Attitude Tracking for Flexible Spacecraft from Quaternion Measurements
نویسنده
چکیده
In this paper the attitude tracking problem is solved for a flexible spacecraft in the case of measurements of the variables describing the attitude error. Such a control could be applied in failure situations for recovering a spacecraft, so increasing the fault tolerance of the spacecraft control system and the success of the mission. The result is a dynamic controller capable of reconstructing the information regarding the spacecraft angular velocity and those regarding the modal variables, describing the dynamics of the flexible appendages present in the spacecraft.
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