HIRENASD机翼静气弹问题的数值模拟方法研究

Research on numerical simulation method for HIRENASD wing static aeroelastic

跨音速状态下由于激波、附面层干扰影响,使得流动控制方程非线性,导致线性化的气动弹性分析方法无法准确对机翼静气动弹性进行分析。针对弹性机翼跨声速非线性静气动弹性问题,本文采用三维可压N-S方程为控制方程,基于双向流固耦合分析方法,以HIRENASD机翼为研究对象,对不同攻角、不同Mach数下的静气动弹性变形进行数值模拟,通过仿真分析,得到了不同攻角、Mach数对弹性机翼变形及应力特性的影响规律,并分析了非线性静气动弹性对机翼纵向气动特性的影响,可为相关飞行器的结构设计提供一定的依据。

In the transonic flow,due to the influence of shock wave and surface layer interference,the flow control equation is nonlinear,with the linear aeroelastic analysis method not accurately analyzing the static aeroelastic of the wing.Aiming at the problem of transonic nonlinear static aeroelastic of elastic wing,the three-dimensional compressible N-S equation is used as the governing equation.The two-way fluid-solid coupling analysis method is used to simulate the static aeroelastic deformation of HIRENASD elastic wing with different angles of attack and different Mach numbers.Through the simulation analysis,the influence curves of different angles of attacks and the Mach numbers on the deformation and stress characteristics of the elastic wing are obtained with the influence of nonlinear static aeroelasticity on the longitudinal aerodynamic characteristics of the wing analyzed,providing a certain basis for the structure design of the relevant elastic aircraft.