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为提高直升机复合材料旋翼桨叶结构设计效率,依据实际工程应用情况,提出了一种基于参数化组件定义的复合材料旋翼桨叶结构优化设计方法。以C型梁复合材料旋翼桨叶为研究对象,建立以精确的桨叶组件定义参数为设计变量的剖面优化和整体优化模型,通过桨叶的剖面优化确定出整体优化的初值,再由桨叶整体优化实现桨叶结构的最优设计。最后对某型主桨叶进行结构设计实例验证,结果表明该方法能够有效地实现直升机复合材料旋翼桨叶结构优化设计。
In order to improve the design efficiency of helicopter composite rotor blade structure, a composite rotor blade structure optimization design method based on parametric component is proposed according to the actual engineering application. Taking the C-beam composite rotor blade as the research object, the section optimization and the overall optimization model are established with the precise parameters of the blade assembly as the design variables. The initial value of the overall optimization is determined through the section optimization of the blade, Optimal Design of Blade Structure Optimized for Leaf Overall Optimization. Finally, the structural design of a main blade is validated. The results show that the proposed method can effectively realize the helicopter composite rotor blade structure optimization design.