旋转周期复合材料层合结构的有限元屈曲分析

李军; 薛明德

旋转周期复合材料层合结构的有限元屈曲分析

李军,
薛明德

清华大学航天航空学院工程力学系, 北京 100084

基金项目: 国家“863”航天高科技项目(863-2-4-1-9)

详细信息

通讯作者:
薛明德,教授,研究方向:结构弹塑性分析和复合材料结构分析 E-mail:xuemd@mail.tsinghua.edu.cn

中图分类号: TB332
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出版历程
- 收稿日期: 2004-05-30
- 修回日期: 2004-09-28
- 刊出日期: 2005-06-14

BUCKLING ANALYSIS OF ROTATIONALLY PERIODICLAMINATED COMPOSITE SHELLS BY FEM

LI Jun,
XUE Mingde

Dept1of Engineering Mechanics, School of Aerospace, Tsinghua University, Beijing 100084, China

摘要

摘要: 针对空间结构中常见的复合材料层合壳体结构发展了一种多层相对自由度层合壳元。这种实体型壳元既可以用较粗的网格很好地模拟层合壳, 又易与三维实体单元相连接, 使变厚度、带有补强的复合材料层合壳体等复杂结构得以正确建模。同时运用旋转周期有限元技术对大规模的空间复合材料层合结构成功实施了屈曲分析。数值算例验证了本文计算策略的有效性。
- 屈曲分析 /
- 三维有限元法 /
- 复合材料 /
- 层合壳 /
- 旋转周期
Abstract: A new multilayer shell element with relative degrees-of-freedom (DOF) was developed for modelinglaminated composite shells of ten used in aerospace st ructures. With this solid-type shell element, satisfactory resolution can be ensured even if a relatively coarse FE mesh is employed, and this element can be easily connected withother solid type element s. All of these features enable it s promising application in the simulation of modern composite st ructures, even if with varying thickness or complicated joint part s. For the buckling analysis of large-scaleaerospace composite laminated st ructures, a computational st rategy that combines the rotationally periodic FEmethod and this new shell element is implemented successfully. The numerical examples show the efficiency andaccuracy of the proposed computational strategy.
- buckling analysis /
- 3D FEM /
- composite materials /
- laminated shell /
- rotational periodicity