Thesis Type: Post Graduate
Institution Of The Thesis: Orta Doğu Teknik Üniversitesi, Faculty of Engineering, Department of Aerospace Engineering, Turkey
Approval Date: 2019
Student: SÜLEYMAN ALTINIŞIK
Consultant: OZAN TEKİNALPAbstract:
In this thesis, the vibration suppression of flexible spacecraft that carries out attitude tracking maneuvers is addressed. Attitude control algorithm that uses quaternion parametrization is employed. The nonlinear tracking controller employs the to-go quaternion and its derivative. Feedback controller designed is based on this recently developed attitude formulation. Piezoelectric sensors and actuators are also included to rapidly suppress structural vibration. The simulation results demonstrate the success of the algorithm in attitude tracking and vibration suppression.