| 复合材料叠层板固化成型后的变形分析计算 |
| |
| 引用本文： | 官霆%孙良新%邢丽英.复合材料叠层板固化成型后的变形分析计算[J].宇航材料工艺,2006,36(1):34-37. |
| |
| 作者姓名： | 官霆%孙良新%邢丽英 |
| |
| 作者单位： | 1. 南京航空航天大学航空宇航学院,南京,210016
2. 北京航空材料研究院,北京,100095 |
| |
| 摘 要： | 分析复合材料铺层的微观结构，研究复合材料成型过程变形特点，以此建立两类针对性的有限元模型，并采用典型复合材料叠层板固化成型温度载荷，进行叠层板翘曲变形和板内应力的计算分析。在此基础上，将计算结果与实际试验制件实测结果进行对比。结果表明，本文所提供的有限元分析计算模型可对实际情况进行简便和较为精确的模拟。
|
| 关 键 词： | 复合材料 叠层板 残余应力 残余变形 |
| 收稿时间： | 2004-10-25 |
| 修稿时间： | 2004-10-252005-03-21 |
Composite Laminates Deformation Analysis and Calculation After Curing |
| |
| Guan Ting,Sun Liangxin,Xing Liying.Composite Laminates Deformation Analysis and Calculation After Curing[J].Aerospace Materials & Technology,2006,36(1):34-37. |
| |
| Authors: | Guan Ting Sun Liangxin Xing Liying |
| |
| Institution: | 1.Nanjing University of Aeronautics and Astronautics, Nanjing 210016;2. Beijing Institute of Aeronautical Materials, Beijing 100095 |
| |
| Abstract: | The micro composition and the deforming theorem of composite laminates are analyzed. Accordingly, the special finite element models are built, and the residual deformation and the stress are calculated and analyzed with the composite curing temperature load. The analysis of the results of the finite element model is completed. Moreover, the calculating results are compared with that of test specimen. The difference between calculation and test are analyzed. The result shows that the composite deforming finite element analyzing method is simple and effective. |
| |
| Keywords: | Composite Laminate Residual stress Residual deformation |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ |
| 点击此处可从《宇航材料工艺》浏览原始摘要信息 |
| 点击此处可从《宇航材料工艺》下载免费的PDF全文 |
