一种机身壁板复合加载试验的载荷计算方案  

A Load Calculation Scheme for Combined Loading Test of Fuselage Panel

作　　者：孙喜桂 郭瑜超[1] 聂小华[1] Sun Xigui;Guo Yuchao;Nie Xiaohua(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,陕西西安710065

出　　处：《工程与试验》2023年第1期27-29,共3页Engineering and Test

基　　金：民用飞机专项科研项目(MJZ3-2N21)。

摘　　要：机身壁板的受力状态十分复杂,而试验平台只能施加拉伸/压缩载荷、剪切载荷、气密载荷等基准载荷及其组合形式。本文介绍了一种机身壁板复合加载试验的载荷计算方案,首先计算出各基准载荷的施加比例,按照该比例将各基准载荷组合起来,然后进行组合载荷作用下的有限元分析,并与原始有限元分析结果进行对比,最终得到长桁的轴力基本一致,且各应变分量的误差都在5%以内,表明该载荷计算方案可以用来确定机身壁板复合加载试验的载荷。The stress state of fuselage panel is very complex,and the test platform can be only used to apply standard loads,such as tensile/compression load,shear load,pressure load or their combination.A load calculation scheme for combined loading test of fuselage panel is introduced in the paper.Firstly,the standard loads ratio is obtained,and the standard loads is combined according to the proportion of each standard loads.The finite element analysis is carried out under the combined loading,and the result is compared with the original finite element analysis result.The axial forces are consistent,and the errors of each strain component are all within 5%.The results show that the load calculation scheme is feasible.

关 键 词：机身壁板 载荷系数 载荷计算方案 

分 类 号：V214.1[航空宇航科学与技术—航空宇航推进理论与工程]