摘要
对火箭发动机(包含发射药)的非稳态温度场进行数值模拟是确定火箭发射药实时温度的一种有效方法。论文首先建立了某火箭发动机传热的数理模型。鉴于发射药由7根药柱构成,结构复杂,无法在结构化网格基础上求出待求区域的温度场,因此,采用三角形非结构化网格并推导出计算区域内各节点的离散方程。编制程序,以数值计算方法求出发射药的温度场。结果表明,各特征点温度的计算值与实测值均吻合较好。因此,采用论文方法能正确模拟上述复杂结构火箭发射药的非稳态温度场。
Simulating the temperature field of a rocket motor （including propellant） by numerical method is an effective way to get real-time temperatures of the rocket propellant. A physical model and a mathematical model for heat transfer of the researched rocket were established. Because the rocket propellant, which consists of seven columns, has a complex structure, it is impossible to calculate the calculated domain＇ s temperature field with structured grids. So triangular unstructured grids were generated in the domain and then all nodes＇ discrete equations were deduced. The transient temperature field of the domain, including propellant, was worked out by numerical method. The comparison between temperature curves, gotten by calculation and test, shows the calculation result is correct. So the transient temperature field of the complex structure propellant can be correctly simulated by the proposed method.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2008年第1期68-71,共4页
Acta Armamentarii
关键词
热学
火箭发射药
二维非稳态温度场
非结构化网格
数值模拟
thermology
rocket propellant
two-dimensional transient temperature field
unstructured grid
numerical simulation
