MORPHING AIRCRAFT WING STRUCTURE FOR THE APPLICATION OF 3D SHOCK CONTROL BUMPS

Abstract

The increasing demand for efficient and adaptable aircraft designs leads to the development of morphing structures, which can alter their shape in response to changing flight conditions. In this study, the design of a hybrid wing skin structure made of a fiber composite laminate and an elastomer is described. The primary goal is to develop a shape-variable structure that can be actively transformed into a shock control bump. As conventional aircraft operate at transonic speeds, a shockwave forms on the wing upper side, leading to wave drag and increased overall drag. Introducing a shock control bump aims to reduce the shock's intensity, thereby mitigating its detrimental effects on drag. In contrast to former structural studies, this bump has a three-dimensional (3D) shape, and thus, the morphing skin section is mounted on all sides. Consequently, the shape-variable structure is designed to allow such complex deformations. A comprehensive sensitivity study is conducted, exploring the impact of composite as well as elastomer design parameters. The results of this study reveal a structural feasible wing skin design that can be deformed to a 3D shock control bump. The proposed design demonstrates potential for application in real-world aircraft designs, offering a promising solution for mitigating transonic shock effects on wing performance and reducing overall drag. This work is part of the DLR project LamTA.