| ON RESIDUAL COMPRESSIVE STRENGTH PREDICTION OF COMPOSITE SANDWICH PANELS AFTER LOW-VELOCITY IMPACT DAMAGE |
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| 作者姓名： | Xie Zonghong Anthony J. Vizzini Tang Qingru |
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| 作者单位： | Department of |
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| 基金项目： | Project supported by the Scientific and Technological Innovation Foundation and the Developing Program for 0utstanding Persons in NPU. |
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| 摘 要： | This paper introduces a nonlinear finite element analysis on damage propagation behavior of composite sandwich panels under in-plane uniaxial quasi-static compression after a low velocity impact. The major damage modes due to the impact, including the residual indentation on the impacted facesheet, the initially crushed core under the impacted area, and the delamination are incorporated into the model. A consequential core crushing mechanism is incorporated into the analysis by using an element deactivation technique. Damage propagation behavior, which corresponds to those observed in sandwich compression after impact (SCAI) tests, has been successfully captured in the numerical simulation. The critical far field stress corresponding to the onset of damage propagation at specified critical locations near the damage zone are captured successfully. They show a good correlation with experimental data. These values can be used to effectively predict the residual compressive strength of low-velocity impact damaged composite sandwich panels.
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| 关 键 词： | 多层结构 碰撞 分层 损伤生长 有限元法 |
| 收稿时间： | 2004-10-26 |
| 修稿时间： | 2005-12-29 |
ON RESIDUAL COMPRESSIVE STRENGTH PREDICTION OF COMPOSITE SANDWICH PANELS AFTER LOW-VELOCITY IMPACT DAMAGE |
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| Xie Zonghong Anthony J. Vizzini Tang Qingru.ON RESIDUAL COMPRESSIVE STRENGTH PREDICTION OF COMPOSITE SANDWICH PANELS AFTER LOW-VELOCITY IMPACT DAMAGE[J].Acta Mechanica Solida Sinica,2006,19(1):9-17. |
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| Authors: | Xie Zonghong Anthony J Vizzini Tang Qingru |
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| Institution: | 1. College of Astronautics, Northwestern Polytechnical University, Xi''an 710072, China;2. Department of Aerospace Engineering, Mississippi State University, MS 39762, USA;3. Aviation Engineering Institute, Civil Aviation Flight University of China, Guanghan 618307, China;1. Guangzhou Institute of Energy Conversion, Guangzhou Center for Gas Hydrate Research, Chinese Academy of Sciences, Guangzhou, 510640, China;2. CAS Key Laboratory of Gas Hydrate, Guangzhou, 510640, China;3. Guangdong Provincial Key Laboratory of New and Renewable Energy Research and Development, Guangzhou, 510640, China;1. Shaanxi Key Laboratory of Impact Dynamics and Its Engineering Application, Northwestern Polytechnical University, Xi''an 710072, Shaanxi, China;2. School of Aeronautics, Northwestern Polytechnical University, Xi''an 710072, China;1. School of Civil Engineering, Southeast University, Nanjing 210096, China;2. Advanced Engineering Composites Research Center, Nanjing Tech University, Nanjing 211816, China;3. College of Civil Engineering, Nanjing Tech University, Nanjing 211816, China |
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| Abstract: | This paper introduces a nonlinear finite element analysis on damage propagation behavior of composite sandwich panels under in-plane uniaxial quasi-static compression after a low velocity impact. The major damage modes due to the impact, including the residual indentation on the impacted facesheet, the initially crushed core under the impacted area, and the delamination are incorporated into the model. A consequential core crushing mechanism is incorporated into the analysis by using an element deactivation technique. Damage propagation behavior, which corresponds to those observed in sandwich compression after impact (SCAI) tests, has been successfully captured in the numerical simulation. The critical far field stress corresponding to the onset of damage propagation at specified critical locations near the damage zone are captured successfully. They show a good correlation with experimental data. These values can be used to effectively predict the residual compressive strength of low-velocity impact damaged composite sandwich panels. |
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| Keywords: | sandwich structures impact delamination damage growth honeycomb core finite element method |
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