Aircraft Maneuver Design Using Bifurcation Analysis and Sliding Mode Control Techniques

In this paper, bifurcation analysis-based methodology is used in conjunction with a sliding-mode-based control to construct and simulate maneuvers for a nonlinear, 6 degree-of-freedom, F-18 high-alpha research aircraft model. Three different types of maneuvers, namely, a minimum-radius level turn, velocity vector roll, spin recovery to a level flight condition, are attempted to demonstrate the usefulness of the proposed approach. The procedure involves constructing the desired maneuvers using constrained bifurcation analysis-based . The results obtained from bifurcation analysis provide the reference inputs for the sliding mode to switch the aircraft between desired flight conditions. Robustness of the sliding mode controller is also examined by introducing uncertainties in aerodynamic parameters. Closed-loop simulation results are later to show the effectiveness of the proposed technique.