飞翼结构构型气动弹性优化设计方法

An Aeroelastic Optimization Design Approach for Structural Configuration of Flying Wings

针对飞翼布局的早期构型设计,基于遗传算法提出一种气动弹性综合优化设计方法。采用等效板多板模型计算翼面结构动力学特性,利用面元法计算气动力。在考虑颤振速度、静气动弹性变形约束的情况下,以飞翼结构质量最小为目标开展优化设计。结果表明,形状参数优化设计对于飞翼的减重更为直接。当涉及构型尺寸参数设计时,同时进行两种参数的综合优化可以得到较轻的机翼结构,但计算成本较大。采用先进行构型优化,再进行尺寸优化的分级优化方法能快速获得最优的参数组合和满意的减重效果。为飞翼式飞行器的结构总体设计提供了一种快速有效的气动弹性综合优化设计方法。

An integrated aeroelastic optimization design approach based on the genetic algorithm is developed for the pre- liminary configuration design of a flying wing. An equivalent multi-plate model is adopted to resolve the structural dynamics characteristics. A panel approach is used to compute the aerodynamic force. A simple parameterization method is used to describe the wing geometry. The approach is applied to a flying wing and the objective is to minimize the structural mass subject to the static aeroelastic deformation and critical flutter speed constraints. It is found that the configuration parameter is more important for reducing the structure mass and a multilevel optimization is advised when the configuration and sizing variables are considered. The method provides a useful tool for the preliminary configuration design of a flying wing.