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- W2000760175 abstract "In this paper, mainly a control method using both spacecraft attitude information and wheel gimbal signals is described. At first, system formation and its equations of motion are described, where interaxis cross coupling is positively utilized. And then described are approximate analytical solutions of the equations, where the system is linearized and complex variables are used. If, sensor signals of both roll and yaw attitude angles of spacecraft are available in gimbal servo electronics, nutational motion of the spacecraft can be decayed very quickly. And the system eigen values can be solved in very simple forms. It is shown that these spacecraft attitude signals bring on by far effective results of the nutation damping compared to the open loop case where only gimbal-axis sensor signals are used. These results are discussed and it is pointed out that outer-rotor type momentum wheels using spiral grooved bearing or ball bearing may cause nutational motion of the spacecraft, i.e. negative nutational damping. Finally, the authors recommend inner-rotor type momentum wheel, in case of spiral grooved or ball bearing, from a stand point of spacecraft nutational motion. Computer simulation results are presented which verify the above-metioned analytical solutions." @default.
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- W2000760175 date "1987-06-01" @default.
- W2000760175 modified "2023-09-25" @default.
- W2000760175 title "Active nutation control of spacecraft using gimballed momentum wheel" @default.
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- W2000760175 doi "https://doi.org/10.1016/0094-5765(87)90179-2" @default.
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