DocumentCode
1232750
Title
Capturability of realistic generalized true proportional navigation
Author
Chakravarthy, A. ; Ghose, D.
Author_Institution
Flight Mechanics & Simulation Div., Aeronautical Dev. Agency, Bangalore, India
Volume
32
Issue
1
fYear
1996
Firstpage
407
Lastpage
418
Abstract
The capturability of a realistic generalized true proportional navigation (RGTPN) guidance law, against a nonmaneuvering target, is analyzed. The RGTPN law is obtained by relaxing the somewhat unrealistic assumption of constant closing velocity, made in all earlier studies on generalized true proportional navigation (GTPN), and incorporating the actual time-varying value in the guidance law. Closed-form solutions for the complete capture region of RGTPN is obtained in terms of both zero and acceptable non-zero miss distances. It is shown that the capture region of RGTPN in the initial relative velocity space is significantly smaller than that of GTPN, for reasonable values of navigation constant (N) and angular direction (η) of the missile commanded latax. However, for certain values of N and η, capturability of RGTPN is found to be better. It is also shown that if in one of the versions of GTPN, which uses constant values of both the closing velocity and the line-of-sight (LOS) angular velocity in the guidance law the corresponding realistic time-varying quantities are used, the capture region actually expands to cover the whole of the initial relative velocity space. A number of examples are given to compare the capture performance of RGTPN with other versions of the GTPN guidance laws.
Keywords
control system analysis; missile guidance; proportional control; radar applications; radar tracking; radionavigation; time-varying systems; actual time-varying value; capturability; closed-form solutions; closing velocity; complete capture region; engagement model; guidance law; homing guidance; initial relative velocity space; line-of-sight angular velocity; missile commanded latax; nonmaneuvering target; realistic generalized true proportional navigation; tactical missiles; Aerospace simulation; Angular velocity; Closed-form solution; Inertial navigation; Missiles; Time varying systems; Velocity measurement;
fLanguage
English
Journal_Title
Aerospace and Electronic Systems, IEEE Transactions on
Publisher
ieee
ISSN
0018-9251
Type
jour
DOI
10.1109/7.481281
Filename
481281
Link To Document