| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系 === 105 === With the popular development of CubeSats, there are more and more different applications for them, Re-entry mission is one of the critical parts of earth observation. Re-entry CubeSat can carry the scientific equipment which can record some measurements during Re-entry phase in order to increase the knowledge of the properties of atmosphere. This research is referred to this kind of mission approach with a 3U CubeSat. In order to reach the objective, attitude determination and control subsystem is required to perform attitude stabilization and pointing control.
This research describes the mission analysis and development of attitude determination and control subsystem for the CubeSat, with emphasis on the operation and control strategy. Moreover, the attitude determination and control subsystem will not be activated during the re-entry since the ADCS hardware cannot sustain under such extreme scenario like supersonic speed and extremely high temperature. But the design of hardware and structure still affect the satellite operation during orbital cruise. Because of the thermal consideration, the use of the sensors are limited. Moreover, the design of the deployable solar panels, which are responsible for performing aerodynamic stability for re-entry phase, will also be investigated, in particular, the deployment strategy is assessed.
Software-in-the-loop simulation is used for mission design and performance analysis. A simulation software has been built up based on MATLAB/Simulink, which contains the dynamic model of the satellite, sensor/actuator model, environment model, attitude controller and estimator. With the design of simulation software, we can get several results from different combination of controller and estimator. The performance of the results can help the designer to define the operation strategy and identify the threshold of operation. Also, the software can simulate the error setting to observe the behavior of satellite, this can help ground operation to identify the possible error condition in real mission.
The simulation of de-orbit scenario will take attitude control into consideration, it can estimate the orbital lifetime to see whether it meets the mission requirement or not. In conclusion, the simulation tool not only helps us to design ADCS and makes the mission planning, but also provides an insight into the operating strategy.
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