국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Attitude Control of a Small Satellite using Magnetic Bearing Momentum Wheel UDC 629.783
저자	Fuyuto Terui, Atsushi Nakajima
Keyword	attitude control; small satellite; magnetic bearing; tether; H∞ control
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr01303.pdf?id=NALTR0001303
보고서번호	NAL TR-1303
발행년도	1996.7
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	An attitude controller for a 50kg-class micro satellite which could be launched by H-II rocket as a piggyback payload of a main satellite is considered.The survey of the proposals of the mission usques and tilt the axis of the momentum wheel relative to the despun mainbody,and this function can be used for the active stabilization of the attitude motion of the sattellite.More precisely,we can make the angular velocity of the satellite mainbody zero using this control actuator.To change the attitude of the satellite mainbody,magnetic torquers or thrusters would be necessary.First,the linearized equations of motion of such a dual spin satellite are formulated.Through the process of linearization,various assumptions are used such as small tilt angles of the wheel and high and almost constant spin rate of the wheel.These linearized equations are used for the analysis of the dynamics of the satellite and the design of the attitude controller.Next,disturbance torque acting on the satellite caused by the release of a tethered subsatellite from it is estimated for the controller design.After that,the attitude controller for estimated disturbance is designed applying the H∞ control theory.Then the performance f the controller is evaluated through numerical simulatoin.