Simulation of flight dynamics and control of HALE Solar UAV

The large-aspect-ratio flexible wing of the HALE Solar UAV has geometrically nonlinear static and dynamic deformation during flight, which has a great influence on the flight dynamic characteristic of the UAV. Considering the coupling of flight dynamics and geometrically nonlinear structure deformation, Hodges geometrically exact beam equations based on Hamilton principle were applied to found the dynamic model of the UAV. Numerical simulation and analysis were taken by discretizing the model in space and integrating it in time domain. Adding a basic pitch control law with single attitude sensor, results show an oscillation coupled with pitch motion and wing twist deformation. This effect has been reduced on another simulation with four elaborately arranged sensors, and illustrates that basic control law using reasonable arranged multi-sensors can effectively ensure flight trajectory, attitude and aeroelastic stability of the UAV.