• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.10
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• pp.127-133
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• 2004

This paper described development of the portable ground control system(PGCS) for unmanned aerial vehicle. In the design of GCS, it upload mission planning that aircraft has to perform and has to receive position, attitude, state, navigation information all about the aircraft. Aircraft states and trajectory are displayed using this system on line. The PGCS is composed of commercial notebook computer, RF modem for communication between aircraft and PGCS, input/output board, remote control receiver, switches and lamps. Performance of this system is verified by flight test of small unmanned aerial vehicle.

• Proceedings of the KIEE Conference
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• 2011.07a
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• pp.1254-1255
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• 2011

최근 무선통신기반 열차제어시스템의 국산화 개발이 진행 중에 있으며, 이동폐색 및 열차간격의 효율적인 제어를 위해서는 열차에 서 직접 열차의 이동위치와 속도를 정확하게 실시간으로 파악할 수 있어야 한다. 하지만 기존 철도시스템에서는 열차의 위치 및 속도확인을 위해 궤도회로와 타코메터를 이용하고 있으며, 효율적인 열차제어를 위해 지상설비의 도움없이 안전하고 정확한 열차위치정보의 확보가 필요하다. 따라서 본 논문에서는 위성항법수신기, 관성센서, 도플러레이더센서, 타코메터와 같이 열차에 탑재 가능한 위치 및 속도센서를 통합 적용하여 단독으로 열차 위치 및 속도파악이 가능한 차상기반 열차위치검지 장치를 구성하고, 한국형 틸팅열차 탑재시험을 통해 위치정확성을 평가하고 철도운영 환경에서의 적용성을 확인한다.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.168.1-168.1
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• 2012

TRIO-CINEMA(TRiplet Ionospheric Observatory-Cubesat for Ion, Neutral, Electron, MAgnetic fields)는 중량 3 kg의 초소형 인공위성 3기로 구성되며, 그 임무는 근 지구 플라즈마 입자 검출 및 자기장계측이다. 3기 중 1기는 UC Berkeley에서, 2기는 경희대학교에서 제작 및 운용된다. 경희대학교 천문대에 IGSS(Integrated Ground Support Software), TNC(Terminal Node Controller), 송신기, 안테나제어기와 안테나로 구성된 지상국을 구축하였으며 위성에 명령을 전달하는 기능을 수행한다. 위성으로부터 데이터 수신은 한국천문연구원의 안테나와 수신기를 이용할 예정이다. 2기의 위성을 하나의 지상국에서 운용하기 위해서는 각 위성에 대한 송신 주파수 변경 및 패스스케줄(pass schedule) 조정이 필요하며, 이를 수행할 수 있는 RF Chain을 구축하였다. 본 연구는 RF Chain 구축과 검증과정을 기술하였으며, 시스템의 검증으로 원거리 필드 테스트, 데이터 통신 테스트, 링크 여유 분석 등을 수행하였다.

• Journal of Satellite, Information and Communications
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• v.1 no.2
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• pp.45-50
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• 2006

A satellite and ground stations which are developed in a program are tested whether the interface between the satellite and ground is well established before satellite operations. These compatibility tests are performed when the satellite is connected with the ground stations after all satellite and ground stations requirements are verified. The content of the RF compatibility test is to check whether the interface requirements which are described on the Interface Control Document are well developed. During the early operation phase and tentative contingency operations of the satellite, KARI ground station uses other oversea ground stations which are located worldwide according to contract between the KARI and the contractor. Since oversea ground stations were not developed for the designated space program, system integrator should check whether the oversea ground stations are satisfied with interface requirements. Using the RF suitcase, RF interface and the content of RF communication can directly be verified during RF compatibility test on oversea ground station without KARI ground station's support. The RF compatibility test using RF suitcase was performed oversea ground stations as well as KARI ground station located on Korea. The content of RF compatibility test was standardized in order to be used at any oversea ground stations, especially fitted for the operations concept of launch and early operations phase. The test content would be RF characteristics, protocol, command loop test, telemetry loop test, and ground station interface test.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.16 no.10
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• pp.6949-6958
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• 2015

Radio based train control system performs train safe interval control by receiving in realtime the position information of trains driving in the control area of the wayside system and providing onboard system in each train with updated movement authority. The performance of the train control system is evaluated to calculate the minimum operation headway, which reflects the operation characteristics and the characteristics of the train as well as the interval control performance of the train control system. In this paper, we propose the operation headway calculation for radio based train control system and a new train interval control algorithm to improve the operation headway. The proposed headway calculation defines line headway and station headway by the estimation the safety margin distance reflecting the performance of the train control system. Furthermore the proposed Enhanced Train Interval Control(ETIC) algorithm defines a new movement authority including both distance and speed, and improves the train operation headway by using braking distance occurring inevitably in the preceding train. The proposed operation headway calculation is simulated with Korean Radio-based Train Control System(KRTCS) and the simulated result is compared to improved train interval control algorithm. According to the simulated results, the proposed operation headway calculation can be used as performance indicator for radio based train control system, and the improved train control algorithm can improve the line and station headway of the conventional radio based train control system.

• Broadcasting and Media Magazine
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• v.13 no.4
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• pp.65-79
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• 2008

최근 TV 디지털 방송에 대한 많은 관심이 집중되면서 국내의 디지털 텔레비전 방송(Digital Multimedia Broadcasting: DMB)과 유럽의 디지털 텔레비전 방송((Digital Video Broadcasting: DVB)에 대한 기술 개발이 지속적으로 이루어지고 있다. 국내의 DMB는 지상파 DMB와 위성 DMB가 있고, 유럽의 DVB는 일반 방송국으로부터 가정용 또는 사무실용의 고정된 장치에서 수신을 하는 DVB-T와, 휴대 전화기나 휴대용 영상기기 등의 저전력, 이동성, 휴대성을 고려한 DVB-H가 있다. 또한 휴대폰이나 PDA와 같은 휴대 통신단말기의 기능복합화 요구에 따라, 국내에서는 휴대폰에 TV 방송기능과 인터넷을 이용할 수 있는 네트워크 서비스가 내장된 단말기가 속속 출시되어 치열한 경쟁구도에 접어들고 있다. 이러한 시장요구에 부응하기 위해 다양한 분야에서 기능 복합화를 실현하고자 하는 " Ubiquitous Convergence화"가 급속도로 진행되고 있다. 그러나 단일 시스템에서 2가지 이상의 기능(GSM/GPRS & DVB-H)이 Convergence화 되어있을 경우, 시스템 상호간 간섭영향으로 각 장치의 기능 저하가 발생하고 있다. 특히, 동일 주파수대역 사용에 의해 방생하는 간섭영향에 대한 적절한 대응이 요구되는 시점이다. 본 고에서는 무선 통신 분야 기술개발의 한 부분으로 부품의 초소형화 및 동일 주파수대역 사용에 의해 발생하는 간섭영향을 제거하는 내용에 대해서 기술한다.

• Journal of Aerospace System Engineering
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• v.14 no.1
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• pp.68-73
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• 2020

This purpose of this paper was to review the development trend of the VTOL MAVs with a ducted propellant that can fly like the VTOL at intermediate and high speeds, hovering, landing, and lifting off vertically over urban areas, warships, bridges, and mountainous terrains. The MAV differs in flight characteristics from helicopters and fixed wings in many respects. In addition to enhancing thrust, the duct protects personnel from accidental contact with the spinning rotor. The purpose of the U.S. Army FCS and DARPA's OAV program is spurring development of a the VTOL ducted MAV. Today's MAVs are equipped with video/infrared cameras to hover-and-stare at enemies hidden behind forests and hills for approximately one hour surveillance and reconnaissance. Class-I is a VTOL ducted MAV developed in size and weight that individual soldiers can store in their backpacks. Class-II is the development of an organic VTOL ducted fan MAV with twice the operating time and a wider range of flight than Class-I. MAVs will need to develop to perch-and-stare technology for lengthy operation on the current hover-and-stare. The near future OAV's concept is to expand its mission capability and efficiency with a joint operation that automatically lifts-off, lands, refuels, and recharges on the vehicle's landing pad while the manned-unmanned ground vehicle is in operation. A ducted MAV needs the development of highly accurate relative position technology using low cost and small GPS for automatic lift-off and landing on the landing pad. There is also a need to develop a common command and control architecture that enables the cooperative operation of organisms between a VTOL ducted MAV and a manned-unmanned ground vehicle.

• Journal of Advanced Navigation Technology
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• v.28 no.1
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• pp.95-101
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• 2024

This paper aims to establish a reconfigurable flight simulation environment to conduct safety evaluation of various electric vertical take-off and landing (eVTOL) aircraft. Since the inceptor, aircraft dynamics model, and controller applied to each eVTOL aircraft are different, it was configured to be variable so that a simulation can be executed for each eVTOL aircraft. Test elements and performance indicators were set to perform safety evaluation of eVTOL aircraft. Ground auxiliary equipments were designed and implemented in a simulation environment according to test procedures for each test element. In addition, to analyze safety performance, a simulation flight data collection environment based on MATLAB/Simulink and a tool for safety performance analysis were implemented. Test flight and analysis were conducted in the implemented simulation environment in this paper. Finally, this study shows the environment was verified by confirming that it was performed normally.