Title :
Finite-time convergent guidance and control based on integrated model
Author :
Lin Lin ; Songyan Wang ; Tao Chao ; Ming Yang
Author_Institution :
Control & Simulation Center, Harbin Inst. of Technol., Harbin, China
fDate :
May 31 2014-June 2 2014
Abstract :
An integrated guidance and control model for missile control system design is established in this paper. Finite-time stability theory is used to design a finite-time convergent guidance and control law based on the proposed model. Some simulation tests are done to verify the validity of the control law designed in this paper and the advantages compared with other guidance laws. The results show the control designed in this paper can satisfy the terminal indicators accurately.
Keywords :
aerospace control; military systems; missile control; stability; control law design; finite time stability theory; finite-time convergent control; finite-time convergent guidance; integrated model; missile control system design; terminal indicators; Convergence; Elevators; Missiles; Stability criteria; Trajectory; finite-time convergence control; terminal guidance; the integrated model;
Conference_Titel :
Control and Decision Conference (2014 CCDC), The 26th Chinese
Conference_Location :
Changsha
Print_ISBN :
978-1-4799-3707-3
DOI :
10.1109/CCDC.2014.6852251
