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. One of the candidate configurations for such an attitude controller is bias momentum control using a magnetically suspended momentum wheel with gimballing capability. 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 linearalized 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 by applying the H-infinity control theory. Then the performance of the controller is evaluated through numerical simulation.
Attitude Control of a Small Satellite Using Magnetic Bearing Momentum Wheel
1996
24 pages
Report
Keine Angabe
Englisch
Unmanned Spacecraft , Small scientific satellites , Attitude control , Magnetic bearings , Spacecraft stability , Tethered satellites , Dual spin spacecraft , Reaction wheels , Momentum , Attitude(Inclination) , Torques , Attitude stability , Magnetic suspension , H-infinity control , Gimbals , Equations of motion , Spacecraft components , Satellite design , Linear equations , Foreign technology
Magnetic bearing momentum wheel
AIAA | 1976
|Magnetic Bearing Momentum Wheel
AIAA | 1977
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