期刊名称：Advances in Science and Technology Research Journal
印刷版ISSN：2080-4075
电子版ISSN：2299-8624
出版年度：2018
卷号：12
期号：1
页码：293-302
DOI：10.12913/22998624/85660
语种：English
出版社：Society of Polish Mechanical Engineers and Technicians
摘要：This paper presents results of experimental and numerical analysis in terms of the finite element method of skin components of aircraft load bearing structures. The subject matter of the study was composite panels with stiffeners in the form of a regular grid of oriented longitudinal elements in accordance with the directions of the principal stresses in the covering. Analysis was conducted in the buckling states of structural deformation which showed that structures with stiffeners exhibit much more favorable behavior in buckling deformation states than in laminar structures. This translates into stress distributions and their gradients, which are milder in forms of stiffened structures.
关键词：buckling;isogrid;loss of stability;aircraft load-bearing structures;finite elements method;nonlinear numerical analysis
