DC Field | Value | Language |
---|---|---|
dc.contributor.author | Lee, Hohyeong | ko |
dc.contributor.author | Kim, Lamsu | ko |
dc.contributor.author | Lee, Dongwoo | ko |
dc.contributor.author | Jang, Kwangwoo | ko |
dc.contributor.author | Jo, Kyoungyong | ko |
dc.contributor.author | Park, Taesan | ko |
dc.contributor.author | Bang, Hyochoong | ko |
dc.date.accessioned | 2023-11-14T02:03:10Z | - |
dc.date.available | 2023-11-14T02:03:10Z | - |
dc.date.created | 2023-11-14 | - |
dc.date.created | 2023-11-14 | - |
dc.date.created | 2023-11-14 | - |
dc.date.issued | 2023-09 | - |
dc.identifier.citation | JOURNAL OF THE KOREAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, v.51, no.9, pp.617 - 625 | - |
dc.identifier.issn | 1225-1348 | - |
dc.identifier.uri | http://hdl.handle.net/10203/314568 | - |
dc.description.abstract | Loitering munitions have several advantages in terms of operational flexibility and versatility. However, due to characteristics of fixed wing shape, control surface effects of longitudinal axis to lateral axis are asymmetric and amount of velocity change during terminal guidance phase is large. Since typical guidance laws do not take into account velocity change, a distinguished guidance law is needed. In this paper, look angle guidance law for loitering munition that is able to tune impact angle and consider velocity change is proposed. In the proposed guidance law, longitudinal axis of loitering munition is controlled by utilizing sliding mode control to generate angular rate and thrust commands that follow look angle and velocity command profile. Lateral axis of loitering munition is controlled by utilizing nonlinear dynamic inversion method for generating angular rate commands that control heading angle. The stability and accuracy of proposed guidance law are shown through Monte-Carlo simulation that added disturbance to 6 degree of freedom model. | - |
dc.language | English | - |
dc.publisher | KOREAN SOC AERONAUTICAL & SPACE SCIENCES | - |
dc.title | Development of Look Angle Guidance Law for Loitering Munition Under Velocity Change | - |
dc.title.alternative | 속도 변화를 고려한 자폭형 고정익 무인기의 관측각 제어 기반 종말 유도 기법 설계 | - |
dc.type | Article | - |
dc.identifier.scopusid | 2-s2.0-85175544593 | - |
dc.type.rims | ART | - |
dc.citation.volume | 51 | - |
dc.citation.issue | 9 | - |
dc.citation.beginningpage | 617 | - |
dc.citation.endingpage | 625 | - |
dc.citation.publicationname | JOURNAL OF THE KOREAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES | - |
dc.identifier.doi | 10.5139/JKSAS.2023.51.9.535 | - |
dc.identifier.kciid | ART002993340 | - |
dc.contributor.localauthor | Bang, Hyochoong | - |
dc.contributor.nonIdAuthor | Jo, Kyoungyong | - |
dc.contributor.nonIdAuthor | Park, Taesan | - |
dc.description.isOpenAccess | N | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordAuthor | Loitering Munition | - |
dc.subject.keywordAuthor | Look Angle Guidance | - |
dc.subject.keywordAuthor | Sliding Mode Control | - |
dc.subject.keywordAuthor | Impact Angle Tunning | - |
dc.subject.keywordAuthor | 6 DOF Simulation | - |
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