摘要
为解决变弯度机翼前缘柔性蒙皮结构设计问题,提出基于遗传算法的柔性蒙皮全参数优化方法。采用"刚度剪裁"设计理念,以大型远程飞机前缘为研究对象,通过优化变量缩减、设计区域规划和边界条件位移等效,对柔性蒙皮结构进行工程简化,在保证变形精度的同时达到降低模型复杂度的目的;基于遗传算法对蒙皮结构进行全参数同步优化,以获得混合优化变量的全局最优解。研究表明,该方法在兼顾优化效率和制造可实现的基础上,使前缘蒙皮变形的最小二乘误差(LSE)降低60%,最大偏移误差降低64%,可显著提高变形精度。
In order to solve the design problem of flexible skin structure on the leading edge of a wing with variable camber,an integrated method of normal optimization of flexible skin based on genetic algorithm is proposed.Based on"stiffness tailoring"concept,taking leading edge of long-range aircrafts as the research object,after a series of pre-simplification,such as design variables cutting down,optimal designing area partition and displacement boundary condition equalizing,in which the skin manufacturability is also taken into account,the final flexible skin model is obtained through a genetic-algorithm-based normal optimization,which boasts of its excellent globally-searching capability in highly coupling state of design variables.This integrated method exhibits great reliability and high efficiency through the numerical verification of a flexible skin model,of which,reducing the least-squares error(LSE)and the maximum deviation error of leading edge skin deformation by 60%and 64%,and significantly improving the deformation accuracy.
作者
吕帅帅
王彬文
杨宇
王志刚
LüShuaishuai;Wang Binwen;Yang Yu;Wang Zhigang(Intelligent Structure and Structural Health Monitoring Laboratory,Aircraft Strength Research Institute,710065,Xi’an,China)
出处
《应用力学学报》
CAS
CSCD
北大核心
2020年第2期617-623,I0011,共8页
Chinese Journal of Applied Mechanics
基金
基于机械机构/柔性结构的机翼前缘变形与驱动技术研究。
关键词
变弯度前缘
柔性蒙皮
全参数优化
边界条件位移等效
变量缩减
遗传算法
morphing leading edge
flexible skin
normal optimization
displacement equivalence of boundary conditions
variables reduction
genetic algorithm
