力学学报 ›› 2010, Vol. 42 ›› Issue (6): 1023-1033.doi: 10.6052/0459-1879-2010-6-lxxb2009-568

• 研究论文 • 上一篇    下一篇

跨音速极限环型颤振的高效数值分析方法

张伟伟1,王博斌2,叶正寅1   

  1. 1. 西北工业大学翼型、叶栅国防科技重点实验室
    2. 清华大学航天航空学院
  • 收稿日期:2009-09-14 修回日期:2009-11-16 出版日期:2010-12-10 发布日期:2010-12-02
  • 通讯作者: 张伟伟 E-mail:aeroelastic@nwpu.edu.cn

High efficient numerical method for lco analysis in transonic flow

1, 2,Zhengyin Ye1   

  1. 1. National Key Laboratory of Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China
    2. School of Aerospace, Tsinghua University, Beijing 100084, China
  • Received:2009-09-14 Revised:2009-11-16 Online:2010-12-10 Published:2010-12-02

摘要: 事先建立一个低阶的非线性、非定常气动力模型是开展非线性流场中气动弹 性问题研究的一个捷径. 基于CFD方法, 通过计算结构在流场中自激振动的响应来获得系统 的训练数据. 采用带输出反馈的循环RBF神经网络, 建立时域非线性气动力降阶模型. 耦合结构运动方程和非线性气动力降阶模型, 采用杂交的线性多步方法计算结构在不同速度(动 压)下的响应历程, 从而获得模型极限环随速度(动压)变化的特性. 两个典型的跨音速极 限环型颤振算例表明, 基于气动力降阶模型方法的计算结果与直接CFD仿真结果吻合很好, 与后者相比 其将计算效率提高了1~2个数量级.

关键词: RBF神经网络

Abstract: Non-linearities can be present in an aeroelastic system due to some aerodynamic phenomena that occur in transonic flight regime or at large angles of attack. The candidate sources are motions of shock wave and separated flow. With the recently well-developed software and hardware technologies, numerical simulation of complex aeroelasticity phenomena becomes possible, such as limit cycle oscillations (LCOs) due to the aerodynamic nonlinearity. However, the computational cost of solving aeroelastic problem in nonlinear flow field is very high, so it is a convenient method to solve this kind of problem by constructing a proper unsteady aerodynamic model previously. Many research works are carried out in reduced order modeling (ROM) for aeroelastic analysis. Most of the reduced order aerodynamic models are dynamic linear models and in proportion to the structural motions. In this study, by using Radial Basis Function (RBF) neural network model, the nonlinear unsteady reduced order aerodynamic model is constructed. The ROM is used to analyze LCOs behaviors for two linear structural models with large shock motion in transonic flow. Different from the traditional design method of the input signals, signals of self-excited vibration of the aeroelastic system are designed as the input signals in this paper. Coupled the structural equations of motion and nonlinear aerodynamic ROM, the system responses are determined by time marching of the governing equations using a kind of hybrid linear multi-step algorithm and the limit cycle behaviors changing with velocities (dynamic pressure) can be analyzed. Two transonic aeroelastic examples show that both the structural responses and the limit cycle oscillation (LCO) characteristics simulated by ROM agree well with those obtained by direct CFD method, and the computational efficiency of ROM based method can be improved by 1-2 orders of magnitude compared with the direct CFD method.

Key words: RBF neural network model

中图分类号: 

  • V211.47