| 摘要 |
A satellite energy and attitude control system includes a first energy wheel, a second energy wheel and a third energy wheel. The first energy wheel is mounted in a first double gimbal and the second energy wheel is mounted in a second double gimbal. The third energy wheel is mounted in a third double gimbal and the first, second and third energy wheels, which have at least two degrees of motion orthogonal to their respective spin axes, are located within a single plane and positioned with respect to each other such that the total angular momentum provided by the first, second and third energy wheels sums to zero approximate an operational range center of the gimbals.
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