Combined Tensile-Bending Load Simulation of the Notched Thick Wall Multi-Layer Laminate Composite Used for Aircraft Body Building

Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F00%3A00000191" target="_blank" >RIV/00216305:26210/00:00000191 - isvavai.cz</a>
Result on the web
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DOI - Digital Object Identifier
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Result language
angličtina
Original language name
Combined Tensile-Bending Load Simulation of the Notched Thick Wall Multi-Layer Laminate Composite Used for Aircraft Body Building
Original language description
A stress strain analysis of a thick wall multi-layered laminate specimen, unsymmetrically loaded by a tensile-bending combination, with the central notch in the shape of a round hole was performed by the finite element method. Orthotropic behavior of single material layers, real nonlinear material properties and geometric nonlinearities induced by large deformations were considered in the finite element model. The performed numerical investigation was used as a prototype simulation of the real materialbehavior to model real tensile-bending loading conditions in riveted lap joints of the aircraft fuselage structure. Results of the parametric study for various tensile loading and various tensile-bending ratio are summarized graphically.
Czech name
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Czech description
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Publication year
2000
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Article name in the collection
Ninth International ANSYS Users Conference and Exhibition
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Number of pages
1
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Publisher name
ANSYS, Inc., Southpointe, 275 Technology Drive, Canonsburgh, PA 15317
Place of publication
Pittsburgh, Pennsylvania, U.S.A.
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