高超声速全机外形气动加热与结构传热快速计算方法

李佳伟; 王江峰; 程克明; 伍贻兆

doi:10.7638/kqdlxxb-2017.0192

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高超声速全机外形气动加热与结构传热快速计算方法

研究论文 | 更新时间：2026-05-28

- 高超声速全机外形气动加热与结构传热快速计算方法
- Rapid method for calculating aero-heating coupled with structure heat transfer on hypersonic vehicles
- 空气动力学学报 2019年37卷第6期页码：956-965
- 作者机构：
  
  南京航空航天大学航空学院,江苏,南京,210016
- 作者简介：
  
  李佳伟(1992-), 男, 湖北天门人, 博士, 主要从事高超声速力/热/结构多场耦合研究.E-mail:ljwnuaa2010@nuaa.edu.cn
  王江峰(1970-), 男, 江苏南京人, 博士, 教授, 主要从事高超声速空气动力学与高温气体动力学.E-mail:wangjf@nuaa.edu.cn
- 基金信息：
  
  国家高技术研究发展计划（2012AA7060102）;国家自然科学基金（90716031）;江苏省研究生科研与实践创新计划（KYCX17_0235）
- DOI：10.7638/kqdlxxb-2017.0192
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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李佳伟, 王江峰, 程克明, 伍贻兆. 高超声速全机外形气动加热与结构传热快速计算方法[J]. 空气动力学学报, 2019, 37(6): 956-965.

LI Jiawei, WANG Jiangfeng, CHENG Keming, et al. Rapid method for calculating aero-heating coupled with structure heat transfer on hypersonic vehicles[J]. 2019, 37(6): 956-965.
李佳伟, 王江峰, 程克明, 伍贻兆. 高超声速全机外形气动加热与结构传热快速计算方法[J]. 空气动力学学报, 2019, 37(6): 956-965. DOI： 10.7638/kqdlxxb-2017.0192.

LI Jiawei, WANG Jiangfeng, CHENG Keming, et al. Rapid method for calculating aero-heating coupled with structure heat transfer on hypersonic vehicles[J]. 2019, 37(6): 956-965. DOI： 10.7638/kqdlxxb-2017.0192.

摘要

发展了一种无黏流场解与工程计算方法相结合的高超声速全机外形气动加热与结构传热快速计算方法。该计算方法结合了三维块结构网格无黏流场数值计算技术可处理复杂外形流动的优点与工程计算方法效率高的特点，将气动热的计算简化为绕飞行器的无黏外流（边界层以外）数值解和边界层内热流求解两个部分，同时耦合了防热结构传热计算模型、高温化学非平衡热效应估算方法以及弹道状态动态插值方法，可用于快速计算与分析三维复杂外形高超声速飞行器在弹道飞行状态下全机热环境参数、防热结构内温度场等随飞行时间的变化特性。以RAM-CII、类X-37B等典型高超声速飞行器为研究对象，在设定的飞行条件及热防护方案下，进行了气动加热与结构传热问题的求解，给出了全机表面热流密度与防热结构材料温度的时变特性。结果对比表明，所发展的方法具有快速、高效的特点，且计算精度可满足工程设计初期选型需求，可为高超声速飞行器的热防护系统初期设计及热环境特性快速计算分析提供技术支持。

Abstract

A new rapid method is presented for computing aero-heating coupled with structural temperature field of thermal protection structure (TPS) for hypersonic vehicles. This method includes the numerical solution of inviscid flow and empirical method for aero-heating. In this method

the calculation of aerodynamic heating is simplified into two parts: the numerical solution of inviscid flow (outside the boundary layer) around the aircraft and the empirical solution of heat flux inside the boundary layer. It has the advantages of dealing with flow over the complex configurations in numerical simulation and high efficiency in the engineering calculation. Furthermore

the present method also considers the effects of high temperature chemical non-equilibrium

the heat transfer process in thermal protection structure

and the dynamic interpolation method of trajectory flight state. These considerations can highly efficiently analyze the flow field around the complex hypersonic vehicles

as well as the characteristics of thermal environment and heat-insulation structure temperature distribution with flying time. Numerical method developed in this paper is applied to solve hypersonic fluid-structural-thermal coupled problems for hypersonic RAM-CII and X-37B configuration under flight conditions based on thermal protection system layout. The distributions of temperature and heat flux are obtained and the time-variant characteristics are analyzed. The calculation results show that the rapid computing technology is credible and can be used for the analysis of thermal protection systems and aerodynamic heating characteristics in hypersonic vehicles design.

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Keywords

references

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