• Journal of the Korean Society of Surveying, Geodesy, Photogrammetry and Cartography
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• v.20 no.4
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• pp.359-366
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• 2002

To survey satellites using only GPS can sometimes cause an impossible situation due to the many different geographical conditions as city cannon and obstacles. Although the GLONASS satellite system does not have the ability to survey itself accurately since it currently lacks of the number of usable satellites, it is able to bridge the gap when combined with GPS. This research used the GPS receiver to perform four analyzing methods to bring out the independent surveying method of GPS and combined surveying method of GPS and GLONASS(4 methods - number of satellites able to receive, precision of raw data, standard deviation from known point and RTK surveying). The result of test surveying satellites showed that 11 hours were possible to measure a minimum of 4 satellites when using an independent surveying method and 4 hours in unified surveying method in a month. Also, the precision of raw data using GPS and GLONASS surveying is 0.08~l.8m better than the GPS surveying in standard deviation. The deviation of known points by GPS and GLONASS also showed better accuracy by 3~l1mm. The RTK showed the range of differences in deviation of survey by leaning towards the GPS independent survey in Northing coordinate and leaned towards the Easting coordinate when GPS and GLONASS were combined. Nonetheless, it can't be said that the unified method is better, because it has limits to its capability.

• Journal of Advanced Navigation Technology
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• v.8 no.2
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• pp.129-135
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• 2004

In this paper, the practical applications of the pseudolite are explained with the basic concept of the pseudolite. Many researches have been developed to improve the performance of the GPS. Most of those researches need the extra equipments. But without the extra equipments, the performance of GPS can be improved only with the change in the software in GPS system. In this paper, the pseudolite and the integrated navigation system including GPS as well as pseudolite only with navigation system for the demand of more precise navigation system are introduced. Also, the advantage of the pseudolite is confirmed by some simulations.

• Journal of Korean Society for Geospatial Information Science
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• v.9 no.1 s.17
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• pp.59-66
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• 2001

Satellite visibility, Accuracy, and Availability were increased by the combined GPS/GLONASS. But, there are some problems such as differences in the time frame, differences in the coordinate datum, and the problem of solving carrier phase ambiguities in the combined carrier frequency solutions due to different GLONASS frequency. Therefore, the accuracy of single point positioning using the combined GPS/GLONASS will be assessed, and intend to study the characteristics of the combined GPS/GLONASS with considered the rate of data acquisition according to the visibility of satellite and elevation cutoff at the combined GPS/GLONASS.

• Bulletin of the Korean Space Science Society
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• 2010.04a
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• pp.36.1-36.1
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• 2010

GNSS(Global Navigation Satellite System)의 하나인 GPS(Global Positioning System)를 이용한 정밀 측위에 있어서 위성의 시계오차는 측위 정확도에 매우 큰 영향을 미친다. GPS위성에는 세슘(Cs)과 루비듐(Rb)으로 이루어진 4개의 원자시계가 탑재되어있으며 현재 사용하고 있는 원자시계의 종류는 NANU(GPS Notice Advisory to Navster Users) 정보를 통해 알 수 있다. 이 연구에서는 IGS(International GNSS Service)에서 제공하는 sp3 파일과 clk 파일을 이용하여 위성시계 특성을 분석하였다. 2000년부터 2009년까지의 sp3 파일에서 각 PRN에 대한 위성시계오차 값을 추출하여 그래프로 분석하였다. 그 결과 대부분의 세슘시계는 직선형태, 루비듐시계는 곡선형태의 특성을 보였으나 일정한 경향은 나타나지 않음을 알 수 있었다. 또한 3주간의 clk 파일에서 위성시계오차 값을 추출하여 각 PRN별로 1차식과 2차식으로 접합(fitting)하고 그 결과를 비교하였다. 세슘시계의 위성시계오차 값의 경우 2차식보다 1차식이 추출 데이터와 일치함을 알 수 있었으며 세슘시계의 위성시계오차 값은 직선형태의 특성을 보이는 것을 확인 할 수 있었다. 그리고 Modified Allan Deviation(MADEV) 방법을 적용하여 분석한 결과 GPS 위성의 block 별로 서로 다른 특성이 보임을 확인할 수 있었다.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.17 no.6
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• pp.1312-1317
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• 2013

Pseudolite is a contraction of the term "pseudo-satellite", used to refer to something that is not a satellite which performs a function commonly in the domain of satellites. Pseudolite are most often small transceivers that are used to create a local, ground-based GPS alternative. Pseudo-range measurement of pseudolite has around 300m range error, when time synchronization error of $1{\mu}sec$ occurs. Therefore the time synchronization methods play an important part in navigation augmentation using pseudolite. This paper proposes three clock synchronization methods that are installation method of pseudolite station, method using KRISS-UTC and method using PRN code phase difference for pseudolite. The simulation platform structure is presented for evaluating proposed clock synchronization performance.

• Journal of Advanced Navigation Technology
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• v.26 no.1
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• pp.9-14
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• 2022

In this paper we investigate the advantages when the GPS Antenna is installed on the rear missile body. In conventional design the GPS antenna locates on the front part of missile. However it causes degraded GPS positioning performance since the missile body blocks the GPS signals. This paper proposes the GPS array antenna design which locates on the rear part of missile body and has the tilted antenna patches to achieve the maximum area of receiving GPS signals. We simulate LOS region of receiving signals and conducted anechoic chamber test to define the effective signal receiving region. And we conduct field test and flight test to check out the enhancement of signal receiving area.

• Journal of Navigation and Port Research
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• v.38 no.4
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• pp.373-378
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• 2014

In order to prepare for recapitalization of differential GNSS (DGNSS) reference station and integrity monitor (RSIM) due to GNSS diversification, this paper focuses on differential correction algorithm using GPS/Galileo pesudorange. The technical standards on operation and broadcast of DGNSS RSIM are described as operation of differential GPS (DGPS) RSIM for conversion of DGNSS RSIM. Usually, in order to get the differential corrections of GNSS pesudorange, the system must know the real positions of satellites and user. Therefore, for calculating the position of Galileo satellites correctly, using the equation for calculating the SV position in Galileo ICD (Interface Control Document), it estimates the SV position based on Ephemeris data obtained from user receiver, and calculates the clock offset of satellite and user receiver, system time offset between GPS and Galileo, then determines the pseudorange corrections of GPS/Galileo. Based on a platform for performance verification connected with GPS/Galileo integrated signal simulator, it compared the PRC (pseudorange correction) errors of GPS and Galileo, analyzed the position errors of DGPS, DGalileo, and DGPS/DGalileo respectively. The proposed method was evaluated according to PRC errors and position accuracy at the simulation platform. When using the DGPS/DGalileo corrections, this paper could confirm that the results met the performance requirements of the RTCM.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.6
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• pp.608-615
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• 2008

Recently, research on GNSS signal receiver, aiding system and integrated navigation system approaching to the new satellite navigation system is needed. It it necessary to develop the GNSS simulator not only to understand the new satellite navigation system but also to develop the core technology about the system. In this paper, the simulator of the GPS and Galileo satellite nagivation is developed in IF(intermediate frequency) signal level.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2014.10a
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• pp.161-162
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• 2014

전 세계 시각 연구실에서는 세계협정시(UTC)를 유지하기 위해 GPS 위성의 코드 신호를 이용해왔다. 최근 GLONASS 위성 시스템이 전 세계적으로 서비스되면서 GLONASS 위성의 코드 신호를 이용한 시각 전송 기법에 대한 연구가 진행되었고 이에 GPS 와 GLONASS를 결합한 시각 전송 기법이 연구되고 있다. 본 논문에서는 GLONASS 위성의 코드 신호를 이용해서 GLONASS 위성과 관측 시스템간의 시각 오프셋을 추출하는 시각 전송 기법에서 윤초에 대해 소개하고 그 적용 결과를 제시하고자 한다.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.161.2-161.2
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• 2012

위성의 지향 정밀도에 영향을 주는 요소로 정밀한 자세명령을 생성해 주어야 하는데, 정밀 자세 명령을 생성하기 위해서는 기준좌표계를 잘 결정해야 한다. 저궤도 위성의 기준좌표계는 GPS위성으로부터 수신한 위성의 위치와 속도 및 시각 정보로부터 기준 시각의 좌표계를 생성하게 된다. 정지궤도 위성의 경우에는 GPS 위성을 사용하기 어려우므로 계속 지상에서 궤도 정보를 올려주거나 탑재 컴퓨터에 궤도전파기나 궤도 결정 알고리즘을 탑재하여 위성의 궤도 정보를 계산하게 된다. 본 연구는 정지궤도 위성의 궤도정보 요구사항을 분석하고 이를 만족하는 궤도전파기/궤도 생성 알고리즘의 개념 설계를 목적으로 한다. 먼저 저궤도위성에서 사용한 방법으로 GPS 위성으로부터 수신한 궤도 정보를 바탕으로 내부 탑재 궤도전파기를 사용하여 실제 궤도 정보가 이용되는 시간까지 궤도 정보를 전파하여 기준좌표계를 생성하는 방법을 검토하였다. 그 다음 기존의 정지궤도 위성에서 사용한 탑재 궤도 전파기/궤도 결정 알고리즘을 검토하고 새로 개발하는 정지궤도 위성의 특성을 고려하여 궤도 정밀도 요구사항을 분석하고 이를 만족하는 탑재 궤도 전파기를 설계하였다. 마지막으로 시뮬레이션을 통해 요구조건 만족과 설계 결과를 검증하였다.