DC Field | Value | Language |
---|---|---|
dc.contributor.author | Jung, Ki-Wook | ko |
dc.contributor.author | Lee, Chang-Hun | ko |
dc.date.accessioned | 2023-11-13T02:00:28Z | - |
dc.date.available | 2023-11-13T02:00:28Z | - |
dc.date.created | 2023-11-09 | - |
dc.date.created | 2023-11-09 | - |
dc.date.issued | 2023-09-21 | - |
dc.identifier.citation | 2023 우주발사체기술 심포지엄 | - |
dc.identifier.uri | http://hdl.handle.net/10203/314489 | - |
dc.description.abstract | This paper proposes a new approach to designing an attitude controller for a launch vehicle during its atmospheric ascent phase, using the parameter optimization technique. To overcome the difficulties in finding the design parameters that stabilizes aerodynamic effects, structural flexibility and propellant sloshing, a loop of the optimization problems is devised to attain the optimal control design parameters: Proportional-Derivative(PD) gain and pole/zero of the notch filter. The emphasis is on the capability of automatically deciding the control parameters for all design points that satisfies the prescribed stability criteria without any a-priori design such as initial guess of the filter design parameters. The proposed design framework is verified by linear control theory including Monte-Carlo sampling of linear system for a launch vehicle model based on KSLV-II. | - |
dc.language | Korean | - |
dc.publisher | 한국항공우주공학 | - |
dc.title | 공력 상승 구간 발사체의 파라미터 최적화 기반 자세 제어 알고리즘 설계 기법 | - |
dc.title.alternative | A Design Scheme for a Launch Vehicle’s Attitude Control Algorithm during Atmospheric Ascent via Parameter Optimization | - |
dc.type | Conference | - |
dc.type.rims | CONF | - |
dc.citation.publicationname | 2023 우주발사체기술 심포지엄 | - |
dc.identifier.conferencecountry | KO | - |
dc.identifier.conferencelocation | 한국과학기술원, 대전 | - |
dc.contributor.localauthor | Lee, Chang-Hun | - |
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