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Guidance Law Design Based on Integral Sliding Mode Control
ZHANG Zhen-Xing 1,LI Shihua 1 *,LUO Sheng 2
1.School of Automation, Southeast University, NanJing 210096
2.China Airborne Missile Academy, Luoyang 471009
*Correspondence author
#Submitted by
Subject:
Funding: the Specialized Research Fund for the Doctoral Program of Higher Education of China (No.20090092110022), Natural Science Foundation of China(No.61074013)
Opened online:18 December 2012
Accepted by: none
Citation: ZHANG Zhen-Xing,LI Shihua,LUO Sheng.Guidance Law Design Based on Integral Sliding Mode Control[OL]. [18 December 2012] http://en.paper.edu.cn/en_releasepaper/content/4501107
 
 
Reviews: The terminal guidance problem for missile intercepting maneuvering targets is developed. Based on integral sliding mode (ISM) control method, a novel guidance law is designed. Regarding the target acceleration as unknown bounded disturbance, a nonlinear ISM guidance law is introduced. The obtained guidance law guarantees the line-of-sight (LOS) angular rate and LOS angle a finite-time convergence characteristics. Simulation comparison results demonstrate the effectiveness of the presented method.
Keywords:Missile; guidance law; integral sliding mode control; finite-time control
 
 
 

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