Finite element modelling of low velocity impact of composite sandwich panels |
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| Affiliation: | 1. Department of Civil Engineering, University of Puerto Rico, Mayagüez, PR 00681, United States;2. Department of General Engineering, University of Puerto Rico, Mayagüez, PR 00681, United States;3. Department of Materials Science and Engineering Department, University of Alabama at Birmingham (UAB), Birmingham, AL 35294, United States;1. Department of Engineering Mechanics, Southeast University, Nanjing 210096, China;2. Faculty of Science, Engineering and Technology, Swinburne University of Technology, John Street, Hawthorn, 3122, Australia;3. School of Mechanical Engineering, Southeast University, Nanjing 210096, China;4. Key Laboratory of Lightweight and Reliability Technology for Engineering Vehicle, College of Hunan Province, Changsha 410114, China;1. School of Engineering, Sun Yat-Sen University, Guangzhou City, 510006, China;2. State Key Laboratory of Advanced Design and Manufacture for Vehicle Body, Hunan University, Changsha, 410082, China;3. School of Aerospace, Mechanical and Mechatronic Engineering, Sydney University, Sydney, NSW 2006, Australia;4. Department of Mechanical Engineering, University of New Orleans, USA |
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| Abstract: | This paper outlines a finite element procedure for predicting the behaviour under low velocity impact of sandwich panels consisting of brittle composite skins supported by a ductile core. The modelling of the impact requires a dynamic analysis that can also handle non-linearities caused by large deflections, plastic deformation of the core and in-plane degradation of the composite skins. Metal honeycomb, frequently used as a core material, is anisotropic and requires a non-standard approach in the elasto-plastic part of the analysis. A suitable yield criteria based on experimental observations is proposed. Comparisons of experimental and finite element responses are shown for sandwich panels with carbon fibre skins and aluminium honeycomb cores. |
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