摘要
为快速准确得到不同静定支持方式的全机及大型部件结构静力试验约束点载荷,首次提出了一种通用求解方法并以MATLAB为平台编写了求解程序。重点研究了约束部位载荷严酷、较大变形工况中作为考核部位及机翼大变形工况中的约束点载荷计算;依据多年型号试验经验提出了一种利用约束点载荷误差判断试验加载准确性的方法。成功用于某大型客机全机静力试验,为实时判断试验加载是否准确提供了重要依据;试验结果表明提出的计算方法和程序准确可靠,已推广应用于其他型号试验。
In order to calculate the statically determinate restraint load of the full scale or large scale parts of aircraft structure static test with different statically determinate support quickly and accurately, a general solution method was firstly proposed, and then solved by Matlab. The calculation of restraint load under constrained components as critical location with heavy load and large displacement, large deformation wing conditions was mainly investigated. A way of estimating the accuracy of loading system through the restraint load error was summarized based on several years of airplanes test experiences. The method was applied on a large passenger aircraft static load test successfully, providing an important basis to estimate the loading accuracy in real-time. The result of test indicates that the methods and program are accurate and reliable. And it can be applied to other aircraft tests.
作者
郭琼
夏峰
刘冰
刘玮
GUO Qiong;XIA Feng;LIU Bing;LIU Wei(Aviation Technology Key Laboratory of Full-Scale Aircraft Static&Fatigue Test,Aircraft Strength Research Institute of China,Xi'an 710065,China)
出处
《科学技术与工程》
北大核心
2020年第19期7934-7940,共7页
Science Technology and Engineering
关键词
静定支持
大型客机
机翼大变形
大位移约束点
约束点载荷
statically determinate support
the large passenger aircraft
large deformation wing
large displacement constrained point
restraint load
