摘要
随着国家载人航天的不断发展,临近空间飞行器对极高速度和长航时的需求日益增长,如何准确模拟航天器再入过程中热化学非平衡气动加热对热防护系统的影响,一直是航天再入空气动力学前沿难题。本文根据宏观表面催化反应理论,在直接模拟蒙特卡罗(DSMC)方法架构的基础上构建有限速率表面催化反应模型。考虑五组元混合气体气相反应、表面催化反应的耦合作用,通过典型算例分析表面催化反应对飞行器再入大气层飞行器表面的影响,其表面热流相比未考虑表面催化反应的结果提高近30%。表面催化反应模型的加入为热化学非平衡表面效应难表征问题提供了新的手段,进一步提升了飞行器再入环境下高超声速气动加热预测能力,支撑飞行器热防护设计向高热载荷、轻量化方向发展。
With the continuous development of manned spaceflight,new requirements such as high speed and long endurance of near-space vehicles continue to emerge.How to accurately simulate the influence of thermochemical non-equilibrium aerodynamic heating on thermal protection system during spacecraft reentry has been a frontier problem of aerospace reentry aerodynamics.According to the macroscopic surface catalytic reaction theory,a finite rate surface catalytic reaction model was constructed on the basis of DSMC.Considering the coupling effect of five-component gas mixture reaction and surface catalytic reaction,the influence of surface catalytic reaction on the surface pressure/heat flow distribution of reentry spacecraft was analyzed by a typical example.The surface heat flux increased by nearly 30%compared with that without considering the surface catalytic reaction.The addition of this model provides a new method for the difficult characterization of thermochemical non-equilibrium surface effects to further improve the hypersonic aerodynamic heating prediction ability of aircraft under reentry environment and support the development of thermal protection design of aircraft towards high thermal load and lightweight.
作者
胡佳志
蒋新宇
李凡
李志辉
HU Jiazhi;JIANG Xinyu;LI Fan;LI Zhihui(Beijing Aerohydrodynamic Research Center,Beijing 100190,China)
出处
《化工进展》
北大核心
2025年第8期4478-4487,共10页
Chemical Industry and Engineering Progress
基金
国家自然科学基金(12332013)
国家重点研发计划(2022YFA1005104)。
关键词
表面催化反应
直接模拟蒙特卡罗方法
耦合计算
稀薄气体动力学
飞行器再入
surface catalytic reaction
direct simulation Monte-Carlo(DSMC)method
coupling calculation
rarefied gas dynamics
vehicle reentry
