复合材料整体加筋板轴压后屈曲失效评估方法

Post-buckling failure evaluation method of integrated composite stiffened panels under uniaxial compression

在飞机结构设计中,为高效完成复合材料加筋板结构设计,亟需一种快速有效的复合材料整体加筋板后屈曲失效评估方法。采用商业有限元软件ABAQUS建立了加筋板有限元模型,研究了复合材料整体加筋板的轴压后屈曲失效评估方法,即"整体-局部"法。通过对单筋条壁板后屈曲的失效分析发现,"整体-局部"法可得到初始脱胶时的位移和载荷值以及较准确的破坏载荷值,是一种能有效确定加筋板后屈曲失效情况的快速评估方法,对提高结构设计效率和减轻飞机结构质量具有重要的工程意义。

A post-buckling failure evaluation method of integrated composite stiffened panels is required for improving the structure design of composite stiffened panels effectively in the aircraft structure design under uniaxial compression.Finite element models were built using commercial finite element software ABAQUS for the study of the failure evaluation method of integrated composite stiffened panels under uniaxial compression at the post-buckling stage,which was also called'global-local'analysis technique.The study of post-buckling failure for a single-stiffener panel shows that'global-local'analysis technique can provide the displacement and load at the initial point of debonding,and the failure load can also be predicted accurately.The'global-local'analysis technique therefore is demonstrated to be an efficient method for rapid evaluation on post-buckling failure of stiffened panels under uniaxial compression,and is significant for improving efficiency of structure design and lightening aircraft's structure weight.