Slew maneuver control under wheel constraints and precision attitude determination of observation satellites = 휠 제한요건 하에서의 관측 인공위성의 자세변환 제어 및 정밀 자세 결정 방식에 관한 연구

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Satellite technology has influenced our ordinary life in the various aspects such as weather forecast, GPS navigation, satellite TV, overseas telephone and so forth. Increasing requirement on national defense has spurred the advancement of satellite technology as well. In a modern war, it is beyond imagination to exclude the help of satellites. According to diverse missions, satellites can be broadly classified into three parts: communication, remote sensing and space science exploration. No matter what missions given, the attitude control of satellite is primarily required in order to achieve the given objective successfully. Frequently the requirement of attitude control concerning payload mission drives whole system requirements. The common idea of conservative design for a satellite is changing with a success of high performance small satellites. The technical advance of VLSI and high performance CPU motivates the study of effective and compact satellites. Short term, low cost, small satellite projects have made it more versatile to design a control system of a spacecraft nowadays. From this standpoint, we have investigated control algorithms that can be used for small satellites mainly. The purpose of this dissertation is to study practical design methods about the attitude control system under the constraints attributed to small satellites. In the practical view point, the small satellite has many limitations of mass, volume, power, cost and so on. The primary interest of this thesis is to find out methods to overcome these constraints. We developed a near minimum time slew maneuvering control algorithm since a satellite needs to point a specific target in order to fulfill its mission. This algorithm is based on an idea utilizing the maximum capacity of a wheel under saturation constraints. A nonlinear observer is designed for estimating states optimally. The extended separation principle of nonlinear systems enables to design the controller and observ...
Advisors
Park, Dong-Joresearcher박동조researcher
Description
한국과학기술원 : 전기및전자공학전공,
Publisher
한국과학기술원
Issue Date
2002
Identifier
174620/325007 / 000945345
Language
eng
Description

학위논문(박사) - 한국과학기술원 : 전기및전자공학전공, 2002.2, [ [viii], 150 p. ]

Keywords

Attitude determination; Attitude control; Satellite; Wheel constraint; 휠 제한요건; 자세결정; 자세변환제어; 인공위성

URI
http://hdl.handle.net/10203/35987
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=174620&flag=dissertation
Appears in Collection
EE-Theses_Ph.D.(박사논문)
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