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dc.contributor.authorZhou, D.
dc.contributor.authorSun, S.
dc.contributor.authorZhou, Jingyang
dc.contributor.authorTeo, Kok Lay
dc.date.accessioned2017-01-30T14:50:03Z
dc.date.available2017-01-30T14:50:03Z
dc.date.created2014-10-23T20:00:19Z
dc.date.issued2014
dc.identifier.citationZhou, D. and Sun, S. and Zhou, J. and Teo, K.L. 2014. A Discrete Sliding-Mode Guidance Law. Journal of Dynamic Systems, Measurement, and Control. 137 (2): pp. 024501-1-024501-6.
dc.identifier.urihttp://hdl.handle.net/20.500.11937/41262
dc.identifier.doi10.1115/1.4028038
dc.description.abstract

Based on the discrete form of the target-missile relative motion equations in plane, a discrete sliding-mode guidance (DSMG) law is proposed. All previous missile seeker's measurements are used in the design of the DSMG law to estimate the target acceleration such that noises in the seeker's measurements are effectively being smoothened. It is proved that the proposed DSMG law is finite time convergent. Quasi sliding-mode bands of the DSMG law are discussed, and the formula for calculating the terminal miss distances of the missile under the DSMG law are presented. Simulation results from a space interception process verify the effectiveness of the proposed method.

dc.publisherThe American Society of Mechanical Engineers
dc.titleA Discrete Sliding-Mode Guidance Law
dc.typeJournal Article
dcterms.source.volume137
dcterms.source.number2
dcterms.source.startPage024501
dcterms.source.endPage1
dcterms.source.issn0740-3224
dcterms.source.titleJournal of Dynamic Systems, Measurement, and Control
curtin.departmentDepartment of Construction Management
curtin.accessStatusFulltext not available


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