Title :
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
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;
Conference_Titel :
Intelligent Control and Automation (WCICA), 2012 10th World Congress on
Conference_Location :
Beijing
Print_ISBN :
978-1-4673-1397-1
DOI :
10.1109/WCICA.2012.6358096
