Recently, observation satellites are required extremely high pointing accuracy and stability to achieve various and complicated missions. However, reaction wheel assembly used as an actuator of the attitude control system can be a major source of disturbances. Therefore, isolation of disturbances is one of the most significant issues in designing a precise attitude control system. On the other hand, reaction wheel is an actuator of attitude control system. Therefore, the purpose of this study is to propose the new design method of vibration isolator in consideration of the torque transmissibility.
A study on design method of vibration isolator for reaction wheel assembly in consideration of the torque transmissibility
