| 复合材料桨叶过渡剖面边界区域应力传递边界效应初探 |
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| 引用本文： | 余洵,王栋,吴堂珍,张波.复合材料桨叶过渡剖面边界区域应力传递边界效应初探[J].直升机技术,2013(3):18-20. |
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| 作者姓名： | 余洵 王栋 吴堂珍 张波 |
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| 作者单位： | 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 |
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| 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。
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| 关 键 词： | 复合材料桨叶 过渡剖面 边界区域 应力传递 |
Preliminary Exploration on Boundary Effect of Stress Transmission of Transitional Section Boundary Area of Composite Blade |
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| Authors: | YU Xun WANG Dong WU Tangzhen ZHANG Bo |
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| Institution: | l (1. China Helicopter Research and Development Institute, Jingdezhen 333001, China; 2. Army Aviation Military Representative Office in Jingdezhen Region, Jingdezhen 333000, China) |
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| Abstract: | 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. |
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| Keywords: | composite blade transitional section boundary area stress transmission preliminary exploration |
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