A comparative outline of the aspects favoring the two-stage horizontally launched space transport vehicle over multi-stage rockets and single-stage horizontally launched space transport vehicles is given. The significant key data for the Saenger space vehicle are discussed. The resulting technical requirements for the propulsion systems are explained with emphasis being placed on the propulsion system of the lower stage, since this represents the greatest technological challenge. Because of the high level of integration, the entire propulsion system, consisting of intake, actual engine and expansion ramp behind the engine, is covered. On this basis, the propulsion concepts taken into consideration for the lower stage up to this point are compared, in retrospect, with regard to their performance as well as the technical and technological problems. The key technologies involved which are presently being pursued are discussed. In this context, the requirements for a technology flight demonstrator, which will become indispensable for the further development of Saenger, and the associated problems are discussed. Based on the information available, apparent development trends and activities in the hypersonic propulsion field in the other European countries are commented on.
High Speed Airbreathing Propulsion in Europe
1991
1 pages
Report
No indication
English
Space Launch Vehicles & Support Equipment , Rocket Engines & Motors , Air breathing engines , Hypersonic flight , Multistage rocket vehicles , Single stage to orbit vehicles , Spacecraft propulsion , Hypersonic vehicles , Propulsion system performance , Rocket engines , Space shuttles , Space transportation , Foreign technology
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