Bifurcation Analysis of Eigenstructure Assignment Control in a Simple Nonlinear Aircraft Model
Gibson, L. P., Nichols, N. and Littleboy, D. M. (1998) Bifurcation Analysis of Eigenstructure Assignment Control in a Simple Nonlinear Aircraft Model. Journal of Guidance, Control and Dynamics, 21 (5). pp. 792-798. ISSN (printed) 0731-5090; (electronic) 1533-3884.
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Aircraft systems are highly nonlinear and time varying. High-performance aircraft at high angles of incidence experience undesired coupling of the lateral and longitudinal variables, resulting in departure from normal controlled ight. The construction of a robust closed-loop control that extends the stable and decoupled ight envelope as far as possible is pursued. For the study of these systems, nonlinear analysis methods are needed. Previously, bifurcation techniques have been used mainly to analyze open-loop nonlinear aircraft models and to investigate control effects on dynamic behavior. Linear feedback control designs constructed by eigenstructure assignment methods at a xed ight condition are investigated for a simple nonlinear aircraft model. Bifurcation analysis, in conjunction with linear control design methods, is shown to aid control law design for the nonlinear system.
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