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 :
بازگشت