大型飞机主起落架静力试验加载控制技术研究  

Study on Loading Control Technology for Static Test of Main Landing Gear of Large Aircraft

作　　者：燕晨耀 吝继锋[1] 王晓鑫[1] Yan Chenyao;Lin Jifeng;Wang Xiaoxin(Full Scale Aircraft Structure Static/Fatigue Laboratory of Aircraft Strength Research Institute of China,Xi′an 710065,Shaanxi,China)

机构地区：[1]中国飞机强度研究所,全尺寸飞机结构静力/疲劳实验室,陕西西安710065

出　　处：《工程与试验》2022年第4期75-77,共3页Engineering and Test

摘　　要：针对大型水陆两栖飞机主起落架静力试验中飞机起落架部位加载空间小且加载精度受飞机变形影响大的问题,对主起落架协调加载及精准控制的方案进行研究,首次提出一种基于计算通道的协调加载控制技术。测试验证及起落架试验应用表明,该技术方案合理、可行,试验加载过程平稳、准确,应变响应线性良好,满足结构强度试验加载要求。该技术在同类型试验中具有一定的推广价值。In the static test of the main landing gear of large amphibious aircraft,the loading space of the landing gear is small,and the loading accuracy is greatly affected by the deformation of the aircraft.The coordinated loading and precise control scheme of the main landing gear is studied,and a coordinated loading control technology based on computational channel is proposed for the first time.The test verification and the landing gear test application show that the technical scheme is reasonable and feasible.The test loading process is stable and accurate,and the strain response is linear,which meets the loading requirements of structural strength test.The method proposed in the paper has certain popularization value in the same type test.

关 键 词：大飞机 结构强度试验 协调加载控制 起落架 

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]