摘要
针对高超声速钝体外形所经历的高空稀薄环境特征,首先以Apollo返回器为例对DSMC代码进行了算例验证,最后以联盟号返回器外形为研究对象,计算给出了真实气体效应对返回器外形高空稀薄气动特性的影响规律,对比分析了完全气体模型与真实气体模型对返回器气动特性的预测差异。结果表明,在高空飞行弹道点下,气体稀薄,化学反应相对较弱,稀薄效应占优,真实气体模型对返回器的高空稀薄气动特性影响较小;两种模型对摩阻分量的预测差异随着飞行高度的增加逐渐显现,且真实气体模型使得摩阻分量的预测结果偏低;在约105km飞行高度处,返回器的阻力系数受攻角的影响最弱。
Attempt has been made to analyze reentry vehicle aerodynamics under hypersonic rarefied condition by use of DSMC code,which has been validated by comparing Apollo capsule aerodynamics with other＇ s results.The purpose of this study is to investigate the effects of real gas model on hypersonic rarefied aerodynamics.The results show that rarefied gas effect influences hypersonic rarefied aerodynamics much more than real gas effect.Real gas effect influences friction a little with increasing rarefaction,and the friction drag predicted by the real gas model tends to be lower than those predicted by the perfect gas model.At 105km altitude,drag coefficient is little affected by angle of attack.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2014年第3期283-290,共8页
Journal of Astronautics
