Result: Lateral acceleration control design of a non-linear homing missile using multi-objective evolution strategies
Title:
Lateral acceleration control design of a non-linear homing missile using multi-objective evolution strategies
Authors:
Source:
Proceedings of the 2004 American Control Conference ACC (June 30-July 2, 2004, Boston Massachusetts). :3628-3633
Publisher Information:
Evanston IL; Piscataway NJ: American Automatic Control Council, IEEE, 2004.
Publication Year:
2004
Physical Description:
print, 5 ref
Original Material:
INIST-CNRS
Subject Terms:
Control theory, operational research, Automatique, recherche opérationnelle, Sciences exactes et technologie, Exact sciences and technology, Sciences appliquees, Applied sciences, Informatique; automatique theorique; systemes, Computer science; control theory; systems, Automatique théorique. Systèmes, Control theory. Systems, Synthèse des systèmes de commande, Control system synthesis, Commande accélération, Acceleration control, Commande non linéaire, Non linear control, Control no lineal, Commande robuste, Robust control, Control robusta, Echantillonnage multiple, Multiple sampling, Muestreo múltiple, Echantillonnage simple, Single sampling, Muestreo simple, Marge gain, Gain margin, Margen ganancia, Marge phase, Phase margin, Margen fase, Missile, Misil, Méthode domaine fréquence, Frequency domain method, Método dominio frecuencia, Optimum Pareto, Pareto optimum, Optimo Pareto, Programmation multiobjectif, Multiobjective programming, Programación multiobjetivo, Saturation, Saturación, Synthèse commande, Control synthesis, Síntesis control, Système incertain, Uncertain system, Sistema incierto
Document Type:
Conference
Conference Paper
File Description:
text
Language:
English
Author Affiliations:
Department of Aerospace, Power & Sensors Cranfield University (RMCS Shrivenham), Swindon SN6 8LA, England, United Kingdom
Rights:
Copyright 2007 INIST-CNRS
CC BY 4.0
Sauf mention contraire ci-dessus, le contenu de cette notice bibliographique peut être utilisé dans le cadre d’une licence CC BY 4.0 Inist-CNRS / Unless otherwise stated above, the content of this bibliographic record may be used under a CC BY 4.0 licence by Inist-CNRS / A menos que se haya señalado antes, el contenido de este registro bibliográfico puede ser utilizado al amparo de una licencia CC BY 4.0 Inist-CNRS
CC BY 4.0
Sauf mention contraire ci-dessus, le contenu de cette notice bibliographique peut être utilisé dans le cadre d’une licence CC BY 4.0 Inist-CNRS / Unless otherwise stated above, the content of this bibliographic record may be used under a CC BY 4.0 licence by Inist-CNRS / A menos que se haya señalado antes, el contenido de este registro bibliográfico puede ser utilizado al amparo de una licencia CC BY 4.0 Inist-CNRS
Notes:
Computer science; theoretical automation; systems
Accession Number:
edscal.18352003
Database:
PASCAL Archive
Further Information
The paper presents the lateral acceleration control design of non-linear missile model using the multiple single objective Pareto sampling method. The interpolated controller design for the uncertain plants is carried out by minimizing gain and phase margins, tracking and actuator rate limit frequency domain based performance objectives. An ad-hoc approach is taken to the controller interpolation. The controller's trade-offs are analyzed using the obtained Pareto optimal solutions (corresponding to a given set of weight vectors). The non-linear simulation results show that the selected interpolated controller is a robust tracking controller for all perturbation vertices.