• 제목/요약/키워드: High-Performance UAV

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Performance of UAV(Unmanned Aerial Vehicle) Communication System Using Civil Wireless Mobile Networks

  • Lee, Byung-Seub
    • 한국위성정보통신학회논문지
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    • 제12권1호
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    • pp.43-48
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    • 2017
  • Recently, demands on civilian UAV (Unmanned Aerial Vehicle) has been increasing and appropriate communication system is required for the UAV. In this paper, the performance of the UAV communication system using commercial wireless mobile network is discussed. The main service area of the wireless mobile network is ground level however the flying range of the UAV is normally in high altitude. Because of this mismatch of service area the performance of the UAV communication system is degraded in high altitude. To compensate performance degradation of the UAV communications system in high altitude, adaptive array antenna is introduced which is able to overcome altitude limitation of the UAV communication system.

Design and Implementation of UAV System for Autonomous Tracking

  • Cho, Eunsung;Ryoo, Intae
    • KSII Transactions on Internet and Information Systems (TIIS)
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    • 제12권2호
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    • pp.829-842
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    • 2018
  • Unmanned Aerial Vehicle (UAV) is diversely utilized in our lives such as daily hobbies, specialized video image taking and disaster prevention activities. New ways of UAV application have been explored recently such as UAV-based delivery. However, most UAV systems are being utilized in a passive form such as real-time video image monitoring, filmed image ground analysis and storage. For more proactive UAV utilization, there should be higher-performance UAV and large-capacity memory than those presently utilized. Against this backdrop, this study described the general matters on proactive software platform and high-performance UAV hardware for real-time target tracking; implemented research on its design and implementation, and described its implementation method. Moreover, in its established platform, this study measured and analyzed the core-specific CPU consumption.

무인항공기용 고분자전해질형 연료전지 시스템의 열교환기 성능 특성 연구 (Experimental Study on the Characteristics of Heat Exchanger of 1 kW PEMFC System for UAV)

  • 강상규;김병준;김한석
    • 한국수소및신에너지학회논문집
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    • 제22권6호
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    • pp.819-826
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    • 2011
  • The proton exchange membrane fuel cell (PEMFC) is regarded as the most promising alternative power sources for unmanned aerial vehicle (UAV) due to its high energy density and silent operation. Since there are many load changes during UAV flight, thermal management is one of the important factor for the performance of PEMFC. In order to reduce the UAV weight for the stable operation of UAV, thermal management system (TMS) studied in this work does not use the fan but use the air flowing into UAV by UAV flight. In order to develop the passive type heat exchanger (HEX) for 1kW PEMFC, four types of HEXs are fabricated and their cooling performances are compared. The parametric study on the cooling performance of HEXs has performed with the variation of operating parameters such as mass flow rates and inlet temperature of air and coolant. Type 4 has the best performance in every case. This study can be helpful to achieve the optimal design of HEX for PEMFC powered UAV.

고고도 장기체공 무인기 동체 및 미익부 구조해석 (Structural Analysis of Fuselage and Empennage of High Altitude Long Endurance UAV)

  • 김현기;김성준;김성찬;신정우;이승규;박상욱;김태욱
    • 한국항공운항학회지
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    • 제24권4호
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    • pp.35-43
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    • 2016
  • UAV has been promoted for practical use in the field of civilian and military. Recently, UAV is required high-specification performance such as long-term flight and precision observation. Among these UAVs, High Altitude Long Endurance UAV(HALE UAV) has been developed for the purpose to replace some of the functions of the satellite such as meteorological observation, communications and internet relay while flying a long period in the stratosphere. In order to fly a long period in harsh environment of the stratosphere, aircraft needs high Lift-Drag-Ratio and weight reduction of the structure. This paper performed the structural analysis for fuselage and empennage of HALE UAV. Critical loading conditions for structural analysis are acquired from flight load analysis and finally the results of structural sizing for weight reduction is presented.

Survey of Electro-Optical Infrared Sensor for UAV

  • Jang, Seung-Won;Kim, Joong-Wook
    • 항공우주산업기술동향
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    • 제6권1호
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    • pp.124-134
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    • 2008
  • The rising demand for the high efficiency and high covertness in UAV motivates the miniature design of the high performing mission sensors, or payloads. One of the promising payload sensors, EO/IR sensor has evolved satisfying its demands and became the main stand-alone mission sensor for 200kg-range UAV. One aspect in development of EO/IR sensor concerns lack of specification criterions to represent its performance. Even though the high demand and competition among each manufacturer caused EO/IR features subject to rapid change collateral to new technology, the datasheets maintained the conventional outdated formats which leave some of the major components in ambiguity. Making comparisons or predicting actual performance with such datasheets is hardly worthwhile; yet, they could be important reference guide for the potential customers what to expect for the upcoming EO/IR. According to UAS Roadmap 2007-2032 published by DoD, one of the main potential customers as well as a main investor of EO/IR technology, EO/IR is expected to play key roll in solving urgent problems, such as see and avoid system. This paper will examine the recent representative EO/IR specialized in UAS missions through datasheets to find out current trend and eventually extrapolate the possible future trend.

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무인 비행체용 저가의 ADGPS/INS 통합 항법 시스템 (Design of a Low-Cost Attitude Determination GPS/INS Integrated Navigation System for a UAV (Unmanned Aerial Vehicle))

  • 오상헌;이상정;박찬식;황동환
    • 제어로봇시스템학회논문지
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    • 제11권7호
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    • pp.633-643
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    • 2005
  • An unmanned aerial vehicle (UAV) is an aircraft controlled by .emote commands from ground station and/o. pre-programmed onboard autopilot system. A navigation system in the UAV provides a navigation data for a flight control computer(FCC). The FCC requires accurate and reliable position, velocity and attitude information for guidance and control. This paper proposes an ADGPS/INS integrated navigation system for a UAV. The proposed navigation system comprises an attitude determination GPS (ADGPS) receive., a navigation computer unit, and a low-cost commercial MEMS inertial measurement unit(IMU). The navigation algorithm contains a fault detection and isolation (FDI) function fur integrity. In order to evaluate the performance of the proposed navigation system, two flight tests were preformed using a small aircraft. The first flight test was carried out to confirm fundamental operation of the proposed navigation system and to check the effectiveness of the FDI algorithm. In the second flight test, the navigation performance and the benefit of the GPS attitude information were checked in a high dynamic environment. The flight test results show that the proposed ADGPS/INS integrated navigation system gives a reliable performance even when anomalous GPS data is provided and better navigation performance than a conventional GPS/INS integration unit.

SIMULINK를 이용한 CRW-type UAV 추진시스템의 동적 성능 모사에 관한 연구 (Dynamic Performance Simulation of the Propulsion System for the CRW-Type UAV Using SIMULINK)

  • 공창덕;박종하
    • 한국추진공학회지
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    • 제8권4호
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    • pp.76-83
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    • 2004
  • CRW Tyre UAV 추진시스템은 수직으로 이착륙이 가능하고 고정익으로 고속 전진 비행이 가능한 개념으로 설계되었다. 이를 위해 추진시스템은 이착륙 시에는 로터를 구동시켜 수직으로 비행하고 고속 비행 시에는 로터를 정지시켜 날개로 사용하고 가스발생기에서 생성된 가스를 주 노즐로 분사하여 본래의 제트엔진으로 사용한다. ICV방법과 SIMULINK를 이용하여 천이 성능 해석을 수행하였다. 연료유량은 터빈 입구온도의 스텝과 과온 현상을 피하기 위해 램프 증가를 하였고 이에 따른 추력의 변화와 터빈 입구온도의 변화를 살펴보았다.

고고도 장기체공 태양광 무인기의 운용 가용성 분석 모델 연구 (Operation Availability Analysis Model Development for High Altitude Long Endurance Solar Powered UAV)

  • 봉재환;정성균
    • 한국전자통신학회논문지
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    • 제17권3호
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    • pp.433-440
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    • 2022
  • 고고도 장기체공 태양광 무인기는 성층권에서 태양광을 에너지원으로 장기간 비행하며 임무를 수행하는 무인기를 의미하며 고고도에서 장기적으로 임무 수행이 가능하여 지역적으로 통신위성 대체, 군사적 목적으로 임시 통신망 구축, 지상 촬영을 통한 감시 정찰 기능 등으로 사용할 수 있다. 이런 임무특성상 임무 수행 가용시간을 분석하는 것은 무인기를 상용화하는 데 매우 중요한 요소이다. 하지만 고고도에서 태양광 전력의 획득은 운용 위도와 계절에 영향을 받고 여러 요소가 복합적으로 작용하여 가용일수의 분석이 쉽지 않다. 본 논문에서는 고고도 장기체공 무인기의 설계 파라미터를 바탕으로 가용시간의 분석 모델 및 로직을 제시하고 태양광 획득 조건에 따른 고고도 장기체공 태양광 무인기의 가용시간을 분석하였다.

Light Source Target Detection Algorithm for Vision-based UAV Recovery

  • Won, Dae-Yeon;Tahk, Min-Jea;Roh, Eun-Jung;Shin, Sung-Sik
    • International Journal of Aeronautical and Space Sciences
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    • 제9권2호
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    • pp.114-120
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    • 2008
  • In the vision-based recovery phase, a terminal guidance for the blended-wing UAV requires visual information of high accuracy. This paper presents the light source target design and detection algorithm for vision-based UAV recovery. We propose a recovery target design with red and green LEDs. This frame provides the relative position between the target and the UAV. The target detection algorithm includes HSV-based segmentation, morphology, and blob processing. These techniques are employed to give efficient detection results in day and night net recovery operations. The performance of the proposed target design and detection algorithm are evaluated through ground-based experiments.

전기동력 무인항공기의 추진시스템 효율 추정에 관한 연구 (Efficiency Estimation on Propulsion System of an Electric Powered UAV)

  • 안일영;양용만;주영철;박상혁;배재성
    • 한국항공운항학회지
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    • 제23권3호
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    • pp.1-7
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    • 2015
  • In the present study, we conducted the research on the high efficiency propulsion system for the development of long-endurance UAV with an electric propulsion system. For the long endurance UAV, fair aerodynamic characteristics with the high efficiency of the propulsion system is required because the flight power and the duration time of the long-endurance UAV vary greatly depending on the efficiency of the propulsion system. Therefore, in this study, the tracking program which records the performance of motor, propeller was developed because of their wide variation in the efficiency depending on the using condition, and records from the existing flight test program were utilized to check the accuracy of the program we had developed. For the development of future long-endurance solar UAV, we confirmed the applied voltage of motor, the optimal rotation of propeller and the gear ratio of reduction gear in order to get the highest efficiency on the propulsion system at the optimal flying condition.