A control moment gyroscope based on rotational vibrations, dynamic model and experimentation

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Tezin Türü: Yüksek Lisans

Tezin Yürütüldüğü Kurum: Orta Doğu Teknik Üniversitesi, Mühendislik Fakültesi, Makina Mühendisliği Bölümü, Türkiye

Tezin Onay Tarihi: 2018

Öğrenci: FERHAT ARBERKLİ

Danışman: KIVANÇ AZGIN

Özet:

Satellite attitude determination and control system is one of the main subsystems of a spacecraft. Within this domain, there are several types of actuators; such as reaction wheels, control moment gyroscopes (CMG), propulsion systems and magnetic torque rods. All of them are common and currently being used on modern satellites and space stations depending on the application. Conventional reaction wheel and CMG operation are based on the continuous rotation of their rotor mass to exchange angular momentum between spacecraft body and their rotor body. It this thesis, vibration is proposed as a new way of actuation instead of continuous rotation. Firstly, a mathematical model of single axis vibrating CMG was developed and the possibility of useful output is investigated. Effects of system excitation parameters were analyzed and interpreted. In addition, unwanted vibrations on spacecraft due to excitation responses were canceled, and performance of the actuator was improved by finding optimum rotor geometry. Finally, two experimentation setups were designed, manufactured, tested and their results were discussed.