大型飞机主起落架连接区静力试验误差控制技术  

Error Control Technology in Static Test on Connection Area of Main Landing Gear of Large Aircraft

作　　者：刘冰[1] 王孟孟[1] 郑建军[1] 郭琼[1] 张永强 LIU Bing;WANG Meng-meng;ZHENG Jian-jun;GUO Qiong;ZHANG Yong-qiang(Key Laboratory of Static and Fatigue Test of Full-Scale Aircraft,AVIC Aircraft Strength Research Institute,Xi'an 710065,China)

机构地区：[1]中国飞机强度研究所全尺寸飞机结构静力/疲劳航空科技重点试验室,西安710065

出　　处：《科学技术与工程》2021年第10期4249-4254,共6页Science Technology and Engineering

摘　　要：主起落架作为飞机的重要部件,其基于全机的连接区静强度试验是飞机地面静强度试验必须的试验项目。试验中主起落架载荷大、变形大,该部位载荷施加的准确性会直接影响试验考核是否满足要求。为了提高该部位载荷施加准确性,提出基于全机约束点反馈的试验误差控制技术,通过分析全机约束点载荷误差的影响因素,筛选确定影响试验考核部位的载荷施加准确性的主要因素,并对主要因素进行优化处理。以某型飞机主起落架连接区为研究对象开展静力试验。结果表明,大型飞机主起落架连接区的试验误差控制技术可保证试验约束点反馈趋势与预期一致,试验误差控制达到了更高的水平且可靠性更高。飞机姿态主动控制及起落架随动加载等技术有效实现试验误差控制,提升了试验加载精度,可为同类试验提供参考。The main landing gear is an important part of the aircraft, and the static strength test of its connection area based on the full-scale aircraft is necessary. Due to the large load and large deformation of the main landing gear during the test, the accuracy of the loading could determine whether the test satisfy meets the requirements. To improve the accuracy of the loading in the target area, an error control technology based on the feedback of constraint point on full-scale aircraft was proposed. The impact factors on error of the constraint point based on the whole aircraft were analyzed, and then the main factors on the accuracy of the loading were selected and optimized to achieve the accurate loading of the main landing gear. The static test for the connection area of the main landing based on a type of aircraft was taken as the example. The results show that the error-control technology of the main landing gear joint area of large aircraft can ensure that the feedback trend of constraint points is consistent with the expectation, and the error control reach a higher level with higher reliability. The active control of aircraft attitude and self-adaptable loading technique for undercarriage can achieve error control effectively and improve the test accuracy. The results of the study provide a reference for similar experiments.

关 键 词：主起落架连接区 静力试验 约束点载荷 误差分析 

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]