复合材料桨叶过渡剖面边界区域应力传递边界效应初探  

Preliminary Exploration on Boundary Effect of Stress Transmission of Transitional Section Boundary Area of Composite Blade

作　　者：余洵[1] 王栋 吴堂珍[1] 张波[1] 

机构地区：[1]中国直升机设计研究所,江西景德镇333001 [2]陆航驻景德镇地区军事代表室,江西景德镇333001

出　　处：《直升机技术》2013年第3期18-20,共3页Helicopter Technique

摘　　要：在复合材料桨叶载荷标定前的解耦或应力应变测量等工作中,会碰到一个"奇怪"的现象:在桨叶过渡剖面边界区域测出的应变(或应力)与"平剖面假设"规定不符。文章从某型号尾桨叶载荷标定前解耦调片工作中碰到的现象引出论点,再用有限元对桨叶传力进行建模分析,给出了定性的结论。文章的目的就是从型号中来,再应用到型号工作中去,为今后的复合材料桨叶载荷测量的贴片位置选择起一指导作用。During de-coupling and stress/strain measuring of composite rotor blades before load cal- ibration, a ＂strange＂ phenomenon was found ： the strain （ or stress） measured in transitional section boundary area of the blades did not comply with the ＂assumption of plane section＂. Based on this phenomenon in a tail blade of a helicopter, this paper has given a qualitative conclusion by using FEM analysis of the blade. The purpose of this paper was to apply technologies obtained from a type development to another type development, thus to give a guide on the selection of gauge - sticking positions of composite blade for load measurement.

关 键 词：复合材料桨叶 过渡剖面 边界区域 应力传递 

分 类 号：V215.2[航空宇航科学与技术—航空宇航推进理论与工程]