• Journal of Satellite, Information and Communications
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• v.2 no.2
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• pp.64-68
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• 2007

This paper describes the development of RF front.end equipment of a wide band high precision satellite navigation receiver to be able to receive the currently available GPS navigation signal and the GALILEO navigation signal to be developed in Europe in the near future. The wide band satellite navigation receiver with high precision performance is composed of L - band antenna, RF/IF converters for multi - band navigation signals, and high performance baseband processor. The L - band satellite navigation antenna is able to be received the signals in the range from 1.1 GHz to 1.6 GHz and from the navigation satellite positioned near the horizon. The navigation signal of GALILEO navigation satellite consists of L1, E5, and E6 band with signal bandwidth more than 20 MHz which is wider than GPS signal. Due to the wide band navigation signal, the IF frequency and signal processing speed should be increased. The RF/IF converter has been designed with the single stage downconversion structure, and the IF frequency of 140 MHz has been derived from considering the maximum signal bandwidth and the sampling frequency of 112 MHz to be used in ADC circuit. The final output of RF/IF converter is a digital IF signal which is generated from signal processing of the AD converter from the IF signal. The developed RF front - end has the C/N0 performance over 40dB - Hz for the - 130dBm input signal power and includes the automatic gain control circuits to provide the dynamic range over 40dB.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• v.2
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• pp.471-474
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• 2006

GPS수신기는 항법센서로서 여러 분야에서 널리 사용되고 있다. 단일 안테나 GPS수신기로부터 일반적으로 위치와 속도 및 시간 정보를 얻을 수 있다. 그러나 고정익 항공기의 운동 특성을 고려하여 단일 안테나 GPS수신기의 측정치로부터 무인항공기의 자세를 추정할 수 있다. 이로써 단일안테나 GPS수신기를 이용하여 무인항공기의 자동 제어가 가능함을 이전 논문에서 보인 바 있다. 본 논문에서는 단일 안테나 GPS수신기를 무인항공기의 기본 센서로 사용하여 자동 이착륙이 가능함을 비행실험을 통해 보인다. 무인항공기의 반응속도와 강건성을 향상시키기 위해 rate gyros의 각속도 측정치를 이용한다. 또한 활주로에 자동착륙하기 위해서는 높은 정확도의 위치 정보가 필요하므로 DGPS를 이용하였다. 비행 실험 동안 무인항공기는 이륙에서 착륙까지 모든 과정을 자동 제어로 수행한다. 대부분 비행은 경로 제어로 이루어진다. 비행 실험 결과를 바탕으로 단일안테나 GPS수신기가 General Aviation 항공기나 무인항공기의 백업이나 저가의 제어 시스템을 위한 주 센서로서 사용이 가능할 것으로 판단된다.

• Proceedings of the Korean Society of Fisheries Technology Conference
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• 2001.10a
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• pp.55-56
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• 2001

최근 선박의 위치정보는 인공위성을 이용한 GPS 및 DGPS 장비를 사용하여 보다 정확한 위치정보를 얻을 수 있을 뿐 만 아니라 첨단 항법장치와 전자산업의 급속한 발전으로 점점더 쉽게 고정도의 위치정보를 언제나 얻을 수 있게 발전하고 있다. 어선어업에 있어서의 조업정보는 과거의 조업정보를 근거로 하는 초기단계의 어군 탐색과정을 거치게 되는데 이러한 조업정보를 자동으로 저장하고 어획자료를 기록하는 장비의 개발을 통하여 보다 편리하게 어장선정을 위한 자료를 도출할 수 있을 것으로 기대된다. (중략)

• Journal of the Korea Institute of Information and Communication Engineering
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• v.22 no.2
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• pp.354-361
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• 2018

This paper describe the Lateral Navigation algorithm design and verification that implementation on Mission Computer's OFP for Korean Utility Helicopter(KUH) instead of Auto Flight Control System(AFCS) Vehicle Management System. The LNAV function transmits Roll command into the AFCS System. The Roll command value will be calculated by control algorithms in MC. The Operational Flight Program(OFP) shall use for its calculations different measurements of the aircraft's attitude and place. Using these inputs, the OFP will translate a navigational demand(for example-to perform the selected flight plan) into Roll commands to the autopilot. By conducting integration test using SIL and ground test, flight test, it is confirmed that the introduced algorithm meets the requirements of the Mission Equipment Package(MEP) system. LNAV function is verified through the System Integration Laboratory(SIL) test, ground and flight test.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.1-7
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• 2006

This paper presents a new point navigation guidance law which is useful for unmanned helicopters. Predicting the future position, the guidance law generates velocity and heading commands, which are used as input to autopilot. This method differs from conventional guidance law in that it reorients the direction of flight velocity vector directly, not by bank angle indirectly. For flight tests, we have developed a flight control system for a R/C helicopters. The system consists of a flight control computer, navigation sensors, and a ground station The results of the test show that the proposed law guides a unmanned helicopter along a line path within a given area. In the future, we are planning to extend the guidance law to the mission of path following. i.e., waypoint navigation.

• The Magazine of the IEIE
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• v.15 no.1
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• pp.106-113
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• 1988

현재 필자가 소속하고 있는 연구실에서는, 컴퓨터 아니메이숀, 컴퓨터 그래픽, 화상처리, 인공지능에 관한 연구등을 하고 있다. 본고에서는 화상처리에 관한 연구중에서, 본 연구실에서 최근에 발표한 컴퓨터 비죤에 관계있는 각종의 도로 정보처리에 관한 연구에 대해서 소개한다. 우선, 화상처리의 수법을 이용한 자동조종의 연구로서, 고속도로에서의 선행차의 자동동정에 관한 연구와 하프변환을 이용한 차량번호판 추출에 관한 연구에 대해서 소개한다. 다음에 도로망 지도처리에 관한 연구로서, 차재형 자동항법 시스템의 개요에 관한 소개와 최단시간 경로에 관한 연구, 도로지도의 자동판독에 관한 연구에 대해서 소개한다. 가까운 미래에, 점점 자동차의 자동화가 추진되고, 인공위성을 이용해서 자동차의 현재 위치를 정확하게 파악할 수 있게 되면, 본고에서 소개하는 연구들이 보다 중요한 의미를 가지게 되리라 생각한다.

• The Science & Technology
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• v.30 no.11 s.342
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• pp.82-83
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• 1997

GPS는 2개 이상의 인공위성에서 발사된 극초단파를 수신하여 이동물체의 위도, 경도, 높이, 표준시간 등을 정확히 파악할 수 있는 최첨단 장비이다. 뛰어난 효능으로 걸프전 때도 각광을 받았던 이 항법시스템은 안개나 사막의 먼지 속에서도 물체의 정확한 위치를 안내해 준다.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.242-250
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• 2004

This paper describes the detection method of wire-like obstacles using millimeter-wave radar system. Passive sensor like CCD camera can be used for the detection of high power electric cables on the hills or mountains and it can give very good quality of obstacle target information. But this system is very limited to use by bad weather condition. The detection capability for different diameters of wire targets using millimeter radar system have been accomplished. To simulate the target on the moving helicopter, rotating targets are used with fixed radar system. In the experiment 11mm, 16mm and 22mm diameter of wires have been detected in single, two and three wires in one position. The detected signal from single wire was very clear on gray level image. Three wires placed very closely together could be recognized in range, cross range image plane. For two and three wires, blur effect due to mutual scattering effect is observed.

• Journal of Korean Society for Geospatial Information Science
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• v.8 no.1 s.15
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• pp.73-84
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• 2000

Map matching technique is an essential part of the car navigation and other related positioning fields such as dead reckoning and GPS data logging upon the GIS database. This paper is to break down map matching techniques, to categorize them, and to propose a simple technique for GPS based map matching technique. For categorization of techniques, two approaches have been adopted. One is to only use geometric information, and the other is to use both geometric and topological information. Some pros and cons of each method have been described. In addition, a simple map matching technique, set forth in this paper, has been introduced for properly utilizing the advantage of GPS points after the absence of the chronic problem of selective availability, which had been prevailed recently. Some research opportunities and problems of the technique have also been discussed.

• Journal of Advanced Navigation Technology
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• v.8 no.2
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• pp.112-119
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• 2004

This paper proposes an attitude determination GPS/INS integrated system scheme for a UAV and presents experimental flight test results. The proposed system is designed as a part of an autopilot system and comprises a GPS attitude determination receiver, an off-the-shelf inertial measurement unit (IMU), and a navigation computer unit (NCU). UAV requires accurate attitude information for stable automatic flight control. The proposed system can provide accurate attitude information for the flight control computer (FCC) so that stable automatic flight control can be achieved. In order to verify the performance of the proposed scheme, an integrated navigation system has been developed. In order to evaluate the developed navigation system, the flight test has been performed. In the flight test, the developed system was shown to provide the position, the velocity and the attitude satisfactorily enough for stable flight control. The accuracy of the attitude information of the developed system was confirmed by comparing attitude of vertical gyro.