• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.9
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• pp.843-849
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• 2007

Recent progress on software engineering especially in object-oriented design concepts has enabled the development of the simulation models of satellite components in view of reliability and reusability. This paper proposes an useful satellite simulator framework using simulation service and generalized model design. The proposed method is verified by a prototyping in .NET/C# environment.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.1
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• pp.103-109
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• 2006

In this paper, VDS(Vehicle Dynamics Simulator) and ACS(Attitude Control Simulator) are developed and are verified using PILS(Process In-the Loop Simulation) between VDS and ACS. VDS is including the AOCS(Attitude & Orbit Control Subsystem) hardware modeling of geosynchronous satellite and consists of modulation concept. ACS performs the attitude determination using sensor data and generates the attitude control commands. In order to transfer the data between VDS and PCDU(Power Control & Distribution Unit), data acquisition boards were mounted. VDS performance is verified using HILS(Hardware In-the Loop Simulation) between VDS and PCDU.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.176-184
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• 2010

The power simulator for a LEO satellite is a useful tool to analyze mission validity and energy balance for various mission scenarios by estimating power generation, power consumption, depth of discharge, bus voltage, charging/discharging current, etc. In this paper, it is described the calculation algorithm of the solar array (SA) power, the satellite load power and the battery modeling method to develop a satellite power simulation. To simulate the SA power generation, three different operation modes (DET, MPPT, CV) of SAR (Solar Array Regulator) are considered with a SA model. The satellite load power is estimated using the satellite unit power database, the unit on/off configuration at some satellite operation modes. The bus voltage and battery charging/discharging current at the specific DoD (Depth of Discharge) are calculated based on the battery characteristics. By this satellite power simulator, it can be conveniently analyzed the energy balance and the validity of a planned mission of a LEO satellite.

• Journal of Satellite, Information and Communications
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• v.1 no.1
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• pp.20-25
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• 2006

The link of Geostationary Communication Satellite has transit delay and noise environments by physical distance. This situation exerts an influence on the degradation of baseband performance of Earth Station. Therefore, it is very important that degradation of baseband performance is grasped previously. This paper is presented that developed the simulator which can evaluate the baseband performance of earth station of a military satellite communication system during the current development. The simulator can mock delay on a satellite channel and bit errors without being used actual satellite links.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• v.9 no.1
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• pp.225-228
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• 2005

본 논문에서는 한정된 위성 전파자원의 활용 및 지상망과의 주파수 공유를 위한 방안으로써, 위성망과 지상망간의 간섭 영향을 분석하고, 신규 지상망 배치시 위성망과의 주파수 공유가 가능한 허용 간섭량 및 위성으로부터의 PFD, 그리고 간섭량 입력에 의한 조정거리를 산출해내는 위성망과 지상망간 간섭분석 시뮬레이터를 구현하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.11
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• pp.1148-1156
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• 2009

ETRI has developed GNSS digitized IF signal generator for providing test and evaluation environment for various software level application and navigation algorithm in Global Navigation Satellite System(GNSS). GNSS digitized IF signal generator provides two main capabilities, GPS and Galileo raw data generation and digitized IF signal generation. GNSS digitized IF signal generator consists of five main modules which are GNSS Satellite Orbit Simulation Module, Navigation Message Generation Module, Error Generation Module, GNSS IF Signal Generation Module, and Message & Signal Steering Module. We verified the signal generated by the GNSS signal generation algorithm using software receiver for generation of signal brother to real GNSS signal.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.194.1-194.1
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• 2012

우주비행체의 내부 장치 고장 혹은 외부 환경에 의한 고장이 발생할 경우를 대비하여 가상 모의 시뮬레이터를 이용한 고장 대응 훈련이 요구된다. 시뮬레이터 개발 초기에 이러한 고장 발생 메커니즘을 설계에 반영하지 않는 경우 교관이 작성한 고장 시나리오에 의한 유기적 고장 발생 및 고장 전파 기능을 납품 후 추가 요구하기는 용이하지 않다. 본 논문에서는 사용자가 시뮬레이터를 이용하여 의도하는 고장을 의미있는 시각(Epoch)에 주입하기 위한 고장 발생 메커니즘 구조를 설명한다. 또한 천리안위성 시뮬레이터 소프트웨어의 고장 발생 예제를 통해 고장 감지, 고장 복구, 관제원의 대응 방법 등을 설명한다.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.132-140
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• 2002

By utilizing OSMI (Ocean Scanning Multi-spectral Imager) onboard KOMPSAT-1, the moon can be imaged. Because the moon has no atmosphere and reflects sun lights at a constant rate, it can be the radiance source for calibration of OSMI. But there are a lot of risks which made KOMPSAT-1 enter into safe-hold mode. So planning the imaging of the moon with OSMI should be determined seriously with consideration to information on KOMPSAT-1 operation, the moon, the sun, etc. But it takes a long time for determining the imaging time of the moon using MCE(Mission Control Element) simulator and there are operational problems to be solved. In this paper, fast simulator for determining imaging time for the moon with OSMI has been developed. The proper timeline for imaging the moon and the position of the moon image in OSMI image coordinates and the phase of the moon are determined. STK was used for acquiring information on KOMPSAT-1, the moon, the sun and the characteristitcs of OSMI are considered. As a result, we can determine imaging time of the moon with OSMI much faster and efficiently.

• Journal of the Institute of Convergence Signal Processing
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• v.12 no.4
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• pp.286-290
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• 2011

LBS(Location Based System) is the essential technology of ubiquitous market and utilizes the GNSS(Global Navigation Satellite). GNSS includes GPS of USA, Galileo of Europe Union, QZSS of Japan, Compass of China, and IRNSS of India. Related researches have recently been conducted. Once the satellite is launched, the maintenance such as modification and verification of its function is difficult. Therefore, before the launch of satellites, more precise and concrete verification of performance and operations are needed. In order to do this, hardware testbed may be developed. but software simulators can provide more flexible and cost effective simulation results. These simulators should provide the essential function handling all kinds of error features experienced upon propagation of the GNSS signal. In this paper, we present a design and implementation results of a window-based simulator applying the modeling of various error features for several GNSS.

• Journal of the Korea Computer Industry Society
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• v.2 no.2
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• pp.131-140
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• 2001

In this paper file transfer efficiencies of satellite and terrestrial links are analyzed, and a simulator that satellite links are supplementarily expanded to SARA(System ARchitect’ Apprentice) model, a terrestrial model of CSDN interface, is constructed. And in satellite transmission an interpretative method and a simulator of file transfer are proposed to evaluate the efficiency of file transfer. The parameters used are the message length and transmission time, and the optimum message length by transmission speed of satellite links. From the results of evaluation, in satellite transfer, it is found that when the length of message is shorter than 512 byte, the file transfer time becomes extremely long and when the length of message is set at 1,024 byte the file transfer time becomes minimum, and if the length of message is set more longer, the file transfer time abruptly increases from 2,048 byte. Therefore, from the results of file transfer simulation in the case of utilizing satellite transmission, it is found that the optimum massage length in the minimum transfer time is present closely at 1,024 byte.