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Wing Leading Edges for Air Breathing Launchers
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English
Abstract
Actively cooled and re-radiative leading edges were investigated as typical thermal protection elements for thermally high loaded areas of advanced launchers. A performance trade-off led to the selection of a C/SiC thermostructural concept. Mechanical and thermal analyses demonstrated the adequacy of the selected design. Manufacturing leading edge demonstrators with a small nose radius, different thicknesses of the outer skin and the integration of stringers was realised with good surface smoothness and contour accuracy. Thermal cycle tests with temperatures up to 1000°C in an oxidising environment were performed without any visible damage.
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Citation
Reich, G., Trabandt, U., and Keller, K., "Wing Leading Edges for Air Breathing Launchers," SAE Technical Paper 941583, 1994, https://doi.org/10.4271/941583.Also In
References
- Keller, K. Winged Launcher Thermal Design Aspects 1991
- Reich, G. Hinger J. Huchler M. Thermal Protection Systems for Hypersonic Transport Vehicles 20th Int. Conf. Environmental Systems Williamsburg, USA 1990
- Kullik, M. Meistring R. Pietsch C. Reich G. Westphal M. High Temperature Thermal Protection Dornier report DO-TN-TPS-001 for the Study: Thermal Protection Systems for Advanced Launchers 1992
- Haug, T. Trabandt U. Baier H. Short Manufacturing Cycle CMC Heat Shields and Hot Structures 202 209 1993
- Trabandt, U. Reich G. et al. Wing Leading Edge C/SiC Demonstrator Final Report, ESA Contract 1993
- Trabandt, U. et al Design of Hot Structures of Short Cycle Manufactured CMC: HT-CMC1 6th European Conference on Composite Materials 20-24 September 1993