Process and a device for controlling the attitude of a three-axis stabilized spinning spacecraft
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United States of America Patent
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Jan 28, 1997
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N/A
app pub date -
Jun 10, 1994
filing date -
Sep 6, 1991
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Abstract
The 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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