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contributor authorQu, Pingping
contributor authorShao, Chuntao
contributor authorZhou, Di
date accessioned2017-05-09T01:16:27Z
date available2017-05-09T01:16:27Z
date issued2015
identifier issn0022-0434
identifier otherds_137_05_051014.pdf
identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/157521
description abstractA guidance law with finite time convergence is designed using the sliding mode control method and finite time convergence control theory, accounting for the missile autopilot as secondorder dynamics. The highorder derivatives of the line of sight (LOS) angle are avoided in the expression of guidance law such that it can be implemented in practical applications. The designed guidance law is effective in compensating the bad influence of the autopilot dynamics on guidance accuracy. In simulations of intercepting a non maneuvering target or a maneuvering target, respectively, the designed guidance law is compared with the adaptive sliding mode guidance (ASMG) law in the presence of missile autopilot lag. Simulation results show that the designed guidance law is able to guide a missile to accurately intercept a nonmaneuvering target or a maneuvering target with finite time, even if it escapes in a great and fast maneuver and the autopilot has a relatively large lag.
publisherThe American Society of Mechanical Engineers (ASME)
titleFinite Time Convergence Guidance Law Accounting for Missile Autopilot
typeJournal Paper
journal volume137
journal issue5
journal titleJournal of Dynamic Systems, Measurement, and Control
identifier doi10.1115/1.4029241
journal fristpage51014
journal lastpage51014
identifier eissn1528-9028
treeJournal of Dynamic Systems, Measurement, and Control:;2015:;volume( 137 ):;issue: 005
contenttypeFulltext


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