Encyclopedia Astronautica
Pegasus XL-2


Solid propellant rocket stage. Loaded/empty mass 4,331/416 kg. Thrust 153.50 kN. Vacuum specific impulse 290 seconds.

Cost $ : 3.400 million.

Status: Active.
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).
Span: 1.27 m (4.16 ft).
Thrust: 153.50 kN (34,509 lbf).
Specific impulse: 290 s.
Specific impulse sea level: 240 s.
Burn time: 73 s.
Number: 92 .

More... - Chronology...


Associated Countries
Associated Engines
  • Pegasus XL-2 Hercules solid rocket engine. 153.5 kN. Isp=290s. Used on Pegasus XL launch vehicle. First flight 1994. More...

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...
  • Pegasus XL/HAPS American air-launched orbital launch vehicle. Five stage version consisting of 1 x L-1011 + 1 x Pegasus XL stage 1 + 1 x Orion 50XL + 1 x Orion 38 + 1 x HAPS More...
  • Minotaur 1 American all-solid orbital launch vehicle. Orbital launch vehicle consisting of a surplus Minuteman M55A1 first stage, Minuteman SR19 second stage, and new Orion 50XL third stage, Orion 38 fourth stage, and optional HAPS fifth stage for velocity trim and multiple payload deployment. Payload 580 kg to an 185 km, 28.5 degree orbit from Cape Canaveral; 310 kg to a 740 km sun-synchronous orbit from Vandenberg. More...
  • Minotaur 2 American all-solid orbital launch vehicle. Suborbital target vehicle consisting of an M55A1 first stage, SR19 second stage, and M57 third stage - essentially a Minuteman II with Orbital guidance and control systems. 440 kg payload on a 6700 km suborbital trajectory. 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...

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