高速飞行器高温绕流流场辐射特性研究-2026增刊2

doi:10.7527/S1000-6893.2026.34011

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高速飞行器高温绕流流场辐射特性研究-2026增刊2

刘向阳¹,刘元春¹,田川²,苗萌³,段毅⁴

1. 北京临近空间飞行器系统工程研究所
2. 空间物理重点实验室
3. 北京空间物理重点实验室
4. 中国运载火箭技术研究院空间物理重点实验室

收稿日期:2026-06-01 修回日期:2026-07-23 出版日期:2026-07-24 发布日期:2026-07-24
通讯作者: 段毅
基金资助:
临近空间高速飞行器尾流场光谱特性研究

Research on the radiation characteristics of high-temperature flow field around high-speed vehicles

Received:2026-06-01 Revised:2026-07-23 Online:2026-07-24 Published:2026-07-24
Contact: Yee DUAN

摘要/Abstract

摘要： 研究临近空间高速飞行器高温绕流流场对飞行器壁面的辐射特性具有重要意义，在气动热环境预示、光辐射噪声预示等方面有重要应用。本文基于高温热化学非平衡Navier-Stokes方程和辐射传输方程，以RAM-C钝锥为研究对象，针对高空高速飞行状态，分析了高温绕流流场对不同壁面位置的辐射特性，包括端头顶点、迎背风子午线、底面中心。研究结果表明，在高空高马赫数状态下，钝锥前体压缩区及尾迹区流场均处于非平衡状态，不同壁面位置的辐射特性存在显著差异。在钝锥顶点，空气离解产生大量N、O原子和NO分子，总辐照度主要由原子辐射机制和NO分子辐射机制组成，占比分别为22.14%、73.98%；在钝锥其他位置，空气离解程度显著降低，原子辐射机制对总辐照度的贡献不足5%，超过90%的辐照度来自NO分子。尾迹流场对钝锥底面中心的辐射强度远低于其他位置，相较顶点低了三个数量级，且辐亮度与视角方位(由极角、方位角定义)、波段密切相关。计算结果表明，极角45°、方位角90°、600~700 nm波段尾迹流场对底面中心的辐亮度最低。

关键词: 高速飞行器, 高温绕流流场, 热化学非平衡, 尾迹流场, 辐射特性

Abstract: Investigating the radiation characteristics of high-temperature flow fields around near-space vehicles holds critical significance, with key applications in aerothermal environment prediction, optical radiation noise estimation and related fields. This study employs the thermochemical nonequilibrium Navier-Stokes equations and the radiation transfer equation, taking the RAM-C blunt cone as the study object to analyze the radiation characteristics at different surface positions (including the stagnation point, windward/leeward meridians, and base center) under high-altitude and high-speed flight conditions. The results indicate that, under high-altitude and high-speed conditions, the flow fields in the compression zone ahead of the blunt cone and its wake region are both in a non-equilibrium state, with significant differences in radiation characteristics across different surface positions. At blunt cone apex, the dissociation of air components generates significant amounts of N atoms, O atoms and NO molecules, with the total irradiance predominantly composed of atomic radiation mechanisms and NO molecular radiation mechanisms, accounting for 22.14% and 73.98%, respectively. At other locations on the blunt cone surface, the degree of air dissociation is significantly reduced, with the atomic radiation mechanism contributing less than 5% to the total irradiance, while over 90% of the irradiance originates from NO molecules. The radiation intensity at the base center of blunt cone is significantly lower than other positions, being three orders of magnitude weaker compared to the apex. Additionally, the radiance is strongly dependent on the viewing aspect (defined by polar and azimuthal angles) and spectral band. The calculation results show that the lowest radiance at the base center occurs along the direction 45° polar angle and 90° azimuthal angle within the 600~700 nm spectral band.

Key words: high-speed vehicle, high-temperature flow field, thermochemical non-equilibrium effect, wake flow field, radiation characteristic

中图分类号:

V411.4

刘向阳刘元春田川苗萌段毅. 高速飞行器高温绕流流场辐射特性研究-2026增刊2[J]. 航空学报, doi: 10.7527/S1000-6893.2026.34011.

参考文献

[1]杜耀文, 孙素蓉, 黄河激, 孟显, 曹进文, 耿金越, 闫聪, 王海兴. 高超声速非平衡流动?辐射特性数值模拟研究[J]. 力学学报, 2023, 55(12): 2807-2817.
[2]BRETT A C, RAMON M, JAY H G, JOSEPH O. Simultaneous Vacuum Ultraviolet through Near IR Absolute Radiation Measurement with Spatiotemporal Resolution in an Electric Arc Shock Tube[C]//41st AIAA Thermophysics Conference, San Antonio, Texas, USA, June 22-25, 2009.
[3]BRANDIS A M, CRUDEN B A. Benchmark Shock Tube Experiments of Radiative Heating Relevant to Earth Re-entry[C]//55th AIAA Aerospace Sciences Meeting Grapevine, Texas, USA, January 9-13, 2017.
[4]CORNETTE E S. Forebody Temperatures and Calorimeter Heating Rates Measured During Project FIRE II Reentry at 11.35 Kilometers per Second[R]. NASA TM X-1305, Nov. 1966.
[5]CAUCHON D L. Radiative Heating Results from the FIRE II Flight Experiment at a Reentry Velocity of 11.4 Kilometers per Second[R]. NASA TM X-1402, July 1967.
[6]ERDMAN P W, ZIPF E C, ESPY P, et al. Flight Measurements of Low-Velocity Bow Shock Ultraviolet Radiation[J]. Journal of Thermophysics and Heat Transfer, 1993, 7(1): 37-41.
[7]ERDMAN P W, ZIPF E C, ESPY P, et al. Measurements of Ultraviolet Radiation from a 5-km/s Bow Shock[J]. Journal of Thermophysics and Heat Transfer, 1994, 8(3): 441-446.
[8]WHITING E E, PARK C, LIU Y, et al. NEQAIR96, Nonequilibrium and Equilibrium Radiative Transport and Spectra Program: User's Manual[R]. NASA RP-1389, 1996.
[9]JOHNSTON C O. Nonequilibrium Shock-Layer Radiative Heating for Earth and Titan Entry[D]. Ph.D. Dissertation, Virginia Tech, 2006.
[10]HARTUNG L C. Development of a Nonequilibrium Radiative Heating Prediction Method for Coupled Flowfield Solutions[J]. Journal of Thermophysics and Heat Transfer, 1992, 6(4): 618-625.
[11]WRIGHT M J, CANDLER G V, BOSE D. Data-Parallel Line Relaxation Method for the Navier-Stokes Equations[J]. AIAA Journal, 1998, 36(9): 1603-1609.
[12]GNOFFO P A, GUPTA R N, SHINN J L. Conservation Equations and Physical Models for Hypersonic Air Flows in Thermal and Chemical Nonequilibrium[R]. NASA TP-2867, 1989.
[13]BRANDIS A M, JOHNSTON C O, CRUDEN B A, et al. Validation of High Speed Earth Atmospheric Entry Radiative Heating from 9.5 to 15.5 km/s[C]//43rd AIAA Thermophysics Conference, New Orleans, Louisiana, June 25-28, 2012.
[14]BRANDIS A M, JOHNSTON C O. Characterization of Stagnation-Point Heat Flux for Earth Entry[C]//45th AIAA Plasmadynamics and Lasers Conference, Atlanta, June 16-20, 2014.
[15]GREENDYKE R B, HARTUNG L C. Convective and Radiative Heat Transfer Analysis for the Fire II Forebody[J]. Journal of Spacecraft and Rockets, 1994, 31(6): 986-992.
[16]OLYNICK D R, HENLINE W D, CHAMBERS L H, et al. Comparison of Coupled Radiative Flow Solutions with Project Fire II Flight Data[J]. Journal of Thermophysics and Heat Transfer, 1995, 9(4): 586-594.
[17]JOHNSTON C O, BRANDIS A M. Features of Afterbody Radiative Heating for Earth Entry[J]. Journal of Spacecraft and Rockets, 2015, 52(1): 105-119.
[18]JOHNSTON C O, PANESI M, BRANDIS A M. Advancements in Afterbody Radiative Heating Simulations for Earth Entry[R]. NASA technical paper: NASA NF1676L-22846, 2016.
[19]JOHNSTON C O. Including Radiative Heating for the Design of the Orion Backshell for Artemis-1: A Narrative[C]//AIAA SCITECH 2025 Forum, 2025.
[20]闵昌万, 苗萌. 高速飞行器尾部观星窗口选择研究[J]. 航空兵器, 2021, 28 (5): 1-6.
[21]JONES, W L, CROSS A E. Electrostatic Probe Measurements of Plasma Parameters for Two Re-entry Flight Experiments at 25000 feet per-second[R]. NASATIC D-6617, 1972.
[22]PARK C. Assessment of two-temperature kinetic model for air[J]. Journal of Thermophysics and Heat Transfer, 1989, 3(3): 233-244.
[23]MILLIKAN R C, WHITE D R. Systematics of vibrational relaxation[J]. Journal of Chemical Physics, 1963, 39(12): 3209-3213.
[24]ENGEL C D. Ablation and radiation coupled viscous hypersonic shock layers, volume 2[R]. NASA technical paper: NASA-CR-112307 73N24310, 1973.
[25]PARK C, JAFFE R L, PARTRIDGE H. Chemical-kinetic parameters of hyperbolic earth entry[J]. Journal of Thermodynamics and Heat Transfer, 2001, 15(1): 76-90.
[26]ROE P. Approximate riemann solvers, parameter vectors, and difference schemes[J]. Journal of Computational Physics, 1981, 43(2):357-372.
[27]YEE H C. On symmetric and upwind TVD schemes[R]. NASA technical report: NASA TM-88325, 1986.
[28]MAZAHERI A, JOHNSTON C O, SEFIDBAKHT S. Three-dimensional radiation ray-tracing for shock-layer radiative heating simulations[J]. Journal of Spacecraft and Rockets, 2013, 50(3): 485-493.
[29]JOHNSON C O, HOLLIS B R, SUTTON K. Spectrum modeling for air shock-layer radiation at Lunar-return conditions[J]. Journal of Spacecraft and Rockets, 2008, 45(5): 865-878.
[30]PATCH R W, SHACKLEFORD W L, PENNER S S. Approximate spectral absorption coefficient calculations for electronic band systems belonging to diatomic Molecules[J]. Journal of quantitative spectroscopy and radiative transfer, 1962, 2(3): 263-271.
[31]NIU Q L, HE Z H, DONG S K. Prediction of shock-layer ultraviolet radiation for hypersonic vehicles in near space[J]. Chinese Journal of Aeronautics, 2016, 29(5): 1367-1377.
[32]DAVID H, JOSEPH O, MICHAEL W, et al. FIRE II calculations for hypersonic nonequilibrium aerothermodynamics code verification: DPLR, LAURA, and US3D[C]//45th AIAA Aerospace Sciences Meeting and Exhibit. Nevada, USA, 2007:605.
[33]穆磊, 马宇, 贺志宏, 董士奎. 高速钝锥体非平衡绕流场光辐射特性模拟[J]. 工程热物理学报, 2012, 33(11): 1958-1962.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

高速飞行器高温绕流流场辐射特性研究-2026增刊2

Research on the radiation characteristics of high-temperature flow field around high-speed vehicles

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