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| 基于气动力降阶模型的高超声速舵面颤振分析 |
| Flutter Analysis of Hypersonic Airfoil Based on Rudder Reduced Order Model |
| 投稿时间：2015-12-18 |
| DOI：10.16018/j.cnki.cn32-1650/n.201601008 |
| 中文关键词: 高超声速 降阶模型 颤振分析 状态空间 模态叠加 |
| 英文关键词: hypersonic reduced order model flutter analysis state space modal superposition |
| 基金项目: |
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| 中文摘要: |
| 采用自回归移动平均模型研究了高超声速环境下的气动力降阶问题，建立气动力降阶模型的状态空间形式，并与结构模态叠加法耦合进行时域颤振分析。采用频带宽度较佳的广义3211型位移输入作为训练输入，完成关键的训练过程并获得广义气动力系数作为训练输出；在此基础上利用MATLAB系统辨识工具箱进行ARMA模型的参数估计；最后完成气动力降阶模型的验证。结果表明，气动力ROM的建立过程简便可靠，一定程度上体现了工程应用特点，在定马赫数工况下，基于气动力ROM的颤振计算效率较传统的CFD方法显著提高。 |
| 英文摘要: |
| The study on aerodynamic reduced order problem in hypersonic environment is based on Autoregressive Moving Average(ARMA)method. Time-domain flutler analysis is carried out by establishing the state space form of aerodynamic ARMA/ROM and coupled with the structural modal superposition method. Firstly, generalized type 3211 displacement input is used as training input whose band width is better. The key training process is completed, and the general aerodynamic coefficient as the training output is obtained. On this basis the parameter estimation of ARMA models is carried out by using MATLAB system identification toolbox. Finally, the verification of aerodynamic reduced order model is completed. The results show that the establishment process of aerodynamic ROM is simple and reliable, and to some extent, it reflects the characteristics of engineering application. In the working condition of limiting Mach number, the flutter calculation efficiency which is based on the aerodynamic ROM is significantly increased than the traditional CFD method. |
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