High angle-of-attack control law design based on global stability analysis

A global stability analysis was presented to guide high angle-of-attack (AOA) control law design for nonlinear aircraft dynamic system. Bifurcation analysis was explored to investigate the structural stability of nonlinear aircraft dynamic system at high AOA. By reasonably selecting equilibrium points, eigenstructure assignment was applied to design gain scheduling control law at high AOA and the extension of stable flight region to high AOA was achieved. By using time domain numerical simulations, the domains of attractor for stable equilibrium points at high AOA were estimated. In contrast to other methods, global asymptotic stability of nonlinear aircraft dynamic system is used rather than Lyapunov local asymptotic stability.