• 한국위성정보통신학회논문지
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• 제6권2호
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• pp.66-71
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• 2011

본 논문에서는 통합이동위성시스템에서 계층적 부호화 방식의 성능과 효용성에 대한 평가 결과를 제시한다. 통합이동위성시스템의 주요 서비스는 멀티미디어 방송 및 멀티캐스팅 서비스가 될 것이다. 통합이동위성시스템에서, 위성과 보조지상장치는 고품질의 서비스를 제공하기 위하여 서로 협력적으로 동작하도록 되어 있다. 계층적 부호화 방식은 수신기에서 채널의 샅애에 적응할 수 있도록 하는 일종의 수신기에 의해 주도되는 적응형 방식이다. 본 논문에서는 터보부호화 방식을 이용한 계층적 부호화 방식을 소개하고 여러 가지 시나리오에서의 성능을 평가하며, 그 효용성에 대하여 논할 것이다. 본 논문에서 제시된 성능 평가 결과 및 분석 내용은 향후 효율적인 통합이동위성시스템을 설계하는데 활용될 수 있을 것이다.

• 한국정보통신학회:학술대회논문집
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• 한국해양정보통신학회 2001년도 춘계종합학술대회
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• pp.345-348
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• 2001

본 논문은 디지털 비디오 방송 컴플라이언트 위성 수신칩에 대한 physical 설계 순서 및 검증에 대한 설계 기술에 관한 것으로서 각각의 설계 순서에 대한 고찰 및 문제점 그리고 물리적 레이아웃에 대한 검증 과정과 그 결과에 대하여 기술하였다.

• International journal of advanced smart convergence
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• 제11권4호
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• pp.41-46
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• 2022

This study is a Ku-band array antenna for the manufacture of low-orbit satellite communication terminals, designed to have miniaturization, high gain, and wide beam width. The transmission of low-orbit satellite communication has a right-rotating circularly polarized wave, and the reception has a left-rotating circularly polarized wave. The 4×8 array antenna was separated for transmission and reception, and it was combined with the RF circuit part of the transmitter and receiver, and was terminated in the form of a waveguide for RF signal impedance matching in the form of a transition from the microstrip line to the waveguide. The 30° beam width of the receiver maximum gain of 19 dBi and the 29° beam width of the transmitter maximum gain of 18 dBi are shown. Through this antenna configuration, the system was configured to suit the low-orbit satellite transmission/reception characteristics.

• Journal of Astronomy and Space Sciences
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• 제28권1호
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• pp.55-62
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• 2011

The precise orbit determination (POD) of low earth orbiter (LEO) has complied with its required positioning accuracy by the double-differencing of observations between International GNSS Service (IGS) and LEO to eliminate the common clock error of the global positioning system (GPS) satellites and receiver. Using this method, we also have achieved the 1 m positioning accuracy of Korea Multi-Purpose Satellite (KOMPSAT)-2. However double-differencing POD has huge load of processing the global network of lots of ground stations because LEO turns around the Earth with rapid velocity. And both the centimeter accuracy and the near real time (NRT) processing have been needed in the LEO POD applications--atmospheric sounding or urgent image processing--as well as the surveying. An alternative to differential GPS for high accuracy NRT POD is precise point positioning (PPP) to use measurements from one satellite receiver only, to replace the broadcast navigation message with precise post processed values from IGS, and to have phase measurements of dual frequency GPS receiver. PPP can obtain positioning accuracy comparable to that of differential positioning. KOMPSAT-5 has a precise dual frequency GPS flight receiver (integrated GPS and occultation receiver, IGOR) to satisfy the accuracy requirements of 20 cm positioning accuracy for highly precise synthetic aperture radar image processing and to collect GPS radio occultation measurements for atmospheric sounding. In this paper we obtained about 3-5 cm positioning accuracies using the real GPS data of the Gravity Recover and Climate Experiment (GRACE) satellites loaded the Blackjack receiver, a predecessor of IGOR. And it is important to reduce the latency of orbit determination processing in the NRT POD. This latency is determined as the volume of GPS measurements. Thus changing the sampling intervals, we show their latency to able to reduce without the precision degradation as the assessment of their precision.

• 한국위성정보통신학회논문지
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• 제4권2호
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• pp.20-27
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• 2009

본 논문에서는 성층권 통신시스템과 위성 시스템간의 주파수 공유를 위한 HAPS 운용 시나리오를 제안한다. 지금까지 간섭 분석을 위해 고려된 시나리오는 모든 HUT가 활성화된 상태를 가정한 것이다. 그러나 가입자의 활성화 상태에 따라서 통신 링크를 형성하는 실제적인 운용 시나리오를 고려할 경우 타 망으로의 간섭 신호를 원래보다 더 경감시킬 수 있다. 유해한 간섭 영향을 줄이기 위하여 HAPS의 운용 측면을 고려한 HAPS 플랫폼의 시간분할 다중빔 운용 시나리오에 대해서 제안하고 운용률에 따른 간섭 영향을 평가한다.

• Journal of Astronomy and Space Sciences
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• 제37권2호
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• pp.117-129
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• 2020

In a Satellite communication system, a link budget analysis is the detailed investigation of signal gains and losses moving through a channel from a sender to receiver. It inspects the fading of passed on data signal waves due to the process of spreading or propagation, including transmitter and receiver antenna gains, feeder cables, and related losses. The extent of the proposed tool is to make an effective, efficient, and user-friendly approach to calculate link budget analysis. It is also related to the satellite communication correlation framework by building up a graphical interface link analysis tool utilizing STK^® software with the interface of C# programming. It provides better kinds of graphical display techniques, exporting and importing data files, printing link information, access data, azimuth-elevation-range (AER), and simulation is also possible at once. The components of the link budget analysis tool include transmitter gain, effective isotropic radiated power (EIRP), free space loss, propagation loss, frequency Doppler shift, flux density, link margin, elevation plot, etc. This tool can be useful for amateur users (e.g., CubeSat developers in the universities) or nanosat developers who may not know about the RF communication system of the satellite and the orbital mechanics (e.g., orbit propagators) principle used in the satellite link analysis.

• Journal of Positioning, Navigation, and Timing
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• 제4권4호
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• pp.173-180
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• 2015

In this study, an algorithm that detects a spoofing signal for a GPS L1 signal was proposed, and the performance was verified through RF spoofing signal simulation. The proposed algorithm determines the reception of a spoofing signal by detecting a correlation distortion of GPS L1 C/A code caused by the spoofing signal. To detect the correlation distortion, a detection criterion of a spoofing signal was derived from the relationship among the Early, Prompt, and Late tap correlation values of a receiver correlator; and a detection threshold was calculated from the false alarm probability of spoofing signal detection. In this study, an RF spoofing environment was built using the GSS 8000 simulator (Spirent). For the RF spoofing signal generated from the simulator, the RF spoofing environment was verified using the commercial receiver DL-V3 (Novatel Inc.). To verify the performance of the proposed algorithm, the RF signal was stored as IF band data using a USRP signal collector (NI) so that the data could be processed by a CNU software receiver (software defined radio). For the performance of the proposed algorithm, results were obtained using the correlation value of the software receiver, and the performance was verified through the detection of a spoofing signal and the detection time of a spoofing signal.

• Journal of Astronomy and Space Sciences
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• 제26권2호
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• pp.221-228
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• 2009

한반도 상공의 전리층 총전자수(TEC, Total Electron Content)를 추정하는 방법을 통해 GPS 수신기와 위성의 코드 바이어스(DCB, Differential Code Bias)를 함께 추정하였다. 한국천문연구원에서 운영하고 있는 GPS 기준국망 데이터를 사용하였으며, 가중치 최소자승법을 이용하여 매 1시간 간격으로 DCB를 산출하였다. 총 3일간의 데이터를 처리한 결과 9개 GPS 수신기의 DCB는 ${\pm}2m$ 이내에서 변화하는 것으로 나타났으며, 3일 동안 크게 변하지 않았다. 또한 일일 평균값으로 산출된 위성의 DCB는 최대 약 4.09ns(nano-second), 최소 약 -6.28ns를 갖는 것으로 나타났다. 그리고 산출된 DCB를 전리층 총전자수 산출에 적용한 결과, 적용 전에 비해 특정시점에서 최대 약 9TECU 이상의 총전자수 변화가 검출됨을 확인 할 수 있었다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1991년도 한국자동제어학술회의논문집(국제학술편); KOEX, Seoul; 22-24 Oct. 1991
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• pp.1649-1654
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• 1991

In 1995 the VSOP satellite, which is called MUSES-B in Japan, will be launched under the VLBI Space Observatory Programme(VSOP) promoted by ISAS(Institute of Space and Astronautical Science) of Japan. We are now developing the GPS Receiver(GPSR) and On-board Orbit Determination System. This paper describes the GPS(Global Positioning System), VSOP, GPSR(GPS Receiver system) configuration and the results of the GPS system analysis. The GPSR consists of three GPS antennas and 5 channel receiver package. In the receiver package, there are two 16 bits microprocessing units. The power consumption is 25 Watts in average and the weight is 8.5 kg. Three GPS antennas on board enable GPSR to receive GPS signals from any NAVSTARs(GPS satellites) which are visible. NAVSATR's visibility is described as follows. The VSOP satellite flies from 1, 000 km to 20, 000 km in height on the elliptical orbit around the earth. On the other hand, the orbit of NAVSTARs are nearly circular and about 20, 000 km in height. GPSR can't receive the GPS signals near the apogee, because NAVSTARs transmit the GPS signals through the NAVSTAR's narrow beam antennas directed toward the earth. However near the perigee, GPSR can receive from 12 to 15 GPS signals. More than 4 GPS signals can be received for 40 minutes, which are related to GDOP(Geometric Dillusion Of Precision of selected NAVSTARs). Because there are a lot of visible NAVSTARs, GDOP is small near the perigee. This is a favorqble condition for GPSR. Orbit determination system onboard VSOP satellite consists of a Kalman filter and a precise orbit propagator. Near the perigee, the Kalman filter can eliminate the orbit propagation error using the observed data by GPSR. Except a perigee, precise onboard orbit propagator propagates the orbit, taking into account accelerations such as gravities of the earth, the sun, the moon, and other acceleration caused by the solar pressure. But there remain some amount of calculation and integration errors. When VSOP satellite returns to the perigee, the Kalman filter eliminates the error of the orbit determined by the propagator. After the error is eliminated, VSOP satellite flies out towards an apogee again. The analysis of the orbit determination is performed by the covariance analysis method. Number of the states of the onboard filter is 8. As for a true model, we assume that it is based on the actual error dynamics that include the Selective Availability of GPS called 'SA', having 17 states. Analytical results for position and velocity are tabulated and illustrated, in the sequel. These show that the position and the velocity error are about 40 m and 0.008 m/sec at the perigee, and are about 110 m and 0.012 m/sec at the apogee, respectively.

• 한국위성정보통신학회논문지
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• 제2권2호
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• pp.64-68
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• 2007

본 논문에서는 기존의 GPS 항법 신호와 유럽에서 새롭게 추진되고 있는 갈릴레오 위성 항법 신호를 동시에 수신할 수 있는 광대역 고정밀 위성 항법 수신기의 RF 수신단 장치 설계 및 제작 결과에 대하여 기술하고 있다. 고정밀 광대역 위성 항법 수신기는 L - 대역 안테나, 항법 신호별 RF/IF 변환부, 그리고 고성능 기저대역 신호 처리부로 구성되어진다. L - 대역 안테나는 $1.1GHz{\sim}1.6\;GHz$를 수신할 수 있어야 하며, 항법 위성이 지평선 가까이에 있을 경우의 항법 신호를 수신할 수 있어야 한다. 갈릴레오 위성 항법 신호는 L1, E5, E6의 서로 다른 대역의 신호를 가지고 있으며, 신호 대역폭이 20MHz 이상으로 기존의 GPS위성 항법 신호보다 광대역이며, 따라서 수신기의 IF 주파수가 높아지며, 수신기의 처리 속도도 빨라져야 한다. 본 연구에서 개발한 수신기의 RF/IF 변환부는 단일 하향 변환기 구조의 디지털 IF 기술로 설계되었으며, IF 주파수는 위성 항법 신호의 최대 대역폭과 표본화 주파수 등을 고려하여 140MHz로 설정하였으며, 표본화 주파수는 112MHz로 설정하였다. RF/IF 변환부의 최종 출력은 디지털 IF 신호로서, IF 신호를 AD 변환기로 처리하여 얻게 된다. 본 연구에서 설계된 위성 항법용 고정밀 수신기 RF 수신단은 - 130 dBm의 입력 신호에 대하여 40dB Hz 이상의 C/N0 특성을 가지며, 40dB 이상의 동적 범위를 갖도록 자동 이득조절 장치가 포함되어 있다.