四种飞行器绕流的三维DSMC计算与传热分析

王保国; 李耀华; 钱耕

四种飞行器绕流的三维DSMC计算与传热分析

北京理工大学宇航学院, 北京 100081

基金项目: 国家自然科学基金(50376004); 高等学校博士学科点专项基金(20030007028)

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出版历程
- 收稿日期: 2010-09-18
- 修回日期: 2010-10-20
- 刊出日期: 2011-01-28

Three-dimensional DSMC calculation and heat transfer analysis of four capsules for hypersonic rarefied conditions

School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China

摘要

摘要: 在地球大气层与火星大气层中,使用自己编制的DSMC(direct simulation Monte Carlo)源程序完成了四种飞行器(即Apollo,Orion,Mars Pathfinder以及Mars Microprobe)高超声速穿越稀薄气体时的三维绕流计算,给出了上述飞行器42个典型飞行工况(其中包括在地球大气层中,飞行高度从250km变到90km,飞行攻角从45°变到-45°,Knudsen数从111.0变到0.0057,飞行速度从7.6km/s变到9.6km/s;在火星大气层中,飞行高度从141.8km变到80.28km,飞行攻角从45°变到0°,Knudsen数从100.0变到0.0546,飞行速度从7.47km/s变到6.908km/s)时详细气动力与气动热的数值结果,并与国外的飞行数据以及美国NASA(National Aeronautics and Space Administration) Langley研究中心发表的计算结果进行了比较,所得结果令人满意.文中采用了三种无量纲参数分别刻画这四种典型飞行器绕流流动的热力学非平衡、化学反应非平衡以及壁面热流分布的特征,这些结果对于指导空间飞行器的热防护气动设计十分有益.
- 直接模拟蒙特卡罗 (DSMC) 算法 /
- 热力学非平衡 /
- 化学反应非平衡 /
- 高温传热分析 /
- 飞行器/探测器
Abstract: Hypersonic rarefied flow field of four vehicles (Apollo, Orion, Mars Pathfinder and Mars Microprobe) in the atmosphere of Earth and Mars was calculated using the DSMC(direct simulation Monte Carlo) source code compiled by us. Detailed aerodynamic coefficients and thermodynamic coefficients of these vehicles under 42 conditions (with the altitude from 250km to 90km, attack angle from 45° to -45°, Knudsen number from 111.0 to 0.0057, velocity from 7.6km/s to 9.6km/s for the Earth atmosphere; with the altitude from 141.8km to 80.28km, attack angle from 45° to 0°, Knudsen number from 100.0 to 0.0546, velocity from 7.47km/s to 6.908km/s for the Mars a tmosphere) were presented and compared with flight data announced by other countries and calculation results published by NASA (National Aeronautics and Space Administration) Langley Research Center. The results are satisfactory. Three-dimensionless parameters were used to describe the characteristics of thermodynamic non-equilibrium, chemical non-equilibrium and wall heat flux of these four typical vehicles respectively. These results are quite useful for thermal protection design of spacecrafts.
- DSMC (direct simulation Monte Carlo) algorithm /
- thermodynamic non-equilibrium /
- chemical reaction non-equilibrium /
- high temperature heat transfer analysis /
- vehicles/entry probes

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