成功大學的CKUTEX (Cheng Kung University Technology Experimental Satellite)微衛星計畫係國內自主發展之實驗型微衛星；CKUTEX微衛星任務為量測衛星與火箭分離階段之數據與驗證實驗酬載系統，實驗酬載系統分別為太陽感測器(Digital Sun Sensor, DSS)與太空及GPS接收器系統。因此微衛星必需提供控制法則使得微衛星與火箭分離後，使衛星能在較小變化之姿態或穩定之角速度繞行衛星軌道。本論文詳述姿態控制器之設計、實現與驗證，針對所選用之制動器引用磁場微分控制，使用軟體分析和設計控制器參數，並選用微電腦單晶片和可程式系統晶片來實現控制器，並發展一套程序迴路模擬(Processor-in-the-loop Simulation)來驗證控制器之可行性與軟體設計之分析，程序迴路係為使用即時模擬系統模擬太空環境與衛星動態，結合控制器電路進而驗證姿態控制演算法的功能與性能。

CKUTEX (Cheng Kung University Technology Experimental Satellite) is part of the self-reliant experimental micro-satellite program in Taiwan. The mission of CKUTEX Satellite is to record pertinent data after its separation from the launch vehicle and verify the self-developed payloads. CKUTEX has 2 payloads, which are space-borne GPS receiver and digital sun sensor, respectively. After the separation, CKUTEX must provide attitude control function in order to stabilize the angular velocity and maintain small attitude changes in orbit.
This thesis describes the design, implementation and verification of the attitude controller. The attitude controller implements B-dot control law. With the aid of software, the design and analysis of controller’s parameters can be achieved. A microcontroller and SOPC (System On Programmable Chip) are implemented for the development of attitude controller. To fully develop and verify the feasibility of the attitude controller, processor-in-the-loop (PIL) simulation is developed. The simulation facility contains a dynamic simulator and real-time controller, as well as some interfacing circuitry. The dynamic simulator is capable of performing simulation of the space environment, orbit dynamic, attitude dynamic, and sensor/actuator models. This real-time simulation verifies the function and performance of the attitude controller.

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