考虑稀薄效应的再入飞行器前缘热化学反应与烧蚀模型研究

汪旭; 肖天白; 张勇豪; 陈松

doi:10.7638/kqdlxxb-2024.0173

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考虑稀薄效应的再入飞行器前缘热化学反应与烧蚀模型研究

研究论文 | 更新时间：2026-05-28

- 考虑稀薄效应的再入飞行器前缘热化学反应与烧蚀模型研究
- An investigation of thermochemical reaction and aerodynamic ablation model on leading edges of reentry vehicles considering rarefaction effect
- 空气动力学学报 2026年44卷第2期页码：113-124
- 作者机构：
  
  1. 中国科学院力学研究所流体力学交叉研究中心,北京,100190
  2. 中国科学院大学未来技术学院,北京,101408
  3. 中国科学院大学工程科学学院,北京,100049
  4. 北京航空航天大学航空科学与工程学院,北京,100191
  5. 杭州市北京航空航天大学国际创新研究院（北京航空航天大学国际创新学院）,杭州,311115
- 作者简介：
  
  汪旭（2002—），男，安徽阜阳人，博士研究生，研究方向：高温气体动力学. E-mail：wangxu242@ucas.mails.ac.cn
  陈松*，副教授，研究方向：稀薄气体动力学，高速烧蚀. E-mail：chensong@buaa.edu.cn
- 基金信息：
  
  国家自然科学基金（12302381）;中国科学院稳定支持基础研究领域青年团队计划（YSBR-107）;高温气体动力学国家重点实验室开放课题（2023KF15）
- DOI：10.7638/kqdlxxb-2024.0173
  中图分类号： V211.3;V411.8
- 纸质出版：2026
- 稿件说明：
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汪旭, 肖天白, 张勇豪, 等. 考虑稀薄效应的再入飞行器前缘热化学反应与烧蚀模型研究[J]. 空气动力学学报, 2026, 44(2): 113−124.

Wang Xu, Xiao Tianbai, Zhang Yonghao, et al. An investigation of thermochemical reaction and aerodynamic ablation model on leading edges of reentry vehicles considering rarefaction effect[J]. 2026, 44(2): 113-124.
汪旭, 肖天白, 张勇豪, 等. 考虑稀薄效应的再入飞行器前缘热化学反应与烧蚀模型研究[J]. 空气动力学学报, 2026, 44(2): 113−124. DOI： 10.7638/kqdlxxb-2024.0173

Wang Xu, Xiao Tianbai, Zhang Yonghao, et al. An investigation of thermochemical reaction and aerodynamic ablation model on leading edges of reentry vehicles considering rarefaction effect[J]. 2026, 44(2): 113-124. DOI： 10.7638/kqdlxxb-2024.0173.

摘要

高温气流与飞行器表面材料的多物理、化学作用导致飞行器表面形貌显著变化，影响流动结构演化与飞行器气动力、热特性。准确预测再入过程的表面材料烧蚀过程对于飞行器热防护系统的设计至关重要。现有的气动烧蚀数值模拟研究主要针对固定壁面温度条件的流场变化，忽视了烧蚀过程中复杂化学反应与壁面材料性质差异导致的升温过程及烧蚀形貌的影响。本研究基于直接模拟蒙特卡罗（DSMC）方法，耦合壁面能量守恒方程，采用开源程序SPARTA对飞行器再入时的气动加热过程开展解耦分析。以柱体模型为例，综合激波后的气-气与气-固化学反应，对解耦后的壁面升温和模型烧蚀两个过程分别建立了相应的控制方程，并分析了在二维条件下的热化学反应与气动烧蚀机制。研究结果表明，本研究开发的可计算烧蚀模型不仅能够提升激波后气体分子内能采样的准确性，也能够复现文献中已有的烧蚀形貌。该模型不仅复现了圆柱烧蚀时前后缘的差异烧蚀形貌，还在引入表面粗糙度对气动加热的放大效应后，使球锥烧蚀退缩距离的预测结果与实验数据的相对误差控制在5%以内。该方法首次在DSMC框架内综合体现了壁面材料特性、变壁温效应以及表面粗糙度对烧蚀过程的物理影响，能够为深入理解变壁面温度下的复杂热化学非平衡现象提供理论依据与数据支撑。

Abstract

High-temperature airflow interacts with the surface material of the aircraft through multiple physical and chemical processes

significantly altering the aircraft's surface morphology

which consequently affects the evolution of flow structures as well as the aerodynamic and thermal characteristics of the vehicle. Accurate prediction of the ablation process during re-entry is crucial for designing thermal protection systems. Existing numerical simulations of aerodynamic ablation primarily focused on flow fields under fixed wall temperature conditions

neglecting the influences of complex chemical reactions and material property differences on the heating process and ablation morphology during ablation. This study employed the Direct Simulation Monte Carlo (DSMC) method

coupled with the wall energy conservation equation

and utilized the open-source program SPARTA to conduct a decoupled analysis of the aerodynamic heating process during vehicle re-entry. Using a cylindrical model as an example

corresponding governing equations were established separately for the decoupled processes of wall heating and model ablation. By integrating gas-gas and gas-solid chemical reactions behind the shock wave

the thermochemical reaction and aerodynamic ablation mechanisms under two-dimensional conditions were analyzed. The results indicate that the developed computable ablation model not only improves the accuracy of internal energy sampling for gas molecules behind the shock wave but also successfully reproduces ablation morphologies documented in existing literature. This model not only reproduces the difference in erosion morphology between the front and rear edges of a cylinder but also

after incorporating the amplification effect of surface roughness on aerodynamic heating

controls the relative error between the predicted retreat distance of the ball cone erosion and experimental data within 5%. This method represents the first comprehensive integration of wall material properties

variable wall-temperature effects

and surface roughness into the physical modeling of the ablation process within a DSMC framework

providing a theoretical basis and data support for deepening the understanding complex thermochemical non-equilibrium phenomena under variable wall temperatures.

关键词

Keywords

references

Gao Zhenxun, Jiang Chongwen, Li Chunxuan. Review of numerical simulation methods for hypersonic and high-enthalpy non-equilibrium flow[J]. Advances in Mechanics, 2023, 53(3): 561−591 (in Chinese). doi: 10.6052/1000-0992-22-051

Yang X F, Gui Y W, Xiao G M, et al. Reacting gas-surface interaction and heat transfer characteristics for high-enthalpy and hypersonic dissociated carbon dioxide flow[J]. International Journal of Heat and Mass Transfer, 2020, 146: 118869. doi: 10.1016/j.ijheatmasstransfer.2019.118869

Guo Yijun, Dai Guangyue, Gui Yewei, et al. Engineering calculation of non-equilibrium effects on thermal environment of reentry vehicles[J]. Acta Aerodynamica Sinica, 2015, 33(5): 581−587 (in Chinese). doi: 10.7638/kqdlxxb-2014.0041

Xu Guowu, Yang Yunjun, Zhou Weijiang. Investigation on ablation effect of return capsule during reentry process[J]. Acta Aerodynamica Sinica, 2017, 35(1): 101−107 (in Chinese). doi: 10.7638/kqdlxxb-2015.0019

Du Yaowen, Sun Surong, Huang Heji, et al. Numerical simulation of non-equilibrium flow-radiation characteristics at hypersonic speeds[J]. Chinese Journal of Theoretical and Applied Mechanics, 2023, 55(12): 2807−2817 (in Chinese). doi: 10.6052/0459-1879-23-373

Gao Tiesuo, Jiang Tang, Ding Mingsong, et al. Simulation of flow field infrared radiation over reentry vehicle with ablation of carbon-based thermal protection material[J]. Infrared and Laser Engineering, 2023, 52(5): 231−241 (in Chinese). doi: 10.3788/IRLA20220606

Yang Junyuan, Li Xudong, Zeng Shuhua, et al. Research on the aero-heating at the sharpened leading edge based on nonlinear coupled constitutive relations[J]. Chinese Journal of Theoretical and Applied Mechanics, 2023, 55(10): 2321−2330 (in Chinese). doi: 10.6052/0459-1879-23-171

Chen S, Stemmer C. Modeling of thermochemical nonequilibrium flows using open-source direct simulation Monte Carlo kernel SPARTA[J]. Journal of Spacecraft and Rockets, 2022, 59(5): 1634−1646. doi: 10.2514/1.a35359

Nieman R, Sands M, Wang Y Q, et al. Informing air–carbon ablation modeling with theoretical calculations of atomic oxygen and nitrogen interacting with carbon surfaces[J]. Physical Chemistry Chemical Physics, 2023, 25(22): 15479−15489. doi: 10.1039/D3CP01354E

Cao Yingfei, Ye Zhifan, Tang Ju, et al. Evolution and response mechanisms of interfacial thermochemical reactions for silicon carbide materials[J]. Acta Aerodynamica Sinica, 2024, 42(4): 96−104 (in Chinese). doi: 10.7638/kqdlxxb-2023.0161

Zheng Ziyu, Shi Jinguang, Xu Yang, et al. Aerothermal prediction for nose of hypersonic projectile based on chemical reaction[J]. Journal of Ballistics, 2022, 34(3): 35−42 (in Chinese). doi: 10.12115/j.issn.1004-499X(2022)03-005

Zhou Yinjia, Zhang Zhixian, Fu Xinwei, et al. Integrated computing method for ablative thermal protection system of reentry vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(7): 124520 (in Chinese). doi: 10.7527/S1000-6893.2020.24520

Sun Xuewen, Yang Haibo, Mi Tao. Heat transfer and ablation of carbon/carbon composites based on multi-field coupling[J]. Chinese Journal of Engineering, 2020, 42(8): 1040−1047 (in Chinese). doi: 10.13374/j.issn2095-9389.2019.06.30.002

Yang Kaiwei, Liang Huan, Zhao Xiaocheng, et al. Three-dimensional ablation/temperature coupling analysis of air rudder leading edge of high speed aircraft[J]. Missiles and Space Vehicles, 2021(2): 39−44 (in Chinese). doi: 10.7654/j.issn.1004-7182.20210209

Long Liping, Han Jun, Wan Tian, et al. Research of coupling computational method about the nose-tip ablation of reentry vehicle[J]. Structure Environment Engineering, 2021, 48(2): 8−14 (in Chinese). doi: 10.19447/j.cnki.11-1773/v.2021.02.002

ZuppardI G, Mongelluzzo G. Aerodynamic analysis of an entry capsule at titan in transition regime[J]. Journal of Spacecraft and Rockets, 2023, 60(2): 659−667. doi: 10.2514/1.a35407

Zuppardi G, Visone G, Votta R, et al. Analysis of aerodynamic performances of experimental flying test bed in high-altitude flight[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2011, 225(3): 247−258. doi: 10.1243/09544100jaero873

Dietrich S, Boyd I D. Scalar and parallel optimized implementation of the direct simulation Monte Carlo method[J]. Journal of Computational Physics, 1996, 126(2): 328−342. doi: 10.1006/jcph.1996.0141

White C, Borg M K, Scanlon T J, et al. dsmcFoam+: An OpenFOAM based direct simulation Monte Carlo solver[J]. Computer Physics Communications, 2018, 224: 22−43. doi: 10.1016/j.cpc.2017.09.030

Plimpton S J, Moore S G, Borner A, et al. Direct simulation Monte Carlo on petaflop supercomputers and beyond[J]. Physics of Fluids, 2019, 31(8): 086101. doi: 10.1063/1.5108534

Liang J, Li Z H, Li X G, et al. Monte Carlo simulation of spacecraft reentry aerothermodynamics and analysis for ablating disintegration[J]. Communications in Computational Physics, 2018, 23(4): 1037−1051. doi: 10.4208/CICP.OA-2016-0213

Achambath A D, Ramjatan S, Schwartzentruber T E. Surface properties on thermal protection system microstructure during hypersonic ablation[C]//Proc of the AIAA Scitech 2019 Forum, San Diego, California. AIAA, 2019: AIAA2019-1283. doi: 10.2514/6.2019-1283

Stern E C, Poovathingal S, Nompelis I, et al. Nonequilibrium flow through porous thermal protection materials, Part I: numerical methods[J]. Journal of Computational Physics, 2019, 380: 408−426. doi: 10.1016/j.jcp.2017.09.011

Bott L, Chen S, Christian S. DSMC study of hypersonic ablation using SPARTA[C]//2nd International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions Engineering. Heilbronn: 2022.

Gan Chi, Chen Song, Zhang Jun. DSMC study of micro-ablation for reentry vehicles[J]. Chinese Journal of Theoretical and Applied Mechanics, 2023, 55(9): 1847−1857 (in Chinese). doi: 10.6052/0459-1879-23-112

Boyd I D, Schwartzentruber T E. Nonequilibrium gas dynamics and molecular simulation[M]. Cambridge: Cambridge University Press, 2017.

Zhang C L, Schwartzentruber T E. Inelastic collision selection procedures for direct simulation Monte Carlo calculations of gas mixtures[J]. Physics of Fluids, 2013, 25(10): 106105. doi: 10.1063/1.4825340

Bird G A. Molecular gas dynamics and the direct simulation of gas flows[M]. Oxford: Clarendon Press, 1994.

Borgnakke C, Larsen P S. Statistical collision model for Monte Carlo simulation of polyatomic gas mixture[J]. Journal of Computational Physics, 1975, 18(4): 405−420. doi: 10.1016/0021-9991(75)90094-7

Scanlon T J, White C, Borg M K, et al. Open-source direct simulation Monte Carlo chemistry modeling for hypersonic flows[J]. AIAA Journal, 2015, 53(6): 1670−1680. doi: 10.2514/1.j053370

Boyd I D. Modeling backward chemical rate processes in the direct simulation Monte Carlo method[J]. Physics of Fluids, 2007, 19(12): 126103. doi: 10.1063/1.2825038

Jiang Guiqing, Liu Lianyuan. Heat transfer of hypersonic gas and ablation thermal protection[M]. Beijing: National Defense Industry Press, 2003 (in Chinese).

Grabow R M, White C O. Surface roughness effects nosetip ablation characteristics[J]. AIAA Journal, 1975, 13(5): 605−609. doi: 10.2514/3.49772

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