Variable Camber Compliant Wing - Design

Abstract

This paper describes the design process and design validation of the US Air Force Research Laboratory developed Variable Camber Compliant Wing. The Variable Camber Compliant Wing was designed and fabricated based on compliant mechanisms and advanced manufacturing technologies, enabling a solution that is light weight, requires low power, and is low cost. The Air Force Research Laboratory demonstrates a new capability and technology for an active wing camber change without discrete control surfaces under realistic aerodynamic conditions. In this particular study, the wing was designed to target, but does not exactly resemble airfoil shapes between the NACA 2410 and NACA 8410, but the design is not only limited to these airfoils. The entire skin is seamless and continuous, constructed from a single piece of non-stretchable composite skin. The smooth elastic deformation of the Variable Camber Compliant Wing is obtained through the underlying compliant mechanism. 2D camber change is achieved by linear actuation to control both leading and trailing edge deflection. 3D shape change is also capable through camber variation along the span using a distributed actuation system. Proving the capability of a smooth 2D and 3D shape change would allow aircraft to significantly reduce fuel burn by continuously optimizing the wing L/D throughout the mission, as well as reduce airframe noise caused by holes and gaps existing on a conventional wing. Future aerodynamic applications and testing plans are discussed in this paper.