采用等效有限元模型的复合材料机翼结构优化

在机翼设计过程中,将等效有限元模型(EFEM)方法应用于考虑静力学和动力学要求的机翼结构优化。提出了"三步走"的结构优化策略,将一个多变量的复杂优化问题转换为一系列少变量的简单优化问题,对某支线客机的复合材料机翼进行了优化设计。首先以位移、静强度和颤振速度作为约束条件对机翼复合材料铺层比例进行优化;然后以静强度和结构稳定性作为约束,以最小化结构质量和结构效率作为优化目标,对各翼肋之间的加强壁板进行优化设计;最后再以位移和颤振速度为约束,对机翼结构总体刚度进行优化设计。结果表明:EFEM方法具有快速建模和计算量少的优点,采用"三步走"优化策略具有更高的效率,适用于初步机翼结构优化设计。

Structural optimization of composite wing using equivalent finite element model

In the process of wing design, equivalent finite element model (EFEM) method was utilized for the optimization of wing structure with static and dynamic constraints. An structure optimization strategy with three steps, which convert a multivariable complex optimization problem to a series of simple optimization problems with a few design variables, was proposed for a composite wing of regional civil jet design. Firstly, the ratio of composite layers was optimized with displacement, static strength and flutter speed as constraints. Then each stiffened panel between ribs was optimized for minimizing structure weight and structure efficiency with the static strength and structure stability as constraints. Finally, the overall stiffness of the wing structure was optimized with displacement and flutter speed as constraints. The results show that the EFEM method is suitable for wing structure preliminary optimization for the advantage of rapid modeling and low computational cost. And the strategy with three steps in the structural optimization has higher efficiency.