• Journal of Navigation and Port Research
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• v.26 no.3
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• pp.303-310
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• 2002

Nowadays, the combined land navigation system using GPS(Global Positioning System) and DR(Deduced Reckoning), etc. has been used. Although GPS is popular with the land navigation system, this is not useful for the kinematic positioning of the vehicles in the urban canyon because of its few satellites. Thus, this study deals with the kinematic positioning of the vehicles with the combined GPS/GLONASS(GLObal Navigation Satellite System) to compliment the drawbacks of GPS. So the kinematic positioning of the vehicles can be performed constantly by the combined GPS/GLONASS based on the high acquisition rate of data with the help of GLONASS despite of many obstacles and few satellites tracked in the test sites. Consequently, the combined GPS/GLONASS can be applicable to the control of traffic flow and the effective management of read system.

• Journal of Space Technology and Applications
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• v.3 no.1
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• pp.58-71
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• 2023

This paper describes a navigation system design for horizontal position estimation using inertial measurement sensors and celestial navigation. In space, stars are widely spread objects in the celestial sphere and have been used mainly to obtain attitude information through star observation. However, it is also possible to obtain information about the horizontal position with the altitude of the star. It is called celestial navigation which is the same principle that former navigators used to locate themselves while sailing on the sea. In particular, in deep space where GPS is not available, it is important to obtain information on the location by making use of stars that are relatively easy to observe. Therefore, we introduce a navigation system that can estimate horizontal position and design two types of systems, loosely coupled and tightly coupled depending on how the measurements are utilized. It is intended to help in the future design of navigation system using celestial navigation by simulation studies that not only verify whether the system correctly estimates horizontal position but also comparing the performance of loosely and tightly coupled methods.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.1
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• pp.36-45
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• 2017

Abstract It is necessary to verify the properties of an inertial measurement unit in the flight environment before applying to military applications. In this paper, we presented a new approach to verify an inertial measurement unit(IMU) in regard to the performance and the robustness in flight environments for the high-dynamics vehicle systems. We proposed two methods for verification of an IMU. We confirmed normal operation of an IMU and properties in flight environment by using direct comparison method. And we proposed real time multi-navigation system to complement the first method. The proposed method made it possible to compare navigation result at the same time. Therefore, it is easy to analyze the performance of an inertial navigation system and robustness during the vehicle flight. To verify the proposed method, we carried out a flight test as well as an experimental test of flight vibration on the ground. As a result of the experiment, we confirmed flight environment properties of an IMU. Therefore, we shows that the proposed method can serve the reliability improvement of IMU.

• The Science & Technology
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• v.29 no.6 s.325
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• pp.18-19
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• 1996

각종 기능을 갖춘 센서와 컴퓨터로 자동항법장치를 한 미래의 자동차가 눈 앞에 다가오고 있다. 단단하고 충격을 줄여주는 특수 플라스틱, 밤에 운전시야를 넓혀주는 적외선 감지장치, 자동으로 펑크를 때워주는 로열티 타이어, 고온에 견디는 세라믹 엔진, 수소를 연료로 하는 공해없는 자동차 등의 개발이 한창 진행중이다.

• Journal of Advanced Navigation Technology
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• v.16 no.5
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• pp.738-743
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• 2012

Kalman filter is generally used in INS/GPS integrated navigation filter. However, the INS with low performance inertia sensor can not find accurate azimuth in initial alignment stage because sensor noise level is too large compare to Earth rotation rate, therefore the performance and stability of Kalman filter can not be guaranteed. In this paper, the extended Kalman filter and particle filter combined filter structure which can be overcome large initial azimuth error is proposed.

• Journal of Ocean Engineering and Technology
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• v.30 no.5
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• pp.367-373
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• 2016

This paper describes the development of a navigation HILS (hardware in the loop simulation) system for an integrated navigation performance analysis of a large diameter unmanned underwater vehicle (LDUUV). The HILS system was used for the performance analysis of the LDUUV. When a conventional HILS system is used, it is not possible to calculate the velocity and position using an inertial navigation system (INS). To cope with this problem, an external acceleration was generated. To evaluate the proposed method, we compare the results of a Monte Carlo simulation and navigation HILS experiment.

• Journal of the Korea Society for Simulation
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• v.24 no.4
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• pp.43-49
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• 2015

Maximum lock-on distance in tactical guidance missile using seeker image is estimated by seeker's FOV, resolution and performance of tracking algorithm. In case, a missile is launched beyond the maximum lock-on distance, the missile is guided by INS pure navigation until it enters the lock-on possible zone. However, the probability of a target's existence within seekers images decreases as flight time goes by. Therefore, it is crucial to determine the distance that satisfies a certain target existence probability (TEP) and the maximum lock-on distance in order for an operator to take over the navigation role between two distances. In this paper, simulation which can analyse TEP in tactical guided missile seeker image is designed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.6
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• pp.502-511
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• 2016

Recently, many kind of smart projectiles are being developed. In case of smart projectile, studying in advance, it uses a navigation data acquired from the GNSS receiver to check its location on the geocentric(WGS84) coordinates and to estimate P.O.I(point of impact). However, because of various error inducing factors, the result of positioning involve some errors. We introduce the advanced algorithm for the reconstruction of a navigation trajectory using weighted PDOP, based on a simulated trajectory acquired from PRODAS. It is very fast and robust to noise and shows reliable output. It can be widely used to estimate an actual trajectory of a projectile.

• Proceedings of the KIEE Conference
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• 2001.07d
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• pp.2190-2192
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• 2001

가스 배관 진단 시스템은 배관 내부에 삽입되어 배관 내에 주입된 가스에 의해 추진되는 시스템으로 배관의 건설, 유지, 보수, 해체 등의 작업을 위한 여러 정보를 수집한다. 배관 진단을 위한 대표적인 센서로는 배관 내부의 찌그러짐(dent)과 주름(wrinkle)의 형태 및 크기를 측정하는 캘리퍼(caliper) 센서와 배관 외부의 파손을 측정하는 MFL(Magnetic Flus Leakage) 센서 그리고 배관 내의 환경 정보를 측정하기 위한 온도 센서와 압력 센서가 있다. 이러한 센서들로 수집된 정보를 활용하기 위해서는 정확한 위치 정보가 필요하므로 IMU(Inertial Measurement Unit)와 주행 거리계를 사용하는 결합 항법 시스템도 필요하다. 본 논문에서는 가스 배관 진단 시스템을 위한 항법 데이터 저장 시스템을 개발한다. 배관 진단 시스템의 특성상 일반적인 측정 센서는 700Hz 이상의 주기로 측정되고 항법 정보는 100Hz 주기 이상으로 측정되며 배관 내 이동 시간은 2시간에서 24시간 이상으로 다양하므로 많은 데이터를 효율적으로 저장할 수 있어야 한다. 따라서 데이터 저장 장치로는 DAT를 사용하게 되며 많은 센서 데이터를 실시간으로 저장하기 위해서 마스터-슬레이브 구조를 갖는 멀티 프로세서 구성을 이용한 항법 데이터 저장 시스템을 설계 제작하였다.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.2
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• pp.47-56
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• 1994

본 연구는 GPS와 노트북 PC를 이용하여 비행경로정보를 얻기 위한 것으로, 이들을 실제 비행기에 장착하여 위치(동경, 북위, 고도), 방위, 속도등의 비행경로정보를 기록하였다. 기록된 자료를 분석한 결과 실제 비행시의 자료들과 일치함을 보였다. GPS와 노트북 PC를 이용한 비행기록장치는 조종훈련생들의 항법교육 및 항법 능력 측정 자료로 이용 될 수 있을 것이다.