|
|||||
|
|
Finite element model for compression after impact behaviour of stitched composites |
|
| Affiliation: | 1. Department of Mechanical Engineering, The University of Akron, Akron, OH 44325-3903, USA;2. Department of Aerospace Engineering, Tokyo Metropolitan University, 6-6 Asahigaoka, Hino, Tokyo 191-0065, Japan;3. Advanced Composite Research Centre, Japan Aerospace Exploration Agency, 6-13-1 Osawa, Mitaka, Tokyo 181-0015, Japan;1. Institute of Chemical Machinery and Process Equipment, Zhejiang University, Hangzhou 310027, China;2. First Aircraft Institute of Aviation Industry Corporation, Xi’an 710089, China;3. School of Materials Science and Engineering, Shanghai Jiaotong University, Shanghai 200030, China;1. Università degli Studi della Campania “Luigi Vanvitelli”, Department of Industrial and Information Engineering, via Roma n 29, 81031 Aversa, Italy;2. Airbus, Kreetslag 10, 21129 Hamburg, Germany;1. King Abdullah University of Science and Technology (KAUST), Physical Sciences and Engineering Division, COHMAS Laboratory, Thuwal 23955-6900, Saudi Arabia;2. Department of Aerospace Engineering, Tokyo Metropolitan University, 6-6 Asahigaoka, Hino-shi, Tokyo 191-0065, Japan;3. Advanced Composite Research Center, Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA), 6-13-1 Osawa, Mitaka-shi, Tokyo 181-0015, Japan |
| Abstract: | A finite element (FE) model using coupling continuum shell elements and cohesive elements is proposed to simulate the compression after impact (CAI) behaviour and predict the CAI strength of stitched composites. Continuum shell elements with Hashin failure criterion exhibit the composite laminate damage behaviour; whilst cohesive elements using traction-separation law characterise the laminate interfaces. Impact-induced delamination is explicitly modelled by reducing material properties of damaged cohesive elements. Computational results have demonstrated the trend of increasing CAI strength with decreasing impact-induced delamination area. Spring elements are introduced into the model to represent through-thickness stitch thread in the composite laminates. Results in this study validate experimental finding that CAI strength is improved when stitching is incorporated into the composite structure. The proposed FE model reveals good CAI strength predictions and indicates good agreement with experimental results, making it a valuable tool for CAI strength prediction of stitched composites. |
| Keywords: | A 3-Dimensional reinforcement B Damage tolerance C Finite element analysis (FEA) E Stitching |
| 本文献已被 ScienceDirect 等数据库收录！ | |