A space transporter concept is presented in which hydrogen fuelled ramjet propulsion theory is applied to a one and a half stage vertical takeoff and landing hydrogen/oxygen rocket core vehicle with ballistic ascent and descent. A payload to gross liftoff ratio of 10%, i.e., 2.5 times the value of pure rocket systems, is possible, with 56% propellant saving and 44% saving in dry weight. These results can be obtained with existing or near term structures and propulsion systems technology. Ramjet technology can be transferred from missile applications. A small size (155 Mg) reusable space transport system with 15.4 Mg payload in low Earth orbit is feasible.
Reusable Air Breathing Ballistic Space Transport Systems
1981
10 pages
Report
No indication
English
Rocket Engines & Motors , Space Launch Vehicles & Support Equipment , Multistage rocket vehicles , Ramjet engines , Reusable launch vehicles , Vertical takeoff , Aerospace technology transfer , Ballistic trajectories , Fuel consumption , Hydrogen oxygen engines , Payload mass ratio , Foreign technology
Air-Breathing Ballistic Space Transporter for Europe
NTIS | 1985
|An air-breathing ballistic space transporter for Europe
NTRS | 1985
|Air-Breathing Reusable Launchers
SAE Technical Papers | 1967
|Air-breathing reusable launchers
Engineering Index Backfile | 1967
|