柔性后缘可变形机翼气动弹性分析方法研究

Research on the Aeroelastic Analysis Method of Flexible Trailing Edge Morphing Wing

高精度可变形机翼气动弹性分析通常采用计算流体力学(CFD)方法计算非定常气动力,然而CFD计算量大、耗时多,不便于开展气动弹性分析。本文提出一种基于气动力降阶模型的柔性后缘可变形机翼气动弹性分析方法,在保证计算精度的同时,大幅提高气动弹性分析效率。基于带外输入的自回归气动降阶分析方法建立柔性后缘可变形机翼气动力状态空间模型,与结构状态空间模型相耦合,得到整个柔性后缘可变形机翼气动弹性系统的状态空间模型,用于计算柔性后缘可变形机翼的颤振特性和阵风响应。研究结果表明,随着后缘偏角的增大,颤振马赫数相比无偏角情况有一定的提高。

CFD method is usually used to calculate unsteady aerodynamic forces for high-precision aeroelastic analysis of morphing wings.However,CFD is not convenient for aeroelastic analysis due to its large amount of calculation and time-consuming.In this paper,an aeroelastic analysis method of flexible trailing edge morphing wing based on aerodynamic reduced order model is proposed,which can greatly improve the efficiency of aeroelastic analysis while ensuring the calculation accuracy.Based on the autoregressive with eXogeneous input(ARX)aerodynamic order reduction analysis method,the state space model of the aerodynamics of the flexible trailing edge morphing wing is established.Coupled with the structural state space model,the state space model of the aeroelastic system of the entire flexible trailing edge morphing wing is obtained,which is used to calculate the flutter characteristics and gust response of the flexible trailing edge morphing wing.The results show that the flutter Mach number increases with the increase of the trailing edge deflection angle.