DocumentCode
550533
Title
Finite time convergent sliding-mode guidance law with impact angle constraint
Author
Zhang Yunxi ; Jiao Gangling ; Sun Mingwei ; Chen Zengqiang
Author_Institution
Dept. of Autom., Nankai Univ., Tianjin, China
fYear
2011
fDate
22-24 July 2011
Firstpage
2597
Lastpage
2601
Abstract
Based on the finite time convergence stability theory and the variable structure control, a finite time convergent sliding-mode guidance law with terminal impact angle constraint is presented. The analysis manifests that the guidance system is convergent. It is proved that, before the final time of the guidance process, the line-of-sight rate will converge to zero in finite time and the terminal impact angle will meet the requirement. Finally, the simulation results show that the guidance law is effective.
Keywords
aerospace control; military systems; missile guidance; stability; variable structure systems; finite time convergence stability theory; finite time convergent sliding mode guidance law; impact angle constraint; line-of-sight rate; stability theory; terminal impact angle; variable structure control; Convergence; Navigation; Optimized production technology; Sliding mode control; Stability analysis; Sun; Switches; Finite time convergence; Guidance law; Sliding-mode control; Terminal impact angle;
fLanguage
English
Publisher
ieee
Conference_Titel
Control Conference (CCC), 2011 30th Chinese
Conference_Location
Yantai
ISSN
1934-1768
Print_ISBN
978-1-4577-0677-6
Electronic_ISBN
1934-1768
Type
conf
Filename
6000872
Link To Document