Phase-Stabilizing Ascent Attitude Control Algorithm Design for Solid Fuel Launch Vehicle고체 연료 발사체의 상승 구간 위상 안정화 제어 알고리즘의 설계 기법

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This study introduces a new optimization-based methodology in linear attitude controller design, specifically for solid launch vehicles during atmospheric ascent phase. A conventional proportional-derivative (PD) feedback structure with dedicated structural filter are employed to stabilize aerodynamic instability and phase-stabilize the structural bending effects. Considering rapidly time-varying nature of launch vehicle states and environments, we devise set of optimization problems to obtain time-scheduled design parameters that satisfies prescribed design criteria by heuristic optimization algorithm. Moreover, the iterative optimization scheme is proposed to resolve the trade-off relationship between the feedback algorithm and the filter. The effectiveness of the proposed methodology is verified by extensive Monte-Carlo sampling based linear analysis and high-fidelity 6-DOF simulations, thereby underlining the proposed method’s capabilities in assisting heuristic design process for engineers or automatically attaining optimal control parameters.
Publisher
Korean Society for Aeronautical and Space Sciences
Issue Date
2024-09
Language
Korean
Article Type
Article
Citation

Journal of the Korean Society for Aeronautical and Space Sciences, v.52, no.9, pp.709 - 719

ISSN
1225-1348
DOI
10.5139/JKSAS.2024.52.9.709
URI
http://hdl.handle.net/10203/322483
Appears in Collection
AE-Journal Papers(저널논문)
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