一种拓扑优化方法在机翼可变后缘中的研究

摘要

实现机翼在不同的飞行状态下的最优气动外形是自适应机翼的一项关键技术。针对传统铰链机构会使机翼表面产生不连续变化从而导致气流提早分离的问题，具有连续平滑变形和轻量化特点的柔性机构受到重视。根据机翼后缘在不同飞行状态下气动外形的要求，以目标形状与实际形状的距离为最小优化目标，对柔性机构进行了拓扑优化。在优化方法上，传统的拓扑优化方法因参数化对象为结构微元，不可避免的存在棋盘化等现象，本文中采用的拓扑优化方法以栽荷路径为参数化对象，同时在约束中引入连接性要求，有效的避免了优化结果物理不可实现的情况。结合实例，运用Isight联合Patran、Nastran进行多学科仿真分析。结果表明：该柔性机构能够实现预期的形状变化。%Making aircraft wing variation under different ilying speeds is a key technology ot variable camber adaptive wing. But traditional hinged mechanism makes wing surface have discontinuous changes, then leading to earlier airflow separation. To solve the problem, compliant mechanism attracts much attention nowadays on account of its characteristics at the continuous smooth deformation and the lightweight. According to the trailing＇s deformation requirements under different flight conditions, with the least distance between actual shape and desired shape as the target, and a load-path-based method is used to make topological optimization in the compliant mechanism. Different from traditional parametric method taking micro structure as parametric object, the method assigns binary pa- rameter to load path, considering the connectivity in the meantime, the optimization result can avoid the hardly achieved problem, such as checkerboard. Combined with examples, using Isight,Patran and Nastran make the simulation analysis, results show that compliant mechanism achieves the deformation requirements.