Design optimization to improve the performance of the aircraft composite structures

Abstract

Specific properties such as the stiffness and strength-to-weight ratio of the sandwich structure have a great impact on aircraft performance. The current research introduces a design methodology to replace the honeycomb core. Four configurations of structure members with a corrugated core were utilized. The skin sheets were made from pre-preg carbon fiber composite lamina and the corrugated cores were made from the same composite with three different thicknesses in addition to a corrugated core of pre-preg fiberglass lamina. Also, other configurations were assembled boxes from the separate structure members. All configurations were subjected to edgewise compression testing. The failure modes combined with the experimental results demonstrate the importance of design optimization in developing the sandwich structure properties. Changing from open-contour structures to closed-contour ones, utilizing different core materials with good wettability, and controlling the load direction enhance the compression capacity-to-weight ratio of the structural composites and improve their fracture resistance.