• Proceedings of the Korean Institute of IIIuminating and Electrical Installation Engineers Conference
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• 2009.10a
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• pp.239-242
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• 2009

Power Control and Distribution Unit (PCDU) plays roles of power generation control for solar array panel, power storage control for battery system, power conversion for unregulated and regulated primary bus and power distribution to bus and payload system. The selection and design of the proper auxiliary power interface for PCDU depending on various mission is one of the most important step for electrical power subsystem design. In this paper, the general design approach of auxiliary power interface for PCDU which can be used for small-sized LEO satellites application is given. And, the auxiliary power design concept for always alived modules such as solar array regulator and house keeping module is also suggested.

• Proceedings of the KIPE Conference
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• 2002.07a
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• pp.681-684
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• 2002

In this paper, electrical power subsystem(EPS) simulator for KOMPSAT 2 has been analyzed designed and simulated by object oriented design(OOP) method. To design EPS simulator, the EPS modules, which modeled solar array, solar array regulator, deployment device controller, battery, power control unit, and EPS control unit, are modeled. To verify the EPS simulator, the modules has been simulated. By OOP designs, the EPS simulator is very powerful because this method is applicable to design other EPS simulator.

• Proceedings of the KIEE Conference
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• 1994.07a
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• pp.310-312
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• 1994

A partial shunt regulator (PSR) which is the power regulator of KOREASAT is modeled. The modeling of the PSR consist of solar array, power circuit, controller. and load models. To realize simple structure. a voltage source of the PSR controller is used the output voltage of the PSR. The model of the PSR has very complex structure with two additional coupled feedback loops. The complex model is simplified to a simple meaningful model with only main feedback control loop. The proposed model is compared to a PSR model with DC voltage source at the PSR controller. The proposed PSR model is verified by comparing the model with SPICE simulation for small signal analysis.

• Journal of the Korean Institute of Telematics and Electronics B
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• v.33B no.3
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• pp.193-201
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• 1996

The space power system for communication satellite which employs the direct energy transfer (DET) method consists of solar array, battry, shunt regulator, charger/discharger and power control unit (PCU). In this paper, the development of the DET power system charger/discharger unit and a microprocessor based PCU is developed for simplicity and flexiblity in the modificatin of control algorithm. A 28V bus voltage, 400W power rting power simulator is built and tested to verify the operation of the simulator at each mode and the stability of mode transition is analyzed.

• Proceedings of the KIEE Conference
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• 2005.07b
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• pp.1368-1370
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• 2005

Satellite is operated only with internal battery when separated from rocket. Internal battery is charged only from SAR(solar Array Regulator), solar cell. So battery will be exhausted and purpose of satellite will be failed if load module is out of order or short. This paper proposed real time current limiter which operated by telemetry of outer processor. This current limiter operates by control signal simultaneously cuts off over current by self over current sensing circuit. So it can reduce waste of battery energy and over load of outer processor.

• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.11-19
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• 2004

A software-controlled unregulated bus system in which the main bus is directly connected to a battery and the duty-ratio for PWM switch is controlled by the on-board satellite software, is usually used for LEO satellites. This paper proposes a new power-stage circuit that can be available for modularization of a power regulator which is used at the software-controlled unregulated bus system satellite. 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. We construct a parallel-module converter which is composed of the proposed power-stage and perform experiment to verify modular characteristics of the proposed power-stage. Finally, we verify the usefulness of the proposed power-stage by comparing above results with those of a parallel-module converter made of conventional power-stage.

• Proceedings of the Korean Institute of IIIuminating and Electrical Installation Engineers Conference
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• 2004.05a
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• pp.442-446
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• 2004

KOMPSAT series use software-controlled unregulated bus system in which the main bus is directly connected to a battery and the duty-ratio for PWM switch is controlled by the on-board satellite software. 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 satellite. 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. We constructs a parallel-module converter which is composed of proposed power-stages and perform experiment to verify modular characteristics of the proposed power-stage. Finally, we verify the usefulness of the proposed power-stage by comparing above results with those of a parallel-module converter made of conventional power-stages.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.4
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• pp.89-101
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• 2006

This paper addresses Electrical Power Subsystem(EPS) design and verification of HAUSAT-2 small satellite through energy balance analysis(EBA) depending on individual operation modes. GaAs solar cells are used for satellite power generation and digital peak power tracking is implemented for EPS architecture. One battery pack is consisted of 4 Li-Ion cells. Battery charge is accomplished by peak power tracker and battery charge regulator. Power conditioning assembly uses three DC-DC converters, and power distribution assembly which consists of commercial IC and MOSFET switch distributes power to subsystems and payloads. The altitude of 650km and sun-synchronous LEO with various local time ascending node(LTAN) are considered in EBA.

• Proceedings of the KIPE Conference
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• 2003.07a
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• pp.93-96
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• 2003

Korea Multi-Purpose SATellite (KOMPSAT) uses software-controlled unregulated bus system In which the main bus is directly connected to a battery and the duty-ratio for PWM switch is generated by the on-board satellite software algorithm. In this paper, we propose a new power-stage circuit that can be available for modularization of a solar array regulator(SAR) which is used in the KOMPSAT. The operations at each mode and current sharing characteristics of the power-stage are analyzed and verified by simulation and experiments on a prototype converter.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2000.06a
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• pp.1246-1251
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• 2000

High level random vibration environments induced while launching of spacecraft can damage sensitive electronic equipment very rapidly, unless the equipment is properly packaged. Thus very careful consideration on the launch environment, especially for high level random vibration, is required in the design stage of electronic equipment of spacecraft. This paper describes the development process of Solar Array Regulator for KOMPAT-2, which is designed and tested by Korean engineers. Both analytical and experimental techniques are introduced in this paper.