Improvement of the carbon composite skin of the fuselage of an aircraft by means of optimization algorithms to define laminate stacking sequences

Abstract

Nowadays the use of composite materials is really common in industries because of its low weight in comparison with its structural benefits. In aeronautic industries, there is a constant interest in lightening all of its components. Especially on civil aircraft fuselages which are done with skin and reinforcements. One of the design’s objectives of this skin is to avoid buckling.

Our objective is to create a laminate that can accomplish the fuselage’s skin’s requirements reducing its weight and preserving its mechanical integrity