高超声速火星进入环境中颗粒运动特性研究

邢好运; 刘卓; 汪球; 赵伟; 高亮杰; 刘中臣; 钱战森

doi:10.6052/0459-1879-23-192

高超声速火星进入环境中颗粒运动特性研究

doi: 10.6052/0459-1879-23-192

邢好运^{*, †},
刘卓^{*, †},
汪球^*, ,,
赵伟^{*, †},
高亮杰^**,
刘中臣^**,
钱战森^**

*.
中国科学院力学研究所高温气体动力学国家重点实验室, 北京 100190
†.
中国科学院大学工程科学学院, 北京 100049
**.
中国航空工业空气动力研究院, 沈阳 110034

基金项目: 广东省重点领域研发计划(2021B0909060004)、国家自然科学基金(12072353,12232018)和中国科学院青年创新促进会(2021020)项目资助

详细信息

通讯作者:
汪球, 高级工程师, 主要研究方向: 高焓气动物理与应用. E-mail: wangqiu@imech.ac.cn

计量
- 文章访问数: 32
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- 被引次数: 0
出版历程
- 网络出版日期: 2023-05-25

RESEARCH ON PARTICLE MOTION CHARACTERISTICS UNDER HYPERSONIC MARS ENTRY ENVIRONMENT

Xing Haoyun^{*, †},
Liu Zhuo^{*, †},
Wang Qiu^{*
, ,},
Zhao Wei^{*, †},
Gao Liangjie^**,
Liu Zhongchen^**,
Qian Zhansen^**

*.
State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
†.
School of Engineer Science, University of Chinese Academy of Science, Beijing 100049, China
**.
AVIC Aerodynamic Research Institute, Shenyang 110034, China

摘要

摘要: 火星大气中会发生不同规模的沙尘暴, 大气中蕴含的尘埃颗粒会对高速进入的火星探测器表面造成侵蚀并导致壁面热流增加, 给探测器的热防护系统设计带来巨大挑战. 本文针对高超声速火星进入环境两相流动问题, 基于Euler-Lagrange框架建立了非平衡流场与颗粒的单向耦合计算方法, 采用模态半径为0.35 μm的火星大气颗粒分布模型, 研究了不同尺寸颗粒在流场中的运动轨迹, 获得了高温相变模型对颗粒运动的影响以及不同粒径颗粒的撞击能量分布. 结果表明, 颗粒在高温流场中运动会吸热融化甚至蒸发, 高温相变模型导致的颗粒直径减小对小尺寸颗粒运动轨迹有较大影响; 当前计算状态下, 直径3 μm以上的颗粒具有较大的Stokes数且颗粒半径在运动过程中基本保持不变, 其运动轨迹受流场影响较小, 该尺寸颗粒的撞击分数均达95%以上, 是造成壁面撞击的主要颗粒尺寸; 撞击能量分数结果表明, 直径3-10 μm之间的颗粒是撞击能量的主要来源, 约占总撞击能量的80%.
- 火星进入 /
- 颗粒 /
- 单向耦合 /
- 高超声速 /
- 热防护系统
Abstract: Dust storms of varying degrees frequently transpire within the Martian atmosphere, and the dust particles present in the atmosphere will cause erosion on the surface of high-speed entering Mars vehicles, leading to increased wall heat flux. Consequently, the design of the vehicle's thermal protection system is confronted with a formidable challenge. In this paper, focusing on the two-phase flow problem in the hypersonic Mars entry environment, a non-equilibrium flow field and particle one-way coupling calculation method based on the Euler-Lagrange framework are established. Moreover, a Mars atmospheric particle distribution model with a modal radius of 0.35 μm is adopted to investigate the motion trajectories of particles with different sizes in the flow field. The effects of the high temperature phase change model on the particle motion and the impact energy distribution of particles with different particle sizes were obtained. The numerical simulation results show that particles are prone to melt or even vaporize during their moving in high-temperature flow fields, and it was confirmed that the high-temperature phase change model engenders a more pronounced effect on the trajectory of smaller particles due to their diminished dimensions. Conversely, particles with diameter above 3 μm exhibited a larger Stokes number, and their motion trajectory remained relatively unaffected by the surrounding flow field, and the radii of these particles remained relatively constant during motion. Particles with a diameter larger than 3 μm account for more than 95% of the impact fraction on the wall, which is the main source of wall impact. The results of the impact energy fraction indicate that particles with diameters between 3 and 10 μm are the main source of impact energy, accounting for approximately 80% of the total impact energy.
- mars entry /
- particle flow /
- one-way couple /
- hypersonic /
- thermal protection system

HTML全文

图 1 颗粒定位示意图

Figure 1. Particle locating algorithm description

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图 2 IDW插值模型示意图

Figure 2. Schematic of IDW interpolation model

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图 3 Schiaparelli飞行器与计算域

Figure 3. Configuration of Schiaparelli and the calculation region

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图 4 壁面热流计算结果对比

Figure 4. Comparison of surface heat flow calculation

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图 5 颗粒运动轨迹结果对比

Figure 5. Comparison of particle trajectory

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图 6 网格无关性研究

Figure 6. Grid independence studies

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图 7 颗粒CFL数无关性检验

Figure 7. Particle CFL number independence test

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图 8 相变模型对颗粒轨迹影响

Figure 8. Effect of phase transition model on particle trajectories

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图 9 不同直径颗粒轨迹示意图

Figure 9. Trajectories of particles with different diameters

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图 10 不同粒径轨迹示意图

Figure 10. Trajectory of different particle sizes

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图 11 相变模型对撞击分数影响

Figure 11. Effect of phase transition model on impact fraction

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图 12 颗粒分布模型^[9](r_m = 0.35 μm)

Figure 12. Particle distribution model for r_m = 0.35 μm

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图 13 撞击能量分数分布

Figure 13. Impact energy fraction distribution

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表 1 程序验证的来流条件

Table 1. Freestream conditions for program test

Conditions	MSL1-1467	T52902	HUPULSE749
MSL D, m	0.0508	0.1778	0.0508
u, m/s	3080	3160	4769
T, K	1095	1793	1045
T_v, K	1095	1793	1045
ρ, g/m³	15.1	92.7	5.75
h₀, MJ/kg	5.6	8.6	12.3
Ma	6.2	4.3	9.89
Y_CO2	1.000	0.719	1.0
Y_CO	0.000	0.179	0
Y_O2	0.000	0.100	0
Y_O	0.000	0.002	0

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表 2 本文程序和LAURA的无量纲激波脱体距离计算结果对比

Table 2. Comparison of Shock standoff distances of sphere-cone model calculated by different codes

	Dimensionless Shock standoff distance	Conditions MSL1-1467	Conditions T52902
Present program LAURA	δ(∆/R)	0.058	0.076
Present program LAURA	δ(∆/R)	0.059	0.077

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