Hawkmoth wings consist of veins and membrane elements that undergo large deformations while moving through the air. The intention of this paper is to create an Euler-Bernoulli beam that can model the complex structure of a hawkmoth forewing. The beam undergoes bending and torsion, and its modal analysis and deformation data are validated against those of the wing structure created based on the finite-element method and a biological wing. A multibody dynamics approach is employed to model the deformation of the beam wing when it oscillates at the frequency of an actual hawkmoth.
This study carries out the transient flight control simulation of a Flapping-Wing Micro Air Vehicle using Extended Unsteady Vortex-Lattice Method. This method uses the panel method and unsteady vortex-lattice (UVLM) method including the leading-edge suction analogy for leading-edge vortices (LEVs) effect and the vortex-core growth model for the effect of eddy viscosity in the vortex wake. This method has advantages in that it requires relatively less computational cost compared to CFD and provides more precise aerodynamic forces and moments than the conventional quasi-steady aerodynamic model. Based on the multibody dynamic analysis with the aerodynamic model, gainscheduling LQR controller is designed for non-linear system to track reference input.