固体火箭发动机喷管两相流场与结构温度场一体化数值模拟与软件实现

Integrated numerical simulation and software implementation on two-phase flow field and structure temperature field of solid rocket motor nozzle

为准确、高效地进行固体火箭发动机的喷管结构设计与性能分析,考虑两相流场和结构温度场之间的相互影响,采用有限差分方法求解二维轴对称两相欧拉方程组,进行喷管气体—颗粒两相无黏流动数值模拟;采用有限元法求解二维轴对称瞬态导热微分方程,进行喷管复合结构温度场数值模拟;根据面向对象编程思想,采用VC++以人机交互的工作方式实现喷管内型面和结构设计,并完成有限差分网格和有限元网格的自动划分和显示;通过数值模拟方法与面向对象软件设计方法的有效结合,实现二维轴对称喷管两相无黏流场和复合结构温度场的一体化数值模拟.数值模拟结果表明,该方法有助于在统一的软件平台上充分利用计算机辅助技术完成喷管性能与结构的综合评估,可以用于固体火箭发动机喷管的工程设计.

To design the nozzle structure of solid rocket motor and analyze its performance accurately and effectively, considering the interaction of two-phase flow field and structure temperature field, the finite difference method is used to solve 2D axis-symmetrical two-phase Euler equations to simulate the non-vis- cous gas-particle two-phase flow field of nozzle; the finite element method is used to solve the 2D axis- symmetrical transient heat conduction differential equations to simulate nozzle composite structure tempe- rature field ; and according to the idea of object-oriented programming, VC ＋ ＋ is used to implement the design of nozzle internal contour and structure by the means of human-computer interaction, and the auto- matic generation and display of finite difference grids and finite element grids are implemented; through the combination of numerical simulation method and object-oriented programming design method, the integrated simulation of two-phase non-viscous flow field and composite structure temperature field for 2D axis-symmetrical nozzle is realized. The numerical simulation indicates that the method is helpful to fully utilize computer aided technology to implement the comprehensive evaluation of performance and structure of nozzle in a united software platform, which is feasible for the nozzle design of solid rocket motor.