EXPERIMENTAL VALIDATION OF NUMERICAL MODEL OF COMPOSITE PANEL FOR AEROSPACE STRUCTURAL APPLICATIONS

被引：0
|
作者：
Mucha, W. [1 ]
Kus, W. [1 ]
Viana, J. C. [2 ]
Nunes, J. P. [2 ]
机构：
[1] Silesian Tech Univ, Dept Computat Mech & Engn, Ul Konarskiego 18A, PL-44100 Gliwice, Poland
[2] Univ Minho, IPC Inst Polymers & Composites, Dept Polymer Engn, Campus Azurem, P-4800058 Guimaraes, Portugal
来源：
ENGINEERING MECHANICS 2020 (IM2020) | 2020年
关键词：
Hat-stiffened panel; Finite element method; Laminate; Bending stiffness;
D O I：
10.21495/5896-3-358
中图分类号：
T [工业技术];
学科分类号：
08 ;
摘要：
Composite panels are widely used in aerospace structural applications (e.g., fuselage, wings). A typical hat-stiffened panel was manufactured using the vacuum infusion process. The applied material is carbon/epoxy 10-layer laminate. The global properties of the laminate were computed from the mechanical properties of a single ply. Finite element model of the panel was created and validated experimentally by measuring bending stiffness of the panel in different points.
引用
收藏
页码：358 / 361
页数：4
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