Satellite attitude control by an internal moving mass and a momentum wheel = 내부 질량과 모멘텀 휠을 사용한 인공위성 자세제어

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The regulation of three angular velocity components and one attitude anglepitch angle- of a satellite in a large tumbled state through an internal moving mass and a momentum wheel is analyzed. Approximate analytic solutions for the amplitude of an internal mass and corresponding dissipating rate of kinetic energy are derived in order to determine feedback gains which maximize the dissipating rate of kinetic energy and which are subject to amplitude constraint. It is shown that effects of system parameters and feedback gains on the performance are predictable by the derived formulas, and that the method for determining feedback gains is not only time-saving but also efficient.
Advisors
Cho, Hyung-Suckresearcher조형석researcher
Description
한국과학기술원 : 기계공학과 항공공학 전공,
Publisher
한국과학기술원
Issue Date
1984
Identifier
64003/325007 / 000821303
Language
eng
Description

학위논문(석사) - 한국과학기술원 : 기계공학과 항공공학 전공, 1984.2, [ [iv], 66, [1] p. ]

URI
http://hdl.handle.net/10203/26592
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=64003&flag=dissertation
Appears in Collection
AE-Theses_Master(석사논문)
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