弯曲载荷下机身壁板结构快速优化设计方法

摘要

给出了机身结构在弯曲载荷作用下，机身壁板尺寸参数确定的原则和方法。通过对机身典型剖面结构形式的简化，得到了机身尺寸参数与壁板应力之间的关系表达式，根据强度控制原则，对壁板结构进行了优化迭代，得到了满足要求的壁板尺寸参数，并与有限元应力分析进行对比。结果表明，所推导的机身壁板应力与有限元分析得到的应力结果吻合较好。该方法可实现机身壁板结构快速优化，对初期结构设计具有指导意义。%The method how to determine the dimensions of fuselage panel under bending moment was introduced. The formula for calculating stress and dimensions was deduced based on the simplified model of typical fuselage structure. After the opitmization analysis using formulae,the panel parameters which satisfied the strength requirements were obtained. It was found that the formula results greatly fit the the FEM results from Msc.Nastran software. This method can achieve the rapid optimization on fuselage panel under bending moment and guide the preliminary structure design.