复合材料加筋板后屈曲承载能力工程分析方法

王菲菲; 崔德刚; 熊强; 罗小强

复合材料加筋板后屈曲承载能力工程分析方法

1.
北京航空航天大学航空科学与工程学院, 北京 100191
2. 成都飞机设计研究所,成都 610041

详细信息

中图分类号: V 214.8
计量
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- 被引次数: 0
出版历程
- 收稿日期: 2012-04-23
- 网络出版日期: 2013-04-30

Engineering analysis of post-buckling loading capability for composite stiffened panels

1.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2. Chengdu Aircraft Design and Research Institute, Chengdu 610041, China

摘要

摘要: 根据复合材料的力学特性,结合有限元理论和工程经验,提出了一种计算复合材料加筋板结构后屈曲承载能力的工程简化理论与方法,并以复合材料J型加筋板计算模型为例,从工程角度说明了计算后屈曲承载能力的思路与公式.利用该方法通过算例计算,将计算结果与实验结果进行对比,发现该种复合材料加筋板稳定性计算方法可以解决后屈曲的几何非线性带来的计算难度,能保持较高的精度,并可用于飞机结构设计的实际应用中.
- 复合材料 /
- 加筋板 /
- 后屈曲 /
- 承载能力
Abstract: A project simplified theory and a method of calculating post-buckling loading capacity of composite stiffened panels based on the basic mechanics characters of composite materials were presented, which combining with FEM theory and engineering experience. Composite J-stiffened panels were taken as an example to illustrate thinking and computational formula of post-buckling analysis from the perspective of engineering. The validity and effectiveness of the method were demonstrated with the experiment. It is shown that the computing method of stability loading capability can solve the geometric non-linear analysis of composite stiffened structure load capability and keep high accuracy faced in the aerostructure design.
- composite materials /
- stiffened panels /
- post-buckling /
- loading capacity

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参考文献(8)

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