• Journal of Positioning, Navigation, and Timing
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• 제10권4호
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• pp.263-269
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• 2021

The carrier-based differential global navigation satellite system (CD-GNSS) has been garnering significant attention as a promising technology for unmanned vehicles for its high accuracy. The CD-GNSS systems to be used for safety-critical applications should provide a certain level of integrity. The integrity of these systems must be analyzed under various conditions, including fault-free and satellite fault conditions. The systems should be able to detect the faults that can cause large biases on the user position errors and quantify the integrity risk by computing the protection level (PL) to protect the user against the faults that are left undetected. Prior work has derived and investigated the PL for the fault-free condition. In this study, the integrity of the CD-GNSS system under the fault condition is analyzed. The position errors caused by the satellite's fault are compared with the fault-free PL (PL_H0) to verify whether the integrity requirement can be met without computing the PLs for the fault conditions. The simulations are conducted by assuming the ephemeris fault, and the position errors are evaluated by changing the size of the ephemeris faults that missed detection. It was confirmed that the existing fault monitors do not guarantee that the position error under the fault condition does not exceed the PL_H0. Further, the impact of the faults on the position errors is discussed.

• 한국항공우주학회지
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• 제40권2호
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• pp.171-177
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• 2012

본 논문에서는 항공기 탑재용 GNSS 수신기 고장검출 알고리즘과 운용범위를 제안하였다. 고장난 항공기 수신기는 항공기에서 계산한 보정정보를 주변 항공기간 상호 교환 후에, 보정정보 일치 여부를 통해 검출한다. 이를 위해, 항공기 수신기 고장검출 알고리즘에 사용되는 검정통계량으로 보정정보 잔차값을 사용하였으며, 운용범위는 지상 기준국을 중심으로 거리에 따른 DGPS 위치오차 증가량을 이용하여 설정하였다. 정확한 고장검출을 위해 운용범위 안의 항공기들만을 사용하여 항공기 탑재용 GNSS 수신기 고장검출을 시도하는 방안을 제안하였다.

• 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.

• 한국항해항만학회지
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• 제31권6호
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• pp.509-514
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• 2007

GPS로 대표되는 위성항법시스템은 위치와 시각 분야 인프라로 그 중요성이 매우 커지고 있다. 또한 위성항법시스템을 사용하고자 하는 분야에서는 위성항법시스템의 예기치 못한 고장으로 인한 피해를 방지하거나 최소화하기 위한 노력도 하고 있다. 이는 위성항법시스템의 고장은 경제적인 손실뿐만 아니라 사회적으로도 큰 영향을 줄 수 있기 때문이다. 현재 해양수산부에서 운영하고 있는 NDGPS 망은 해양 분야를 위한 서비스를 넘어서 내륙을 포함한 국내의 모든 위성항법시스템 사용자를 위한 인프라로 발전되고 있고 국내의 각 기관 및 관련 단체에서는 이를 다양한 분야에 적용하려는 노력들이 활발히 진행되고 있다. 본 논문은 현재 운영되고 있는 NDGPS 기준국과 감시국에서 수행하고 있는 무결성 감시가 실제 위성 고장과 관련된 데이터 분석을 통해 위성 고장에 적절히 대응하기에는 부족함을 보이고, 무결성 감시기능 고도화를 위한 검사 기법별로 NDGPS 망에 적용하기 위해 요구사항을 분석하여 기존 NDGPS 망의 구조를 그대로 유지하면서 적용 가능한 검사 기법을 제시하였다.

• Journal of Positioning, Navigation, and Timing
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• 제12권1호
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• pp.51-58
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• 2023

Geofencing supports unmanned aerial vehicle (UAV) operation by defining stay-in and stay-out regions. National Aeronautics and Space Administration (NASA) has developed a prototype of the geofencing function, SAFEGUARD, which prevents stayout region violation by utilizing position estimates. Thus, SAFEGUARD depends on navigation system performance, and the safety risk associated with the navigation system uncertainty should be considered. This study presents a methodology to compute the safety risk assessment-based along-track position error bound under nominal and Global Navigation Satellite Systems (GNSS) failure conditions. A Kalman filter system using pseudorange measurements as well as pseudorange rate measurements is considered for determining the position uncertainty induced by velocity uncertainty. The worst case pseudorange and pseudorange rate fault-based position error bound under the GNSS failure condition are derived by applying a Receiver Autonomous Integrity Monitor (RAIM). Position error bound simulations are also conducted for different GNSS fault hypotheses and constellation conditions with a GNSS/INS integrated navigation system. The results show that the proposed along-track position error bounds depend on satellite geometries caused by UAV attitude change and are reduced to about 40% of those of the single constellation case when using the dual constellation.

• 한국항공우주학회지
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• 제42권6호
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• pp.453-460
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• 2014

본 논문에서는 위성항법시스템의 무결성 저해 요인 중, 항법메시지에 담겨 전송되는 궤도력 (Ephemeris) 정보의 고장 여부를 판단할 수 있는 알고리즘을 분석 및 성능 평가를 수행하였다. 알고리즘은 반송파 측정값과 두 지상 기준국간의 기저벡터 정보가 활용된다. 주요 특징으로 기준국 기저선과 위성이 이루는 기하학적 조건 기저선 길이에 따라 동일 궤도력 고장에 대해 알고리즘의 성능의 편차가 발생할 수 있음을 확인하였다. 또한 알고리즘 적용이 적합한 GBAS의 지상 기준국 안테나 배치 방안 및 제주국제공항에 운용되었을 때의 한계치 및 성능 지표 (MDE : Minimum Detectable Error)를 계산하였다.

• International Journal of Aeronautical and Space Sciences
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• 제16권1호
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• pp.89-101
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• 2015

To satisfy civil aviation requirements using the Global Navigation Satellite System (GNSS), it is important to guarantee system integrity. In this work, we propose a fault detection algorithm for GNSS ephemeris anomalies. The basic principle concerns baseline length estimation with GNSS measurements (pseudorange, broadcasted ephemerides). The estimated baseline length is subtracted from the true baseline length, computed using the exact surveyed ground antenna positions. If this subtracted value differs by more than a given threshold, this indicates that an ephemeris anomaly has been detected. This algorithm is suitable for detecting Type A ephemeris failure, and more advantageous for use with multiple stations with various long baseline vectors. The principles of the algorithm, sensitivity analysis, minimum detectable error (MDE), and protection level derivation are described and we verify the sensitivity analysis and algorithm availability based on real GPS data in Korea. Consequently, this algorithm is appropriate for GNSS regional implementation.

• 한국군사과학기술학회지
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• 제16권6호
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• pp.762-770
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• 2013

Korean military is currently using and operating a precision approach and landing system, called RAPCON (ASR/PAR), which is imported from overseas. However, drawbacks of this system are operational and cost problems that come along, e.g. straightness of the radio waves, limited ability of narrow searching, lack of interoperability, and high cost of installation and maintenance. Moreover, as the civilian air traffic control uses a similar system compared to the military, the so called DME/VOR/ILS, disturbance between these two systems triggered the consideration of GNSS as alternative system. In this paper, we conduct a research on trends in the field of precise approach and landing systems based on GNSS, analyze weaknesses of GNSS(jamming, fault) and consider possible solutions. Furthermore, we propose the precise approach and landing system based on GNSS to be used by the Korean military as we found it to be also suitable for military purposes. Finally, we examine the benefits of a domestic development with different focuses(development/cost of mass production/operational advantages and potential for increased performance).

• Journal of Positioning, Navigation, and Timing
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• 제12권1호
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• pp.11-22
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• 2023

In this paper, we propose an efficient satellite selection method for multi-constellation GNSS. The number of visible satellites has increased dramatically recently due to multi-constellation GNSS. By the increased availability, the overall GNSS performance can be improved. Whereas, due to the increase of the number of visible satellites, the computational burden in implementing advanced processing such as integer ambiguity resolution and fault detection can be increased considerably. As widely known, the optimal satellite selection method requires very large computational burden and its real-time implementation is practically impossible. To reduce computational burden, several sub-optimal but efficient satellite selection methods have been proposed recently. However, these methods are prone to the local optimum problem and do not fully utilize the information redundancy between different constellation systems. To solve this problem, the proposed method utilizes the inter-system biases and geometric assignments. As a result, the proposed method can be implemented in real-time, avoids the local optimum problem, and does not exclude any single-satellite constellation. The performance of the proposed method is compared with the optimal method and two popular sub-optimal methods by a simulation and an experiment.

• 한국항행학회논문지
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• 제14권5호
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• pp.640-647
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• 2010

최근 많은 연구자들에 의하여 위성항법 측정값 중 반송파 측정값에 대한 고장검출 연구가 진행되어 왔으나, 육상교통 환경에서의 적용연구는 활발히 진행되지 않았다. 본 논문에서는 움직이는 물체의 동적특성과 복수의 위성항법 수신기 사이의 기준 거리 제한 조건을 활용하여 위성항법 반송파 측정값의 고장검출을 수행하였다. 반송파 측정값의 고장은 다중경로 등을 포함하고 있으며 측정값 영역에서 고장검출을 수행함으로써 위치결정을 수반하는 기존의 고장검출 방법에 비하여 그 구현이 용이함을 확인하였다.