• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• v.2
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• pp.455-458
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• 2006

관성항법장치는 관성항법장치를 구성하는 관성센서인 가속도계 및 자이로의 오차요소에 의해 수평축 항법오차는 슐러주기를 가지고 서서히 증가하는 반면에 수직축 오차는 기하급수적으로 증가하는 특성을 가지고 있다. 그러므로 관성항법장치를 장시간 운용하는 경우에는 비관성 보조센서를 이용하여 관성항법장치의 수직축 항법오차에 대한 보정을 반드시 수행하여야 한다. 관성항법장치의 수직축 항법오차를 보정하기 위한 비관성 보조센서의 일종인 기압고도계는 계측된 대기압과 모델링 된 대기압을 비교하여 항체의 고도를 측정하는 방법을 이용하기 때문에 항체의 자세변화 등에 매우 민감하고 대기압 측정오차에 의해 매우 큰 진폭의 잡음 및 바이어스가 존재한다. 본 논문에서는 시뮬레이션 및 시험을 통하여 기압 고도계의 잡음 및 바이어스 오차 성분에 의한 baro-inertial 고도루프의 성능분석 결과를 제시하고 기압고도계 잡음에 둔감한 INS/기압고도계 칼만필터의 설계 결과를 제시한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.6
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• pp.51-56
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• 2005

This paper introduces an altitude determination algorithm using GPS/INS/Baroaltimeter and evaluates the algorithm by real field tests. The test results show that the proposed method can determine the altitude of an aircraft continuously and sensitively. Therefore, it is appropriate to be used as an altimeter for a flight control system, especially for the automatic take-off and landing. In addition, it is shown that the second and the third baro-inertial vertical channel damping methods are essentially complementary filters while the proposed scheme improves these complementary filters.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2015.10a
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• pp.273-275
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• 2015

GPS(Global Positioning System; 위성항법시스템)는 수평오차 10m 내외의 정확도로 내비게이션 유닛과 스마트폰 등 다양한 이동기기에 널리 활용되고 있다. 그러나 널리 알려진 바와 같이 GPS는 교량, 빌딩, 그리고 대형 구조물 등 주변 환경에 의하여 위성의 가시성이 영향을 받으며 이로 인하여 위치 정보의 가용성과 정확도가 크게 저하되는 단점이 있다. 본 논문에서는 GPS 수직오차를 개선하기 위한 방안으로 저가형 기압고도계를 보조센서로 활용하여 수직 위치정보 정확도를 향상시키는 방법을 제안하였다. 제안된 방법은 융합 모델에 의한 칼만필터를 활용하여 GPS와 기압고도계를 융합하는 특성을 가진다. 마지막으로 정적 실험과 동적 실험을 통하여 기압고도계의 특성을 분석하고 제안된 융합 필터의 성능을 분석하였다.

• Journal of the Institute of Electronics and Information Engineers
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• v.49 no.10
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• pp.18-22
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• 2012

This paper suggests an altitude determination algorithm using GPS and barometric altitude sensors and evaluates the algorithm by digital map contour. A code based GPS altitude has lots of errors so that the car navigation companies can not use this data. Therefore, altitude is calculated by convergence data with GPS and barometric altitude variance in this paper. The modified altitudes are compared with the digital map contour and then this algorithm's effect is evaluated for the car navigation systems.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.4
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• pp.300-308
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• 2012

In GPS/INS/barometer navigation system for UAV, two procedures were proposed in order to set three reference parameters for the pressure altitude of QNH or QFE settings, using the navigation data from on-board system alone. These procedures yield required the reference parameters through mathematical process with the altitude and the atmosphere properties measured for a short duration of flight, of which a special pattern is requested according to the selected procedure. Dependency only upon the on-board navigation data can eliminate a requirement for the atmospheric measurement system in the ground support system and can expand a flight boundary to a remote area where the ground support is not available. Especially the procedure with the regression method uses altitude and pressure but temperature to produce the three reference parameters. No need of temperature measurement for the pressure altitude system can simplify the on-board air data system.

• Journal of Advanced Navigation Technology
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• v.20 no.1
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• pp.29-36
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• 2016

Accuracy of GPS (global positioning system) deteriorates dramatically or positioning is impossible in urban area occasionally since high-rise buildings and elevated roads make the reception of navigation signal very difficult so that number of visible satellites decreases. In these cases, vertical error usually becomes much larger than the horizontal error due to the intrinsic geometry of GPS satellites. To obtain more accurate and reliable height information, this paper proposes a hybrid method that combines GPS and a low-cost barometric altimeter. In the proposed method, the sea-level pressure and the sea-surface temperature are applied to the output of the altimeter. Next, the difference between the ellipsoid and the geoid is compensated. Finally, a simple Kalman filter combines the compensated barometric altitude and the GPS height. By static and car experiments, performance of the proposed method is evaluated. By the experiment results, it can be seen that the proposed method improves the altitude accuracy considerably.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.4
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• pp.47-56
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• 2005

In GPS/INS/barometer navigation system for UAV, vertical channel damping loop was introduced to suppress divergence of the vertical axis error of INS, which could be reduced to the level of accuracy of pressure altitude measured by a pitot-static tube. Because static pressure measured by the pitot-static tube depends on the speed and attitude of the vehicle, static pressure error models, based on aerodynamic data from wind tunnel test, CFD analysis, and flight test, were applied to reduce the error of pressure altitude. Through flight tests and sensitivity analyses, the error model using the ratio of differential pressure and static pressure turned out to be superior to the model using only differential pressure, especially in case of high altitude flight. Both models were proposed to compensate the effect of vehicle speed change and used differential and static pressure which could be obtained directly from the output of pressure transducer.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.1
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• pp.89-94
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• 2006

DGPS provides less altitude accuracy than horizontal accuracy according to geometric characteristics of GPS satellite arrangement. To assist DGPS altitude measurements, two barometric altitude sensors were used and set up at the mobile and the reference station respectively to get the differential altitude. This differential altitude is coupled with the DGPS altitude measurement by a Kalman filter so that the improved altitude is estimated. The differential altitude is based on the relative altitude measurement but results in providing the absolute altitude. The precision of this differential altitude is verified by experiments in accordance with a baseline length.

• ICROS
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• v.14 no.3
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• pp.64-69
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• 2008

• The Journal of Korean Institute of Communications and Information Sciences
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• v.40 no.1
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• pp.165-170
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• 2015

The topic of this paper is the advanced absolute altitude determination for 3-D positioning using barometric altimeter and the reference station. Barometric altimeter does not provide absolute altitude because atmosphere pressure always varies over the time and geographical location. Also, since Global Navigation Satellites system such as GPS, GLONASS has geometric error, the altitude information is not available. It is the reason why we suggested the new method to improve the altitude accuracy. This paper shows 3-D positioning algorithm using absolute altitude determination method and evaluates the algorithm by real field tests. We used an accurate altitude from RTK system in Seoul as a reference data and acquired the differential value of pressure data between a reference station and a mobile station equipped in low cost barometric altimeter. In addition, the performance and advantage of the proposed method was evaluated by 3-D experiment analysis of PNS and CNS. We expect that the proposed method can expand 2-D positioning system 3-D position determination system simply and this 3-D position determination technique can be very useful for the workers in the field of fire-fighting and construction.