Advanced Launch Vehicle Configurations and Performance Trades
Advanced Launch Vehicle Configurations and Performance Trades
- New search for: P. R. Gord
- New search for: K. J. Langan
- New search for: M. E. Stringer
- New search for: P. R. Gord
- New search for: K. J. Langan
- New search for: M. E. Stringer
A concept for a near-term multi-stage space launch system has been proposed. The configuration incorporated full reusability, horizontal take-off and landing characteristics, and a payload goal of 50,000 lbs into a 100 n mi circular airbreathing propulsion system, augmented by conventional rocket propulsion as required. The second stage (orbiter) featured a high lift-to-drag ratio aerodynamic design with a dedicated high volume payload bay. Propulsion for the second stage was provided by a conventional rocket engine. The orbiter component was carried nestled within the booster mold lines and staged through a bottom drop mode. Sensitivity studies were performed on the synergisms between elements of the boost propulsion system; dynamic pressure effects on system performance; degraded ramjet thrust at high Mach numbers; and booster weight at staging. The configuration evolution and results from the sensitivity studies are described in detail.
Document information
Advanced Launch Vehicle Configurations and Performance Trades
1990
13 pages
Report
No indication
English
Space Launch Vehicles & Support Equipment , Launch vehicle configurations , Spacecraft launching , Aerodynamic characteristics , Pressure effects , Propulsion , Rocket engines , Air breathing engines , Booster rocket engines , Dynamic pressure , Lift drag ratio , Mach number , Payloads , Ramjet engines , Takeoff
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