테이퍼를 갖는 복합재료 날개의 공탄성해석

Abstract

항공기 날개의 테이퍼 비가 공력탄성 안정성에 미치는 영향을 조사하였다. 일반적인 형상의 공탄성 해석에 적합한 유한요소법과 DPM을 이용하여 해석을 수행하였다. 알루미늄 날개와 복합재료 날개의 자유진동해석을 수행한 뒤 이 해석결과를 이용하여 플러터 속도 및 진동수를 계산하였다. 알루미늄 날개와 복합재료 날개 모두 플러터 모우드의 변화가 없다면 테이퍼 비가 감소함에 따라 플러터 속도는 증가하는 것으로 나타났다.

An effect of taper ratio on aeroelastic stability has been studied for aluminum and composite wings. Aeroelastic analyses utilize the finite element method and the doublet point method which are suitable for arbitrary wings. The flutter velocity and frequency are computed using the results from the free vibrational analysis for the aluminum and composite wings. The flutter velocity of the aluminum and composite wings increases as the taper ratio decreases as long as there is no change in flutter mode.

An effect of taper ratio on aeroelastic stability has been studied for aluminum and composite wings. Aeroelastic analyses utilize the finite element method and the doublet point method which are suitable for arbitrary wings. The flutter velocity and frequency are computed using the results from the free vibrational analysis for the aluminum and composite wings. The flutter velocity of the aluminum and composite wings increases as the taper ratio decreases as long as there is no change in flutter mode.