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황승재,김상곤,이융교,Hwang, SeungJae,Kim, SangGon,Lee, YungGyo 항공우주시스템공학회 2016 항공우주시스템공학회지 Vol.10 No.1
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.
고고도 장기체공 태양광 무인기 EAV-3의 프로펠러 설계 및 성능해석
박동훈(Donghun Park),황승재(Seungjae Hwang),김상곤(Sanggon Kim),김철완(Cheolwan Kim),이융교(Yunggyo Lee) 한국항공우주학회 2016 韓國航空宇宙學會誌 Vol.44 No.9
고고도 장기체공 태양광 무인기 EAV-3의 프로펠러를 설계하고 전산해석을 수행하였다. 실험설계법(Design of Experiment, DOE)을 사용하여 설계변수들의 실험점들을 획득하고 목적함수와 구속함수들에 대한 크리깅 근사모델을 생성하였다. 요구조건 및 제약조건들과 함께 반응면을 평가하여 프로펠러 형상을 설계하였으며, 근사모델 기반의 최적설계를 수행하여 설계의 타당성을 검증하였다. 상용 CFD 코드를 이용하여 해석을 수행하고 그 결과를 설계코드 및 시험결과와 비교하였다. 설계점 고도에서 해석 결과가 설계코드의 예측과 잘 일치하였다. 또한 시험장치와 지지대 기둥에 의한 폐쇄효과가 풍동시험 결과에 포함되어 있으며, 이를 포함한 해석 결과가 시험 결과와 잘 일치함을 확인하였다. Design and performance analysis of propeller for solar-powered HALE UAV, EAV-3 are conducted. Experiment points of design variables are obtained by using Design of Experiment(DOE) and Kriging meta-model is generated for objective and constraints function. The geometry of propeller is designed by evaluating the response surface with requirement and restrictions. The validity of the design is verified by meta-model based optimization. Computational analyses are carried out by using commercial CFD code and the results are compared with those from a design code and wind tunnel test. The results showed good agreement with predictions of the design code at the design altitude. Also, it is confirmed that the blockage effect due to the measurement device and support strut is included in the test data and the results including this effect compare well with the test data.