DocumentCode
1345297
Title
Optimality of Proportional Navigation Based on Nonlinear Formulation
Author
Jeon, In-soo ; Lee, Jin-Ik
Author_Institution
Dev. 1st R&D Center, JIN-IK LEE Agency for Defense, Daejeon, South Korea
Volume
46
Issue
4
fYear
2010
Firstpage
2051
Lastpage
2055
Abstract
The proportional navigation (PN) guidance law is derived for an ideal pursuer with a stationary target, by obtaining an optimal feedback solution minimizing a performance index of the range-weighted control energy. Without any linearization of system equations, the optimal PN with an arbitrary navigation constant is obtained. Thus the exact analyses on optimality of PN based on nonlinear formulation is presented here.
Keywords
feedback; missile guidance; nonlinear control systems; optimal control; performance index; arbitrary navigation constant; nonlinear formulation; optimal feedback solution; performance index; proportional navigation guidance law; range-weighted control energy; stationary target; system equation linearization; Aerodynamics; Closed-form solution; Feedback control; Image processing; Missiles; Navigation; Time frequency analysis;
fLanguage
English
Journal_Title
Aerospace and Electronic Systems, IEEE Transactions on
Publisher
ieee
ISSN
0018-9251
Type
jour
DOI
10.1109/TAES.2010.5595614
Filename
5595614
Link To Document