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四种飞行器绕流的三维DSMC计算与传热分析
引用本文: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[J].航空动力学报,2011,26(1):1-20.
作者姓名:王保国  李耀华  钱耕
作者单位: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,高等学校博士学科点专项基金
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...

关 键 词: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
收稿时间:2010/9/18 0:00:00
修稿时间:2010/10/20 0:00:00

Three-dimensional DSMC calculation and heat transfer analysis of four capsules for hypersonic rarefied conditions
WANG Bao-guo,LI Yao-hua and QIAN Geng.Three-dimensional DSMC calculation and heat transfer analysis of four capsules for hypersonic rarefied conditions[J].Journal of Aerospace Power,2011,26(1):1-20.
Authors:WANG Bao-guo  LI Yao-hua and QIAN Geng
Institution:WANG Bao-guo,LI Yao-hua,QIAN Geng(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)
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.
Keywords: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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