DocumentCode
526327
Title
Notice of Retraction
A unified approach to optimal proportional navigation
Author
Guo Jian-guo ; Zhou Jun
Author_Institution
Inst. of Precision Guidance & Control, Northwestern Polytech. Univ., Xi´an, China
Volume
6
fYear
2010
fDate
9-11 July 2010
Firstpage
74
Lastpage
77
Abstract
Notice of Retraction
After careful and considered review of the content of this paper by a duly constituted expert committee, this paper has been found to be in violation of IEEE´s Publication Principles.
We hereby retract the content of this paper. Reasonable effort should be made to remove all past references to this paper.
The presenting author of this paper has the option to appeal this decision by contacting TPII@ieee.org.
A unified approach to optimal proportional navigation for missile is purposed based on guidance performance according to the case of attacking the target without any maneuverability. The mathematic model of guidance system is built according to nonlinear relative movement relationship between missile and target, based on zeroing relative distance and zeroing the rate of line of sight. Due to the model, the optimal true proportional navigation law of guidance system is derived by using optimizing the linear quadratic performance in the case of intercepting nonmaneuvering target, at the same time the unified optimal proportional guidance law is obtained according to optimizing the different linear quadratic performance. Finally, the target is intercepted applying the guidance law through the mathematic simulation, the performance of guidance system under two optimal proportional guidance law is compared on a common basis.
After careful and considered review of the content of this paper by a duly constituted expert committee, this paper has been found to be in violation of IEEE´s Publication Principles.
We hereby retract the content of this paper. Reasonable effort should be made to remove all past references to this paper.
The presenting author of this paper has the option to appeal this decision by contacting TPII@ieee.org.
A unified approach to optimal proportional navigation for missile is purposed based on guidance performance according to the case of attacking the target without any maneuverability. The mathematic model of guidance system is built according to nonlinear relative movement relationship between missile and target, based on zeroing relative distance and zeroing the rate of line of sight. Due to the model, the optimal true proportional navigation law of guidance system is derived by using optimizing the linear quadratic performance in the case of intercepting nonmaneuvering target, at the same time the unified optimal proportional guidance law is obtained according to optimizing the different linear quadratic performance. Finally, the target is intercepted applying the guidance law through the mathematic simulation, the performance of guidance system under two optimal proportional guidance law is compared on a common basis.
Keywords
missile guidance; optimal control; guidance performance; guidance system mathematical model; line of sight; linear quadratic performance; maneuverability; nonlinear relative movement; optimal proportional missile navigation; optimal true proportional navigation law; Acceleration; linear quadratic; nonlinea; optimal control; proportional navigation;
fLanguage
English
Publisher
ieee
Conference_Titel
Computer Science and Information Technology (ICCSIT), 2010 3rd IEEE International Conference on
Conference_Location
Chengdu
Print_ISBN
978-1-4244-5537-9
Type
conf
DOI
10.1109/ICCSIT.2010.5563595
Filename
5563595
Link To Document