• 대한전기학회:학술대회논문집
• /
• 대한전기학회 2001년도 하계학술대회 논문집 D
• /
• pp.2075-2077
• /
• 2001

For precise positioning, GPS carrier measurements are often used. In this case, accurate position having mm${\sim}$cm error can be obtained. For 3D positioning, in CDGPS, more than five carrier phase measurements are required. When GPS signals are blocked or carrier phase measurements are insufficient, it cannot provide positioning solution. By integrating CDGPS with INS, continuity of positioning solution can be guaranteed. However, when a vehicle moves in low speed or in stationary, the CDGPS/INS integrated system is difficult to compensate INS attitude errors because GPS velocity error become relatively lange. In this paper, we used the 3D attitude GPS receiver to compensate the INS attitude error. By field experiments, it is shown that the proposed integration system maintains the navigation performance even when a vehicle is in low speed or GPS signal is blocked for a period of time.

• 한국항행학회논문지
• /
• 제21권6호
• /
• pp.601-607
• /
• 2017

이 연구에서는 GNSS (global navigation satellite system) 인프라 기반 측위 보정정보 생성을 위한 전처리 단계인 GPS (global positioning system) 반송파 위상 측정치의 고장 검사를 수행하였다. 기존 CARST (carrier acceleration ramp step test) 방법은 수신기 시계 오차를 제거하기 위해 평균값을 이용함으로써 검사 대상에 영향을 준다. 따라서 이 연구에서는 차분 기법을 적용하여 기존 CARST 결과와 비교하였다. 실 데이터에 인위적인 고장을 인가하여 고장 시뮬레이션을 수행한 결과 차분 기법을 적용할 경우 각각의 위성에 대해 독립적인 고장 검출이 가능한 것으로 판단되었으며 단일차분과 이중차분은 유사한 결과를 나타내었다. 실 데이터를 이용하여 기존의 방법과 비교한 결과 위성 간 차분, 수신국간 차분 결과의 장단점을 확인할 수 있었다. 그러나 결과 값에 대한 위성 및 수신기 시계 오차의 영향은 추가적인 분석이 필요할 것으로 판단된다.

• Journal of Astronomy and Space Sciences
• /
• 제22권4호
• /
• pp.491-500
• /
• 2005

세계 각국은 국제적으로 통일된 시각동기 체계를 따르고 있으며 국가표준시 유지를 위하여 GPS(Global Positioning System)를 활용하고 있다. 현재 국내 GPS 기반 시각동기 연구는 코드데이터와 방송궤도력을 사용하고 있다. 이 연구에서는 보다 정확한 시계오차 추출을 위하여 반송파위상 데이터를 사용하였으며, 방송궤도력 뿐만 아니라 정밀궤도력, 신속궤도력, 그리고 초신속궤도력을 사용하였다. 정밀궤도력을 사용하여 산출된 시계오차를 참값으로 가정하였을 때, 신속궤도력과 초신속궤도력의 경우 약 0.5ns의 정밀도를 나타내었으며, 방송궤도력의 경우는 2ns 이하의 정밀도를 나타내었다.

• 제어로봇시스템학회논문지
• /
• 제22권11호
• /
• pp.967-976
• /
• 2016

This paper presents a 3D carrier-smoothed GNSS/DR (Global Navigation Satellite System/Dead Reckoning) integrated system for precise ground-vehicle trajectory estimation. For precise DR navigation on sloping roads, the AHRS (Attitude Heading Reference System) methodology is employed. By combining the integrated carrier phase of GNSS and DR sensor measurements, a vehicle trajectory with an accuracy of less than 20cm is obtained even when cycle slip or change of visibility occur. In order to supplement the weak GNSS environment with DR successfully, the DR sensor is precisely compensated for using GNSS Doppler measurements when GNSS visibility is good. By integrating a multi-GNSS receiver with low-cost IMU, a precise 3D navigation system for land vehicles is proposed in this paper. For real-time implementation, a decoupled Kalman filter is employed in the integrated system. Through field experiments, the performance of the proposed system is verified in various road environments, including sloping roads, good-visibility areas, high multi-path areas, and under-ground parking areas.

• Journal of Communications and Networks
• /
• 제7권3호
• /
• pp.248-257
• /
• 2005

In this paper, we develop design procedures for carrier tracking loop for orthogonal frequency division multiplexing (OFDM) systems or other systems of blocked data. In such communication systems, phase error measurements are made infrequent enough to invalidate the traditional loop design methodology which is based on analog loop design. We analyze the degradation in the OFDM schemes caused by the tracking loop and show how the performance is dependent on the rms phase error, where we distinguished between the effect of the variance in the average phase over the symbol and the effect of the phase change over the symbol. We derive the optimal tracking loop including optional delay in the loop caused by processing time. Our solution is general and includes arbitrary phase noise apd additive noise spectrums. In order to guarantee a well behaved solution, we have to check the design against margin constraints subject to uncertainties. In case the optimal loop does not meet the required margin constraints subjected to uncertainties, it is shown how to apply a method taken from control theory to find a controller. Alternatively, if we restrict the solution to first or second order loops, we give a simple loop design procedure which may be sufficient in many cases. Extensions of the method are shown for using both pilot symbols and data symbols in the OFDM receiver for phase tracking. We compare our results to other methods commonly used in OFDM receivers and we show that a large improvement can be gained.

• 대한전기학회:학술대회논문집
• /
• 대한전기학회 2001년도 하계학술대회 논문집 D
• /
• pp.1984-1986
• /
• 2001

In order to provided continuous solutions, latest developing navigation systems tend to integrate GPS receiver with INS or DR. Using the GPS carrier-phase measurements, an attitude GPS receiver with three antennas obtain the 3-dimensional attitude such as roll, pitch, and heading as well as position and velocity. With these angle measurements, in the attitude GPS/INS integrated system, attitude or gyro errors can be directly compensated. In this paper, we develop an integrated navigation system that combines attitude GPS receiver with INS. The performance of real-time integrated navigation system is determined by not only the implements of integration filter but also the synchronization of measurements. To meet these real-time requirements, the navigation software is implemented in multi-tasking structure in this paper. We also employ time-synchronization technique in the multi-sensor fusion. Experimental results show that the performance of the attitude GPS/INS integrated system is consistent even when cycle-slip occurs in carrier-phase measurements.

• 한국통신학회논문지
• /
• 제40권9호
• /
• pp.1846-1855
• /
• 2015

본 논문에서는 저비용 단일 GNSS(Global Navigation Satellite System) 수신기를 이용하여 정밀한 위치를 추정하는 방법으로 반송파 위상 TD(Time Differenced) 측정치를 이용한 상대위치 결정기법을 제안하고 성능을 분석하였다. 제안하는 상대위치 결정기법은 반송파 위상 측정치를 활용하지만 시각 간 차분을 사용하므로 하나의 GNSS 수신기로 동작하며, 미지정수 결정 문제를 고려하지 않아도 된다. 또한 차분 간격이 짧은 시간일 경우 공간적 공통오차 및 위성시계 오차를 효율적으로 제거할 수 있다. 제안하는 위치결정 알고리즘은 오차해석을 통해 코드측정치를 이용한 절대위치 결정기법보다 성능이 우수함을 증명하고 실차 실험으로 구현된 알고리즘 및 오차해석 결과를 검증하였다. 그 결과, 위치추정 성능은 약 10분 동안 3m이내에 수렴하여 코드기반의 절대위치기법에 비하여 약 4배 이상 향상된 정확도 및 정밀도를 확인할 수 있었다.

• 제어로봇시스템학회논문지
• /
• 제5권1호
• /
• pp.62-68
• /
• 1999

The attitude of a vehicle can be precisely determined using GPS carrier phase measurements from more than two antennas attached to a vehicle and an efficient integer ambiguity resolution technique. Many methods utilizing the known baseline length as a constraint of independent elements of integer ambiguities are proposed to resolve integer ambiguity at real time. Three-dimensional search space is reduced to two-dimensional search space with this constraint. Thus the true integer ambiguity can be easily determined with less computational burden and fewer number of measurements. But there are still strong requirements for the real time integer ambiguity resolution, which uses single epoch measurement of long baseline. In this paper, a new constraint from the geometry of multiple baselines is derived. With this new constraint, two-dimensional search space is further reduced to one-dimensional search space. It makes possible to determine integer ambiguity with single epoch measurement. The proposed method is applied to real data to show its effectiveness.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
• /
• 한국우주과학회 2003년도 한국우주과학회보 제12권2호
• /
• pp.48-48
• /
• 2003

A precision orbit determination (POD) system of low Earth orbiter using the GPS dual frequency measurements has been developed. It is an option of KOMPSAT-2 POD process system. In this research, the orbit determination using the real dual frequency carrier phase measurements of the SAC-C satellite was conducted to verify KOMPSAT-2 POD system reliability. The SAC-C satellite is an international cooperative mission between NASA, the Argentine Commission on Space Activities (CONAE), Centre National d'Etudes Spatiales (CNES or the French Space Agency), Instituto Nacional De Pesquisas Espaciais (Brazilian Space Agency), Danish Space Research Institute, and Agenzia Spaziale Italiana (Italian Space Agency). The SAC-C was launched at November 21, 2000. The altitude of SAC-C is 702 km and it carries a TurboRogue III GPS and four high gain antennas developed by the JPL. The receiver is able to generate the dual frequency code and carrier phase data. Double-differenced carrier phase measurements were formed using 25 IGS stations. The data were sampled at 30 seconds interval. Fully dynamic approach was adopted for POD. The POD results were compared with those of JPL using GOA n software. The comparison verifies that deci-meter level 3D position accuracy of low Earth orbiting satellite could be achieved. The POD system has been developed successfully.

• 한국항해항만학회:학술대회논문집
• /
• 한국항해항만학회 2006년도 International Symposium on GPS/GNSS Vol.1
• /
• pp.377-382
• /
• 2006

Precision approach and landing of aircraft in a remote landing zone autonomously present several challenges. Firstly, the exact location, orientation and elevation of the landing zone are not always known; secondly, the accuracy of the navigation solution is not always sufficient for this type of precision maneuver if there is no DGPS availability within close proximity. This paper explores an alternative approach for estimating the navigation parameters of the aircraft to the landing area using only time-differenced GPS carrier phase measurement and range measurements from a vision system. Distinct ground landmarks are marked before the landing zone. The positions of these landmarks are extracted from the vision system then the ranges relative to these locations are used as measurements for the extended Kalman filter (EKF) in addition to the precise time-differenced GPS carrier phase measurements. The performance of this navigation algorithm is demonstrated using simulation.