Airfoil structural morphing based on S.M.A. actuator series: numerical and experimental studies

ABSTRACT: Multiple flight regimes during typical aircraft missions mean that a single unique optimized configuration, that maximizes aerodynamic efficiency and maneuverability, cannot be defined. Discrete components such as ailerons and flaps provide some adaptability, although they are far from optimal. Wing morphing can significantly improve the perfor-mance of future aircraft, by adapting the wing shape to the specific flight regime requirements, but also represents a challenging problem: the structure has to be stiff to maintain its shape under loads, and yet be flexible to deform without collapse. One solution is to adopt structural elements made of smart materials; Shape Memory Alloys (SMAs) have demonstrated their suitability for many static applications due to their high structural integration potential and remarkable actuation capabilities. In this work, the airfoil camber at the wing trailing edge on a full scale wing of a civil regional transportation aircraft is controlled by substituting a traditional split flap with a hingeless, smooth morphed flap. Firstly, the development and testing of an actuator device based on a SMA ribbon, capable of a net rotation of 5 deg, is presented. Then, a flap bay is designed and experimentally tested in presence of static loads, based on a compliant rib buil