Aircraft wing rock dynamics and control

Abstract

The dynamics of wing rock on rigid aircraft having single, two, and three rotational degrees-of-freedom are analyzed. For the purpose of the analysis, nonlinear mathematical models of the aircraft are developed. The aerodynamic expressions contained in the models can be built by fitting the appropriate aerodynamic data into the model. The dynamic analysis is performed analytically using a technique combining the Multiple Time Scales method, Center Manifold Reduction principle, and bifurcation theory. The technique yields solutions in parametric forms and leads to the separation of fast and slow dynamics, and a great insight into the system behavior. Further, a unified framework for the investigation of wing rock dynamics and control of aircraft is developed. Good agreement between the analytical results and the numerical simulations is demonstrated. Based on the results of the dynamic analysis, appropriate control strategies for the wing rock alleviation are developed. The control power limitation of the conventional aerodynamics control surfaces is considered and its effects on the alleviation of wing rock are investigated. Finally, the potential use of advanced controls to overcome the conventional controls limitation is discussed.