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contributor authorZhou, Di
contributor authorQu, Pingping
contributor authorSun, Sheng
date accessioned2017-05-09T00:57:29Z
date available2017-05-09T00:57:29Z
date issued2013
identifier issn0022-0434
identifier otherds_135_05_051009.pdf
identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/151349
description abstractA slidingmode guidance (SMG) law is designed to intercept maneuvering targets with impact angle constrained flight trajectories under the assumption of ideal missile autopilot. Furthermore, accounting for the autopilot as secondorder dynamics, a new guidance law with terminal impact angle constraint is designed using the dynamic surface control method. Some firstorder lowpass filters are introduced into the designing process to avoid the occurrence of highorder derivatives of the line of sight (LOS) angle in the expression of the guidance law such that the guidance law can be implemented in practical applications. The proposed guidance law is effective in compensating for the secondorder autopilot lag. Simulation results show that it is able to guide a missile to impact a maneuvering target with a desired angle and a small miss distance.
publisherThe American Society of Mechanical Engineers (ASME)
titleA Guidance Law With Terminal Impact Angle Constraint Accounting for Missile Autopilot
typeJournal Paper
journal volume135
journal issue5
journal titleJournal of Dynamic Systems, Measurement, and Control
identifier doi10.1115/1.4024202
journal fristpage51009
journal lastpage51009
identifier eissn1528-9028
treeJournal of Dynamic Systems, Measurement, and Control:;2013:;volume( 135 ):;issue: 005
contenttypeFulltext


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