Abstract
Reaction wheel assembly used as main actuator of an attitude control system can be a major source of disturbances. Although vibration isolator for a reaction wheel assembly is required to attenuate a disturbance, a control torque has to be transmitted for an attitude control of a satellite. This paper introduces a new design method of vibration isolator for reaction wheel assembly. Proposed method is based on H-infinity formulation and optimizes not only parameters of vibration isolator, but also parameters of satellite's controller simultaneously. At first, numerical model of a parallel link isolator is formulated. Next, the formulations of new design method and constraint conditions are described. After that, results of numerical analysis and availability of proposed method are shown.
