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Titre du document / Document title

Missile autopilot design using discrete-time variable structure controller with sliding sector

Auteur(s) / Author(s)

POWLY A. A. (1) ; SEETHARAMA BHAT M. (1) ;

Affiliation(s) du ou des auteurs / Author(s) Affiliation(s)

(1) Indian Institute of Science, Bangalore 560012, INDE

Résumé / Abstract

In this paper a discrete variable structure controller with sliding sector is designed for tracking the lateral acceleration command for a dual-input air-to-air missile. A new algorithm is developed for the variable-width sliding-sector design by considering the dissipativeness property of the system. The width of the sliding sector is based on the norm of the linear uncertain system state and the reference input. The switching surface design is based on the reduced-order dynamics. The control law is designed such that the state trajectory from any initial point is driven into the sliding sector around the equilibrium point in the vicinity of the the switching surface σk and thereafter remains inside it. The discrete sliding condition considered is ∥σk+1∥ < ∥σk. Inside the sliding sector, the closed-loop system is dissipative with a linear control law. The uncertain missile plant with matched and mismatched uncertainty is considered, and the conditions on the norm-bound of the uncertainty are given for robust stability in the sense of Lyapunov. Simulation results of the missile autopilot are also included to show the efficacy of the proposed controller.

Revue / Journal Title

Journal of guidance, control, and dynamics    ISSN  0731-5090   CODEN JGCODS 

Source / Source

2004, vol. 27, no4, pp. 634-646 [13 page(s) (article)] (26 ref.)

Langue / Language

Anglais

Editeur / Publisher

American Institute of Aeronautics and Astronautics, Reston, VA, ETATS-UNIS  (1982) (Revue)

Mots-clés anglais / English Keywords

Lyapunov function

;

Geometrical model

;

Equilibrium point

;

Trajectory

;

Missile

;

Robust stability

;

Closed feedback

;

Control synthesis

;

Control program

;

Reduced order systems

;

Uncertain system

;

Discrete time

;

Missile control

;

Mots-clés français / French Keywords

Fonction Lyapunov

;

Modèle géométrique

;

Point équilibre

;

Trajectoire

;

Missile

;

Stabilité robuste

;

Commande boucle fermée

;

Synthèse commande

;

Programme commande

;

Système ordre réduit

;

Système incertain

;

Temps discret

;

Commande missile

;

Mots-clés espagnols / Spanish Keywords

Función Lyapunov

;

Modelo geométrico

;

Punto equilibrio

;

Trayectoria

;

Misil

;

Estabilidad robusta

;

Bucle realimentación cerrada

;

Síntesis control

;

Programa mando

;

Sistema incierto

;

Tiempo discreto

;

Localisation / Location

INIST-CNRS, Cote INIST : 19058, 35400011381416.0130

Nº notice refdoc (ud4) : 15974162



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