Wing camber control architectures based on SMA: numerical investigations

Benefits in terms of aerodynamic efficiency, aeroelastic behaviour, stability and manoeuvrability performance coming from the adaptive variation of wing geometric (e.g. thickness and chamber) and mechanical (e.g. rigidity) parameters were widely proved. In this scenario, more and more efficient architectures based on innovative materials like shape memory alloys, piezoelectrics, magneto-rheologic fluids were ideated and related morphing ability was tested. Due to the large transmitted forces and deformations, for static applications, SMA based-on architectures were implemented. The essential idea of all these architectures is to integrate a SMA actuator, lacking of remarkable structural value, within a classical wing structure or within a suitably designed one. The main disadvantage of such architectures derives by the necessity of deforming a classical structure, not designed for reaching large displacements. In order to avoid these problems, in this work, the idea of integrating compliant structures by SMA elements, was considered. Some deformation strategies, focused on the wing aft part morphing, were ideated; related performance in terms of vertical displacement and rotation of the trailing edge was estimated by a FE approach. Each architecture is characterised by SMA rod elements able to guarantee large deformations and shape control under aerodynamic loads.