SFB 259: High Temperature Problems of Reusable Space Vehicles

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The objective of this collaborative research centre is to acquire new basic knowledge and develop investigation methods in the field of high temperature problems of future reusable space vehicles, defined as aerodynamically sustained transport devices equipped with air-breathing engines and operating in the hypersonic range. The capacibility of these transport devices to take off and land horizontally and therefore their reusability requires one or two-staged winged flight vehicles which cover all flight ranges up to Mach 25 between take off, earth orbiting and landing. Thereby during a hypersonic flight, especially during the reentry of the upper stage, extremely high temperatures are encountered, posing problems to which solutions have to be described and investigated.For the realization of the entire transport system it is therefore essential that exact information is acquired on the interaction of the hot flow with the structure made from high temperature materials. The work of the collaborative research centre 259 places its emphasis primarily on this subject.Materials, construction methods and hot structures as well as their realistic computation and testing are critical factors for the development of future space vehicles. In particular the behaviour of non-metallic compound materials C/C and C/SIC (carbon fibre reinforced carbon and carbon fibre reinforced sillicon carbide) at the encountered high temperatures is investigated.To achieve a reliable control of the thermal loads, it is essential for the projected missions to have improved diagnostic methods under reentry conditions and detailed knowledge of the material behaviour, combustions processes and the operation procedures. These complex problems are solved by a close cooperation between the scientists of the disciplines concerned.