POST-CRITICAL DEFORMATION STATES OF COMPOSITE THIN-WALLED AIRCRAFT LOAD-BEARING STRUCTURES

被引：0
|
作者：
Kopecki, Tomasz [1 ]
Bakunowicz, Jerzy [1 ]
Lis, Tomasz [1 ]
机构：
[1] Rzeszow Univ Technol, Fac Mech Engn & Aeronaut, Rzeszow, Poland
来源：
JOURNAL OF THEORETICAL AND APPLIED MECHANICS | 2016年 / 54卷 / 01期
关键词：
skin; loss of stability; finite element method; composite; equilibrium path;
D O I：
暂无
中图分类号：
O3 [力学];
学科分类号：
08 ; 0801 ;
摘要：
The study presents results of experimental examination of a model representing a fragment of an aircraft wing structure with the skin made of a glass fibre/epoxy composite. For such a system, the deformation pattern has been found and the representative equilibrium path determined. The finite element method has been used to develop the corresponding numerical model, the correctness of which has been then verified by comparing the obtained results with the course of the relevant experiment. Conformity of the results allowed one to determine usefulness of the applied methods in the assessment of mechanical properties of modified solutions involving integral skin stiffening elements.
引用
收藏
页码：195 / 204
页数：10
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