摘要
针对受压加筋曲壳的后屈曲特点,提出了一个后屈曲载荷的快速计算方法。用一部分有效蒙皮代替蒙皮失稳后的承载能力,利用欧拉失稳模型估算后屈曲失稳临界载荷。以外形参数给定的机身加筋壳结构为例,基于蒙皮局部失稳的简化模型,利用二次序列法优化求解结构的最佳布局。然后按照之前提出的后屈曲载荷的快速计算方法,设计筋条的截面刚度,最终得到最轻的机身结构质量。
According to the post-buckling＇s characteristics of compressed stiffened shellDa fast calculate method was proposed. The conception of effective skin was defined to calculate the skin post- buckling load capacity, and the post-buckling critical load was estimated by the Euler buckling model. It took a settled shape parameters of stiffened shell structure of fuselage for example. This paper used sequential quadratic programming method to obtain the optimum solution which is based on simplified model of skin local buckling. Then the rib＇s section stiffness is designed based on the fast calculate method of post-buckling critical load.
出处
《飞机设计》
2014年第3期11-15,共5页
Aircraft Design
关键词
复合材料
加筋圆柱壳
非线性有限元
后屈曲
composite
stiffened cylindrical shell
nonlinear finite element method
post buckling
