Aircraft maneuver design using bifurcation analysis and sliding mode control techniques

Khatri, AK and Jatinder, Singh and Sinha, NK (2012) Aircraft maneuver design using bifurcation analysis and sliding mode control techniques. Journal of Guidance, Control and Dynamics, 35 (5). pp. 1435-1449. ISSN 0731-5090

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Official URL: http://dx.doi.org/10.2514/1.56361

Abstract

In this paper, bifurcation analysis-based methodology is used in conjunction with a sliding-mode-based control algorithm to construct and simulate maneuvers for a nonlinear, 6 degree-of-freedom, F-18 high-alpha research vehicle aircraft model. Three different types of maneuvers, namely, a minimum-radius level turn, velocity vector roll, and spin recovery to a level flight condition, are attempted to demonstrate the usefulness of the proposed approach. The procedure involves constructing the desired maneuvers using constrained bifurcation analysis-based methodology. The results obtained from bifurcation analysis provide the reference inputs for the sliding mode controller to switch the aircraft between desired flight conditions. Robustness of the sliding mode controller is also examined by introducing uncertainties in aerodynamic parameters. Closed-loop simulation results are later presented to show the effectiveness of the proposed technique.

Item Type: Article
Additional Information: Copyright to this article belongs to M/s. American Institute of Aeronautics and Astronautics
Uncontrolled Keywords: Velocity vector roll maneuver;Fighter aircraft;Aircraft maneuver design;Analysis mode;Sliding mode control techniques
Subjects: AERONAUTICS > Aeronautics (General)
AERONAUTICS > Aircraft Design, Testing & Performance
Depositing User: Users 11 not found.
Date Deposited: 07 Jan 2013 07:54
Last Modified: 07 Jan 2013 07:54
URI: http://nal-ir.nal.res.in/id/eprint/11426

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