Missile controlled by aero-fin and divert thrusters using H2 decoupling analytical design

Author

Xue, Mantian ; Zhang, Weidong ; Jia, Xiaohong ; Jia, Jie

Author_Institution

Dept. of Mech. Eng., McMaster Univ., Hamilton, ON, Canada

fYear

2012

fDate

6-8 July 2012

Firstpage

1383

Lastpage

1388

Abstract

Reaction jet thruster provides extra moment in order to change the trajectory of the missile rapidly. However, it will induce interactions between the airflow and the thruster´s jet. In this paper, a simple H2 decoupling analytical design under internal model control structure is adapted to a novel designed model of divert controlled missile. Using this model, controller can handle the system uncertainty and the coupling problem induced by reaction jet thruster. Simulation results showed the effectiveness of this design method.

Keywords

aerodynamics; aerospace components; aerospace propulsion; missile guidance; trajectory control; H2 decoupling analytical design; aero-fin controlled missile; airflow; divert controlled missile; divert thrusters; internal model control structure; missile trajectory; reaction jet thruster; system uncertainty handling; Adaptation models; Aerodynamics; Atmospheric modeling; Mathematical model; Missiles; Trajectory; Uncertainty; Missile control; analytical design; decoupling control;

fLanguage

English

Publisher

ieee

Conference_Titel

Intelligent Control and Automation (WCICA), 2012 10th World Congress on

Conference_Location

Beijing

Print_ISBN

978-1-4673-1397-1

Type

conf

DOI

10.1109/WCICA.2012.6358096

Filename

6358096