Tracking control using attitude measurements for flexible spacecraft

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.