AEROELASTIC ANALYSIS FOR A THREE-DIMENSIONAL STRUCTURALLY NONLINEAR WING WITH A CONTROL SURFACE

摘要

In this paper, aeroelastic analysis for a three-dimensional semi-monocoque, but structurally nonlinear wing with a control surface is attempted. An equivalent plate analysis (EPA) is used to reduce the problem size for a three-dimensional semi-monocoque main wing which consists of the skin, spar, and rib and a thin solid control surface. The main wing and control surface are connected by torsional springs, and the extended component mode synthesis is used to combine these two separate components with torsional springs. The first-order shear deformation theory of plates was the basis of the present equivalent plate analysis, and a finite element method was applied to solve it. A panel-based commercial program ZAERO is adopted to calculate generalized unsteady aerodynamic forces. Flutter analyses are performed combining ZAERO and present EPA. It is confirmed that the predicted results are moderately accurate for flutter speed and frequency.