Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Electric power Small fixed wing UAV Aerodynamic performance Analysis

전기 동력 소형 고정익 무인항공기 공력성능 연구

  • Jeong, Seongrok (The 2nd Team of Aeronautical Center, Defence Agency for Technology and Quality)
  • 정성록 (국방기술품질원 항공센터 항공 2팀)
  • Received : 2018.08.06
  • Accepted : 2018.12.25
  • Published : 2019.02.28
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Abstract

In this paper, the performance of a small fixed wing unmanned aerial vehicle is predicted theoretically with the minimum specifications and a low Reynolds number. Based on the results, it was compared with the results of an actual flight test and simple electric motor wind tunnel test. As a result of the validity of the analysis, a 3.5 kilograms class fixed wing small UAV can predict aerodynamic performance by general theory analysis. However, the required thrust was analyzed as a possible design error. Based on the results of this study, this paper proposed a method to minimize the design error when developing small fixed wing UAV flying in a low Reynolds number.

본 연구에서는 전기 동력 소형 고정익 무인항공기의 낮은 레이놀즈 영역 및 최소한의 제원으로 운용에 필요한 성능을 일반적인 이론 분석으로 예측하였다. 이를 간단한 전기모터 풍동시험과 실증 비행시험을 통해 비교 분석하여 이론 분석의 타당성을 확인하였다. 분석한 결과의 타당성 확인 결과, 3.5 kg의 고정익 소형 무인항공기는 일반적인 이론분석으로 공력 성능의 분석이 가능하지만, 필요추력은 설계오류가 발생할 가능성이 있는 것으로 확인된다. 이러한 연구 결과를 바탕으로 낮은 레이놀즈 영역에서 비행하는 유사 소형 고정익 무인항공기 개발 시 설계오류를 최소화 하는 방법을 제안하였다.

Keywords

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Fig. 1 Small UAV

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Fig. 2 lift to drag ratio

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Fig. 3 Thrust system wind tunnel test

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Fig. 5 Take off velocity

Table 1 Small UAV specification

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Table 2 Aerodynamic performance

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Table 3 Thrust test result(1)

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Table 4 Take off velocity measured by flight test

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Table 5 Cruising Speed measured by flight test

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