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Please use this identifier to cite or link to this item: https://scholarbank.nus.edu.sg/handle/10635/111538
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dc.titleAn Optimization Approach to Integrated Aircraft-Controller Design
dc.contributor.authorYang, G.-H.
dc.contributor.authorLum, K.-Y.
dc.date.accessioned2014-11-28T01:53:21Z
dc.date.available2014-11-28T01:53:21Z
dc.date.issued2003
dc.identifier.citationYang, G.-H.,Lum, K.-Y. (2003). An Optimization Approach to Integrated Aircraft-Controller Design. Proceedings of the American Control Conference 2 : 1649-1654. ScholarBank@NUS Repository.
dc.identifier.issn07431619
dc.identifier.urihttp://scholarbank.nus.edu.sg/handle/10635/111538
dc.description.abstractThis paper is concerned with the problem of optimizing aircraft parameters such as the size of its control surfaces, while meeting closed-loop dynamic performance requirements that are formulated as an optimization problem with matrix inequality constraints. New necessary and sufficient conditions for the solvability of the problem are obtained by introducing extra auxiliary variables. Iterative LMI-based algorithms are developed and applied to the redesign of horizontal tail and spoiler for the F-4.
dc.sourceScopus
dc.subjectAircraft design
dc.subjectControl surfaces
dc.subjectH∞ control
dc.subjectLinear matrix inequalities (LMIs)
dc.subjectLinear systems
dc.subjectOptimization
dc.typeConference Paper
dc.contributor.departmentTEMASEK LABORATORIES
dc.description.sourcetitleProceedings of the American Control Conference
dc.description.volume2
dc.description.page1649-1654
dc.description.codenPRACE
dc.identifier.isiutNOT_IN_WOS
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