• 한국항행학회논문지
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• 제25권3호
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• pp.194-202
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• 2021

GNSS (global navigation satellite system)측정치 보정 후에 남아 있는 전리층 잔류 오차에 대해 시뮬레이션 기반의 영향분석(오차 및 서비스 영역 분석 등)을 수행하기 위해서는 위해서는 전리층 잔류 오차에 대한 통계적 모델링이 필수적으로 선행되어야 한다. 본 논문에서는 국내 GNSS 측정치 및 Klobuchar 모델을 활용하여 국내 정상상태 전리층 환경에서의 전리층 잔류 오차에 대한 보수적인 표준편차의 해석적 모델을 도출하였다. 다양한 전리층 활동 상태를 포함하기 위해 미(美) CAT I (category I) LAAS (local-area augmentation system) 전리층 통계치 산출일 중 ROTI (rate-of-tec index) 지수를 활용하여 전리층 활동이 비정상적인 날짜는 제외하고 GNSS 분석 데이터를 구성하였다. GNSS 데이터 처리를 통해 전리층 잔류 오차를 계산하고, 잔류 오차 거동의 특성을 근거하여 지역 시 및 위성 앙각에 따라 통계치를 산출하였다. 마지막으로 전리층 잔류 오차의 확률적 거동을 보수적으로 포함할 수 있는 표준편차값에 대한 해석적 모델을 감쇠 지수 접합을 통해 도출하였다.

• Journal of Positioning, Navigation, and Timing
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• 제13권2호
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• pp.189-197
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• 2024

Galileo is a European Global Navigation Satellite System (GNSS) that has offered the Galileo Open Service since 2016. Consequently, the standardization of GNSS augmentation systems, such as Satellite Based Augmentation System (SBAS), Ground Based Augmentation System (GBAS), and Aircraft Based Augmentation System (ABAS) for Galileo signals, is ongoing. In 2023, the European Union Space Programme Agency (EUSPA) released prior probabilities of a satellite fault and a constellation fault for Galileo, which are 3×10^-5 and 2×10^-4 per hour, respectively. In particular, the prior probability of a Galileo constellation fault is significantly higher than that for the GPS constellation fault, which is defined as 1×10^-8 per hour. This raised concerns about its potential impact on GBAS integrity monitoring. According to the Global Positioning System (GPS) Standard Positioning Service Performance Standard (SPS PS), a constellation fault is classified as a wide fault. A wide fault refers to a fault that affects more than two satellites due to a common cause. Such a fault can be caused by a failure in the Earth Orientation Parameter (EOP). The EOP is used when transforming the inertial axis, on which the orbit determination is based, to Earth Centered Earth Fixed (ECEF) axis, accounting for the irregularities in the rotation of the Earth. Therefore, a faulty EOP can introduce errors when computing a satellite position with respect to the ECEF axis. In GNSS, the ephemeris parameters are estimated based on the positions of satellites and are transmitted to navigation satellites. Subsequently, these ephemeris parameters are broadcasted via the navigation message to users. Therefore, a faulty EOP results in erroneous broadcast ephemeris data. In this paper, we assess the conventional ephemeris fault detection monitor currently employed in GBAS for wide faults, as current GBAS considers only single failure cases. In addition to the existing requirements defined in the standards on the Probability of Missed Detection (PMD), we derive a new PMD requirement tailored for a wide fault. The compliance of the current ephemeris monitor to the derived requirement is evaluated through a simulation. Our findings confirm that the conventional monitor meets the requirement even for wide fault scenarios.

• Journal of Positioning, Navigation, and Timing
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• 제1권1호
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• pp.59-64
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• 2012

Precise Point Positioning (PPP) has been widely used in navigation and orbit determination applications as we can obtain precise Global Positioning System (GPS) satellite orbit and clock products. Kinematic PPP, which is based on the GPS measurements only from the spaceborne GPS receiver, has some advantages for a simple precise orbit determination (POD). In this study, we developed kinematic PPP technique to estimate the orbits of GRACE-A satellite. The comparison of the mean position between the JPL's orbit product and our results showed the orbit differences 0.18 cm, 0.54 cm, and 0.98 cm in the Radial, in Along-track, and Cross-track direction respectively. In addition, we obtained the root mean square (rms) values of 4.06 cm, 3.90 cm, and 3.23 cm in the satellite coordinate components relative to the known coordinates.

• Journal of Positioning, Navigation, and Timing
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• 제3권4호
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• pp.163-170
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• 2014

A pseudolite is used as a GPS backup system, and is also used for the purpose of indoor navigation and correction information transmission. It is installed on the ground, and transmits signals that are similar to those of a GPS satellite. In addition, in recent years, studies on the improvement of positioning accuracy using the pseudorange measurement of a pseudolite have been performed. As for the effect of the time synchronization error between a pseudolite and a GPS satellite, a time synchronization error of 1 us generally induces a pseudorange error of 300 m; and to achieve meter-level positioning, ns-level time synchronization between a pseudolite and a GPS satellite is required. Therefore, for the operation of a pseudolite, a time synchronization algorithm between a GPS satellite and a pseudolite is essential. In this study, for the time synchronization of a pseudolite, "a pseudolite time synchronization method using the time source of UTC (KRIS)" and "a time synchronization method using a GPS timing receiver" were introduced; and the time synchronization performance depending on the pseudolite time source and reference time source was evaluated by designing a software-based pseudolite time synchronization performance evaluation simulation platform.

• Journal of Positioning, Navigation, and Timing
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• 제8권3호
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• pp.119-127
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• 2019

COsmicheskaya Sisteyama Poiska Avariynich Sudov Search and Rescue Satellite-Aided Tracking (COSPAS-SARSAT) is an international communication support program to perform search and rescue (SAR) operations in emergency situations by using satellite signals relayed from a beacon. The legacy COSPAS-SARSAT was originally composed of low altitude and geostationary Earth orbit satellites; thus, a limited number of directional dish antennas was sufficient to cover the limited number of visible satellites at the local user terminal. However, the second generation COSPAS-SARSAT newly added the medium Earth orbit satellites, e.g., Global Navigation Satellite Systems (GNSS) to the existing system, so that the number of visible satellites increase dramatically, and the system upgrade to cover all the visible satellites is foreseen. The additional use of planned Korea Positioning System (KPS) to existing GNSS is envisaged to provide a better performance of their SAR service. This paper presents the benefits of the additional use of KPS together with the phased array antennas at the local user terminal of the COSPAS-SARSAT. This is to effectively response to the increase of the number of visible satellites. Numerical simulation is included to evaluate the performance improvement of COSPAS-SARSAT in terms of the number of visible satellites, geometry between satellites and user, and position estimation accuracy.

• Journal of Positioning, Navigation, and Timing
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• 제9권4호
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• pp.347-356
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• 2020

In this study, Inclined Geosynchronous Orbit (IGSO) and Geostationary Orbit (GEO) of BeiDou System (BDS) and Quasi Zenith Satellite System (QZSS) satellites positions and clock errors calculated by broadcast ephemeris and compared with Multi-GNSS Experiment (MGEX) products provided by five Analysis Centers (ACs). Root Mean Square Errors (RMSE) calculated for satellite position error. The IGSO results showed that 1.82 m, 0.91 m, 1.28 m in BDS and 1.34 m 0.36 m 0.49 m in QZSS and the GEO results showed that 2.85 m, 6.34 m, 6.42 m in BDS and 0.47 m, 4.79 m, 5.82 m in QZSS in the direction of radial, along-track and cross-track respectively. RMS calculated for satellite clock error. The IGSO result showed that 2.08 ns and 1.24 ns and the GEO result showed that 1.28 ns and 1.12 ns in BDS and QZSS respectively.

• Journal of Positioning, Navigation, and Timing
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• 제12권2호
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• pp.121-128
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• 2023

When calculating the user's position using satellite signals, the signals originating from the satellite pass through the ionosphere and troposphere to the user. In particular, the ionosphere delay error that occurs when passing through the ionosphere delays when the signal is transmitted, generating a pseudorange error and position error at a large rate. Therefore, to improve position accuracy, it is essential to correct the ionosphere layer error. In a receiver capable of receiving dual frequency, the ionosphere error can be eliminated through a double difference, but in a single frequency receiver, an ionosphere correction model transmitted from a Global Navigation Satellite System (GNSS) satellite is used. The popularly used Klobuchar model is designed to improve performance globally. As such, it does not perform perfectly in the Korea region. In this paper, the characteristics of the delay in the ionosphere in the Korean region are identified through an analysis of 10 years of data, and an improved ionosphere correction model for the Korean region is presented using the widely employed Klobuchar model. Through the proposed model, vertical position error can be improved by up to 40% relative to the original Klobuchar model in the Korea region.

• 한국위성정보통신학회논문지
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• 제6권1호
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• pp.80-85
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• 2011

본 논문에서는 소프트웨어 기반의 실시간 GPS L1 수신기에 대한 블록 상관기법을 제안한다. 최근 다양한 위성항법 환경에서 보다 효율적인 항법 수신기 개발을 위하여 소프트웨어 기반의 실시간 수신기 개발이 필요하다. 실시간 소프트웨어 수신기는 입력신호 처리부, 신호획득부, 신호추적부, 항법데이터 처리부, 항법해 계산부로 구성되고 각 처리부는 해당 기능을 수행하기 위한 단위 컴포넌트로 구성된다. 이러한 소프트웨어 환경에서의 수신기 개발을 용이하게 수행하기 위한 소프트웨어 기반의 수신기를 개발함으로써 다양한 모델을 적용하거나 새로운 컴포넌트 조합으로 다양한 시뮬레이션을 수행할 수 있다는 장점을 제공하고 있다. 본 논문에서는 이러한 소프트웨어 기반의 수신기가 실시간의 성능을 나타낼 수 있는 블록 상관기법을 제안하고 이에 대한 성능을 검증하였다.

• 한국항행학회논문지
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• 제21권6호
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• pp.549-553
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• 2017

2014년에 착수된 한국형 SBAS인 KASS 개발 사업은 2022년 APV-1급 SOL서비스를 목표로 개발이 수행 중에 있다. KASS 연구개발에는 개발 요구조건 및 성능 요구조건을 분석하기 위해 비행시험이 이루어져야 한다. 그러나 국내에는 아직 평가항목이 제시되어 있지 않아 FAA 및 ICAO 규정서를 분석하여 KASS 개발을 위한 비행시험용 평가 항목이 구성되어야 하고, 국제적 기준에 부합하여 만들어져야 한다. 본 논문에서는 위성항행시스템을 적용한 비행시험용 SBAS 구간별 절차 검증을 분석한다.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.278-280
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• 2004

GPS Navigation Solutions are used for operational orbit determination for the KOMPSAT-1 spacecraft. GPS point position data are definitely affected by systematic errors as well as noise. Indeed, the systematic error effects tend to be longer term since the GPS spacecrafts have periods of 12 hours. And then, the overlap method of determining orbit accuracy is always optimistic because of the presence of systematic errors with longer term effects. In this paper, we investigated the measurement noise and the system error for the KOMPSAT-l GPS Navigation Solutions. To assess orbit accuracy with this type of data, we use longer data arcs such as 5-7 days instead of 30 hour data arc. For this assessment, we should require much more attention to drag and solar radiation drag parameters or even general acceleration parameters in order to assess orbit accuracy with longer data arcs. Thus, the effects of the consideration of the drag, solar radiation drag, and general acceleration parameters were also investigated.