本文選題：高超聲速　切入點：降階模型　出處：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：高超聲速飛行器的熱氣動彈性問題是當(dāng)今氣動彈性領(lǐng)域的重要發(fā)展方向之一,相關(guān)研究涉及了計算空氣動力學(xué)、計算結(jié)構(gòu)動力學(xué)、計算熱力學(xué)等多個領(lǐng)域,通常采用CFD/CTD/CSD耦合計算方法求解經(jīng)典的流固熱多場耦合問題。本文在全面回顧高超聲速熱氣動彈性發(fā)展過程及其分析方法的基礎(chǔ)上,提出了一種包含氣動力和熱流的新的降階方法。本文的主要工作如下:首先建立典型高超聲速飛行器翼面的流場和結(jié)構(gòu)模型,并研究了適合于該飛行條件下的氣動力、氣動熱降階模型。詳細闡述了ARMA/ROM的模型建立、訓(xùn)練數(shù)據(jù)獲取、參數(shù)識別及其在氣動彈性分析中的運用,并與CFD計算結(jié)果進行對比驗證該方法的正確性和合理性。其次通過參考焓方法對翼面氣動熱計算進行降階。結(jié)果表明,對于本文模型,ARMA/ROM能高效高精度地辨識氣動力、同時修正后的參考焓理論能較好的擬合氣動熱。最后將上述氣動力和氣動熱的降階模型運用于高超聲速熱氣動彈性的雙向耦合分析。在氣動加熱過程中的任一時刻,對結(jié)構(gòu)施加微小擾動,求解該時刻結(jié)構(gòu)的全瞬態(tài)響應(yīng)。引入溫度模態(tài),將微小溫度變化分解到各階溫度模態(tài)上。在各階溫度模態(tài)下進行氣動力訓(xùn)練得到相應(yīng)的ARMA模型,線性疊加后獲得以溫度模態(tài)為基礎(chǔ)的ARMA降階模型。耦合修正后的參考焓方法,實現(xiàn)了針對氣動生熱過程中任一時刻的全瞬態(tài)響應(yīng)求解。結(jié)果證明,該方法能有效提高全瞬態(tài)計算效率。
[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.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V211.47

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