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- W4296558708 abstract "This article considers attitude control of a rigid body (e.g., small satellite) with internal rotating-mass actuators that, unlike reaction wheels, cannot perform unrestricted rotations. Instead, the rotational stroke of each actuator is limited to <inline-formula xmlns:mml=http://www.w3.org/1998/Math/MathML xmlns:xlink=http://www.w3.org/1999/xlink> <tex-math notation=LaTeX>$[-alpha,alpha]$ </tex-math></inline-formula> rad, where <inline-formula xmlns:mml=http://www.w3.org/1998/Math/MathML xmlns:xlink=http://www.w3.org/1999/xlink> <tex-math notation=LaTeX>$alpha > 0$ </tex-math></inline-formula> . We present two attitude-feedback control methods. The first method addresses setpoint tracking of constant attitude commands, whereas the second approach addresses command following of time-varying attitude commands. Both methods use control signals that are continuous and piecewise sinusoidal but whose derivatives can contain discontinuities. The main analytic results show that these attitude-feedback controls achieve asymptotic setpoint tracking for a constant attitude command and approximate command following for a time-varying attitude command. The results also show that the controls satisfy the strict actuator amplitude constraint. Each control method is demonstrated in numerical simulations of a small satellite in deep space. Finally, we present single-axis closed-loop attitude control experiments for a small-satellite system on an air bearing." @default.
- W4296558708 created "2022-09-21" @default.
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- W4296558708 date "2023-03-01" @default.
- W4296558708 modified "2023-10-02" @default.
- W4296558708 title "Small-Satellite Attitude Control Using Continuous Sinusoids With Strict Amplitude Constraints" @default.
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- W4296558708 doi "https://doi.org/10.1109/tcst.2022.3201191" @default.
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