• Title/Summary/Keyword: 장기체공

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Research on Dual Flight Control System for High Altitude Long Endurance UAV (고고도 장기체공 무인기의 비행제어시스템 이중화에 대한 연구)

  • An, Seok-Min;Kim, Seong-Uk;Yu, Hyeok
    • 한국항공운항학회:학술대회논문집
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    • 2015.11a
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    • pp.55-58
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    • 2015
  • 고고도 장기체공 무인기는 일반적인 무인기와 달리 고고도에서의 환경과 장시간의 체공에 따른 위험도가 높을 수밖에 없다. 따라서 신뢰도를 높이기 위한 다양한 방안을 강구해야 한다. 가장 중요한 요소 중 하나가 비행제어시스템이며, 본 논문에서는 비행제어시스템의 이중화에 따른 설계결과와 비행시험결과를 기술하였다.

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Structural Analysis of Fasteners in the Aircraft Structure of the High-Altitude Long-Endurance UAV (고고도 장기체공 무인기용 기체구조 체결부 구조 해석)

  • Kim, Hyun-gi;Kim, Sung Joon;Kim, Sung Chan;Kim, Tae-Uk
    • Journal of Aerospace System Engineering
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    • v.12 no.1
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    • pp.35-41
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    • 2018
  • Unmanned Aerial Vehicles (UAV) have been used for various purposes in multiple fields, such as observation, communication relaying, and information acquisition. Nowadays, UAVs must have high performance in order to acquire more precise information in larger amounts than is now possible while performing for long periods. At present, domestically, a high-altitude long-endurance UAV (HALE UAV) for long-term flight in the stratosphere has been developed in order to replace some functions of the satellite. In this study, as a part of structural soundness evaluation of the aircraft structure developed for the HALE UAV, the structural soundness of the fasteners of the fuselage and tail is evaluated by calculating the margin of safety(M.S). The result confirms the validity of the design of the fasteners in the aircraft structure of the UAV.

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

  • Bong, Jae-Hwan;Jeong, Seong-Kyun
    • The Journal of the Korea institute of electronic communication sciences
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    • v.17 no.3
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    • pp.433-440
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    • 2022
  • High Altitude Long Endurance(HALE) solar powered UAV is the vehicle that flies for a long time as solar power energy sources. It can be used to replace satellites or provide continuous service because it can perform long-term missions at high altitudes. Due to the property of the mission, it is very important for HALE solar powered UAV to have maximum flight time. It is required for mission performance to fly at high altitudes continuously except a return for temporary maintenance. Therefore mission availability time analysis is a critical factor in the commercialization of HALE solar powered UAV. In this paper, we presented an analytic model and logic for available time analysis based on the design parameters of HALE solar powered UAV. This model can be used to analyze the possibility of applying UAV according to the UAV's mission in concept design before the UAV detail design stage.

Multidisciplinary Design Optimization(MDO) of a Medium-Sized Solar Powered HALE UAV Considering Energy Balancing (에너지 균형조건을 고려한 중형 태양광 추진 고고도 장기체공 무인기의 다분야 통합 최적설계)

  • Park, Kyung-Hyun;Min, Sang-Gyu;Ahn, Jon;Lee, Dong-Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.40 no.2
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    • pp.129-138
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    • 2012
  • A MDO study of a midium-sized solar powered High Altitude Long Endurance (HALE) UAV has been performed, focused on energy balance. In the MDO process, Vortex Lattice Method(VLM) is employed for the aerodynamic modeling of the vehicle, of which structural weight is estimated with the modeling proposed by Cruz. Tail volume ratios have been set as constants, while the location of tail surfaces is determined from longitudinal static stability criterion. By balancing the available energy from solar cells, battery, and altitude, with the energy-requirement of the vehicle, the possibility of continuous flight over 24-hours has been investigated. The solar radiation level is set as that of summer at the latitude of $36^{\circ}$ north. During the daytime, the aircraft climbs using solar energy, accumulating potential energy, which supplements energy balance during the night. Optimizations have been sought in size of the vehicle, its weight distribution, and flight strategy.

Test and Simulation of An Engine for Long Endurance Miniature UAVs (장기체공 소형 UAV용 엔진 성능시험 및 시뮬레이션)

  • Shin, Young-Gy;Chang, Sung-Ho;Koo, Sam-Ok
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.33 no.5
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    • pp.99-105
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    • 2005
  • Development of an engine with good fuel economy is very important for successful implementation of long endurance miniature UAVs (unmanned aerial vehicles). In the study, a 4-stroke glow-plug engine was modified to a gasoline-fueled spark-ignition engine. Engine tests measuring performance and friction losses were conducted to tune a simulation program for performance prediction. It has been found that excessive friction losses are caused by insufficient lubrication at high speeds. The simulation program predicts that engine power and fuel economy get worse with high altitude due to increasing portion of friction losses. The simulation results suggest quantitative guidelines for further development of a practical engine.

Multi-Stage Turbocharger Gasoline IC Engine Simulation for HALE UAV (고고도 장기체공 무인기 적용을 위한 다단 터보차저 가솔린 엔진 시스템 시뮬레이션)

  • Kang, Seungwoo;Bae, Choongsik;Lim, Byeungjun
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.1
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    • pp.101-107
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    • 2019
  • This study conducted a simulation to observe the performance of a multi-turbocharged gasoline internal combustion engine for a high-altitude long-endurance unmanned aerial vehicle (HALE UAV). The WAVE 1-D engine simulation software from Ricardo was used for the engine system modeling and simulation. The specifications of a 2.4-L four cylinder gasoline engine from commercial vehicles and maps of commercial vehicle turbochargers were applied to the multi-stage turbocharged engine system model. Three turbochargers and intercoolers were installed in series for the appropriate intake of pressure for the gasoline engine at a high altitude of 60,000 ft. There was one wastegate for the turbochargers. The operability of the engine system was analyzed via this simulation model.

Design of Guidance Law and Lateral Controller for a High Altitude Long Endurance UAV (고고도 장기체공 무인기의 유도 및 방향축 제어 알고리즘 설계)

  • Koo, Soyeon;Lim, Seunghan
    • Journal of Aerospace System Engineering
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    • v.13 no.2
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    • pp.1-9
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    • 2019
  • This paper elaborates on the directional axis guidance and control algorithm used in mission flight for high altitude long endurance UAV. First, the directional axis control algorithm is designed to modify the control variable such that a strong headwind prevents the UAV from moving forward. Similarly, the guidance algorithm is designed to operate the respective algorithms for Fly-over, Fly-by, and Hold for way-point flight. The design outcomes of each guidance and control algorithm were confirmed through nonlinear simulation of high altitude long endurance UAV. Finally, the penultimate purpose of this study was to perform an actual mission flight based on the design results. Consequently, flight tests were used to establish the flight controllability of the designed guidance and control algorithm.

Reverse-Engineering and Analysis of Performance for Medium-Altitude Long Endurance Unmanned Aerial Vehicle (중고도-장기체공 무인비행을 위한 비행체 성능 분석 및 역설계)

  • Shim, Ho-Joon;Chang, Kyoungsik;Chung, In Jae;Kim, Sun-Tae;Joh, Chang-Yeol
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.44 no.6
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    • pp.520-529
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    • 2016
  • The main purpose of this study was to analyze the performance of a medium-altitude long endurance unmanned aerial vehicle through reverse-engineering method. The external configuration data of the RQ-1 Predator was reverse-engineered from related photos and specification data available on public domains, which also were used to generate the CATIA modeling and weigh distribution data of the UAV. The aerodynamic characteristics of RQ-1 Predator were mainly predicted the vortex lattice method and an empirical method, which the propeller performance was analyzed by the empirical method proposed by Howe. The rate of climb, service ceiling, range, and the loiter endurance of the UAV was analyzed, which showed good agreement with the reference data.

A Study on the Development of Low-Altitude and Long-Endurance Solar-Powered UAV from Korea Aerospace University (3) - Flight Test Results and Analysis of Solar Powered UAV - (한국항공대학교 저고도 장기체공 태양광 무인기 개발에 관한 연구 (3) - 태양광 무인기 비행실험 결과 및 분석 -)

  • Kim, Doyoung;Kim, Taerim;Jeong, Jaebaek;Park, Sanghyuk;Bae, Jae-Sung;Moon, Seokmin
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.50 no.7
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    • pp.489-496
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    • 2022
  • This paper introduces the system for KAU-SPUAV, which is designed and developed by Korea Aerospace University, and verifies its performance through flight test. Specification of two versions of KAU-SPUAV, avionics system, and Ground Control System (GCS) are introduced. Three missions are performed with suggested UAVs: LTE signal mapping, circumnavigation of Jeju island seashore, and long endurance flight. Each mission consists of long distance and long endurance flight which takes advantage of KAU-SPUAV. Research team of KAU-SPUAV confirmed its versatility through suggested flight data. Also based on flight results, the team found the potential of performance improvement of KAU-SPUAV.

A Study on the Development of Low-Altitude and Long-Endurance Solar-Powered UAV from Korea Aerospace University (1) - System Design of a Solar Powered UAV with 4.2m Wingspan - (한국항공대학교 저고도 장기체공 태양광 무인기 개발에 관한 연구 (1) - 주익 4.2m 태양광 무인기 시스템 설계 -)

  • Jeong, Jaebaek;Kim, Doyoung;Kim, Taerim;Moon, Seokmin;Bae, Jae-Sung;Park, Sanghyuk
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.50 no.7
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    • pp.471-478
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    • 2022
  • This paper is about research and development of Korea Aerospace University's Solar-Powered UAV System that named of KAU-SPUAV, and describes the design process of the 4.2 m solar UAV that succeeded in a long flight of 32 hours and 19 minutes at June 2020. In order to improve the long-term flight performance of the KAU-SPUAV, For reduce drag, a circular cross-section of the fuselage was designed, and manufactured light and sturdy fuselage by applying a monocoque structure using a glass fiber composite material. In addition, a solar module optimized for the wing shape of a 4.2 m solar drone was constructed and arranged, and a propulsion system applied with the 23[in] × 23[in] propeller was constructed to improve charging and flight efficiency. The developed KAU-SPUAV consumes an average of 55W when cruising and can receive up to 165W of energy during the day, and its Long-term Endurance was verified through flight tests.