• Journal of Power Electronics
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• 제6권1호
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• pp.18-28
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• 2006

The Electric Power Subsystem (EPS) is one of the most critical systems on any satellite because nearly every subsystem requires power. This makes the choice of power systems the most important task facing satellite designers. The main purpose of the Satellite EPS is to provide continuous, regulated and conditioned power to all the satellite subsystems. It has to withstand radiation, thermal cycling and vacuums in hostile space environments, as well as subsystem degradation over time. The EPS power characteristics are determined by both the parameters of the system itself and by the satellite orbit. After satellite separation from the launch vehicle (LV) to its orbit, in almost all situations, the satellite subsystems (attitude determination and control, communication and onboard computer and data handling (OBC&DH)), take their needed power from a storage battery (SB) and solar arrays (SA) besides the consumed power in the EPS management device. At this point (separation point, detumbling mode), the satellite's angular motion is high and the orientation of the solar arrays, with respect to the Sun, will change in a non-uniform way, so the amount of power generated by the solar arrays will be affected. The objective of this research is to select satellite EPS component types, to estimate solar array illumination parameters and to determine the efficiency of solar arrays during both detumbling and normal operation modes.

• Journal of Astronomy and Space Sciences
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• 제24권2호
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• pp.179-194
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• 2007

인공위성 전력계의 설계 및 분석은 위성 전체의 무게, 크기 및 성능을 결정하는 중요 변수로 작용한다. 위성체의 모든 타 부분체들은 전력계 설계의 영향을 받으며 특히 발사체 선정, 열 제어계 설계 및 구조계 설계의 경우 전력계의 성능 및 제한 조건 등 전력계 설계 결과에 매우 큰 영향을 받는다. 이 논문에서는 현재 국내에서 지속적으로 개발되고 있는 저궤도 위성의 전력계 설계를 위한 새로운 프로그램을 소개하고 타 위성의 설계 자료를 이용한 개발된 프로그램의 성능 실험 결과를 기술하였다. 실험 결과 제안된 전력계 설계 프로그램은 전력계 사이징 뿐 아니라 궤도상에서의 전력계 성능을 예측하는데도 사용할 수 있음을 보였다.

• 항공우주기술
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• 제9권2호
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• pp.176-184
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• 2010

지구 저궤도 위성의 임무 운용 시 전력 시스템을 안전하고 운용하고 에너지 균형을 만족하는 임무를 설계하기 위해 계획된 임무에 대한 전력 파라미터를 예측해야 한다. 이 논문에서는 다양한 미션 프로파일에 대해 위성의 생성 전력, 소모 전력, 배터리 방전 정도(Depth of Discharge, 이하 DoD), 버스 전압, 충/방전 전류 등을 예측함으로써 미션의 유효성 및 에너지 균형을 검증하기 위한 전력 시뮬레이터를 제안한다. 제안된 전력 시뮬레이터에는 인공위성의 생성 전력을 모사하기 위해 태양전지판(Solar Array, 이하 SA)의 모델, SAR (Solar Array Regulator)의 3가지 동작 모드를 구현하였다. 또한 소모 전력을 모사하기 위해 버스 및 탑재체의 각 유닛 별 소모 전력, Unit on/off configuration, 탑재체 운용 모드 등을 고려하였다. 버스 전압 및 충/방전 전류를 예측하기 위해 배터리 및 주변 회로를 모델링하고 임의의 DoD, 충방전 전류에 대해 배터리 전압 및 버스 전압을 예측한다. 구현된 전력 시뮬레이터를 이용해 에너지 균형을 분석하고 임무 계획의 적합성을 쉽게 판단할 수 있다.

• KSII Transactions on Internet and Information Systems (TIIS)
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• 제18권6호
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• pp.1638-1658
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• 2024

As a crucial development direction for the sixth generation of mobile communication networks (6G), Low Earth Orbit (LEO) satellite networks exhibit characteristics such as low latency, seamless coverage, and high bandwidth. However, the frequent changes in the topology of LEO satellite networks complicate communication between satellites, and satellite power resources are limited. To fully utilize resources on satellites, it is essential to determine the association between satellites before power allocation. To effectively address the satellite association problem in LEO satellite networks, this paper proposes a satellite association-based resource allocation algorithm. The algorithm comprehensively considers the throughput of the satellite network and the fairness associated with satellite correlation. It formulates an objective function with logarithmic utility by taking the logarithm and summing the satellite channel capacities. This aims to maximize the sum of logarithmic utility while promoting the selection of fewer associated satellites for forwarding satellites, thereby enhancing the fairness of satellite association. The problems of satellite association and power allocation are solved under constraints on resources and transmission rates, maximizing the logarithmic utility function. The paper employs an improved Kuhn-Munkres (KM) algorithm to solve the satellite association problem and determine the correlation between satellites. Based on the satellite association results, the paper uses the Lagrangian dual method to solve the power allocation problem. Simulation results demonstrate that the proposed algorithm enhances the fairness of satellite association, optimizes resource utilization, and effectively improves the throughput of LEO satellite networks.

• 대한전기학회:학술대회논문집
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• 대한전기학회 1995년도 하계학술대회 논문집 A
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• pp.198-201
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• 1995

The overall design criteria for the optimal design of a small LEO satellite power system are described in summary. The analysis result of the KITSAT-I whole orbit data suggests the efficient power opertion for KITSAT-I and also gives some crutial information for developing a new satellite power system.

• 항공우주시스템공학회지
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• 제8권1호
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• pp.42-47
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• 2014

The role of Electrical Power Subsystem (EPS) is to generate a power and distribute it to the electrical devices for the system operation. For on-orbit operation of cube satellite, it is also necessary to supply power to on-board mission devices as commercial satellite does. Recently, commercial EPS products dedicated for the cube satellite application has been developed and widely used for the power subsystem design. In this paper, a permanent magnet attitude stabilization method without external power has been introduced because it has advantage from power consumption point of view and the EPS design of cube satellite by applying the commercial EPS products has been introduced and investigated. This paper also deals with the specification of the commercial EPS products for the beginner of the cube satellite design.

• 항공우주시스템공학회지
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• 제17권1호
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• pp.88-96
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• 2023

우리나라에서 개발 중인 저궤도 위성은 아리랑 위성으로, 이제까지 꾸준한 성능향상이 있었다. 이때 탑재체의 성능향상에 따른 탑재체의 전력요구도는 늘어나게 되었고 이에 위성 내부 전력 공급장치의 설계 및 Solar Array의 구성 등 위성 설계가 달라진다. 이에 따라 위성에 전력을 공급하며 위성 통합시험을 진행하는 전력계 전기지상지원장비 설계 시 전력 증가에 따라 많은 고려사항이 필요로 한다. 본 논문은 탑재체에 따른 위성 전력요구도의 변화 및 전력요구도 증가에 따른 전력계 전기지상지원장비 설계 시 고려할 사항에 대해서 다룬다.

• Journal of Power Electronics
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• 제16권2호
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• pp.666-674
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• 2016

In this paper, a high efficiency satellite electrical power supply system is proposed. The increased efficiency of the power supply system allows for downscaling of the solar array and battery weight, which are among the most important satellite design considerations. The satellite power supply system comprises two units, namely a generation unit and a storage unit. To increase the efficiency of the solar array, a maximum power point tracker (MPPT) is used in the power generation unit. In order to improve the MPPT performance, a novel algorithm is proposed on the basis of the hill climbing method. This method can track the main peak of the array power curve in satellites with long duration missions under unpredicted circumstances such as a part of the array being damaged or the presence of a shadow. A lithium-ion battery is utilized in the storage unit. An algorithm for calculating the optimal rate of battery charging is proposed where the battery is charged with the maximum possible efficiency considering the situation of the satellite. The proposed system is designed and manufactured. In addition, it is compared to the conventional power supply systems in similar satellites. Results show a 12% increase in the overall efficiency of the power supply system when compared to the conventional method.

• 대한전자공학회:학술대회논문집
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• 대한전자공학회 2006년도 하계종합학술대회
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• pp.897-898
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• 2006

This paper proposes a new power-stage circuit that can be available for modularization of the power regulator which is used at the software-controlled unregulated bus system. And we analyze the proposed power-stage operation according to its operating modes and verify it by performing software simulation and hardware experiment using prototype. By constructing a parallel-module converter which is composed of proposed power-stages, we verify the operations and usefulness of the proposed power-stage.

• Journal of Astronomy and Space Sciences
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• 제28권2호
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• pp.133-141
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• 2011

A satellite power system should generate and supply sufficient electric power to perform the satellite mission successfully during the satellite mission period, and it should be developed to be strong to the failure caused by the severe space environment. A satellite power system must have a high reliability with respect to failure. Since it cannot be repaired after launching, different from a ground system, the failures that may happen in space as well as the effect of the failures on the system should be considered in advance. However, it is difficult to use all the hardware to test the performance of the satellite power system to be developed in order to consider the failure mechanism of the electrical power system. Therefore, it is necessary to develop an accurate model for the main components of a power system and, based on that, to develop an accurate model for the entire power system. Through the power system modeling, the overall effect of failure on the main components of the power system can be considered and the protective design can be devised against the failure. In this study, to analyze the failure mode of the power system and the effects of the failure on the power system, we carried out modeling of the main power system components including the solar array regulator, and constituted the entire power system based on the modeling. Additionally, we investigated the effects of representative failures in the solar array regulator on the power system using the power system model.