Space observation using space probes have been revealing information related to the origin of galaxies and planets. Observing a target far from the Earth enables acquiring data about condition of an early universe or exoplanets. High pointing accuracy is required for acquiring a high resolution image of a target. Vibration generated by equipments in a bus part declines the pointing accuracy of an observation satellite, therefore methods using Tip Tilt Mirror and Stewart Platform have been studied for suppressing the influence of vibration. However, because these conventional methods use actuators, there are possibilities that observation with high pointing accuracy must be despaired if those actuators are broken. The proposed mechanism is not requiring actuators for suppressing the influence of vibration. The proposed mechanism is utilizing flux pinning effect and enables connection between mission and bus parts of an observation satellite using pinning force rather than mechanical structure. Pinning force, which works as magnetic force, can be approximated by linear spring damping force. Our aim is to build micro vibration isolator that enables suppressing the vibration without any control using flux pinning effect. The properties of pinning force must be sufficiently understood for the proposed mechanism. Numerical analysis were performed and the results are discussed for understanding pinning force working on proposed mechanism. A design approach for the proposed mechanism is also discussed in this paper.
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