Thesis Type: Postgraduate
Institution Of The Thesis: Orta Doğu Teknik Üniversitesi, Faculty of Engineering, Department of Mechanical Engineering, Turkey
Approval Date: 2014
Student: CANER GENÇOĞLU
Supervisor: HASAN NEVZAT ÖZGÜVENAbstract:
Airborne structures are required to be lightweight in today's designs. However this lowers the overall stiffness of the structure and causes low frequency vibration problems for which passive vibration control techniques are inadequate. Active vibration control using piezoelectric patches is a promising technology to solve vibration problems of aerospace structures. Many studies were done on beam and plate geometries, however studies on cylinder geometry which is used extensively as engineering structure, is relatively rare. In this study, first a cantilever beam is studied to verify the analysis, modeling and control concepts to be used in the cylinder structure since cantilever beam has simpler dynamics. Finite element model of the beam with piezoelectric patch is generated. Control simulations are done on the mathematical model of the cantilever beam derived from the finite element model. Experimental works are carried out on the beam to verify the controller designed in the simulation stage. The second structure studied is a hollow cylinder with piezoelectric patch actuator and sensor pair. This study is an extension of the beam study with the addition of determining the optimal piezoelectric patch placement. Optimal location of piezoelectric patch actuator is determined based on a method that uses the controllability Gramian of the system with piezoelectric patch for the target modes to be controlled. After patch placement control simulations are made to design the controller and verify the placement of actuator. Experimental works are also made over the cylinder to verify the designed controller and the patch placement.