直升机复合材料国产化桨叶剖面特性的分析

由于国产复合材料性能较进口复合材料有较大变化，根据替代前后桨叶的动力学特性基本不变的原则对原桨叶结构进行了调整。采用薄壁梁横截面剪流相等的原理推导了桨叶扭转刚度的计算公式，基于挥舞刚度、摆振刚度、质量分布的定义得到了迭代公式。对某直升机替代前后桨叶的剖面特性进行了计算。结果表明：替代前后桨叶的扭转刚度、挥舞刚度、摆振刚度及单位长度质量分布完全一致，说明替代前后桨叶的剖面特性有很好的一致性。

Analysis of section characteristics of helicopter blades with domestic composite

Domestic composite helicopter rotor blades performance is much different from imported , so that blades structure are adjusted based on equality standard of blades dynamic characteristics in condition imported composite is replaced by domestic composite. First, this paper deduces torsional rigidity formula using shear flow principle in thin - walled beam, and flap stiffness , lag stiffness and mass distribution of unit length iteratire formula ~ecording to their definitions. Second, section characteristics of replaced blades and original blades are calculated. The results show that replaced blades are identical with original ones . These indicates that there is good consistent of replaced section characteristics with original.