Aerothermoelastic analysis of hypersonic vehicles is a complex multidisciplinary coupling problem. Thus, accurate modeling of varying disciplines with low computational cost is necessary. This work developed a tractable approach-based reduced-order modeling technology to solve the radiative thermal transfer problem in a hypersonic simulation. A method that combines proper orthogonal decomposition and unassembled discrete empirical interpolation method is developed to construct the reduced-order modeling. First, high-dimensional original systems are projected on the optional basis generated by proper orthogonal decomposition, and the nonlinear term is further approximated by unassembled discrete empirical interpolation method. Then, a numerical integration method for the solution of the reduced system of nonlinear differential equations is provided. Case studies that use a classical hypersonic control surface model, in which the time history and spatial distribution of the thermal load are known a priori, are conducted to validate the accuracy and efficiency of the reduced-order modeling methodology and to assess the robustness of the reduced-order modeling for thermal solution. Results indicate the ability of reduced-order modeling to reduce the nonlinear system size with reasonable accuracy.

中文翻译：

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高超声速飞行器辐射传热的降阶模型

高超声速飞行器的气动热弹性分析是一个复杂的多学科耦合问题。因此，需要以低计算成本对不同学科进行准确建模。这项工作开发了一种基于易处理方法的降阶建模技术，以解决高超声速仿真中的辐射热传递问题。开发了一种结合适当正交分解和未组装离散经验插值方法的方法来构建降阶建模。首先，将高维原始系统投影到通过适当正交分解生成的可选基础上，并通过未组装的离散经验插值方法进一步逼近非线性项。然后，给出了求解非线性微分方程简化系统的数值积分方法。使用经典高超音速控制面模型的案例研究，其中热负荷的时间历程和空间分布是先验已知的，用于验证降阶建模方法的准确性和效率，并评估该模型的稳健性。热解的降阶建模。结果表明降阶建模能够以合理的精度减小非线性系统的规模。