• Journal of the Korean Society for Aeronautical & Space Sciences
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• 제31권1호
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• pp.67-72
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• 2003

In this paper, solar cell array of KOMPSAT 1 was modeled and analyzed. The modeling results of solar array were achieved by neural algorithm, which is a powerful nonlinear system modeling tool. Using solar cell array modeling, the solar cell array was analyzed and verified by simulation considering solar cell data of KOMPSAT 1. The characteristics curves and power generation of the solar array are analyzed by using the modeling.

• Journal of the Korean Solar Energy Society
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• 제37권5호
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• pp.49-63
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• 2017

Solar cells have widely been utilized for a satellite to convert sunlight energy into electricity in space. Many different types of solar cells appropriate for each satellite program are available in current markets, which enables us to construct a solar array light and small often required from a low Earth orbit (LEO) synthetic aperture radar (SAR) satellite. Thus, it is important to choose a proper solar cell satisfying the requirements of mass and size for the solar array. In this article, we have surveyed typical suppliers and have discussed some characteristics of solar cells. Conceptual design examples of the solar array for LEO SAR satellites using several types of solar cells have been performed to show the pros and cons of solar cells by comparison of the total mass and size necessary for the solar array.

• Solar Energy
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• 제19권4호
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• pp.63-69
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• 1999

The conventional grid connected PV(Photovoltaic) system has a unstable output pattern due to its dependence on the weather condition, although solar-cell array averagely has a regular output characteristics to have a peak output nearly at noon. Therefore assuming the high density grid connection in the future, this unstable output pattern can be one of the main reasons to generate power disturbance such as voltage variation, frequency variation and harmonic voltage generation in low voltage distribution line. However general grid connected solar-cell system do not have functions to cope with these disturbances. Therefore this study proposed a advanced type grid connected PV system with functions to suppress output power fluctuation due to solar-cell array output variation and showed the levelling effect of fluctuation due to instantaneous array output variation.

• Journal of Astronomy and Space Sciences
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• 제36권2호
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• pp.69-74
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• 2019

Spacecraft requires sufficient power in orbit to perform its mission. So as to comply with system requirements, the sufficient power should be made by a solar cell array by photovoltaic power conversion. A life time of space program depends on its mission considering parts reliability and parts grade. Based on the mission life time, power equipment might be designed to meet specifications. In outer space, solar cell array might generate the dc power by photovoltaic conversion effects and GaInP/GaAs/Ge solar cells are used in this study. Space programs that require more than five years should select parts for high reliability applications. Therefore, reliability analysis for high reliability applications should be performed to check its fulfilment of the requirements. This program should also require more five years for its mission and we performed its analysis using parts count method (PCM) for its reliability. Finally, we performed reliability analysis and obtained quantitative figures found out 99.9%. In this study, we presented the reliability analysis of the 300 W GaInP/GaAs/Ge solar cell array.

• Journal of Astronomy and Space Sciences
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• 제36권3호
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• pp.181-186
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• 2019

The attitude information of spacecraft can be obtained by the sensors attached to it using a star tracker, three-axis magnetometer, three-axis gyroscope, and a global positioning signal receiver. By using these sensors, the spacecraft can be maneuvered by actuators that generate torques. In particular, electromagnetic-torque bars can be used for attitude control and as a momentum-canceling instrument. The spacecraft momentum can be created by the current through the electrical circuits and coils. Thus, the current around the electromagnetic-torque bars is a critical factor for precisely controlling the spacecraft. In connection with these concerns, a solar-cell array can be considered to prevent generation of a magnetic dipole moment because the solar-cell array can introduce a large amount of current through the electrical wires. The maximum value of a magnetic dipole moment that cannot affect precise control is $0.25A{\cdot}m^2$, which takes into account the current that flows through the reaction-wheel assembly and the magnetic-torque current. In this study, we designed a 300-W solar cell array and presented an optimal wire-routing method to minimize the magnetic dipole moment for space applications. We verified our proposed method by simulation.

• Proceedings of the KIPE Conference
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• 전력전자학회 1998년도 전력전자학술대회 논문집
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• pp.138-142
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• 1998

This paper has been analyzed, modeled, designed, fabricated, and tested for solar cell simulator which has solar array characteristics. The main purpose is the development of solar cell simulator to test electrical power subsystem for GEO Communication Spacecraft. The maximum power of the simulator is about 5 ㎾, which is consist of 12 independent simulator modules with 420 W power rating. The 12 simulator modules are independently controlled like as real solar array system.

• Journal of Power Electronics
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• 제17권2호
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• pp.514-521
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• 2017

This paper proposes a shadowing compensation method for the solar modules of grid-connected photovoltaic generation systems. The shadowing compensator (SC) implemented by the proposed shadowing compensation method is used only for the solar modules that can be shaded by predictable sources of shading. The proposed SC can simplify both the power circuit and the control circuit as well as improve power efficiency and utilizes a voltage equalizer configured by a modified multi-winding fly-back converter. The proposed SC harvests energy from the entire solar cell array to compensate for the shaded sub-modules of the solar cell array, producing near-identical voltages of all shaded and un-shaded sub-modules in the solar cell array. This setup prevents the formation of multiple peaks in the P-V curve under shaded conditions. Hardware prototypes are developed for the SCs implemented by the conventional and modified multi-winding fly-back converters, and their performance is verified through testing. The experimental results show that both SCs can overcome the multiple peaks in the P-V curve. The proposed SC is superior to the SC implemented by the conventional multi-winding fly-back converter.

• Proceedings of the KIEE Conference
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• 대한전기학회 1999년도 하계학술대회 논문집 F
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• pp.2565-2567
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• 1999

The output characteristics of solar cell vary with load and solar insolation. Therefore solar cell must always track maximum power point. If photovoltaic system is stand-alone. It is necessary to maintain for output of voltage source inverter. In this paper, stand-alone photovoltaic system consists of boost chopper and voltage source inverter. We make it to track maximum power point by revolution of solar cell array instead of detecting situation of sun in any conditions. And we prove that maximum power point tracking by revolution of solar cell array is better than fixed solar cell.

• Proceedings of the KIPE Conference
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• 전력전자학회 1997년도 전력전자학술대회 논문집
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• pp.365-369
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• 1997

In this paper, solar array of KOMPSAT was modeled and analyzed. The modeling results of solar array was achieved by neural algorithm, which is powerful of nonlinear system with a few data sets. The algorithm was analyzed and verified by simulation considering on solar cell data of KOMPSAT. The characteristics VI curves and power generation of solar array are analyzed by using the modeling.

• Proceedings of the KIPE Conference
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• 전력전자학회 1998년도 Proceedings ICPE 98 1998 International Conference on Power Electronics
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• pp.972-977
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• 1998

This paper deals with stand-alone Photovoltaic system(SPVS) with charge and discharge controller. Main power source of SPVS are generally solar cell and battery. Therefore SPVS can be classified into variable types in accordance with connection method between battery and solar cell array. Mainly used one of them is direct connection type which has advantages such as simple structure and simple controller. However most big drawback of this system is energy loss by voltage disharmony between solar cell array and battery. Therefore SPVS with charge and discharge controller which can operate solar cell array at maximum power point is designed and experimented with a laboratory prototype.