文档介绍：超音速旋转火箭弹气动特性仿真与分析
陈东阳 1,Laith , 芮筱亭 1,王强林 2
(,江苏南京 210094
技术研究中心,江苏南京 210000)
摘要:采用计算流体力学方法(CFD),基于剪切应力传输(SST)湍流模型,求解
大长细比卷弧翼火箭弹在超音速情况下的气动力和气动热问题。首先对火箭弹流场进行了
数值计算,与实验数据做了对比与分析。然后,采用薄壁模型来模拟结构耦合传热,计算
了一定海拔高度下,旋转情况下火箭弹的气动加热,并与不旋转的情况进行了对比分析。
计算结果表明,该数值方法不仅能较好的计算气动力系数,同时能较好的模拟旋转火箭弹
的气动热分布。在低转速和海拔高度下的特定条件下,旋转情况下的温度分布比不旋转的
稍微大一点,旋转情况下的火箭弹尾部截面压力分布不对称,尾部流线更加紊乱,弹头和
尾翼前缘温度较高,应当在火箭弹设计中予以考虑。
关键词:气动力; 气动加热; 数值模拟; 旋转
中图分类号: 文献标识码:A
Aerodynamic characteristics simulation and analysis of supersonic spinning rocket
CHEN Dong-yang1, LAITH ,RUI Xiao-ting1, WANG Qiang-lin2
(1. Institute of Launch Dynamics, Nanjing University of Science & Technology, Nanjing
210094;2. Jiangsu Engineering Technology Research Center for Energy Conservation and
Emission Reduction of Transportation,Nanjing,210000)
ABSTRACT:This work introduces the application putational fluid dynamics
(CFD),based on the shear stress transport (SST) turbulence model, on solving the aerodynamic
loads and aerodynamic heating problems of a finned slender rocket. Firstly, the aerodynamic
coefficients of a supersonic rocket are calculated pared with experimental data and
analyzed. Then, aerodynamic heating of the rocket, considering conjugate heat transfer, is
calculated in the condition of spinning and a certain height. The results pare