一种新的柱形曲板轴压屈曲试验四边简支边界的实现方法  

A New Method for Implementation of Simple Supported Boundary in Stability Test of Cylindrical Panel under Axial Compression

作　　者：孙璐妍 余音[1,2] 陈博[3] 汪海[1,2] 

机构地区：[1]上海交通大学航空航天学院,上海200240 [2]上海交通大学民机结构强度综合试验室,上海200240 [3]中国商用飞机有限责任公司上海飞机设计研究院,上海201210

出　　处：《机械工程学报》2014年第8期53-58,共6页Journal of Mechanical Engineering

基　　金：国家自然科学基金(61175074);上海市科委重大科技攻关(12dz1100302)资助项目

摘　　要：提出一种新的柱形曲板轴压屈曲试验四边简支边界的实现方法。针对柱形曲板轴压稳定性试验简支边界条件的实现问题,设计一种支持边夹具及压盘,能够实现试件支持边的简支要求,消除试件成形回弹和厚度不均等因素引起的装配问题,且方便对试件进行对中调节。通过加强试件的边界,改善试件边界受载不均的情况,有效避免边界提前失稳的现象。加强后,试件的加载边面积变大,通过其与压盘间的摩擦力作用,形成加载边的简支约束。在某型号飞机的结构试验中,该方法得到成功应用。该试验借助于光学测量技术全场测量试件考核区的面外位移,得到试件屈曲模态。试验结果与有限元法分析结果进行对比,两者不仅模态一致,且试验屈曲载荷平均值与有限元结果相差在1%以内,验证了该方法的适用性和有效性。A new stability test method for implementation of simple supported boundary in stability test of cylindrical panel under axial compression is presented. As there have been no standards for implementation of simple supported boundary in stability test of cylindrical panel under axial compression so far, a set of fixtures are designed to implement the boundary condition of simple supporting rightly. By this fixture, the specimen assembly problem caused by flaws such as spring back, uneven thickness and so on could be solved. And it also provided conveniences for specimen adjusting in commissioning tests. Reinforced treatment for specimen can effectively avoid the boundary failure in the test. It can also enlarge the contact area so that the platen would implement the simple support boundary condition at the loading edges due to the friction without fixtures. The method has been successfully applied to the stability test of a cylindrical panel part of an aircraft. The buckling mode of specimen is obtained with the aid of optical measurement techniques. The test is also simulated with finite element method by introducing common geometric imperfections to the model. The simulation test result is identical with that of practical test, proving the validity and applicability of the method.

关 键 词：夹具 柱形曲板 屈曲 飞机结构 

分 类 号：TU33[建筑科学—结构工程]