Thermal protection system -design and -layout with respect to the specified requirements are driven by the thermal analysis on the basis of the given themodynamic boundary conditions i.e. the time histories of environmental gas pressure for example. In contrast to the specified thermal requirements e.g. maximum structure temperature valid for the material to be applied, these boundary conditions differ essentially betweeen the flight phases launch and re-entry: During launch, ambient gas pressure decreases within the first about 150 seconds to conditions which are near vacuum from the insulation's point of view. Re-entry is characterised by a continuously pressure increase over a much longer time period of the order of 1000 seconds.
Experiences in experimental investigations on thermal characterisation of lightweight fibrous insulation for re-entry spacecraft TPS
Erfahrungen bei der experimentellen Untersuchung der thermischen Eigenschaften von Leichtgewichtsisolierungen aus Fasermaterial für Hitzeschilde beim Wiedereintritt von Raumfähren
Spacecraft Structures, Materials & Mechanical Testing, International Conference, European Space Agency, 1996 ; 1049-1055
1996
7 Seiten, 9 Bilder, 2 Tabellen, 8 Quellen
Aufsatz (Konferenz)
Englisch
British Library Online Contents | 1996
|British Library Conference Proceedings | 1996
|Lightweight Conformal Spacecraft Thermal Radiator
SAE Technical Papers | 2005
|Ceramic-Fibrous-Insulation Thermal-Protection System
NTRS | 1992
|Lightweight High-Temperature Thermal Insulation
NTRS | 1985
|