The Study of Nonlinear Flutter Analysis Method for an Aircraft Full Composite Wing with High-aspect-ratio

摘要

A nonlinear flutter analysis method using CFD/CSD was presented in this paper. The computational method couples a nonlinear finite element method model with CFD solver. The structural analysis was based on a 4-node thin shell element and a new corotational (CR) formulation, which can be employed to analyze geometric nonlinearities arising from large deflections. The expression of tangent stiffness equations under geometric nonlinear structure was derived. Aerodynamic load was calculated by CFD solver with the Navier-Stokes equations as the control equations. This paper showed that the geometric nonlinear method is computationally high efficient and good agreement by examined. The geometric nonlinear method can be successfully applied for the nonlinear flutter analysis to full composite wing with high-aspect-ratio. The flutter speed of the composite wing is near 0.65Ma.