The objectives of the technology program 'aerothermodynamics and propulsion integration' are defined. An overview of the special aerothermodynamic phenomena which must be regarded in the design of the Saenger lower stage, which presently stands in the center of the technology program, is given. The design tools, which must be provided, the components like the inlet, and the afterbody, which must be designed and tested, and the special problems like forebody optimization, heat load determination, and upper stage separation, which must be treated, are discussed. The general work plan, with the major activities up to the start of the development of the Saenger space transport system is presented, including the development and manufacturing of an experimental vehicle (HYTEX) as a means for the validation of the design tools and methods which are achieved in the technology program, and for the creation of a free flight data base. Examples given include applications of predesign methods and numerical methods for the determination of global forces and moments, aerodynamic loads and heat loads, for the latter also a study of the influence of different flow physical model assumptions. Results from the inlet study, the stage separation study, etc., show the advancement in these areas.
Aerothermodynamics and Propulsion Integration in the Saenger Technology Programme
1991
12 pages
Report
No indication
English
Missile Aerothermodynamics and Propulsion Integration
British Library Conference Proceedings | 1996
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