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微衛星之任務為藉由量測衛星與火箭分離階段之數據，包括分離時之位置、速度、姿態以及相關之推力以重建衛星與火箭分離時之推進與控制特性。本論文詳述CKUTEX微衛星姿態估測與控制次系統之設計與實現，並探討分離階段軌道與姿態重建之方式；為針對衛星軌道與姿態進行判定，CKUTEX微衛星將搭載GPS接收器酬載進行時間、位置與速度之量測，並搭載磁力計與太陽感測器於軌道量測資料以結合衛星動態模式進行衛星姿態判定。此外，由於小型發射載具於衛星脫離時有可能存在足以影響操控、通聯與充電之角速度，因此當衛星脫離發射載具後，將使用磁力計、磁力線圈控制姿態以穩定旋轉角速度；而在實驗階段CKUTEX微衛星將嘗試以微推進系統及相搭配之控制單元以控制衛星姿態，並依姿態估測技術估算其效能與各項參數。除了軟體模擬與分析，並於地面建置一套硬體測試迴路(Hardware in the Loop)以模擬太空環境與衛星動態，進而驗證CKUTEX微衛星姿態判別與控制演算法的效能及正確性。

The objective of the CKUTEX (Cheng-Kung University Technology Experimental Satellite) micro-satellite project is developing domestic experimental satellite technique. CKUTEX micro satellite will reconstruct the satellite and launcher’s propulsion and control characteristics by using the data collected at the satellite in separation stage including position, velocity, attitude and torque. The thesis describes the design and implementation of the CKUTEX micro-satellite attitude determination and control subsystem and investigates the method to reconstruct trajectory and attitude in separation stage. To determine the satellite orbit and attitude, the CKUTEX micro-satellite will carry a GPS receiver payload to measure time, position, and velocity. The magnetometer and the sun-sensor will be carried also to determine satellite’s attitude by combining measurement data and satellite dynamic model. In addition, the angular velocity that can affect control, communication, and recharging after separation may exist. To stabilize the angular rate, the satellite will use magnetometer and magnetic torque rods after separation from the launch vehicle. In the experiment stage, the CKUTEX micro-satellite would try to use micro-thruster system with corresponding control unit to control satellite attitude, and compute the performance and parameters with attitude estimation technique. In addition to software simulation and analysis, the hardware in the loop which can simulate space environment and satellite dynamics is also constructed to validate the performance and the correctness of the CKUTEX micro-satellite attitude determination and control algorithm.

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