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Reconfigurable flight control strategies using model predictive control

Reconfigurable flight control strategies using model predictive control
Reconfigurable flight control strategies using model predictive control
Tracking control for large amplitude manoeuvres in the presence of damages to the airframe and control surface is addressed. The control reconfiguration algorithm is based on model predictive control, a constrained reseding horizon optimization is solved under the constraints of hard limits of actuator position and rate saturation and critical aircraft state limits imposed by allowable structural loads. Changed stability and control derivatives of the damaged aircraft are identified online and used buy the receding horizon controller as internal model for prediction. An emphasis is given to incorporate handling quality specification according to MIL-STD-1797A. The results demonstrate the ability of the proposed scheme to maintain flight after a failure; trach the pilot commands despite loss of actuator effectiveness, and to coordinate the use of the remaining active control surfaces to provide the decoupling between the rotational axes. Finally the issue of the online (onboard) implementation of the constrained optimization is examined.
receding horizon control, constrained optimization, online identification, reconfigurable control
43-48
IEEE
Kale, M.
5abb02f0-2e93-42a2-a9ab-95d44a9450b5
Chipperfield, A.J.
524269cd-5f30-4356-92d4-891c14c09340
Kale, M.
5abb02f0-2e93-42a2-a9ab-95d44a9450b5
Chipperfield, A.J.
524269cd-5f30-4356-92d4-891c14c09340

Kale, M. and Chipperfield, A.J. (2002) Reconfigurable flight control strategies using model predictive control. In Proceedings of the 2002 IEEE. IEEE. pp. 43-48 .

Record type: Conference or Workshop Item (Paper)

Abstract

Tracking control for large amplitude manoeuvres in the presence of damages to the airframe and control surface is addressed. The control reconfiguration algorithm is based on model predictive control, a constrained reseding horizon optimization is solved under the constraints of hard limits of actuator position and rate saturation and critical aircraft state limits imposed by allowable structural loads. Changed stability and control derivatives of the damaged aircraft are identified online and used buy the receding horizon controller as internal model for prediction. An emphasis is given to incorporate handling quality specification according to MIL-STD-1797A. The results demonstrate the ability of the proposed scheme to maintain flight after a failure; trach the pilot commands despite loss of actuator effectiveness, and to coordinate the use of the remaining active control surfaces to provide the decoupling between the rotational axes. Finally the issue of the online (onboard) implementation of the constrained optimization is examined.

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More information

Published date: 2002
Keywords: receding horizon control, constrained optimization, online identification, reconfigurable control

Identifiers

Local EPrints ID: 58753
URI: http://eprints.soton.ac.uk/id/eprint/58753
PURE UUID: f29bcf85-41ce-481b-aefe-eaf837f842e8
ORCID for A.J. Chipperfield: ORCID iD orcid.org/0000-0002-3026-9890

Catalogue record

Date deposited: 18 Aug 2008
Last modified: 09 Jan 2022 03:12

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Contributors

Author: M. Kale

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