一种直升机旋翼桨叶剖面设计方法

Method for designing blade sections of helicopter rotors

Abstract

本发明公开了一种基于拓扑优化的直升机旋翼桨叶剖面设计方法,属于直升机技术领域。首先根据气动要求确定外形参数,指定优化目标函数、约束函数,建立优化模型;然后采用有限元软件建立桨叶几何模型并划分网格,将节点、网格和材料信息导入到MATLAB软件中,采用以每一个单元密度为设计变量的SIMP算法;再次求解当前设计状态的旋翼桨叶敏度信息,并采用敏度过滤方法以避免棋盘格问题,更新桨叶剖面单元的密度信息;最后求解更新前后的密度差值,满足收敛条件则结束优化,否则以更新后的密度为初始设计参数继续迭代计算直到收敛,最后输出桨叶结构型式。本发明提出的桨叶设计方法可以应用于概念设计阶段的桨叶结构初步设计。
The invention discloses a method for designing blade sections of helicopter rotors, and belongs to the technical field of helicopters. The method comprises determining appearance parameters according to pneumatic requirements, designating optimization objective functions and constraint functions, and establishing optimization models; utilizing finite element software to establish blade geometric models and dividing grids, importing node, grid and material information into matrix laboratory (MATLAB) software, and utilizing an implicit method for pressure linked equations (SIMP), wherein the SIMP uses every cell density as a design variable; calculating rotor blade sensitivity information in a current design state again, utilizing a sensitivity filter method to avoid checkerboard problems, and updating density information of blade section units; and calculating density differences before and after update, ending optimization if convergence conditions are met, otherwise, continuing iterative computations with updated densities as initial design parameters till convergence is achieved, and outputting blade structural styles. The method for designing blade sections of helicopter rotors can be applied to initial designs of blade structures of conceptual phases.

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