오일러 방정식을 이용한 무힌지 로우터 블레이드의 정지 비행시 정적 공탄성 해석

Abstract

The static aeroelastic characteristics of hingeless rotor blades in hover are investigated using Euler equations. Finite elements based on a large deflection beam theory are used for structural analysis. A three-dimensional flow field of a helicopter rotor in hover is calculated by using Euler equations described in a body-fixed rotating coordinate frame. No wake modeling is included but the wake is calculated as a part of the solution of the overall flow field. Comparison of the numerical results in the subsonic and transonic region show good agreements with the experimental data. Numerical results of the steady-state deflections for the rotor blade are presented and compared with those based on the panel method. The difference between two results increases as the collective pitch angle increases It is found that the aerodynamic wake dynamics effect plays an important role in steady-state tip deflections for the hingeless rotor blades in hover.