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高速飞行器在运行过程中其表面承受严苛的气动热环境，因此气动热热流密度是热管理系统设计的重要输入。然而，在方案设计初期，存在计算网格量大、耦合计算复杂、方案迭代周期快等难点。本文提出一种基于FLUENT用户自定义函数（UDF）的三维球锥体冷却结构与气动热耦合响应快速仿真方法。该方法无需构建外流场，在有效减少网格数量的情况下，可获得高速飞行器气动热热流密度三维分布。为验证方法的有效性，将已开展风洞试验且内部设有冷却通道的模型设定为研究对象，对比分析了采用本文方法、传统仿真方法以及试验获得的气动加热效果。结果表明，3种方法获得的煤油出口温度误差在5%以内，固体监测点温度曲线趋势一致，结果较为接近。本文提出的仿真方法，能够有效实现高速球锥体飞行器气动加热效果，提高计算效率，为热管理系统热载荷计算提供重要输入。
Abstract：The surface of high-speed aircraft is subjected to severe aerodynamic heat, and the aerodynamic heat flux density is an important input for the design of thermal management systems. However, in the early stage of scheme design, there exist difficulties such as large computational grid, complex coupled calculations, and fast iteration cycles of the scheme. In this paper, a three-dimensional coupled response cooling structure and aerodynamic thermal rapid simulation method is proposed based on FLUENT userdefined function(UDF) for spherical cone aircraft. It is not required to construct the external flow field by using the three-dimensional simulation model. The three-dimensional distribution of aerodynamic thermal flux density of high-speed aircraft can be obtained by using the method while the number of grids can be effectively reduced. In order to verify the effectiveness of the method, a simulation model with internal cooling channels that has been tested by wind tunnel is taken as the research object. The aerodynamic heating effects obtained by using the method proposed in this paper, traditional simulation methods, and experiments are compared and analyzed. The results showed that the temperature error of the kerosene outlet obtained by the three methods is within 5%, and the trend of the solid monitoring point temperature curve is consistent. The simulation method proposed in this paper can effectively achieve the aerodynamic heating effect of high-speed spherical cone aircraft, improve calculation efficiency, and provide important input for thermal load calculation of thermal management systems.
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基本信息:
DOI：10.16338/j.issn.2097-0714.20250068
中图分类号:V211;V411.8
引用信息:
[1]王立志,吴韬,戎毅.高速球锥体飞行器气动热-冷却结构耦合响应快速三维仿真方法研究[J].空天技术,2026,No.470(02):94-101.DOI:10.16338/j.issn.2097-0714.20250068.
基金信息:
高端压缩机及系统技术全国重点实验室(2025011245)
2026-04-15
2026-04-15