• Electronics and Telecommunications Trends
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• v.23 no.4
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• pp.137-146
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• 2008

위성항법수신기는 항법위성(GPS)들이 현재 위치와 시간이 담긴 전파신호를 지상으로 송신하면, 이런 신호를 받아 전파가 도달하기까지 걸린 시간을 계산해 자신의 현재 위치를 파악하게 된다. 경도와 위도, 높이를 동시에 파악하기 위해서는 3개 위성신호가 요구되고, 위성간 시간 오차를 제거해 위치 측정의 정확도를 높이기 위한 신호용으로 또 하나의 위성이 필요해 4개 위성이 요구된다. 항법의 형태는 육표기반 항법, 천체기반 항법, 센서기반 항법, 무선기반 항법 및 위성기반 항법으로 분류되며 그 중 전역이고 간섭 영향 및 재밍(jamming)이 어려우며 정확도 측면에서 우수한 위성항법시스템에는 GPS(미국), GLONASS(러시아)가 운용중이고, Galileo(유럽연합), COMPASS(중국), QZSS(일본), IRNSS(인도)이 개발중이다. 위성항법시스템 다원화에 따라 위성항법 수신기 기술도 이중주파수처리 및 타 시스템과의 호환성 제공이 요구되는바, 본 논문에서는 위성항법 수신기 기술 동향을 소개하고자 한다.

• Journal of Satellite, Information and Communications
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• v.4 no.1
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• pp.36-44
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• 2009

The key technologies of GNSS receiver for GNSS sensor station are under development as a part of a GNSS ground station in ETRI. This paper presents the GNSS receiver implementation and signal processing result which is implemented based on FPGA to process the Galileo E1 and E5 signal. To verify the working and performance for GNSS receiver which is implemented based on FPGA, live signal received from GIOVE-B which is second test satellite is used. We gather GIOVE-B signal by using prototyping antenna and RF/IF units including IF-component. To verify Galileo E1 and E5 signal processing function from GIOVE-B, FPGA based signal processing module is implemented as a prototyping hardware board.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.2
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• pp.48-55
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• 2006

Performance characteristics of the position-domain Hatch filter is analyzed for differential global navigation satellite systems. It is shown that the position-domain Hatch filter generates white measurement residual sequences, which is beneficial property for fault detection. It is also shown that the position-domain Hatch filter yields more accurate a priori state estimate than the position-domain Kalman-type filter. Thus, it can be concluded that the position-domain Hatch filter is beneficial in wide application areas where fault-tolerance and accuracy are required at the same time.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.7
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• pp.59-69
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• 2005

A position domain Hatch filter is proposed as an efficient carrier-smoothed-code processing algorithm for real-time kinematic differential global satellite navigation systems. The well-known range domain Hatch filter is newly interpreted with a stochastical point of view. The interpretation result is extended to derive the position domain Hatch filter. By a covariance simulation, it is shown that Hatch gain is, in general, more efficient than Kalman-type gain in carrier-smoothed-code processing and the proposed position domain Hatch filter is more advantageous than the conventional range domain Hatch filter if the visible satellite constellation changes during the positioning task.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.20 no.4
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• pp.31-38
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• 2012

In this paper, requirements of GNSS receiver station installation are derived for optimizing the performance of network based GNSS precise positioning by concern of international organization(IGS, NGS) recommendation. Also a analysis method of network based GNSS precise positioning is suggested in order to evaluate the availability depending on various network configurations. To evaluate network candidates, a performance evaluation method is proposed for positioning of users according to a geometric configuration and the baseline distance. After the proposed method is used to Ochang region that is a the test area 6 network candidates are derived and the performance of positioning was analyzed. Finally, Ansung, Gongju, Eumsung, Boeun network configuration was selected as the best positioning performance. An optimal Receiving station network was selected using the proposed method.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2007.12a
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• pp.90-93
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• 2007

해양수산부에서 해양 DGPS기준국과 연계하여 전국망 위성항법보정시스템 (NDGPS) 구축 사업을 추진 중에 있으며, 2008년도 춘천기준국이 설치 완료되면 우리나라 전역에서 실시간 DGPS 측위 정보를 이용할 수 있게 되었다. 따라서 DGPS 이용 활성화를 위하여 무엇보다도 DGPS 측위 정확도의 신뢰성이 요구되는바, 실시간 DGPS 의 측위 정확도를 측정 ${\cdot}$ 분석하여 신뢰성을 검증하였다. 실시간 NDGPS 측위 정확도는 Static 측정에 있어 0.42m(RMS), 회전운동에 의한 Dynamic 측정시 0.48m(RMS)로 분석되었으며, RTK에 의한 비교 측정 ${\cdot}$ 분석도 병행하였다. 따라서 위성항법보정시스템 (DGPS)은 높은 정확도를 요구하는 GIS구축사업 분야에 직접적으로 이용될 수 없으나 실시간 측위 정보를 필요로 하는 GIS활용 분야에서 DGPS가 다양하게 이용될 수 있을 것이다.

• Proceedings of the Korean Institute of Intelligent Systems Conference
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• 2004.04a
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• pp.38-41
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• 2004

납치ㆍ유괴는 개인의 자유로운 활동에 많은 영향을 미치는 위험요소이다. 이러한 위험 요소로부터 벗어나기 위해서 개인의 위치를 확인할 수 있는 시스템이 절실히 필요하다. 위성 항법 시스템(Global Positioning System, GPS)은 기상 상태에 상관없이 지구 전역에서 사용 가능한 효율적인 항법 시스템으로 위치정보에 대한 지표를 제공한다. GPS는 현재 지속적인 개발에 의해 수신 모듈의 소형화 고성능화가 이루어지고 있으며, 고정 또는 이동하는 시스템의 위치정보를 제공한다. GPS 시스템을 개인이 휴대하게 되면 개인의 이동경로를 확인할 수 있게 된다. 일반적으로 개인의 이동경로는 생활권역 내에 특정 지역으로 한정되는 경우가 많으며 이동경로 자체도 주된 교통수단과 맞물려 일정한 패턴을 형성한다. 이러한 이동특성에 착안하여 본 논문에서는 개인 안전을 위해 GPS의 위치정보와 소프트 컴퓨팅 기법을 접목한 시스템을 휴대한 사용자의 이동경로를 학습하여 개인의 안전을 보장하는 방법을 제안한다.

• The KIPS Transactions:PartA
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• v.8A no.4
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• pp.429-438
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• 2001

GPS (Global Positioning System) is the most ideal navigation system which can be used on the earth irrespective of time and weather conditions. GPS has been used for various applications such as construction, survey, environment, communication, intelligent vehicles and airplanes and the needs of GPS are increasing in these days. This paper deals with the design and implementation of the RTOS (Real-Time Operating System) for a GPS navigation computer in the GPS/INS integrated navigation system. The RTOS provides the optimal environment for execution and the base platform to develop GPS application programs. The key facilities supplied by the RTOS developed in this paper are priority-based preemptive scheduling policy, dynamic memory management, intelligent interrupt handling, timers and IPC, etc. We also verify the correct operations of all application tasks of the GPS navigation computer on the RTOS and evaluate the performance by measuring the overhead of using the RTOS services.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.18 no.1
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• pp.19-26
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• 2010

To expand the application area of global navigation satellite systems, precision landing is one of the most critical area to be solved. For the development and validation of the precision landing system, many aspects need to be analyzed including the system architecture, signal characteristics, atmospheric delay, communication delay, accuracy, integrity, and availability. Among them, the signal characteristics analysis requires the processing of measurements collected by real-flight experiments. This paper presents the processing results of the real measurements collected by a flight and landing experiment. To process and analyze the data, double differencing position-domain hatch filter is utilized. Accuracy of the proposed filter is evaluated utilizing reference trajectory generated by commercial software. Finally, by comparing with conventional range domain characteristics of position domain filter is analyzed.

• Journal of the Korean Society of Surveying, Geodesy, Photogrammetry and Cartography
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• v.32 no.1
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• pp.63-73
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• 2014

Recently, researches on DBRN(DataBase Referenced Navigation) system are being carried out to replace GNSS(Global Navigation Satellite System), as weaknesses of GNSS were found that are caused by the intentional interference and the jamming of the satellite signal. This paper describes the gravity gradient modeling and the construction of EKF(Extended Kalman Filter) based GGRN(Gravity Gradient Referenced Navigation). To analyze the performance of GGRN, fourteen flight trajectories were made for simulations over whole South Korea. During the simulations, we considered the errors in both DB(DataBase) and sensor as well as the flight altitudes. Accurate performances were found, when errors in the DB and the sensor are small and they located at lower altitude. For comparative evaluation, the traditional TRN(Terrain Referenced Navigation) was also developed and performances were analyzed relative to those from the GGRN. In fact, most of GGRN performed better in low altitude, but both of precise gravity gradient DB and gradiometer were required to obtain similar level of precisions at the high altitude. In the future, additional tests and evaluations on the GGRN need to be performed to investigate on more factors such as DB resolution, flight speed, and the update rate.