Author(s)

F. Romano, G. Gatta, R. Paino & F. Palmiero

Abstract

This work describes the structural design of a composite material aileron of a business aircraft with the target of weight reduction with respect to the metallic reference baseline. It proposes a multi-step procedure for the design and analysis of a composite material structure. A carbon-epoxy material is used for the structural item. An integrated procedure (FEM/analytical and computational formulations) for the design and analysis is developed. In the first level the structural item is considered as concentrated elements. The internal loads are evaluated by elementary theory and a preliminary layup configuration for the structural components (skin, spar, etc.) is chosen by means of a stand-alone approach using a structural sizing

Keywords