Method and device for controlling attitude of a spacecraft
A technology of attitude control and spacecraft, which is applied in the field of attitude control of satellites and spacecraft, and can solve problems such as reducing the total angular momentum of satellites
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[0051] The invention involves taking a non-zero initial total angular momentum H TOT Attitude control of a spinning spacecraft. total angular momentum H TOT The axis of is hereinafter referred to as the "kinetic axis".
[0052] "Attitude control" shall be understood herein to mean at least changing the orientation of the spacecraft with respect to the kinematic axis, in other words, in a frame of reference associated with the geometry of the spacecraft known as the "aircraft frame of reference" , aligning the kinematic axis with a predetermined axis in the aircraft frame of reference.
[0053] In the following description, consider the following situation in a non-limiting manner: the spacecraft is a satellite 10, and the initial total angular momentum H TOT corresponds to the angular momentum transferred to the satellite 10 upon separation from the satellite's vehicle. For example, the satellite 10 has been placed by a vehicle in GTO (Geosynchronous Transfer Orbit) and is...
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