摘要
应用能量变分方法，对多向铺设的复合材料层合板结构进行了后屈曲分析．在分析中计及了几何非线性和物理非线性的影响，导出了层合板结构的总势能表达式，最后获得在面内纵向压缩载荷下的非线性后屈曲控制方程．通过对几种碳／环氧复合材料层合板铺层情况的编程计算，得到了不同的经典临界值Ｐｌｃｒ及其后屈曲平衡位形曲线，即Ｐｌ／Ｐ１ｃｒ～Ｗｌ／Ｈ曲线，并总结出一些带有规律性的结论．
The post-buckling is analyzed for multioriented composite laminates by means of the en-ergy variational method. The influences of geometry nonlinearity and physics nonlinearity of the composite material are taken into account. The total potential energy expressions for composite laminates are proposed. The governing equations of nonlinear post-buckling for composite laminates under axial compressive loads in plane can be obtained. Numerical re-sults are given for graphite/epoxy composite laminates with various fiber orientation and dif-ferent layer numbers. The classical critical buckling load P1cr and the curves of post-buckling equilibrium P1/P1cr～W1/H are obtained. Some conclusions beneficial to practical engineering are sumarized.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1994年第2期174-178,共5页
Journal of Beijing University of Aeronautics and Astronautics
关键词
层板
复合材料
屈曲
后屈曲
航空
laminates
composite materials
non-linear
buckling
post-buckling
