Author： Hennuyer Claire Leconte Nicolas Langrand Bertrand Markiewicz Éric
Publisher： Edp Sciences
E-ISSN： 2257-7750|15|2|133-137
ISSN： 2257-7777
Source： Mechanics & Industry, Vol.15, Iss.2, 2014-05, pp. : 133-137
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Abstract
The finite element analysis of the behaviour of airframes subjected to crash or impact loadings requires the use of suitable finite elements, in particular for the modelling of riveted assemblies. In order to predict the structure survivability, it is indeed necessary to focus on these areas because stress concentrations, and consequently crack initiations, which can lead to catastrophic loss of the airplane, are likely to occur. Because of the local nature of the phenomenon, the disproportion between the aircraft and the assembly scale, and the large number of fasteners in a complete structure (more than 100 000), super-elements for the fasteners and for the perforated sheets have been developed in order to suitably model assemblies in structural calculations. However, these two types of finite elements can not be currently connected together. The paper presented here focuses on how to link these finite elements.
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