基于误差控制的大展弦比机翼静强度试验载荷处理技术  

Load Process Technology Based on Error Control for Static Strength Test of High-aspect Ratio Wing

作　　者：刘冰[1] 张赟[1] 刘玮[1] 吴强[2] 

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 [2]上海飞机设计研究院强度部,上海201210

出　　处：《科学技术与工程》2017年第30期356-360,共5页Science Technology and Engineering

摘　　要：全机静力试验中,机翼作为主要考核部位,其受载是否准确对试验结果具有重大意义。高空长航时飞机机翼一般展弦比较大,试验中其加载方向会随着机翼的变形发生变化,导致试验机受载与实际情况不同,试验结果不准确。为解决上述问题,提出了一种针对大展弦比机翼试验载荷的处理技术,将原始载荷处理为试验载荷并进行修正。最后以某大型客机机翼为研究对象,对其载荷进行处理并应用。结果表明该处理方法满足试验要求,具有较高的精度,对同类问题具有很高的参考价值。The initial load of airfoil is uniform load,which can＇t be used directly and should be processed.In the static test of high-aspect ratio wing,the load direction will be inflected because of the large deformation which makes test result inaccurate.A load process method aim at high-aspect ratio wing was proposed for solve the problem mentioned above,which include additional load revise.At last,the load of wing of one aircraft was taken as research object and the test result indicates that the method was reasonable,which can be used as a reference for other similar static test.

关 键 词：大展弦比机翼 载荷处理 载荷修正 

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]