원주 제한 삼체문제에서의 저추력 달 포착 궤도 설계Low Thrust Lunar Capture Trajectory design in Circular Restricted Three body Problem

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In this paper, low thrust spacecraft trajectory optimization for the lunar capture trajectory in the circular restricted threebody problem (CRTBP) is presented. Explanations of the controlled motion of the satellite under the dynamics of CRTBP are presented with the application of the Hills region and Jacobi constant in the trajectory optimization. The initial orbit of the spacecraft of interest is assumed to be a geosynchronous transfer orbit (GTO) with a semi-major axis of 43444km and eccentricity of 0.8.
Publisher
한국항공우주학회
Issue Date
2020-07-10
Language
Korean
Citation

한국항공우주학회 2020년도 춘계학술대회, pp.672 - 673

URI
http://hdl.handle.net/10203/287124
Appears in Collection
AE-Conference Papers(학술회의논문)
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