立方衛星為近幾年非常熱門的議題，也已經有許多成功的任務，所以許多人開始思考利用立方衛星執行新型態的任務，地球重返任務則為其中一種，這種任務很大的意義在於科學量測，使我們對大氣層的垂直分布可以更加掌握。地球重返任務遇到的挑戰包含: 如何脫離軌道，重返時的高溫以及姿態穩定, 而本篇研究著重於因應這些挑戰所帶來的限制，也就是地球重返任務的立方衛星在軌道上的姿態控制系統的設計，模擬與分析，這其中當然也考量到用於重返時的姿態穩定外型，對於在軌道
上操作的影響，以及脫離軌道的時間以及軌道估算，而地球重返任務立方衛星本身的熱防護，也限制了衛星姿態控制的感測器選用，因此如何利用僅有的感測器完成任務也是一項挑戰。本研究利MATLAB/Simulink 建立模擬環境也就是軟體迴路模擬，並決定出從衛星釋放初期的減滾(Detumbling)，到三軸穩定之姿態控制流程與策略，其中包含控制法則的選用以及姿態估測器的搭配選擇，並建立明確的判斷條件。軌道與脫離軌道的估算則會利用另一個獨立的程式計算與分析, 並考量配合姿態控制的結果。
軟體迴路模擬完成大部分的模擬環境建置，讓環境接近真實狀況，包含動態方程式，軌道估算，感測器模型，控制器以及擾動分析，由於感測器的選擇上受到限制所以在估測上會有比較大的挑戰，本研究將嘗試並比較不同估測方法的效能，並且在模擬加入感測器的特性，最後將姿態估測結果直接回饋給控制器，觀察相互搭配的影響。經過模擬分析並比較相關的廠商資料以及論文，決定出穩定及控制衛星的策略流程與控制法則。而脫離軌道的估算也會是一個重點，由於較不對稱的外型在姿態
改變上會影響軌道的脫離，所以要與姿態模擬的結果相互搭配。整個軟體迴路模擬完善後可以提供更完整的任務分析以及控制器設計，同時也可以讓衛星操作人員更熟悉可能遇到的狀況。

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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