| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系專班 === 96 === The implementation of active attitude control techniques is still barely exploited for nano- and picosatellites. Commonly, pure passive stabilization, if at all, is preferred due to its simplicity. But in order to enhance the capabilities of nanosatellites in the perspective of ever challenging mission objectives, advanced attitude control strategies need to be developed and tested.
The primary purpose of this thesis is to develop a consistent attitude control strategy for the PACE mission, in order to carry out attitude control experiments on this 2 kg space-craft. PACE is the first indigenous nanosatellite developed at the National Cheng Kung Uni-versity (NCKU) in Taiwan. Control laws for pure magnetic actuation as well as for momen-tum-biased stabilization are presented, implemented and simulated. The use of a single mo-mentum wheel for attitude control of a nanosatellite is unique to the PACE mission and has not been carried out prior to this thesis. For the on-board estimation of the satellite’s attitude, an Extended Kalman Filter has been developed and simulated.
The simulations access the performance of the attitude determination process and demonstrate the superiority of the momentum-biased stabilization over the pure magnetic stabilization in the presence of the disturbance forces. All the presented attitude modes take advantage of novel and/or commercially available, highly miniaturized devices that make the PACE nanosatellite truly an ideal platform for attitude control experiments.
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