Accessibility navigation


Closed loop design for a simple nonlinear aircraft model using eigenstructure assignment

Gibson, L. P., Nichols, N. ORCID: https://orcid.org/0000-0003-1133-5220 and Littleboy, D. M. (1997) Closed loop design for a simple nonlinear aircraft model using eigenstructure assignment. In: AIAA Atmospheric Flight Mechanics Conference , 11-13 August 1997, American Institute of Aeronautics and Astronautics, Reston, Virginia, USA, pp. 746-754.

Full text not archived in this repository.

It is advisable to refer to the publisher's version if you intend to cite from this work. See Guidance on citing.

Abstract/Summary

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 flight. The aim of this work is to construct a robust closed-loop control that optimally extends the stable and decoupled flight envelope. 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 investigate control effects on dynamic behavior. In this work linear feedback control designs calculated by eigenstructure assignment methods are investigated for a simple aircraft model at a fixed flight condition. Bifurcation analysis in conjunction with linear control design methods is shown to aid control law design for the nonlinear system.

Item Type:Conference or Workshop Item (Paper)
Refereed:Yes
Divisions:Science > School of Mathematical, Physical and Computational Sciences > Department of Meteorology
Science > School of Mathematical, Physical and Computational Sciences > Department of Mathematics and Statistics
ID Code:27628

University Staff: Request a correction | Centaur Editors: Update this record

Page navigation