Rapid method for calculating aero-heating coupled with structure heat transfer on hypersonic vehicles

LI Jiawei; WANG Jiangfeng; CHENG Keming; WU Yizhao

doi:10.7638/kqdlxxb-2017.0192

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Rapid method for calculating aero-heating coupled with structure heat transfer on hypersonic vehicles

更新时间：2026-05-28

- Rapid method for calculating aero-heating coupled with structure heat transfer on hypersonic vehicles
- Vol. 37, Issue 6, Pages: 956-965(2019)
- 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：
- 基金信息：
- DOI：10.7638/kqdlxxb-2017.0192
  CLC： V211.3
- Published：2019
- 稿件说明：
移动端阅览
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.

关键词

Keywords

references

WANG J F, WU Y Z. Progress in numerical simulation techniques of hypersonic aerodynamic problems[J]. Acta Aeronautics et Astronautics Sinica, 2015, 36(1): 159-175. (in Chinese)

CHENG K M, LYU Y W. An analysis of coupling feature in continuing gasdynamic heating over flight vehicles[J]. Journal of Nanjing University of Aeronautics and Astronautics, 2000, 32(2): 150-155. (in Chinese)

卞荫贵, 徐立功.气动热力学[M].合肥:中国科技大学出版社, 1997: 15-20.

SINHA K K, REDDY D S. Effect of chemical reaction rates on aeroheating predictions of reentry flows[J]. Journal of Thermophysics and Heat Transfer, 2011, 25(1): 21-33.

HAMILTON H H, WEILMUENSTER K J, DEJARNETTE F R. Approximate method for computing convective heating on hypersonic vehicles using unstructured grids[J]. Journal of Spacecraft and Rockets, 2014, 1288: 1305.

ZOBY E V, MOSS J N, SUTTON K. Approximate convective-heating equations for hypersonic flows[J]. Journal of Spacecraft and Rockets, 1981, 18(1): 64-70.

TIAN X A, WANG C P, CHENG K M. Experimental investigation of dynamic characteristics of oblique shock train in Mach 5 flow[J]. Journal of Propulsion Technology, 2014, 35(8): 1030-1039. (in Chinese)

DONG W Z, GAO T S, DING M S. Numerical study of coupled surface temperature distribution and aerodynamic heat for hypersonic vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1): 311-324. (in Chinese)

YANG K, YUAN Z C, ZHU Q H, et al. Numerical simulation of hypersonic thermochemical nonequilibrium blunt body flows[J]. Journal of Propulsion Technology. 2014, 35(12): 1585-1591. (in Chinese)

XIA G, LIU X J, CHENG W K, et al. Numerical simulation of coupled aeroheating and solid heat penetration for a hypersonic blunt body[J]. Journal of National University of Defense Technology, 2003, 25(1): 35-39. (in Chinese)

GENG X R, ZHANG H X, SHEN Q, et al. Study on an integrat-ed algorithm for the flowfields of high speed vehicles and the heat transfer in solid structures[J]. Acta Aerodynamica Sinica, 2002, 20(4): 422-427. (in Chinese)

ZHANG S T, CHEN F, LIU H. Fluid-thermal-structural coupling analysis on leading edge of hypersonic inlets[J]. Acta Aerodynamica Sinica, 2017, 35(3): 436-443. (in Chinese)

ZHAO J S, GU L X, MA H Z. A rapid approach to convective aeroheating prediction of hypersonic vehicles[J]. Science China Technological Sciences, 2013, 56(8): 2010-2024.

LI H P. The calculation and analysis of aerodynamic heating distributions for the hypersonic aircrafts[D]. Shanghai: Shanghai Jiao Tong University, 2010. (in Chinese)

HAMILTON H H, WEILMUENSTER K J, DEJARNETTE F R. Approximate method for computing laminar and turbulent convective heating on hypersonic vehicles using unstructured grids[C]//41st Annual AIAA Thermophysics Conference, 2009. AIAA 2009-4310.

ZOBY E V, SIMMONDS A L. Engineering flowfield method with angle-of-attack applications[J]. Journal of Spacecraft and Rockets, 1985, 22(4): 398-404.

LE J L, GANIMEDOV V L, MUCHNAJA M I, et al. The calculations of aerodynamic heating and viscous friction forces on the surface of hypersonic flight vehicle[J]. Journal of Experiments in Fluid Mechanics, 2002, 16(1): 8-20. (in Chinese)

LIJ L, TANG Q G, HUO L, et al. The rapid engineering aero-heating calculation method for complex shaped hypersonic vehicles[J]. Journal of National University of Defense Technology, 2012, 34(6): 89-93. (in Chinese)

CHEN J Q, TU G H, ZHANG Y F, et al. Hypersonic boundary layer transition: what we know[J]. Acta Aerodynamica Sinica, 2017, 35(3): 311-337. (in Chinese)

张志成, 主编.高超声速气动热和热防护[M].北京:国防工业出版社, 2003: 46-136.

卞荫贵, 钟家康.高温边界层传热[M].科学出版社, 1986.

QJ1734-89, 1989.

SHI K, WANG J F, LI J W. Numerical method of aerodynamic heating with heating with ablation effects for hypersonic vehicles[C]//2th China Aviation Science and Technology Conference, 2015.

TANG G Q. Calculating method of aerodynamic heating for hypersonic multi-body separation process[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2013. (in Chinese)

WU J, YAN C. Research on the coupling of aero-dynamic heating and thermal response[J]. Journal of Missiles and Space Vehicles, 2009, (4): 35-39. (in Chinese)

JI W D, WANG J F, TANG G Q. Calculating method of aerodynamic heating for hypersonic multi-body separation process[J]. Acta Aerodynamica Sinica, 2014, 32(6): 761-766. (in Chinese)

BOVA S W, HOWARD M A. Coupling strategies for high-speed aeroheating problems[R]. Sandia National Laboratories, 2011.

WANG J. Calculating method of aerodynamic heating for hypersonic aircrafts[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2012. (in Chinese)

FAY J A. Theory of stagnation point heat transfer in dissociated air[J]. Journal of the Aerospace Sciences, 1958, 25(2): 73-85.

欧阳水吾, 谢中强.高温非平衡空气扰流[M].北京:国防工业出版社, 2003.

DUNN M G. Theoretical and experimental studies of reentry plasmas[R]. NASA CR-2232, 1973.

JOSEPB W C. Effect of angle of attack and blunt ness on laminar heating-rate distributions of a 15° cone at mach number of 10.6[R]. NASA TN D-5450, 1969.

ZHOU J W, LI J C, SHI Z G, et al. Research of infrared detectability of hypersonic vehicle[J]. Journal of Acta Optica Sinica, 2015, 35(5): 1-8. (in Chinese)

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Statistical characteristics of high-temperature turbulent boundary layer considering chemical non-equilibrium effect

Influence of cavities on hypersonic boundary layer transition

Overview of wall functions for compressible turbulent boundary layers

Progresses in engineering application research on hypersonic flow stability and transition

Application of NPLS technique in the researches on hypersonic boundary layer transition

Related Author

LIU Pengxin

LI Chen

SUN Dong

FU Yalu

YUAN Xianxu

YANG Qiang

FENG Shuo

WANG Bofu

Related Institution

State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang

Computational Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang

Shanghai Institute of Applied Mathematics and Mechanics, School of Mechanics and Engineering Science, Shanghai University, Shanghai

National Key Laboratory of Aerospace Flight Aerodynamics Science and Technology, Mianyang

China Academy of Launch Vehicle Technology, Beijing

AI问答

⁰