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.
Full text not archived in this repository.
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.
Repository Staff Only: item control page