The realization possibilities of alternative combined propulsion system configurations for spacecraft which horizontally take off and land and have a payload capacity of 10t for low Earth orbits, are discussed. It is shown that the combined system with air breathing booster phase in which the aspirated air flow is cooled by the liquid hydrogen fuel is technically feasible. In order to obtain the required thrust density during the starting phase it is necessary to synchronize the rocket engine part on the ground, indicating a crucial point of this development, namely the control of the different operating conditions during the cooperation between the air breathing turboramjet part and the integrated turborocket part. It is demonstrated that the basic technological competence is available in Europe.
Kombinationsantriebe fuer Raumflugzeuge (Combined Spacecraft Propulsion Systems)
1986
36 pages
Report
Keine Angabe
Englisch
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