• 한국항공우주학회지
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• 제44권2호
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• pp.165-171
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• 2016

정지궤도복합위성은 추력기 분사를 이용하여 자세제어, 궤도 유지, 휠 오프로딩 등을 수행한다. 장착된 추력기 중 1, 2, 3번 추력기는 태양전지판과 같은 축에 장착된다. 이로 인하여 추력기 1, 2, 3번은 플룸 외란의 영향이 크게 발생한다. 그러므로 위성 설계 단계에서 부터 플룸 외란의 영향을 분석해야 한다. 본 논문에서는 정지궤도복합위성의 초기 형상을 이용하여 추력기에서 발생하는 플룸 외란을 계산하는 과정을 기술하고 추력기 조정각에 따른 플룸 외란의 영향을 분석하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2009년 춘계학술대회논문집
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• pp.142-147
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• 2009

COMS (Communication, Ocean and Meteorological Satellite) is a geostationary satellite and has been developing by KARI for communication, ocean and meteorological observations. It will be tested under vacuum condition and very low temperature in order to verify thermal design of COMS. The test will be performed by using KARI large thermal vacuum chamber, which was developed by KARI, and the COMS will be the first flight satellite tested in this chamber. The purposes of thermal balance test are to correlate analytical model used for design evaluation and predicting temperatures, and to verify and adjust thermal control concept. KARI has plan to use heating plates to simulate space hot condition especially for radiator panels such as north and south panels. They will be controlled from 90K to 273K by circulating GN2 and LN2 alternatively according to the test phases, while the shroud of the vacuum chamber will be under constant temperature, 90K, during all thermal balance test. This paper presents thermal modelling including test chamber, heating plates and the satellite without solar array wing and Ka-band reflectors and discusses temperature prediction during thermal balance test.

• 한국항공우주학회지
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• 제34권11호
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• pp.54-60
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• 2006

본 논문에서는 광학 탑재체를 장착하기 위해 단일 태양전지판으로 구성된 통신해양기상위성(COMS)에 대한 휠오프로딩의 접근 방법에 대하여 다루었다. 먼저 연료 소모량을 줄이고 실제적 구현 측면을 고려하기 위해 COMS의 형상을 바탕으로 수치계산을 수행하였고 이를 바탕으로 휠오프로딩에 사용되는 추력기 조합을 제안하였다. 본 논문에서는 매일 두 번에 걸쳐 휠오프로딩을 수행하는 것으로 가정하였다. 또한 제안된 추력기 조합의 효율성을 검증하기 위하여 궤도 시뮬레이션을 수행하였으며 몇 가지 접근 방법의 결과와 비교하였다.

• Journal of Power Electronics
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• 제8권3호
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• pp.217-227
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• 2008

The electric power subsystems (EPS) of most remote sensing satellites consist of a solar array as a source of energy, a storage battery, a power management and control (PMC) unit and a charge equalization unit (CEU) for the storage battery. The PMC and CEU use high frequency transformers in their power modules. This paper presents a design, implementation and testing results of a high frequency transformer for the EPS of satellite applications. Two approaches are used in the design process of the transformer based on the pre-determined transformer specifications. The transformer is designed based on an ETD 29 ferrite core. The implemented transformer consists of one center-tapped primary coil with eleven center-tapped secondary coils. The offline calculation results and measured values of R, L for transformer coils are convergence. A test circuit for measuring the transformer parameters like voltage, current and B-H hysteresis was implemented and applied. The test results confirm that the voltage waveforms of both primary and secondary coils were as desired. No overlapping occurred between the control signal and the transformer, which was not saturated during testing even during a short circuit test of the secondary channels. The dynamic B-H loop characteristics of the used transformer cores were measured. The sample test results are given in this paper.

• 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.

• 조명전기설비학회논문지
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• 제21권9호
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• pp.64-75
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• 2007

Photovoltaic systems utilize the infinite clean energy of the sun, without creating any air pollution or noise and mechanical vibration. A PV system operates without the need of fuel, rotation surfaces, high temperatures or high pressures. It is therefore to do maintain and simple to install as well as having a long life cycle. The global market for PV systems continues to grow rapidly by 30[%] per year. This paper suggests a new design method for the PV system installation that will allow to the improvement of system efficiency. This method is in accordance with the loss parameter compensation method designed for the PV systems and investigated through simulation and practical experimentation. It was applied to an interconnected 10[kW] grid PV system and was demonstrated in the field. Features such as solar array, PCS, system efficiency, performance and stability were considered. Through the proposed optimal parameter design method, the features of the system were studied, and the 10[kW] PV system was demonstrated and analyzed.

• Journal of Electrical Engineering and Technology
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• 제10권4호
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• pp.1389-1399
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• 2015

This research suggests maximum power point tracking (MPPT) for the solar photovoltaic (PV) power scheme using a new constant voltage (CV) fractional order incremental conductance (FOINC) algorithm. The PV panel has low transformation efficiency and power output of PV panel depends on the change in weather conditions. Possible extracting power can be raised to a battery load utilizing a MPPT algorithm. Among all the MPPT strategies, the incremental conductance (INC) algorithm is mostly employed due to easy implementation, less fluctuations and faster tracking, which is not only has the merits of INC, fractional order can deliver a dynamic mathematical modelling to define non-linear physiognomies. CV-FOINC variation as dynamic variable is exploited to regulate the PV power toward the peak operating point. For a lesser scale photovoltaic conversion scheme, the suggested technique is validated by simulation with dissimilar operating conditions. Contributions are made in numerous aspects of the entire system, including new control algorithm design, system simulation, converter design, programming into simulation environment and experimental setup. The results confirm that the small tracking period and practicality in tracking of photovoltaic array.

• 전기학회논문지
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• 제57권10호
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• pp.1796-1801
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• 2008

In this paper, a new current based maximum power point tracking (CMPPT) method is proposed for a single phase photovoltaic power conditioning system and the current based MPPT modifies incremental conductance method. The current based MPPT method makes the entire control structure of the power conditioning system simple and uses an inherent current source characteristic of solar cell array. In addition, digital phase locked loop using an all pass filter is introduced to detect phase of grid voltage as well as peak voltage. Controllers about dc/dc boost converter, dc-link voltage, dc/ac inverter is designed for a coordinated operation. Furthermore, PI current control using a pseudo synchronous d-q transformation is employed for grid current control with unity power factor. 3kW prototype photovoltaic power conditioning system is built and its experimental results are given to verify the effectiveness of the proposed control schemes.

• 한국분말재료학회지
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• 제18권1호
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• pp.56-63
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• 2011

Recently, $TiO_2$ nanotubes have considerably researched because of their novel application about photocatalysis, dye-sensitized solar cells (DSSCs), lithium ion battery, etc. In this work, self-standing $TiO_2$ nanotube arrays were fabricated by anodic oxidation method using pure Ti foil as a working electrode in ethylene glycole with 0.3M $NH_4F$ + $2%H_2O$. Growth behavior of $TiO_2$ nanotube arrays was compared according to temperature, voltage and time. The morphology, structure and crystalline of anodized $TiO_2$ nanotube arrays were observed by FE-SEM (field emission scanning electron microscope) and XRD (X-ray diffraction).

• 한국산업정보학회논문지
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• 제19권1호
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• pp.31-41
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• 2014

정지궤도위성은 다수의 탑재체를 하나의 위성체 플랫폼에 탑재하고 2010년 6월 26일에 발사되었다. 전력계는 태양 및 식 기간 상태에서 완전 조절 $50V_{DC}$ 전력 버스를 제공한다. 위성에서 요구되는 전력은 태양전지 배열기 윙에서 생성되며, 에너지는 192.5Ah 용량의 리튬-이온 배터리에 저장된다. 본 논문은 전력계의 성능 평가를 향후 정지궤도위성 설계에 활용하기 위해 전력계의 중요 설계 변수들을 선정하고, 지상에서 시험 결과와 궤도상에서 운영 결과를 비교 분석하였다. 설계로부터 궤도상에서 운영 결과까지의 성능 평가를 통해 전력계는 중요한 성능감소 없이 정상적으로 동작되고 있음을 입증하였다.