| Summary: | 碩士 === 大葉大學 === 機械與自動化工程學系 === 98 === In this study, satellite attitude control and solar panel vibration are investigated. In order to carry out simulations with realistic configuration, the weights of the momentum wheels and solar panels are obtained from NSPO. The involved parameters include material properties, momentum wheel speeds and output torques, etc. We use SolidWorks to build a satellite model, including three momentum wheels, two solar panels, two triangle props. We use MATLAB to design a controller to control the satellite model in different cases in order to investigate the satellite tracking error and solar panel vibration.
We do the satellite attitude control in accordance with Sliding Mode Control (SMC). This control scheme has advantages of robustness, high availability and high efficiency. Because the space is an adverse circumstance, it is extraordinary difficult to maintain or repair. Therefore, choosing a high availability controller is a major topic for aeronautical engineering.
In addition to SMC, in this study we also compare two kinds of panel’s material: rigid and flexible bodies. In this paper, we can observe the effects of vibration reduction with flexible body, and make the satellite attitude more stable ultimate.
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