System and method for controlling the attitude of a flying object
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United States of America Patent
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Issued Date -
Jul 22, 2004
app pub date -
Aug 29, 2003
filing date -
Aug 30, 2002
priority date (Note) -
Abandoned
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Abstract
The attitude of a satellite is controlled by at least three reaction wheels having mutually different rotation axes and at least two control moment gyroscopes having gimbal axes which extend in an equal direction. The reaction wheels and the control momentum gyros are controlled according to calculated values. When the rotors of the gyroscopes are given rotations in opposite directions to each other, angular momentum vectors are produced in respective directions normal to the directions of rotation of the rotors about their gimbal axes.
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