| Summary: | 碩士 === 國立成功大學 === 電機工程學系碩博士班 === 97 === 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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