust 561.90 kN. Specific impulse 9900 seconds. Lockheed airliner swept wing. Release conditions: Belly-mounted, 36,800 kg, 17.1 m length x 7.9 m span at 925 kph at 11,890 m altitude More...

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