• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2022.06a
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• pp.412-414
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• 2022

Global Navigation Satellite Systems (GNSSs)을 이용한 위치정보 서비스가 다양해짐에 따라, 전파 교란 및 기만에 대한 GNSSs의 취약성에 대한 우려도 점점 커지고 있다. 이에 미국, 러시아, 유럽 등 자체적으로 GNSS를 보유하고 운영하고 있는 국가조차도 GNSS의 취약성을 보완할 수 있는 부가적인 항법시스템을 개발하고 있다. 그 중 현재 운영 중인 Medium Frequency (MF) 주파수 대역의 신호를 이용하여 Differential GNSS (DGNSS) 정보를 전달하는 인프라를 활용하여 항법 신호를 송출하는 Ranging Mode (R-Mode) 시스템이 유럽과 한국을 중심으로 개발 중에 있다. 하지만 MF 주파수 대역의 신호는 일몰 이후에 전리층 일부가 소멸되면서 상위 전리층에서 신호가 반사되어 지표면에서 강한 세기로 수신되는 특성을 갖고 있다. 이런 특성은 지표를 통해 전파하는 원 신호를 수신하는 과정에 큰 오차요소로 작용할 수 있다. 본 논문에서는 현재 송출되고 있는 R-Mode 신호의 야간 특성을 분석하고자 한다. 현재 충주, 어청도 DGNSS 기준국에서 송출하고 있는 R-Mode 신호를 다양한 안테나 종류로 수신해보고, 항법 시스템의 정밀도 성능에 악영향을 줄 수 있는 특성에 대한 보완방법을 모색하였다.

• Journal of Advanced Navigation Technology
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• v.26 no.4
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• pp.195-204
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• 2022

In this paper, we described the rapid initial alignment techniques of projectile navigation system for use in inclined launch systems. One-shot alignment technique, one of the rapid initial alignment techniques, is possible to align a navigation system within seconds because it uses external information from an launcher navigation system. However, since it has only been used in vertical launch systems, its performance in inclined launch systems has not been verified. Therefore, this paper analyzed the error elements that occur when the one-shot alignment technique is applied to the inclined launch system, and introduced a method to improve the alignment performance by minimizing those errors. Additionally, By simulating and testing the performance of the proposed alignment technique, it was verified that it is effective even in an environment where a real navigation system is used.

• Journal of Advanced Navigation Technology
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• v.22 no.3
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• pp.220-227
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• 2018

The most widely used method for constructing an inertial navigation system (INS)/global navigation satellite system (GNSS) coupling system is to construct an integrated navigation system using a Kalman filter. However, depending on the trajectory, non-observable state variables may be generated. In this case, the state variables are not estimated. To solve this problem, a integrated navigation system is constructed and then an observability analysis is performed. In this paper, a 24th order position-matched Kalman filter is defined to design an INS/GNSS integrated navigation system for vehicles moving with a large pitch angle change. To verify the appropriateness of the error state variables applied to the Kalman filter, an observability analysis was performed. The trajectory was divided into five segments, and the piece-wise constant system (PWCS) was assumed for each segment, and the results were analytically analyzed. The analytical results and the simulation results confirm that the error state parameters of the Kalman filter are well-designed to the estimation side.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2011.06a
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• pp.25-26
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• 2011

사용자 의사거리 보정 잔차(UDRE)는 위성항법보정정보의 측위성능을 예측하는데 이용하는 매우 중요한 무결성 감시정보이다. 위성항법보정정보 사용자는 위성별로 제공되는 사용자 의사거리 보정 잔차 정보를 이용하여 목표로 하는 측위성능을 보장할 수 있는지 여부를 계산하고, 이 결과를 반영하여 위성항법보강시스템의 보정정보를 사용할지 아니면, 무시할지를 판단한다. 즉, 사용자 의사거리 보정 잔차는 위성별로 제공되는 보정정보를 이용하여 보정을 한 후에도 제거되지 않고 남는 위성과 사용자 수신기 간의 통계학적 거리 오차로서 가우시안 분포를 갖는다고 본다. 따라서 동일한 위성항법신호 환경이라도 위성항법보강시스템의 종류와 응용분야별로 다르게 설정되는 측위성능의 보장 수준에 따라 사용자 의사거리 보정 잔차는 다른 값을 갖게 된다. 본 논문은 위성항법보강시스템의 무결성 감시성능에 영향을 미치는 사용자 의사거리 보정 잔차 추정기법의 성능해석을 목적으로 다중 기준국 원시정보를 이용한 사용자 의사거리 보정 잔차 추정기법 구조분석과 영향력을 소개하고, 성능에 영향을 미치는 인자와 사용자 의사거리 보정 잔차 추정성능의 지표에 대해 정의한다. 그리고 마지막으로 성능해석의 방법을 제안하고, 타당성을 검증한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.12
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• pp.1086-1092
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• 2012

It has been studied for DGPS/INS(Differential Global Positioning System/Inertial Navigation System) to offer the more precise and reliable navigation data with the aviation industry development. The flight performance evaluation of navigation system is very significant because the reliability of navigation data directly affect the safety of aircraft. Especially, the high-level navigation system, as DGPS/INS, need more precise flight performance evaluation method. The performance analysis is performed by comparing between the DGPS/INS navigation data and reference trajectory which is more precise than DGPS/INS. The GPS receiver, which is capable of post-processed CDGPS(Carrier-phase DGPS) method, can be used as reference system. Generally, the DGPS/INS is estimated the CG(Center of Gravity) point of aircraft while the reference system is output the position of GPS antenna which is mounted on the outside of aircraft. For this reason, estimated error between DGPS/INS and reference system will include the error due to lever arm. In order to more precise performance evaluation, it is needed to compensate the lever arm. This paper presents procedure and result of flight test which includes lever arm compensation in order to verify reliability and performance of DGPS/INS more precisely.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2016.10a
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• pp.961-964
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• 2016

This paper describes the implementation of AUSV system for Sonar Image acquisition. The system be controlled by FF-PID algorithm for the thrusters using motion sensor and DGPS. As experimental results, the control performance is that the error distance from the destination positions are under 5m in total survey track of 1km, and the image deviation is under 12 pixel from the manned survey method, which the comparison with the total image quality is almost the same as the manned survey one. Thus the AUSV system is a new method of system can be utilized on the limited survey area as the surveyor should not be able to approach on sea surface.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.6
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• pp.481-487
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• 2013

In GPS(Global Positioning System)/INS(Inertial Navigation System) integrated navigation systems, GPS antennas and an inertial measurement units are usually installed outside and inside of the vehicle, respectively. By the difference of installed locations, performance of GPS/INS integrated navigation systems is affected by lever arm errors. For more accurate navigation, lever arm errors need to be compensated correctly since it directly affects the accuracy of navigation states. This paper proposes an effective lever arm error compensation method that utilizes velocity measurements of GPS and INS. By an experiment, feasibility of the proposed algorithm is verified. It is also shown that lever arm compensation is especially important when vehicles are experiencing rotational movements.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.6
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• pp.505-514
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• 2014

The effects of reflected wave of the sea on pseudolite ranging accuracy are analysed in this paper, when a pseudolite navigation system is used for wide area outdoor applications such as aircraft and vessels positioning. Methods for minimizing the influence of sea surface reflection wave were proposed. The methods include the appropriate correlator in pseudolite navigation system through the correlation performance comparison analysis in receiver design, the use of the technology of multiple antennas, and locating the transmitting station antenna on an appropriate position. From the results of experiments, the method of locating the antenna position shows the most reliable performance against the effect of surface reflection wave. The analysis results of the ranging accuracy improvement are addressed, when the multipath caused by sea surface reflection exists.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.2
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• pp.128-136
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• 2011

An approach to improve the performance of SDINS and GPS integrated system for bank-to-turn flight vehicles is described. Then, it is shown through the simulation that a specific gyro misalignment error results in an increased heading error of SDINS. A new modelling method is presented herein for identifying of sensor and attitude error. The main advantage of the proposed method is that it not only estimates the gyro misalignment error of SDINS, but also improves estimate performance of heading error of SDINS in the presence of the gyro misalignments.

• Journal of Navigation and Port Research
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• v.37 no.1
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• pp.35-40
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• 2013

In the eLoran navigation system, the dominant deterioration factors of navigation accuracy are the TOA measurement errors on user receiver and the GDOP between the receiver and the transmitters. But if the ASF data measured at dLoran reference station are provided for users through the Loran data channel, it will be possible to correct the TOA measurement errors. The position accuracy can be determined by the DOP depending on the geometry of receiver-transmitters, and their optimal placement improves the navigation accuracy. In this study we determined the geometric placement in case of up to six stations, and evaluated the performance of position accuracy for the receiver-transmitter geometry set of eLoran stations. The proposed geometry of eLoran stations can be referred for the construction of eLoran infrastructure meeting the capability of HEA for maritime, and time/frequency users in Korea.