끝단질량이 부착된 복합재료 날개의 진동특성

Abstract

The analysis of vibration characteristics including the natural frequencies and modes for various shaped composite wings with tip mass and engine has been performed using the finite element method based on the shear deformable theory. The present analysis presents the effect of sweptback angle. fiber orientation and aspect ratio of a composite wing on vibration characteristics. The wing is composed of graphite/epoxy laminate with symmetric stacking sequence. In case of [θ2/0]s composite wing, bending-torsion modes are highly coupled in the range of 15°-30 for fiber orientation θ. As θ increases, the lowest mode, which can always be characterized as first bending, reduces due to the decrease in spanwise bending stiffness. The present finite element method which uses 8-node quadrilateral elements give very accurate results.