DESIGN OF A LINEAR QUADRATIC OPTIMAL CONTROL FOR AIRCRAFT

Aranda Almansa, Joaquín, Cruz García, Jesús Manuel de la, Parrilla, M. y Ruipérez García, Pablo . (2000) DESIGN OF A LINEAR QUADRATIC OPTIMAL CONTROL FOR AIRCRAFT. 4th Portuguese Conference on Automatic Control


Título DESIGN OF A LINEAR QUADRATIC OPTIMAL CONTROL FOR AIRCRAFT
Autor(es) Aranda Almansa, Joaquín
Cruz García, Jesús Manuel de la
Parrilla, M.
Ruipérez García, Pablo
Resumen In this paper we have investigated the use of genetic algorithm for the selection of weighting matrices of performance index for the linear quadratic control design. We can easily consider in the fitness index of the genetic algorithm different design specifications and their verifications in different operations conditions. As well as a measure of robustness s(S+T) evaluated at the input and at the output for linearized models obtained for different parameters. This technique is applied to design a control for the longitudinal dynamic of an aircraft. The robustness and specifications are evaluated for different values of mass, airspeed, centre of gravity, and transport delay.
Palabras clave optimal control
genetic algorithm
aircraft control
Editor(es) Controlo’2000
Fecha 2000-10-04
Identificador ACPR2000b
bibliuned:607
Publicado en la Revista 4th Portuguese Conference on Automatic Control
Idioma eng
Versión de la publicación publishedVersion
Tipo de recurso Article
Derechos de acceso y licencia http://creativecommons.org/licenses/by-nc-nd/4.0
info:eu-repo/semantics/openAccess
Tipo de acceso Acceso abierto
Notas adicionales In this paper we have investigated the use of genetic algorithm for the selection of weighting matrices of performance index for the linear quadratic control design. We can easily consider in the fitness index of the genetic algorithm different design specifications and their verifications in different operations conditions. As well as a measure of robustness s(S+T) evaluated at the input and at the output for linearized models obtained for different parameters. This technique is applied to design a control for the longitudinal dynamic of an aircraft. The robustness and specifications are evaluated for different values of mass, airspeed, centre of gravity, and transport delay.

 
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Creado: Wed, 14 Nov 2007, 12:02:42 CET