<div class="section abstract"><div class="htmlview paragraph">The objective of this paper is to analyze a complete fuselage of an airplane made
of composite materials. The analysis presented includes designing a 3D fuselage
structure in which parameters are calculated using various stress and
deformation scenarios. Static numerical results propose a composite fuselage
structure to reduce stress and deformation levels by 45 and 33% compared to an
equivalent (existing) aluminum fuselage. This work is to continue with specific
characteristics of the composite and considerations to more realistic loading
conditions (dynamism, impact, fatigue). A complete study should suggest
converting flying vehicles to composites, to increase performances, minimize
weights, and improve payloads.</div></div>