A comparison of morphing control strategies for a flexible wing micro air vehicle model incorporating Spatial Hysteresis damping

摘要

In this work we wish to improve upon our previous one-dimensional, nonlinear model describing the heave dynamics of an aeroelastic wing micro air vehicle. We incorporate a non-local internal damping type, known as spatial hysteresis, into the model. Here we compare the use of three linear feedback control laws, designed for the linearized system, acting to morph the aircraft wings to a certain shape over time. The control designs we compare are the Linear Quadratic Regulator, Linear Quadratic Gaussian, and Central controllers, with the latter two resulting in a nonlinear compensator when implemented in the nonlinear system.