• Journal of Navigation and Port Research
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• v.31 no.3 s.119
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• pp.229-233
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• 2007

This paper presents the performance of PV(Photovoltaic) system, the design of MPPT(Maximum Power Point Tracker). Output of PV power system is DC, and PV power system is linked to the DC bus. The current(I)-voltage(V) output characteristic of PV cells changes with solar irradiance and cell temperature as parameters. As various PV modules respond differently to each of the parameters cited above. Maximum output of PV modules am be achieved by MPPT(Maximum Power Point Tracker) algorithm This paper includes a discussion on the performance of PV module, MPPT algorithm and the influence of PV module angle.

• Proceedings of the KIEE Conference
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• 2003.07e
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• pp.28-30
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• 2003

본 논문은 10kW태양광 발전시스템의 설치 및 운전 상황에 대한 내용으로서 발전 뿐만아니라 학습용으로 이용할 수 있도록 10kW 단독운전 또는 7kW와 3kW 병렬운전이 가능하도록 구성되었다. 태양전지판은 20직렬 10병렬로 구성되며, 10병렬 태양전지판은 방위각 $0^{\circ}$, 경사각 $46^{\circ}\sim8^{\circ}$로 이루어져 있으므로 필요에 따라서 다양한 경사각으로 3kW까지 선택 운전할 수 있도록 구성되어 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.7
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• pp.622-627
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• 2014

A pico-class satellite has limitation to generate power from the solar cells due to its limited accommodation area to install the solar cells. The variation of incidence angle between solar panels and sunlight induced by the revolution and rotation of the satellite is one of the key parameters to determine the power generation. In this study, we proposed a concentrating photovoltaic system for pico-class satellite applications to enhance power generation when the ${\beta}$ angle between the sunlight and the solar panel is zero by effectively concentrating solar energy on solar panels. The feasibility of the conceptual idea has been demonstrated by power measurement test using solar simulator and commercial multi-array lens system.

• Proceedings of the KIEE Conference
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• 2003.07b
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• pp.1371-1373
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• 2003

본 논문은 10kW 태양광 발전시스템의 설치 및 운전 상황에 대한 내용으로서 발전 뿐만아니라 학습용으로 이용할 수 있도록 10kW 단독운전 또는 7kW와 3kW 병렬운전이 가능하도록 구성되었다. 태양전지판은 20직렬 10병렬로 구성되며, 10병렬 태양전지판은 방위각 $0^{\circ}$, 경사가 $46^{\circ}{\sim}8^{\circ}$로 이루어져 있으므로 필요에 따라서 다양한 경사각으로 3kW까지 선택 운전할 수 있도록 구성되어있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.4
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• pp.318-325
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• 2015

Pico satellite has limited surface to install the solar cells due to its extremely limited size. Also, the sun incidence angle with respect to the solar panel continuously varies according to the attitude control strategy and its important parameter for the power generation. In this study, a concentrating photovoltaic system for pico satellite application has been proposed that can enhance the power generation efficiency in case of the unfavorable condition of the sun incidence angle with respect to the solar panel of the satellite using the fresnel lens. To prove the possibility of maximizing the power generation efficiency of the proposed concentrating power system, we have performed the power measurement test using a solar simulator and commercial fresnel lens. And on-orbit analysis of the power generation efficiency using the STK which is a commercial S/W has also been performed based on the test results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.7
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• pp.709-716
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• 2009

Thermal condition according to the operation attitude of a satellite in orbit would be essential to be known because the orbit attitude is a dominant factor to affect satellite thermal design. In this paper, the change in space thermal environment and the thermal effect in thermal design are studied for a low earth orbit satellite according to the yaw motion. The present satellite retains sun-pointing attitude during daylight due to the fixed type solar arrays. And it also moves along the orbit with constant yaw motion in a longitudinal axis so that a star tracker which is a star sensor for satellite's attitude control always looks into the deep space. This attitude is considered in its better visibility to the stars for a successful mission operation. Also, it is required to access the corresponding thermal effects due to the yaw motion. Therefore, we try to verify these by the thermal analysis for the satellite thermal model with the yaw motion.