Proceedings Second International Conference on Composite Science and Technology 9 - 11 June 1998 Durban South Africa

摘要

The design and development of supersonic/hypersonic flight vehicles, of Future reusable space transportation systems, launch vehicles and of advanced propulsion systems constitute challanging issues for the aeronautical engineers and the research workers insolved in these problems. It is a well-known fact that during their flight missions, the structure of flight vehicles has to with stand severe aerodynamic, aeroacoustic and thermomechanical loads. The temperatures involved are likely to range from the extreme lows of cryogenic fuels and radiation to space, to the highs associated with aerodynamic heating, heat from propulsion unit and radiation from the sun. In spite of the increased flexibility which is likely to characterize the structure of these flight vehicles, they have to be able to fulfill a multitude of missions in complex environmental conditions and feature an expanded operational envelope. The same is valid with the resuable space vehicles, which, for evident reasons, require a prolongation of their operational life, without impairing upon the security of flight.