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- W2069439137 abstract "Aircraft systems are highly nonlinear and time varying. High-performance aircraft at high angles of incidenceexperience 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 envelopeas 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 investigatecontrol effects on dynamic behavior. Linear feedback control designs constructed by eigenstructure assignmentmethods at a � xed � ight condition are investigated for a simple nonlinear aircraft model. Bifurcation analysis, inconjunction with linear control design methods, is shown to aid control law design for the nonlinear system." @default.
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- W2069439137 date "1998-09-01" @default.
- W2069439137 modified "2023-10-16" @default.
- W2069439137 title "Bifurcation Analysis of Eigenstructure Assignment Control in a Simple Nonlinear Aircraft Model" @default.
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- W2069439137 doi "https://doi.org/10.2514/2.4308" @default.
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