Lateral acceleration control design of a non-linear missile: a soft computing approach

  • Authors:

  • T. Sreenuch;A. Tsourdos;E. J. Hughes;B. A. White

  • Affiliations:

  • Department of Aerospace, Power and Sensors, Cranfield University--RMCS, Shrivenham, Swindon SN6 8LA, UK;Department of Aerospace, Power and Sensors, Cranfield University--RMCS, Shrivenham, Swindon SN6 8LA, UK;Department of Aerospace, Power and Sensors, Cranfield University--RMCS, Shrivenham, Swindon SN6 8LA, UK;Department of Aerospace, Power and Sensors, Cranfield University--RMCS, Shrivenham, Swindon SN6 8LA, UK

  • Venue:
  • International Journal of Systems Science
  • Year:
  • 2004

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Abstract

This paper presents the lateral acceleration control design of non-linear missile model using the multiple single objective Pareto sampling method. The LTI controller design for the uncertain plants is carried out by minimizing gain-phase margin and tracking fequency domain-based performance objectives. The Pareto optimal solutions (corresponding to a given set of weight vectors) are obtained. The selected solution, as illustration, is analysed. The gain-scheduling controller is obtained by the interpolation of zeros, poles and gains, where the smooth deterministic transition rule is implemented using the TS fuzzy model. The non-linear simulation results show that the selected interpolated controller is a robust tracking controller for all perturbation vertices.