Encyclopedia Astronautica
Pegasus XL-2


Hercules solid rocket engine. 153.5 kN. Isp=290s. Used on Pegasus XL launch vehicle. First flight 1994.

Thrust (sl): 127.000 kN (28,550 lbf). Thrust (sl): 12,954 kgf. Chamber Pressure: 58.00 bar. Area Ratio: 65.

Gross mass: 4,331 kg (9,548 lb).
Unfuelled mass: 416 kg (917 lb).
Height: 3.58 m (11.74 ft).
Diameter: 1.27 m (4.16 ft).
Thrust: 153.50 kN (34,508 lbf).
Specific impulse: 290 s.
Specific impulse sea level: 240 s.
Burn time: 73 s.
Number: 33 .

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Associated Countries
See also
Associated Launch Vehicles
  • 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
  • Hercules American manufacturer of rocket engines and rockets. Hercules, Wilmington, Delaware, USA. More...

Associated Propellants
  • Solid 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. 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...

Associated Stages
  • Pegasus XL-2 Solid propellant rocket stage. Loaded/empty mass 4,331/416 kg. Thrust 153.50 kN. Vacuum specific impulse 290 seconds. More...

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