| Summary: | 碩士 === 國立成功大學 === 電機工程學系碩博士班 === 98 === 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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