Nonlinear Stabilizing Control of High Angle of Attack Flight Dynamics
University of Maryland College Park United States
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This paper discusses a new approach to the feedback control of aircraft at high angles of attack. This approach is based on recent results on control of nonlinear systems at bifurcation points 3,4,5. The lateral dynamics of a slender aircraft studied by Ross 6 provides a convenient model for illustrating this application. It is shown how local bifurcation control can be used in the stabilization of the so-called wing rock phenomenon.