3U 큐브위성의 자세 제어방식에 따른 생산 전력 분석

Abstract

In this thesis, as a preliminary design stage of a KMSL(Korea Microgravity Science Laboratory) cubesatellite, we tried to verify whether it is possible to stably produce the required power to perform microgravity science mission in space environment. To this end, the structural, electrical components and element parts of the scientific payloads consisting of the KMSL cubesatellite were first placed and configured in order to obtain the mass properties such as the center of gravity and the moment of inertia and etc. The electrical power system was the designed to stably generate sufficient power while operating the KMSL cubesatellite in the space environment and supply it to each of subsystems and payloads. The attitude control system was also designed and implemented to satisfy the KMSL cubesatellite's mission requirements for rotational angular velocity (2°/sec) (that is mandatory to perform scientific missions) and constructed a B-dot control algorithm for rotational angle control of he KMSL cubesatellite. It was found that the KMSL cubesatellite injected at an initial angular velocity [45°/sec, 35°/sec, 25°/sec] can produce an average of 4 W in the detumbling control period (separate mode) where rotational angular velocity attenuation is large. During the omnidirectional control period (including the normal mode, mission mode, and communication mode), where the angularity is controlled at ω <2°/sec, an average of 5 W was found to stably generate. Based on the results obtained from calculating the power production during the attitude control period, it is judged that it is possible to set the limit of the required power demand for each mission scenario and to design a specific mission.