Transient analysis method of aerothermoelasticity based on ARMA model

基于ARMA模型的瞬态热气动弹性分析方法

¹ School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
² National Key Laboratory of Aircraft Configuration Design, Xi'an 710072, China
³ Unmanned System Research Institute, Northwestern Polytechnical University, Xi'an 710072, China
⁴ National Key Laboratory of Unmanned Aerial Vehicle Technology, Xi'an 710072, China
⁵ Sichuan Tengden Technology Co., Ltd., Chengdu 610036, China

Received: 27 February 2025

Abstract

A novel time-domain method is introduced to address the challenges of aerothermoelastic analysis in the rapidly changing transient thermal environments for hypersonic vehicles. The present method strikes a balance between the computational accuracy and the efficiency. Firstly, the autoregressive moving average (ARMA) model is used to replace the aerodynamic simulations. Subsequently, a time-domain method for aeroelastic analysis is established by coupling the ARMA model and the modal superposition method. Thereafter, the aerodynamic heating is calculated by using the numerical method based on Euler equations in conjunction with the established engineering techniques. The transient thermal field is simulated by using the bidirectional coupling of aerodynamic heating, heat conduction and heat radiation. Finally, based on the hierarchical coupling strategy, an efficient and accurate time-domain method for aerothermoelastic analysis in the transient thermal environment is presented. This method utilizes the structural mode as a connecting hub between aeroelastic analysis and transient thermal field simulation. The performance of the present method for aerothermoelastic analysis is evaluated by using the hypersonic wing. Results indicate that computational efficiency is improved by about 3.5 times comparing with the aerothermoelastic analysis method that directly employs the RANS method for aerodynamic calculations. Meanwhile, the relative error in the thermal flutter boundary is below 12%.

摘要

针对时变性强的瞬态热环境下高超声速飞行器所面临的热气动弹性问题, 发展了一种兼顾计算精度与效率的瞬态热气动弹性时域分析方法。采用自回归滑动平均模型(autoregressive moving average, ARMA)进行非定常气动力降阶, 并耦合模态叠加法建立气动弹性时域分析方法; 结合基于Euler方程的数值方法与工程算法进行气动热高效计算, 并通过气动热-热传导-热辐射双向耦合实现瞬态热环境求解; 以结构热模态为枢纽实现气弹分析与热环境计算之间的单向耦合, 从而建立了瞬态热环境下的热气动弹性时域分析方法。针对高超声速机翼开展的热气弹分析算例表明: 相较于不使用降阶模型而直接采用RANS方法进行气动力计算的热气弹分析方法, 所建立的瞬态热气动弹性分析方法计算效率提升约3.5倍, 同时热颤振边界的相对误差控制在12%以内。