PARAMETRIC MODELING OF A COMBINED LOADED LAMINATE COMPOSITE IN RIVETED AIRCRAFT FUSELAGE JUNCTIONS

Result code in IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F00%3A00000193" target="_blank" >RIV/00216305:26210/00:00000193 - isvavai.cz</a>

Result on the web

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DOI - Digital Object Identifier

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Result language

čeština

Original language name

Parametric Modeling of a Combined Loaded Laminate Composite in Riveted Aircraft Fuselage Junctions

Original language description

The parametric stress-strain analysis of a riveted wall for the multilayer laminate composite GLARE3 was performed by the finite element method. The model of a riveted junction, enabling continuous change of tensile-bending ratio at different stress levels, was built. A sample solution algorithm was created. Orthotropic material properties of laminate layers, material nonlinearity of metal layers and geometric nonlinearity of the solution caused by large deflections of the whole model were considered atthe problem solution. Results of the parametric study are evaluated graphically.

Czech name

Parametric Modeling of a Combined Loaded Laminate Composite in Riveted Aircraft Fuselage Junctions

Czech description

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Type

D - Article in proceedings

CEP classification

JI - Composite materials

OECD FORD branch

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Project

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Continuities

Z - Vyzkumny zamer (s odkazem do CEZ)

Publication year

2000

Confidentiality

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

Article name in the collection

International Conference Engineering Mechanics 2000

ISBN

80 - 86246 - 03

ISSN

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e-ISSN

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Number of pages

1

Pages from-to

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Publisher name

Institute of Theoretical and Applied Mechanics, Academy of Sciences of the Czech Republic

Place of publication

Svratka, Czech Republic

Event location

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Event date

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Type of event by nationality

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UT code for WoS article

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