Vibration parameters identification in a spacecraft subjected to active vibration damping

Abstract The increasing need for better pointing accuracy of antennas connected to spacecrafts has lead to a requirement for more efficient vibration control, which in turn calls for better knowledge of the vibration parameters. This paper presents the results from a study of identification of vibration parameters in a spacecraft where active vibration damping is a part of the attitude control. A mathematical model of a simple spacecraft is modelled in MATLAB and suitable controllers are developed in order to perform both effective vibration damping and attitude control. Simulations show how both open loop and closed loop vibration parameters may be identified.