Optimization-Based Determination of Apollo Guidance Law Parameters for Korean Lunar Lander 달착륙 임무를 위한 최적화 기반 아폴로 유도 법칙 파라미터 선정

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This paper proposes an optimization-based procedure to determine the parameters of the Apollo guidance law for Korean lunar lander mission. A lunar landing mission is formulated as a trajectory optimization problem to minimize the fuel consumption and the reference trajectory for the lander is obtained by solving the problem in the pre-flight phase. Some parameters of the Apollo guidance, which are coefficients of the polynomial used to define the guidance command, are selected based on the reference trajectory obtained in the pre-flight phase. A case study for the landing guidance of Korean lunar lander mission using the proposed procedure is conducted to demonstrate its effectiveness.
Publisher
KOREAN SOC AERONAUTICAL & SPACE SCIENCES
Issue Date
2017-08
Language
Korean
Article Type
Article
Citation

JOURNAL OF THE KOREAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, v.45, no.8, pp.662 - 670

ISSN
1225-1348
DOI
10.5139/JKSAS.2017.45.8.662
URI
http://hdl.handle.net/10203/226018
Appears in Collection
AE-Journal Papers(저널논문)
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