Author(s)

A. Schumacher & W. Becker

Abstract

The present work is concerned with the optimal composite design for aircraft structures. In aircraft construction an important goal, among others, is the realization of a certain desired aeroelastic performance of the wings, e.g. in regard of the eifectiveness of the ailerons, together with the realization of sufficient strength and stiffness. Unlike in the case of isotropic wing faces the employment of fiber- reinforced laminates gives additional potential to improve these goal characteristics. The present work mainly focuses on a basic lay-up design investigation in order to enable a subsequent detailed finite element analysis and structural optimization in a most-effective way. For this purpose the considered aircraft wing is ideal

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