DC Field | Value | Language |
---|---|---|
dc.contributor.author | 정철구 | ko |
dc.contributor.author | 이창훈 | ko |
dc.contributor.author | 탁민제 | ko |
dc.date.accessioned | 2021-12-08T06:43:19Z | - |
dc.date.available | 2021-12-08T06:43:19Z | - |
dc.date.created | 2021-12-07 | - |
dc.date.created | 2021-12-07 | - |
dc.date.created | 2021-12-07 | - |
dc.date.issued | 2021-11-12 | - |
dc.identifier.citation | 2021 한국군사과학기술학회 종합학술대회 | - |
dc.identifier.uri | http://hdl.handle.net/10203/290227 | - |
dc.description.abstract | This paper deals with the optimal midcourse guidance maximizing the final velocity for the air-to-air missiles using convex optimization. To this end, a highly nonlinear optimal control problem is first converted into the second-order cone programming (SOCP) using successive linearization and convexification techniques. In the proposed approach, the angle-of-attack rate is chosen as a pseudo control input in order to obtain the control affine system. Additionally, linear regularization terms on the performance index are introduced to relieve the sub-problem infeasibility issue in the successive linearization procedure. Finally, numerical simulations are performed to validate the proposed approach. | - |
dc.language | Korean | - |
dc.publisher | 한국군사과학기술학회 | - |
dc.title | 컨벡스 최적화를 이용한 공대공 유도탄의 중기 유도 기법 | - |
dc.type | Conference | - |
dc.type.rims | CONF | - |
dc.citation.publicationname | 2021 한국군사과학기술학회 종합학술대회 | - |
dc.identifier.conferencecountry | KO | - |
dc.identifier.conferencelocation | 대전컨벤션센터 | - |
dc.contributor.localauthor | 이창훈 | - |
dc.contributor.localauthor | 탁민제 | - |
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