Nonlinear optimal missile guidance for stationary target interception with pendulum motion perspective

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dc.contributor.authorCho, Namhoon
dc.date.accessioned2021-08-13T08:37:04Z
dc.date.available2021-08-13T08:37:04Z
dc.date.issued2021-07-28
dc.description.abstractThis study outlines the set of equations constituting the necessary conditions that should be solved to determine the optimal guidance command for a missile to intercept a stationary target along a desired impact direction at a prespecified final time. Unlike the earlier studies on nonlinear optimal guidance problems, the present study formalises the optimal control problem with both final time and final state fixed. The pure control effort quadratic norm is considered as the performance index to be minimised. A noticeable finding from the study of the necessary conditions is that the flight path angle of the optimal trajectory obeys the simple pendulum dynamics. Full characterisation of the exact optimal solution requires numerically solving a set of four nonlinear algebraic equations with respect to four unknowns.en_UK
dc.identifier.citationCho N. (2021) Nonlinear optimal missile guidance for stationary target interception with pendulum motion perspective. In: IEEE 2021 American Control Conference, 25-28 May 2021, New Orleans, LA, pp. 3908-3913en_UK
dc.identifier.issn2378-5861
dc.identifier.urihttps://doi.org/10.23919/ACC50511.2021.9483418
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/16992
dc.language.isoenen_UK
dc.publisherIEEEen_UK
dc.rightsAttribution-NonCommercial 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by-nc/4.0/*
dc.subjectNonlinear equationsen_UK
dc.subjectIntegral equationsen_UK
dc.subjectDynamicsen_UK
dc.subjectOptimal controlen_UK
dc.subjectTrajectoryen_UK
dc.subjectPerformance analysisen_UK
dc.subjectMissile guidanceen_UK
dc.titleNonlinear optimal missile guidance for stationary target interception with pendulum motion perspectiveen_UK
dc.typeConference paperen_UK

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