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• W2147958727 endingPage "1279" @default.
• W2147958727 startingPage "1273" @default.
• W2147958727 abstract "Most existing methods for satellite attitude control assume that full knowledge of satellite attitude is available by algebraic manipulation of at least two vector measurements from attitude sensors such as Sun, Earth-horizon, Earth-magnetic or star tracker sensors. Kalman filtering is usually used when only one vector measurement is available, however, asymptotic stability of nonlinear and uncertain dynamics of satellite is not guaranteed in this case. This technical note presents a coupled nonlinear estimator-controller for satellite attitude determination and control by using a 3-axis gyro and a single vector measurement for a fully actuated satellite. We assume that the moment-of-inertia matrix of satellite is unknown. Asymptotic convergence of the satellite attitude and angular velocity to their desired values is proven. Performance of the proposed controller is illustrated in a realistic case study by simulation where a magnetometer is used to provide the single vector measurement." @default.
• W2147958727 created "2016-06-24" @default.
• W2147958727 creator A5022312048 @default.
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• W2147958727 date "2012-05-01" @default.
• W2147958727 modified "2023-09-23" @default.
• W2147958727 title "Rigid Body Attitude Control Using a Single Vector Measurement and Gyro" @default.
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• W2147958727 doi "https://doi.org/10.1109/tac.2011.2174663" @default.
• W2147958727 hasPublicationYear "2012" @default.
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