关键词: 夹具　柱形曲板　屈曲　飞机结构

Abstract: 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.

Key words: fixture;cylindrical panel;buckling;aircraft structure