HAL Id: hal-01495625
https://hal.archives-ouvertes.fr/hal-01495625 Submitted on 25 Mar 2017
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Aide à la conception optimale d’une section de fuselage
d’avion entièrement composite
Magali Olivier-Mailhé, Samir Ben Chaabane, Françoise Léné, Stéphane Grihon, Georges Duvaut
To cite this version:
Magali Olivier-Mailhé, Samir Ben Chaabane, Françoise Léné, Stéphane Grihon, Georges Duvaut. Aide à la conception optimale d’une section de fuselage d’avion entièrement composite. 8e Colloque national en calcul des structures, CSMA, May 2007, Giens, France. �hal-01495625�
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*Département de Mécanique des systèmes,
Ecole Supérieure d’Ingénieurs Léonard de Vinci
2/12 av Léonard de Vinci 92916 Paris la défense cedex magali_mailhe@yahoo.fr
**Laboratoire de Mécanique, Matériaux et Structures,
Université Pierre et Marie Curie
4 pl Jussieu
75252 Paris Cedex 5
***Airbus Toulouse ESANT
7RXORXVH&HGH[RÉSUMÉ. L’utilisation de matériaux composites pour concevoir un fuselage ouvre de nombreuses possibilités et permet un allègement notable. La modélisation par éléments finis d’un barrel percé d’ouvertures est menée. L’étude de l’influence de plusieurs paramètres est proposée afin de déterminer le type de conception répondant au critère de stabilité au flambage tout en assurant un poids minimal.
ABSTRACT. Using composite materials to build aircraft structures allows minimizing the weight. It also presents new parameters that can be optimized. The finite element modelling of a barrel with several openings is presented. This study exposes the influence of several factors on the critical buckling load and determines the best type of conception in terms of weight.
MOTS-CLÉS: matériaux composites, fuselage, flambage KEYWORDS: composite materials, fuselage, buckling
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