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GUIDANCE LAW EVALUATION FOR MISSILE GUIDANCE SYSTEMS
Author(s) -
Lin ChihMin,
Hsu ChunFei,
Chang ShingKuo,
Wai RongJong
Publication year - 2000
Publication title -
asian journal of control
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.769
H-Index - 53
eISSN - 1934-6093
pISSN - 1561-8625
DOI - 10.1111/j.1934-6093.2000.tb00029.x
Subject(s) - missile , heading (navigation) , missile guidance , guidance system , proportional navigation , constant (computer programming) , sensitivity (control systems) , control theory (sociology) , law , interception , computer science , noise (video) , engineering , simulation , control engineering , aerospace engineering , artificial intelligence , control (management) , image (mathematics) , political science , ecology , electronic engineering , biology , programming language
In missile guidance system, to reduce the interception “miss distance,” it is important to choose a suitable guidance law and navigation constant. This paper investigates and compares the system behavior of guidance laws under different navigation constants. Based on use of the adjoint technique, miss distance sensitivity analyses which consider the system noise, target step maneuver, initial heading error and system parameters for different guidance laws and navigation constants are presented. Based on these analyses, some suggestions for choosing a suitable guidance law and navigation constant are given for the design of missile guidance systems. Also, a suggestion for the optimal escape time for pilots of fighter planes is given.