On tapered warp-free laminates with single-ply terminations |
| |
| Affiliation: | 1. Sir Lawrence Wackett Aerospace Research Centre, School of Aerospace, Mechanical and Manufacturing Engineering, RMIT University, Melbourne, GPO Box 2476, Melbourne, VIC 3001, Australia;2. Carbon Revolution Pty. Ltd, Geelong Technology Precinct, Waurn Ponds, VIC 3216, Australia;3. School of Engineering, Faculty of Science and Engineering and Built Environment, Deakin University, Waurn Ponds, VIC 3216, Australia;1. Université de Toulouse; INSA, UPS, Mines ALBI, ISAE; ICA (Institut Clément Ader), ISAE (Institut Supérieur de l’Aéronautique et de l’Espace), 10, avenue Edouard Belin, BP 54032-31055 Toulouse Cedex 4, France;2. Sogeti High Tech, Avenue Escadrille Normandie Niemen, Parc du Millénaire, 31703 Blagnac, France;1. CIMEC Centro de Investigación de Métodos Computacionales, UNL, CONICET, Col. Ruta 168 s/n, Predio Conicet Dr Alberto Cassano, 3000 Santa Fe, Argentina;2. Institut für Statik und Dynamik, Leibniz Universität Hannover, Appelstraße 9A, 30167 Hannover, Germany;1. Graduate Major in Mechanical Engineering, Tokyo Institute of Technology, 2-12-1 Ookayama, Meguro-ku, Tokyo, 152-8550, Japan;2. Division of Mechanical and Aerospace Engineering, Hokkaido University, Kita 13, Nishi 8, Kita-ku, Sapporo, Hokkaido 060-8628, Japan;3. Department of Transdisciplinary Science and Engineering, Tokyo Institute of Technology, 2-12-1 Ookayama, Meguro-ku, Tokyo, 152-8550, Japan |
| |
| Abstract: | This article reviews the current state of the art in the design of traditional uni-directional fibre laminate construction; beyond the ubiquitous balanced and symmetric design. A ply termination algorithm is then employed to develop permissible tapered designs, with single-ply terminations and ply contiguity constraints, which are free from undesirable changes in mechanical coupling characteristics. More importantly however, is the fact that all tapered designs have immunity to thermal warping distortion; which include all combinations of anti-symmetric (or cross-symmetric), non-symmetric and symmetric angle- and cross-ply sub-sequence symmetries. Tapered designs are presented for laminates with fully uncoupled properties, and those possessing extension–shearing and/or bending–twisting coupling. Such designs represent typical fuselage skin thicknesses, i.e., with between (n =) 12 and 16 plies, but due consideration is also given to new fuselage design concepts with grid-stiffeners and/or geodesic stiffener arrangements, for which thinner designs (n ? 8) are of interest. |
| |
| Keywords: | A: Laminate B: Extension-Shearing C: Bending-Twisting D: Thermomechanical |
| 本文献已被 ScienceDirect 等数据库收录！ |
|
