Spacecraft attitude control method for controlling moment gyro singularity avoidance
A technology for controlling moment gyro and singularity avoidance, applied in attitude control, three-dimensional position/channel control and other directions, which can solve the problem of singularity of SGCMG group
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[0037] Moment of inertia of rigid spacecraft , The initial quaternion of the spacecraft , Instruction quaternion , The initial angular velocity , Command angular velocity , , The maximum amplitude of the external disturbance torque is . The SGCMG group adopts a pyramid configuration, Installation angle for SGCMG frame, flywheel angular momentum , The initial and terminal frame angular velocity , The maximum frame angular velocity , The maximum frame angular acceleration .
[0038] A spacecraft attitude control method for controlling moment gyro singularity avoidance, the specific steps are:
[0039] The first step is to determine the angular momentum set of the SGCMG group
[0040] According to the singular angular momentum of the SGCMG group Plot the singular momentum surface of the redundant configuration of the SGCMG group. The singular angular momentum expression of the SGCMG group is:
[0041] (1)
[0042] among them Is the number of SGCMG, Need to traverse both p...
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