Integral global sliding mode guidance for impact angle control

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dc.contributor.authorHe, Shaoming
dc.contributor.authorLin, Defu
dc.contributor.authorWang, Jiang
dc.date.accessioned2019-01-09T13:51:30Z
dc.date.available2019-01-09T13:51:30Z
dc.date.issued2018-10-18
dc.description.abstractThis Correspondence proposes a new guidance law based on integral sliding mode control (ISMC) technique for maneuvering target interception with impact angle constraint. A time-varying function weighted line-of-sight (LOS) error dynamics, representing the nominal guidance performance, is introduced first. The proposed guidance law is derived by utilizing ISMC to follow the desired error dynamics. The convergence of the guidance law developed is supported by Lyapunov stability. Simulations with extensive comparisons explicitly demonstrate the effectiveness of the proposed approach.en_UK
dc.identifier.citationHe S, Lin D, Wang J. (2019) Integral global sliding mode guidance for impact angle control. IEEE Transactions on Aerospace and Electronic Systems, Volume 55, Issue 4, 2019, pp.1843-1849en_UK
dc.identifier.issn0018-9251
dc.identifier.urihttps://doi.org/10.1109/TAES.2018.2876588
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/13806
dc.language.isoenen_UK
dc.publisherIEEEen_UK
dc.rightsAttribution-NonCommercial 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by-nc/4.0/*
dc.subjectAerodynamicsen_UK
dc.subjectConvergenceen_UK
dc.subjectMissilesen_UK
dc.subjectClosed-form solutionsen_UK
dc.subjectKinematicsen_UK
dc.subjectMathematical modelen_UK
dc.titleIntegral global sliding mode guidance for impact angle controlen_UK
dc.typeArticle

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