中文摘要：

提出了一种适用于飞行器初步设计和详细设计阶段的静气动弹性响应分析方法。基于该方法进行静气动弹性响应分析时三维气动力单独求解,再与结构进行耦合计算。在初步设计阶段气动力可选取由Euler方程、N-S方程或高阶面元法计算,详细设计阶段气动力可选取风洞试验气动力。该文对一大展弦比机翼进行了静气动弹性响应分析,算例中使用CFD方法计算气动力,用以提供各种状态的刚性气动力;再将气动力通过插值分配到线性气动力网格或结构有限元模型上;并最终通过线性化方法对平衡状态附近的气动力进行弹性化处理。还将分析结果与适用于初步设计阶段初期的基于线性气动力的分析结果进行了对比。结果表明：两者在气动力分布和气动力系数方面存在较大的差别,但在宏观的剪力、弯矩分布方面差别较小,基于三维气动力分析结果可以作为初步设计阶段参考。

英文摘要：

A method is provided to obtain static aeroelastic responses in the early and detailed design stages of aircrafts.Based on this approach,three-dimensional aerodynamic forces are calculated independently,and then coupled with the structure.The aerodynamic forces can be computed with Euler solver,Navier-Stokes solver or High-order panel method in the early stage and provided by wind-tunnel tests in the detailed stage.The method is applied to obtain static aeroelastic responses of a high-aspect-ratio wing in this study.The rigid aerodynamic forces of different flight conditions are calculated with CFD tools and transmitted to linear aerodynamic grids or structural grids.Finally,the rigid aerodynamic forces of equilibrium are flexibilized with a linear aerodynamic influence coefficient matrix.The results are compared with static aeroelastic reponses calculated based on linear aerodynamic forces generally used in early design stage.It could be concluded that there is great difference in aerodynamic forces distribution and aerodynamic coefficients,small difference in macroscopical distribution of shear and bending moment.The method of this study is intended to provide an assessment of static aeroelastic effects in early design process stage of the aircraft.