高アスペクト比複合材翼のダイバージェンス特性

概要

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The structural design of a light and highly rigid airplane is possible by use of aeroelastic tailoring of fiber reinforced composite materials. In this paper, the tailoring effects for divergence characteristics of high aspect ratio composite wing are investigated. In order to obtain precisely a large wing deflection caused by aerodynamic loads, the structural model is locally expressed by the Euler angles, and the structural and aerodynamic analyses are coupled. The structural and aerodynamic analyses are done by the finite difference method and by the lifting line theory, respectively. The spanwise lift distribution and the magnitude of wing deflection are obtained for high aspect ratio wing which is made by composite cantilever beam. The divergence speed is obtained from the velocity when a numerical solution diverges. As a result, it is showed that the fiber angle against composite beam axis has a great influence to divergence velocity, and if the composite structure is properly tailored, the divergence velocity is able to be high by a bending-torsional coupling effect.
東海大学の論文