Title :
Design and Numerical Simulation Analysis of Missile Control System
Author :
Lin De-fu ; Fan Jun-fang
Author_Institution :
Dept. of Flying Vehicle Design, Beijing Inst. of Technol., Beijing, China
Abstract :
The missile control system design and analysis are detailed from both nonlinear and linear control perspectives. The control parameters of backstepping based nonlinear autopilot were determined based on step and sine input commands. Then the characteristics of two control parameters were examined. A linear three-loop autopilot based on optimal control was also presented for comparison. The numerical simulation results show that the backstepping recursive approach provides a systematically constructive procedure for missile autopilot. The based nonlinear autopilot exhibits excellent tracking performance and robustness.
Keywords :
linear systems; missile control; nonlinear control systems; numerical analysis; optimal control; recursive functions; backstepping based nonlinear autopilot; backstepping recursive approach; control parameters; linear control analysis; missile autopilot; missile control system design; nonlinear control analysis; numerical simulation analysis; optimal control; sine input command; step input command; three-loop autopilot; Backstepping; Control system analysis; Control system synthesis; Control systems; Missiles; Nonlinear control systems; Numerical simulation; Optimal control; Robustness; System analysis and design; autopilot; backstepping; missile control; numerical simulation; optimal control;
Conference_Titel :
Computer Modeling and Simulation, 2010. ICCMS '10. Second International Conference on
Conference_Location :
Sanya, Hainan
Print_ISBN :
978-1-4244-5642-0
Electronic_ISBN :
978-1-4244-5643-7
DOI :
10.1109/ICCMS.2010.122
