Closed loop analysis of a simple aircraft model using bifurcation methods

This paper presents work performed into the analysis of nonlinear aircraft dynamics using bifurcation methods. Published work on the application of bifurcation methods to study non-linear aircraft dynamics has been available for many years. These works mainly consider the case of open loop aircraft and the way in which flight dynamic effects give rise to departures. This study, however, conducts a preliminary investigation into the analysis of control laws for closed loop aircraft using bifurcation analysis techniques. Bifurcation methods are initially applied to a simple open loop aircraft model with constant aerodynamic derivatives to demonstrate the use of bifurcation analysis. The bifurcation techniques are then used to analyse a simple control law of the closed loop aircraft model to detect known flaws, that is integrator wind-up and rate limit effects.