The two stage to orbit Saenger space transportation system is considered. The technology development concentrates first on the needs of the lower stage. Its requirements for aerothermodynamics and propulsion integration are sketched. The aerothermodynamic design challenge is discussed. The design tools and the design methodology are reviewed. The validation of both the computational and the experimental methods, as well as the test of vehicle components, like the inlet and control surfaces, make the experimental vehicle Hytex mandatory. Contents and workplan of the technology program 'Aerothermodynamics and propulsion integration' are laid out. Selected results from the current work are presented.
Aerothermodynamic Challenges of the Saenger Space-Transportation System
1991
10 pages
Report
Keine Angabe
Englisch
Safety and Flight Abort Aspects of the SAENGER Space Transportation System
British Library Conference Proceedings | 1993
|