Journal of the Korean Society for Aeronautical & Space Sciences (한국항공우주학회지)

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Minimization of the Bending Deflection of the Human-powered Aircraft Wing Induced by Change of an Incidence Angle

인간동력항공기의 붙임각 변화에 따른 날개 끝단 굽힘변위 최소화 연구

  • Received : 2018.08.13
  • Accepted : 2019.01.29
  • Published : 2019.02.01
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Abstract

Human-powered aircraft has wings with a shape of high aspect ratio which results in large bending displacement. This paper aims to improve the structural limitation by changing an incidence angle of the wings. The tendency change of bending displacement at the wing tip is observed assuming that airfoil and cross-sectional shape of the wing is fixed, and amount of the total lift generated is satisfied. Quasi-steady lift, drag and the aerodynamic moment are distributed with regard to sections of the wing. Those are analyzed using a numerical nonlinear lifting-line method and 'geometrically exact beam' (GEB) program in EDISON. 'Variational Asymptotic Beam Sectional Analysis' (VABS) program is used to check if the present wing is structurally solid. Furthermore, the predicted tip deflections are verified by comparing with DYMORE.

인간동력항공기의 날개는 고세장비의 형상을 가지고 있어 큰 굽힘변위가 발생한다. 본 논문에서는 고세장비 형상의 날개가 가지는 구조적인 한계를 붙임각을 변경함으로써 개선하고자 하였다. 날개의 익형 및 단면형상을 고정시킨 후 동일 수준의 양력 발생을 만족시킨다는 전제하에 붙임각의 변경에 따른 날개 끝단의 굽힘변위 변화 경향을 관측하였다. 이를 위해 유한날개의 양력, 항력, 모멘트 하중을 날개의 각 섹션에 분포시켰다. 그리고 EDISON의 "geometrically exact beam (GEB)" 프로그램과 "Variational Asymptotic Beam Sectional Analysis (VABS)" 단면해석 프로그램을 사용하여 변경된 설계안의 구조 안전도를 평가하였다. 또한, 다물체 동역학 해석 프로그램 DYMORE를 이용하여 본 논문에서 예측한 날개의 끝단 변위 예측값을 비교 검증하였다.

Keywords

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