DocumentCode
1556597
Title
Guidance Laws Based on Input-to-State Stability and High-Gain Observers
Author
Yan, Han ; Ji, Hai-bo
Author_Institution
Dept. of Autom., Univ. of Sci. & Technol. of China, HeFei, China
Volume
48
Issue
3
fYear
2012
fDate
7/1/2012 12:00:00 AM
Firstpage
2518
Lastpage
2529
Abstract
A novel three-dimensional guidance law based on input-to-state stability (ISS) and high-gain observers for interception of maneuvering targets is proposed. The ISS method is introduced to design a guidance law to achieve robust tracking of a maneuvering target. Since in practice the line-of-sight (LOS) rate is difficult for a pursuer to measure accurately, a high-gain observer is utilized to estimate it. Stability analysis as well as simulation results show that the presented approach is effective.
Keywords
missile guidance; observers; robust control; target tracking; ISS method; LOS; high-gain observer; input-to-state stability method; line-of-sight; maneuvering target interception; missile guidance; robust tracking; three-dimensional guidance law; Acceleration; Closed loop systems; Missiles; Navigation; Observers; Stability analysis; Upper bound;
fLanguage
English
Journal_Title
Aerospace and Electronic Systems, IEEE Transactions on
Publisher
ieee
ISSN
0018-9251
Type
jour
DOI
10.1109/TAES.2012.6237606
Filename
6237606
Link To Document