复合材料机身加筋壁板结构稳定性分析(英文)

supported by National Natural Science Foundation of China ( No. 11202078)Local buckling load and overall buckling load of stiffened composite fuselage panel were analyzed by both FEM and engineering method. In engineering method,local buckling of the stiffened panel was simplied as plate supported on four sides,and overall buckling was considered as the transverse shear effects. Eigenvalue analysis method was used for local buckling of stiffened panel,and non-linear arc-length method was used for overall buckling of stiffened panel in finite element method. The results of two methods are consistent.针对复合材料机身壁板结构局部失稳和总体失稳,分别运用工程计算方法和有限元方法进行计算。工程方法计算局部失稳把结构简化为四边简支板的失稳,总体失稳把结构简化为考虑横向剪切的欧拉失稳;有限元法运用特征值分析法计算加筋板局部失稳,运用非线性弧长法计算加筋板的总体失稳。最后,两种方法得到的结果一致。     

基于汽车正面碰撞的吸能盒设计及优化

对汽车正面碰撞有限元模型进行了分析,建立了可替代整车碰撞模型的子模型,并对其进行验证。在所建立的子模型的基础上,设计出了双层波纹管样式的吸能盒结构,利用自适应响应面法对其厚度进行优化设计。整车碰撞仿真结果表明:吸能盒结构吸收的能量比原结构提高了14.2%,纵梁碰撞力比原结构减小了15.3%。