基于多点约束的大展弦比机翼静气动弹性计算

基于雷诺平均N-S方程和多块结构网格技术计算大展弦比机翼的气动力.机翼采用梁模型结构,利用有限元方法计算结构变形.建立基于多点约束(MPC,Multi-Point Constrain)的气动、结构数据的双向传递方法.采用MPC数据插值方法快捷地实现自主研发的计算流体力学(CFD,Computational Fluid Dynamics)程序和NASTRAN计算结构力学(CSD,Computational Structural Dynamics)软件的耦合计算,发展出可以考虑结构非线性的静气动弹性CFD/CSD耦合计算方法,该方法比只考虑单方向变形的柔度法更精确.开展了某大展弦比机翼的静气动弹性数值计算分析,结果显示只考虑机翼纵向变形而忽略展向变形对计算结果会有一定影响,而该算例几何非线性影响较小.

MPC based static aeroelastic numerical method for high aspect ratio wing

The steady aerodynamic loads were calculated with N-S equations and the multi-block structured grid technique was used to improve the computational efficiency. A beam model was applied to a high aspect ratio wing, and its structural deformations were evaluated by the finite element method with or without geometry nonlinearity. A multi-point constrain (MPC) method was used for the information exchange between the aerodynamic loads calculations and the structure deformations calculations. The static aeroelasticity was further considered. By successive iterations between self-developed computational fluid dynamics (CFD) solver and NASTRAN computational structural dynamics (CSD) software based on the MPC interpolation method, a quick and accurate coupled CFD-CSD method was achieved for the nonlinear static aeroelastic problem. Obviously the present method is more accurate than the conventional flexibility approach only considering single-direction deformation. Numerical analysis of a high aspect ratio wing demonstrates that spanwise deformation would have certain influence on its static aeroelastic characteristics and that geometric nonlinearity has small effect on this common airliner wing.