非线性壁板颤振分析

doi:10.7527/S1000-6893.2014.0221

Abstract

Abstract:

Nonlinear panel flutter caused by the interaction between nonlinear fluid and geometrically nonlinear structure is studied by an improved computational fluid dynamics and computatienal structural dynamics (CFD/CSD) coupled program. A flux splitting scheme combined with implicit time marching technology and geometric conservation law is utilized to solve unsteady aerodynamic pressure; the finite element corotational theory is applied to modeling the geometric nonlinear two-dimensional and three-dimensional panels, and an approximate energy conservation algorithm is developed to obtain nonlinear structure response. The two solvers are connected by a second-order loosely coupled method and applied to the solution of panel flutter problems for supersonic, transonic and subsonic Mach numbers. A representative limited cycle oscillation appears when geometric nonlinearity and aerodynamic nonlinearity are considered. The flutter boundary and amplitude of limit cycle oscillation are discussed.

Key words: nonlinear aeroelasticity, limited cycle oscillation, panel flutter, geometrically nonlinearity, CFD/CSD coupled

CLC Number:

AN Xiaomin, XU Wei, XU Min. Analysis of nonlinear panel flutter[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(4): 1119-1127.

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Analysis of nonlinear panel flutter

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