• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2014년도 추계학술대회 논문집
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• pp.189-192
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• 2014

Recently, development of electric powered UAV for high altitude and long endurance mission has been conducted worldwide. Long endurance requirement necessitates high lift over drag (L/D) aerodynamic characteristics and lightweight structures, leading to highly flexible wings with high aspect ratio. These highly flexible wings increase the danger of catastrophic aircraft failure due to flutter, which is a dynamic aeroelastic instability occurring from the interaction of aerodynamic, inertial, and elastic forces acting on the aircraft flying through the air. In this paper, flexible wing for electric powered UAV whose skin is fabricated using mylar film for lightweight design is briefly explained. In addition, flutter analysis procedures and results for the flexible wing in order to substantiate the aeroelastic stability requirements are presented.

• 한국태양에너지학회:학술대회논문집
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• 한국태양에너지학회 2012년도 춘계학술발표대회 논문집
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• pp.313-318
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• 2012

In the present study, the preliminary study on a small solar-powered RC airplane are performed for the development of a long-endurance solar-powered UAV. Solar energy enables the solar-powered UAV to fly longer or eternally. The solar-powered UAV transfers the solar energy to electric energy and this energy is used for the flight and the battery charge. To increase the flying time, the efficiency of the solar-cell power system must be increased and the required power for flight must be minimized. Hence, the system integration including solar cell and controller, the power system design, and the aerodynamic and structural designs of the UAV is very important. The present study have performed the design, manufacture, and flight test of the small solar-powered UAV for the preliminary study of the long-endurance solar-powered UAV. From this study, the system integration technology of the solar-powered UAV design is established, and the possibility and the issue points for the development of the long-endurance solar-powered UAV are discussed.

• 신재생에너지
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• 제7권3호
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• pp.59-66
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• 2011

Recently, an UAV using green energy for propulsion has been developed due to exhaustion of fossil fuel. This aircraft runs on electric motors rather than internal combustion engines, with electricity coming from fuel cells, solar cells, ultracapacitors, and/or batteries. Especially solar cells are installed in HALE UAV and flight tests are performed in the stratosphere. Although the solar powered UAV has the advantage of zero emission, its energy conversion efficiency is low and operation time is limited. Therefore, the solar powered UAV has been designed to operate with the secondary battery obtaining flexibility of energy management. In this study, we suggest the new operational concept of the solar powered UAV using directed-energy rayed from the surface of earth to UAV. An UAV is able to secure additional power through attaching solar cell to the lower surface of elevator. As a result, the additional energy supplied by directed-energy can improve the energy management and operational flexibility of the solar powered UAV.

• 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.

• International Journal of Aeronautical and Space Sciences
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• 제17권1호
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• pp.132-138
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• 2016

Korea Aerospace Research Institute (KARI) is developing an electric-driven HALE UAV in order to secure system and operational technologies since 2010. Based on the flight tests and design experiences of the previously developed electric-driven UAVs, KARI has designed EAV-3, a solar-powered HALE UAV. EAV-3 weighs 53kg, the structure weight is 22kg, and features a flexible wing of 19.5m in span with the aspect ratio of 17.4. Designing the main wing and empennage of the EAV-3 the amount of the bending due to the flexible wing, 404mm at 1-G flight condition based on T-800 composite material, and side wind effects due to low cruise speed, $V_{cr}=6m/sec$, are carefully considered. Also, unlike the general aircraft there is no center of gravity shift during the flight because of the EAV-3 is the solar-electric driven UAV. Thus, static margin cuts down to 28.4% and center of gravity moves back to 31% of the Mean Aerodynamic Chord (MAC) comparing with the previously designed the EAV-2 and EAV-2H/2H+ to upgrade the flight performance of the EAV-3.

• 한국항공우주학회지
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• 제41권11호
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• pp.908-914
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• 2013

본 연구에서는 소형 태양광 무인항공기를 개발하여 비행시험을 수행하였다. 태양광 무인기는 날개에 설치된 태양전지로부터 전력을 생산하고, 생산된 전력의 일부를 비행동력으로 사용하며, 나머지를 일몰 후 비행을 위해 배터리에 저장을 한다. 태양광 무인항공기는 공기역학적으로 매우 효율이 높아야 하며, 구조적으로 경량이면서 고강도를 가져야 한다. 또한, 태양광 무인기의 전기추진시스템과 태양광 발전시스템도 높은 효율을 가져야 한다. 본 연구에서는 12시간 이상의 연속 비행을 위한 태양광 무인항공기 및 태양광 시스템을 개발하고, 그 성능을 파악하기 위해 비행시험을 수행하였다. 가을과 겨울철의 비행시험 결과 본 연구에서 개발한 태양광 무인항공기의 사계절 모두 12시간 이상의 연속비행이 가능함을 알 수 있었다.

• 항공우주기술
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• 제12권1호
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• pp.1-9
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• 2013

태양전지 및 전기동력을 이용한 장기 체공 무인기의 체공 효율을 증가시키기 위해서는 구조 경량화가 필수적이다. 본 논문에서는 24시간 장기체공 전기동력 무인항공기인 EAV-2H의 주익 경량화 및 구조 건전성 확보를 위하여 Mylar Film과 섬유강화 복합재료로 구성된 주익을 설계하였다. 보이론 해석을 이용하여 주익 Spar의 형상 선정 및 구조 사이징을 수행하였다. EAV-2H 임무를 고려하여 하중해석을 수행하고 주익의 주요 구성품에 대해 유한요소해석을 수행하였다. 마지막으로 주익의 정적구조시험을 통해 주익의 구조 건전성을 확인하였다. 본 연구를 통하여 개발된 EAV-2H 주익은 이전 모델인 EAV-2에 비교하여 Span 기준 42%의 중량이 감소되었으며, 설계극한하중을 부가하는 정적구조시험을 통과하였다.

• 한국항공운항학회지
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• 제23권1호
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• pp.24-29
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• 2015

In order to increase endurance flight efficiency of long endurance electric powered UAV, main wing of UAV should have high aspect ratio and low structural weight. Since a spar which consists of thin and slender structure for weight reduction can cause catastrophic failure during the flight, it is important to develop verification method of structural integrity of the spar with the light weight design. In this paper, process of structural analysis using non-linear finite element method was introduced for the verification of structural integrity of the spar. The static strength test of the spar was conducted to identify structural characteristic under the static load. Then, the experimental result of the spar was compared to the analytical result from the non-linear finite element analysis. It was found that the developed process of structural analysis could predict well the non-linear structural behavior of the spar under ultimate load.

• 한국추진공학회지
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• 제17권4호
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• pp.49-55
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• 2013

한국항공우주연구원 (이하 항우연)에서 개발중인 중형 전기동력 무인기 EAV2의 추진시스템에 대한 비행시험결과에 대하여 기술 하였다. EAV2는 날개 길이 6.9 m, 무게 18 kg의 저속 장기 체공형 무인기이다. 전기 동력원으로는 태양전지, 연료전지, 배터리의 세 가지를 동시에 사용한다. EAV2는 2012년 6월에 22시간 이상 체공 비행에 성공하였다. 시험 결과, 전기추진 시스템은 비행 중 일어나는 여러 상황에서 필요한 동력을 성공적으로 공급하였으며, 각 동력원들은 설계된 목적에 부합하게 작동되었다.

• 항공우주시스템공학회지
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• 제10권1호
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• pp.59-65
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• 2016

Korea Aerospace Research Institute (KARI) is developing an electric-driven HALE UAV in order to secure system and operational technologies since 2010. Based on the 5 years of flight tests and design experiences of the previously developed electric-driven UAVs, KARI has designed EAV-3, a solar-powered HALE UAV. EAV-3 weighs 53 kg, the structure weight is 21 kg, and features a flexible wing of 19.5 m in span with the aspect ratio of 17.4. Designing the main wing and empennage of the EAV-3 the amount of the bending due to the flexible wing, 404 mm at 1-G flight condition based on T-800 composite material, and side wind effects due to low cruise speed, V_cr = 6 m/sec, are carefully considered. Also, unlike the general aircraft there is no center of gravity shift during the flight. Thus, the static margin cuts down to 28.4% and center of gravity moves back to 31% of the Mean Aerodynamic Chord (MAC) comparing to the previously developed scale-down HALE UAVs, EAV-2 and EAV-2H, to minimize a trim drag and enhance a performance of the EAV-3. The first flight of the EAV-3 has successfully conducted on the July 29, 2015 and the test flight above the altitude 14 km has efficiently achieved on the August 5, 2015 at the Goheung aviation center.