Enhanced strength analysis method for composite open-hole plates ensuring design office requirements |
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Affiliation: | 1. ONERA, 29 avenue de la Division Leclerc, F-92322 Châtillon, France;2. LBMS, ENSTA Bretagne, 2 rue François Verny, F-29200 Brest, France;3. AIRBUS, 316 route de Bayonne, F-31060 Toulouse Cedex 9, France;1. Institute of Materials and Structures, Riga Technical University, Kalku St. 1, LV-1658, Riga, Latvia;2. AIRBUS UK, Filton, Bristol BS99 7AR, UK;1. Engineering Optics Lab, Department of Mechanical and Aerospace Engineering, IIT Hyderabad, India;2. NDT & E Lab, Department of Mechanical and Aerospace Engineering, IIT Hyderabad, India;1. School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing, 210094, China;2. College of Applied Science, Taiyuan University of Science and Technology, Taiyuan, 030024, China;3. Institute of Applied Mechanics and Biomedical Engineering, Taiyuan University of Technology, Taiyuan, 030024, PR China;1. ONERA – The French Aerospace Lab, F-59045 Lille, France;2. Univ Lille Nord de France, F-59000 Lille, France;3. ECLille, LML, F-59650 Villeneuve D’Ascq, France |
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Abstract: | The use of unidirectional carbon fibre-reinforced composites in the design of primary structures, such as the centre wing box, has spread increasingly over the past few years. However, composite structures can be weakened by the introduction of geometrical singularities, such as holes or notches. The semi-empirical aspect of the current open-hole failure approaches requires the allowables to be systematically fitted against specific test results. This point constitutes a strong limitation for optimum design. A simplified strength analysis method for perforated plates is presented, ensuring design office requirements in terms of precision and computational time. The predictions of the proposed approach are compared successfully with a large experimental database, with different configurations of perforations, different stacking sequences and in different Carbon/Epoxy materials. |
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Keywords: | A. Laminates B. Strength C. Computational modeling |
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