Impact angle control guidance synthesis for evasive maneuver against intercept missile

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dc.contributor.authorYogaswara, Y. H.
dc.contributor.authorHong, Seong-Min
dc.contributor.authorTahk, Min-Jea
dc.contributor.authorShin, Hyo-Sang
dc.date.accessioned2018-01-24T10:06:14Z
dc.date.available2018-01-24T10:06:14Z
dc.date.issued2017-09-11
dc.description.abstractThis paper proposes a synthesis of new guidance law to generate an evasive maneuver against enemy’s missile interception while considering its impact angle, acceleration, and field-of-view constraints. The first component of the synthesis is a new function of repulsive Artificial Potential Field to generate the evasive maneuver as a real-time dynamic obstacle avoidance. The terminal impact angle and terminal acceleration constraints compliance are based on Time-to-Go Polynomial Guidance as the second component. The last component is the Logarithmic Barrier Function to satisfy the field-of-view limitation constraint by compensating the excessive total acceleration command. These three components are synthesized into a new guidance law, which involves three design parameter gains. Parameter study and numerical simulations are delivered to demonstrate the performance of the proposed repulsive function and guidance law. Finally, the guidance law simulations effectively achieve the zero terminal miss distance, while satisfying an evasive maneuver against intercept missile, considering impact angle, acceleration, and field-of-view limitation constraints simultaneously.en_UK
dc.identifier.citationYogaswara YH, Hong S-M, Tahk M-J, Shin H-S, Impact angle control guidance synthesis for evasive maneuver against intercept missile, International Journal of Aeronautical and Space Sciences, Vol. 18, Issue 4, 2017, pp. 719-728en_UK
dc.identifier.issn2093-274X
dc.identifier.urihttp://dx.doi.org/10.5139/IJASS.2017.18.4.719
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/12928
dc.language.isoenen_UK
dc.publisherKorean Society for Aeronautical and Space Sciencesen_UK
dc.rightsAttribution-NonCommercial 3.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by-nc/3.0/*
dc.subjectMissile guidanceen_UK
dc.subjectEvasive maneuveren_UK
dc.subjectImpact angle controlen_UK
dc.subjectArtificial potential fielden_UK
dc.titleImpact angle control guidance synthesis for evasive maneuver against intercept missileen_UK
dc.typeArticleen_UK

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