Impulsive spacecraft formation control using orbital energy and angular momentum vector = 궤도 에너지와 각운동량 벡터를 이용한 위성 정렬 비행 제어

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This paper presents a multi-impulsive formation control strategy using orbit energy-matching and relative angular momentum vector between leader and follower satellites. These conservative parameters (energy and angular momentum) provide analytical and global solutions for orbital maneuver design without relying on Gauss Variational Equations. The relationship with orbit element differences is discussed in the simplifying assumptions. The proposed approach is free from small variation assumptions, so that it is suitable for handling even the case of large error corrections. General limitations of impulsive control and associated compensation maneuvers are also addressed.
Advisors
Bang, Hyo-Choongresearcher방효충researcher
Description
한국과학기술원 : 항공우주공학전공,
Publisher
한국과학기술원
Issue Date
2010
Identifier
455473/325007  / 020065175
Language
eng
Description

학위논문(박사) - 한국과학기술원 : 항공우주공학전공, 2010.08, [ iv, 99 p. ]

Keywords

Orbital Energy-matching; Impulsive Control; Satellte Formation Flying; Relative Motion Representation; 상대 운동 표현; 궤도 에너지 동기화; 순간 추력 제어; 위성 정렬 제어

URI
http://hdl.handle.net/10203/26413
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=455473&flag=dissertation
Appears in Collection
AE-Theses_Ph.D.(박사논문)
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