Thermo-mechanical design aspects for primary composite structures of large transport aircraft |
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| Institution: | 1. IK4-IKERLAN, P° J. M. Arizmendiarrieta 2, 20500 Arrasate-Mondragón, Spain;2. Universidad del País Vasco, Alameda Urquijo (s/n), 48013 Bilbao, Spain;3. TLK-ThermoGmbH, Hans-Sommer-Straße 5, 38106 Braunschweig, Germany;1. Department of Electrical and Computer Engineering, University of Virginia, Charlottesville, VA 22904, USA;2. NASA Langley Research Center, Hampton, VA 23681, USA;3. NASA Internships, Fellowships & Scholarships (NIFS) Program, NASA Langley Research Center, Hampton, VA 23681, USA;1. CEA, DEN, DTN/SMTA/LPMA, Cadarache, F-13108 Saint Paul-lez-Durance, France;2. National Center for Nuclear Research, 05-400 Otwock-Świerk, Warsaw University of Technology, pl.Politechniki 1, 00-661 Warsaw, Poland;1. School of Energy and Safety Engineering, Tianjin Chengjian University, Tianjin 300384, PR China;2. Key Laboratory of Efficient Utilization of Low and Medium Grade Energy (Tianjin University), MOE, Tianjin 300072, PR China;3. College of Energy and Environmental Engineering, Hebei University of Engineering, Handan 056038, PR China;4. School of Energy and Environmental Engineering, Hebei University of Technology, Tianjin 300401, PR China |
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| Abstract: | Thermo-mechanical design aspects for primary carbon fibre reinforced plastics (CFRP) components, especially wings, of future large transport aircraft are discussed. Numerical simulations of the heating of a wing under intensive sun irradiation and of cooling during taxiing and take-off result in the recommendation of an appropriate design temperature. The study of flat stringer-stiffened panels reveals the influence of imperfections and boundary conditions on the buckling load under simultaneous thermal and mechanical loading. |
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