变弯度机翼后缘结构试验技术研究  

Research on the Test Technology of Trailing Edge Structure of Variable Camber Wing

作　　者：李耀 庞宝才[1] 周挺[1] LI Yao;PANG Baocai;ZHOU Ting(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi′an710065,Shaanxi,China)

机构地区：[1]中国飞机强度研究所,强度与结构完整性全国重点实验室,陕西西安710065

出　　处：《工程与试验》2024年第1期42-47,共6页Engineering and Test

摘　　要：本文针对全尺寸变弯度机翼后缘柔性蒙皮大变形的结构特点,对变弯度机翼后缘结构试验技术进行了研究。在对几种随动加载方法进行对比研究的基础上,提出了一种丝杠模组与力控作动筒联合主动控制的随动加载方案。通过变弯度机翼后缘结构地面试验对该随动加载方法进行了试验验证,试验结果表明,采用该随动加载方法,加载精度与测量结果均满足试验要求,可以实现气动载荷的准确施加。本研究为可动翼面的载荷施加提供了参考,试验数据为变弯度机翼后缘设计改型提供了依据。The test technology of the trailing edge of a full-size variable camber wing with the structural characteristics of large deformation is studied in the paper.Based on the comparative study of several tracking-loading methods,a tracking-loading scheme based on the joint active control of screw module and force control actuator is proposed.The method is verified by the ground test of the trailing edge structure of variable camber wing.The test results show that the loading accuracy and measurement results meet the test requirements,and the aerodynamic load can be accurately applied by using this method,which provides a reference for the load application of movable wing surface.The experimental data can provide a basis for the design and modification of the trailing edge of variable camber wing.

关 键 词：变弯度机翼 大变形 随动加载 气动载荷 

分 类 号：V216.1[航空宇航科学与技术—航空宇航推进理论与工程]