DocumentCode
2514920
Title
An observer-based missile guidance law
Author
Zhu, Zheng ; Xia, Yuanqing ; Fu, Mengyin ; Wang, Shuo
Author_Institution
Dept. of Autom. Control, Beijing Inst. of Technol., Beijing, China
fYear
2011
fDate
23-25 May 2011
Firstpage
1282
Lastpage
1287
Abstract
Nonlinear sliding mode guidance laws with finite time convergence are derived for the missile interception in this paper. The proposed guidance laws guarantee that the missile can intercept a maneuverable target with unknown target acceleration. Specially, the control design consists of the estimation of the target acceleration by extended state observer (ESO) and thus it achieves the decrease of undesired chattering effectively. Also, simulation results are presented to illustrate the effectiveness of the control strategies.
Keywords
control system synthesis; missile guidance; observers; control design; extended state observer; finite time convergence; maneuverable target; missile interception; nonlinear sliding mode guidance law; observer-based missile guidance law; unknown target acceleration; Acceleration; Convergence; Missiles; Observers; Trajectory; Uncertainty; Upper bound; ESO; Finite-time control; Guidance law; Sliding mode control;
fLanguage
English
Publisher
ieee
Conference_Titel
Control and Decision Conference (CCDC), 2011 Chinese
Conference_Location
Mianyang
Print_ISBN
978-1-4244-8737-0
Type
conf
DOI
10.1109/CCDC.2011.5968387
Filename
5968387
Link To Document