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

Kód výsledku v 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>

Výsledek na webu

—

DOI - Digital Object Identifier

—

Jazyk výsledku

angličtina

Název v původním jazyce

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

Popis výsledku v původním jazyce

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.

Název v anglickém jazyce

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

Popis výsledku anglicky

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.

Druh

D - Stať ve sborníku

CEP obor

JI - Kompositní materiály

OECD FORD obor

—

Projekt

—

Návaznosti

Z - Vyzkumny zamer (s odkazem do CEZ)

Rok uplatnění

2000

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název statě ve sborníku

Ninth International ANSYS Users Conference and Exhibition

ISBN

—

ISSN

—

e-ISSN

—

Počet stran výsledku

1

Strana od-do

—

Název nakladatele

ANSYS, Inc., Southpointe, 275 Technology Drive, Canonsburgh, PA 15317

Místo vydání

Pittsburgh, Pennsylvania, U.S.A.

Místo konání akce

—

Datum konání akce

—

Typ akce podle státní příslušnosti

—

Kód UT WoS článku

—