高超声速环境下的气动力降阶模型研究

发布时间：2018-03-24 04:24

本文选题：高超声速　切入点：降阶模型　出处：《南京航空航天大学》2016年硕士论文

【摘要】：高超声速飞行器的热气动弹性问题是当今气动弹性领域的重要发展方向之一,相关研究涉及了计算空气动力学、计算结构动力学、计算热力学等多个领域,通常采用CFD/CTD/CSD耦合计算方法求解经典的流固热多场耦合问题。本文在全面回顾高超声速热气动弹性发展过程及其分析方法的基础上,提出了一种包含气动力和热流的新的降阶方法。本文的主要工作如下:首先建立典型高超声速飞行器翼面的流场和结构模型,并研究了适合于该飞行条件下的气动力、气动热降阶模型。详细阐述了ARMA/ROM的模型建立、训练数据获取、参数识别及其在气动弹性分析中的运用,并与CFD计算结果进行对比验证该方法的正确性和合理性。其次通过参考焓方法对翼面气动热计算进行降阶。结果表明,对于本文模型,ARMA/ROM能高效高精度地辨识气动力、同时修正后的参考焓理论能较好的拟合气动热。最后将上述气动力和气动热的降阶模型运用于高超声速热气动弹性的双向耦合分析。在气动加热过程中的任一时刻,对结构施加微小扰动,求解该时刻结构的全瞬态响应。引入温度模态,将微小温度变化分解到各阶温度模态上。在各阶温度模态下进行气动力训练得到相应的ARMA模型,线性叠加后获得以温度模态为基础的ARMA降阶模型。耦合修正后的参考焓方法,实现了针对气动生热过程中任一时刻的全瞬态响应求解。结果证明,该方法能有效提高全瞬态计算效率。
[Abstract]:The thermo-hydrodynamic elasticity of hypersonic vehicle is one of the most important development directions in the field of Aeroelasticity. The related research involves many fields, such as computational aerodynamics, computational structural dynamics, computational thermodynamics, etc. The classical fluid-solid thermal multi-field coupling problem is usually solved by CFD/CTD/CSD coupling method. Based on a comprehensive review of hypersonic thermal Aeroelastic development process and its analytical methods, A new order reduction method including aerodynamic and heat flow is proposed. The main work of this paper is as follows: firstly, the flow field and structure model of the wing surface of a typical hypersonic vehicle is established, and the aerodynamic force suitable for the flight condition is studied. In this paper, the establishment of ARMA/ROM model, the acquisition of training data, parameter identification and its application in Aeroelastic analysis are described in detail. Compared with the CFD calculation results, the method is proved to be correct and reasonable. Secondly, the aerodynamic heat calculation of the wing surface is reduced by the reference enthalpy method. The results show that the aerodynamic force can be identified efficiently and accurately by the ARMA / ROM model in this paper. At the same time, the modified reference enthalpy theory can fit the aerodynamic heat well. Finally, the reduced order model of aerodynamic force and aerodynamic heat is applied to the bidirectional coupling analysis of hypersonic thermal Aeroelasticity. The whole transient response of the structure is solved by applying small disturbance to the structure. The temperature mode is introduced and the tiny temperature variation is decomposed to each order temperature mode. The corresponding ARMA model is obtained by aerodynamic training under each order temperature mode. After linear superposition, the ARMA reduced order model based on the temperature mode is obtained. Coupled with the modified reference enthalpy method, the full transient response at any time during the aerodynamic heat generation process is solved. The results show that, This method can effectively improve the efficiency of all transient calculation.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V211.47

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