带防热层复合材料锥壳热固化变形的数值模拟

张纪奎; 马志阳; 李学梅; 程小全

带防热层复合材料锥壳热固化变形的数值模拟

1.
北京航空航天大学航空科学与工程学院, 北京 100191
2. 航天材料及工艺研究所, 北京 100076

基金项目: 国家自然科学基金青年基金资助项目(50903002); 北京航空航天大学凡舟青年基金资助项目(20090506)

详细信息

中图分类号: TB332
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出版历程
- 收稿日期: 2012-08-30
- 修回日期: 2012-11-26
- 网络出版日期: 2013-08-30

Numerical simulation of cure deformation of composite taper shell with thermal protection layer

1.
School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2. Aerospace Research Institute of Materials and Processing Technology, Beijing 100076, China

摘要

摘要: 采用数值模拟方法研究带防热层缠绕成型复合材料锥壳热固化变形的形成机理和影响因素.建立了带防热层复合材料锥壳热固化变形预测的三维有限元程序.计算结果表明:外层防热材料和内层结构材料热膨胀系数不匹配是引起壳体固化变形的主要原因.提出在内层和外层之间增加中间过渡层的方法控制壳体的固化变形,中间层材料为丁腈橡胶片时可使固化变形减小20%以上.采用数值模拟方法讨论了中间层模量、厚度以及缠绕张力对壳体固化变形的影响,分析结果表明:固化变形随中间层模量的增加而增加,随中间层厚度的增加略有减小;缠绕张力释放增加壳体的固化变形,缠绕张力越大引起的固化变形越大.
- 复合材料 /
- 防热层 /
- 固化变形 /
- 数值模拟 /
- 影响因素
Abstract: A three-dimensional finite element model was developed to simulate and predict the cure deformation during the winding processing of a composite taper shell with thermal protection layers. According to the results of numerical simulation, the first cause of the shell's cure deformation was the thermal expansion coefficient difference between protection material and structural material which lay on outer layers and inner layers respectively. Meanwhile, this cure deformation can be controlled effectively by adding the middle layer between outer layers and inner layers, which reduced about 20% deformation by using nitrile rubber as the middle layer's material. The effects of other influence factors were also discussed: cure deformation was increased by improving the middle layer's modulus and decreased slightly by increasing the middle layer's thickness; the relief of winding tension, to some degree, had an impact on deformation, and larger tension leads to higher deformation.
- composite materials /
- thermal protection layer /
- cure deformation /
- numerical simulation /
- influence factor

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参考文献(14)

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