| 摘要 |
PCT No. PCT/EP92/02050 Sec. 371 Date Jun. 10, 1994 Sec. 102(e) Date Jun. 10, 1994 PCT Filed Sep. 4, 1993 PCT Pub. No. WO93/04924 PCT Pub. Date Mar. 18, 1993The invention provides an improved process and apparatus for controlling the attitude of a three-axis stabilized spacecraft. Separate dead zone elements are used to define threshold values for limiting nutation amplitude and deviation of the spin direction of the spacecraft from a desired orientation, and a continuous check is performed to determine whether the nutation amplitude and deviation of the spacecraft exceed the threshold values. A control intervention is initiated to reduce the nutation, even when the spin direction is within the range limited by the applicable threshold value.
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