Pegasus XL-2
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Hercules solid rocket engine. 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.
Related
- Country
- USA
- Launch Vehicles
- Pegasus XL, Pegasus XL/HAPS, Minotaur 1, Minotaur 2
- Propellants
- Solid
- Stages
- Pegasus XL-2
- Agency
- Hercules