Abstarct: In this thesis; vibration behavior of a satellite wing is studied and, using active and passive vibration control systems, its vibration is reduced and controlled. The satellite wing is modeled as a cantilevered Rayleigh beam and its natural frequencies, corresponding mode shapes and its response to a concentrated impact load, which is exerted on the tip of the beam, is extracted. In order to reduce the vibration response, the active controllers such as PID and LQR, as well as the passive controllers such as nonlinear energy sink, is used. In this study; three nonlinear energy sinks with different stiffness are used. Also, in order to design the active controller, four different configurations for the location of sensor and actuator are intended. For each of these controllers, the response of the system is studied and finally three controllers are proposed. These controllers are reduced the amount of settling time from 24.34 sec to 0.53, 0.43 and 2.41 sec, respectively. Also, the maximum system amplitude for these controllers are reduced %50.1, %43.45 and %24.8 respectively.