Abstract: A numerical study of a design concept for actively controlling wing twist is described in this paper. The concept consists of morphing elements which were designed to provide a rigid and seamless skin while maintaining structural rigidity. The wing structure is first modeled in CATIA V5 then imported into ANSYS for structural analysis. Athena Vortex Lattice method (AVL) is used to estimate aerodynamic response as well as aerodynamic loads of morphing wings, afterwards a structural optimization performed via ANSYS Static. Overall, the results presented in this paper show that the concept provides efficient wing twist while preserving an aerodynamically smooth and compliant surface. Sufficient structural rigidity in bending is also obtained. This concept is suggested as a possible alternative for morphing skin applications.
Abstract: An investigation of adaptable winglets for enhancing
morphing aircraft performance is described in this paper. The
concepts investigated consist of various winglet configurations
fundamentally centered on a baseline swept wing. The impetus for
the work was to identify and optimize winglets to enhance the
aerodynamic efficiency of a morphing aircraft. All computations
were performed with Athena Vortex Lattice modelling with varying
degrees of twist and cant angle considered. The results from this
work indicate that if adaptable winglets were employed on aircraft’s
improvements in aircraft performance could be achieved.
Abstract: An investigation of adaptable winglets for morphing
aircraft control and performance is described in this paper. The
concepts investigated consist of various winglet configurations
fundamentally centred on a baseline swept wing. The impetus for the
work was to identify and optimize winglets to enhance controllability
and the aerodynamic efficiency of a small unmanned aerial vehicle.
All computations were performed with Athena Vortex Lattice
modelling with varying degrees of twist, swept, and dihedral angle
considered. The results from this work indicate that if adaptable
winglets were employed on small scale UAV’s improvements in both
aircraft control and performance could be achieved.