大展弦比机翼试验随动加载系统研究

在飞机结构试验中,通常会遇到试验加载点随试验件变形而移动变化的问题,尤其是机翼大变形会导致加载点与翼面不垂直的问题。开发一种适用于全复合材料机翼试验的随动加载系统,该系统引入有限元分析方法将机翼变形划分成N个特征飞行点,采用飞行点随动加载来保证各级加载点与翼面的垂直度,实现垂直跟随加载;应用该加载系统进行大展弦比的机翼静力试验。结果表明:运用该加载系统可顺利实现该无人机机翼试验,且加载过程平稳,试验件无抖动,变形均匀,应变数据符合试验要求,可以为类似加载系统提供设计依据。

The design of servo loading systems on high aspect ratio wing test

It occur that the loading point changes with the test piece in the aircraft structure test. In particularly, the large deformation of the wing will cause the issue that loading point is not perpendicular with the flat of the wing. In this paper, a kind of servo loading systems is applied in composite materials airplane wing. The wing is divided into N characteristic of flying points by using the method of finite element analysis. To keep all levels of loading points are vertical with the flat of wing we keep the fly points move with loading. It implements vertical following loading. This system is used to complete the highSaspectSratio test. The test results show that the system can realize the test of the UAV by using the servo load systems,and the laoding procedure is smooth. The test piece is no jitter, its deformation is uniform, and the strain data meets the test requirements which can offer a reference for the analogous loading systems and has a large practical significance and application value.