高超声速火箭橇气动热理论分析  

Aerothermal Analysis of Hypersonic Rocket Sled

作　　者：赵卫星 余远锋 闫华东 ZHAO Weixing;YU Yufeng;YAN Huadong(Test and Measuring Academy of China Ordnance Industries,Huayin 714200,China)

机构地区：[1]中国兵器工业试验测试研究院,陕西华阴714200

出　　处：《兵器装备工程学报》2021年第S02期154-158,196,共6页Journal of Ordnance Equipment Engineering

基　　金：国防基础科研计划项目(JCKY2016208A006)。

摘　　要：分析了高超声速火箭橇橇体在运动中所涉及的气动热计算问题,对于8Ma以下的气动热问题,介绍了量热完全气体与热完全气体热力学参数计算方法,并通过数值计算比较了不同速度下两种气体的热力学参数变化情况,在低马赫数时,两种气体计算结果的差别不大,随着来流速度的增大,两种气体计算结果的差值增大。对于8Ma以上的气动热问题,介绍了高温真实气体的气动热计算方法,为高超声速火箭橇的气动热计算奠定了理论基础。Taking the hypersonic rocket sled as the research object,the aerothermal calculation problems involved in the motion of the sled body were analyzed.For the aerothermal problems below 8Ma,the calculation methods of thermodynamic parameters of calorically perfect gas and thermally perfect gas were introduced,and the changes of thermodynamic parameters of the two gases at different speeds were compared by numerical calculation,at low Mach numbers,the difference between the calculated results of the two gases in small,but with the increase of the flow velocity,the difference between the calculated results of the two gas increases.For the aerothermal problem above 8Ma,the aerothermal calculation method of high temperature real gas was introduced,which lays a theoretical foundation for the aerothermal calculation of hypersonic rocket sled.

关 键 词：高超声速 火箭橇 气动热 完全气体 真实气体 

分 类 号：V414.1[航空宇航科学与技术—航空宇航推进理论与工程]