固体火箭发动机喷管结构瞬态温度场的理论预估

THEORETICAL CALCUIATION OF TRANSIENT TEMPERATURE FIELD OF COMPOSITE NOZZLE IN SOLID ROCKET MOTOR

关键词:  固体火箭发动机  火箭发动机喷管  温度分布  有限元法  应用

Key words:  Solid rocket engine  Rocket engine nozzle  Temperature distribution  Finite element method  Application

摘要:

本文采用目前广泛应用、效果显著的有限元法,对固体火箭发动机复合喷管结构的轴对称瞬态温度场进行了理论预估.在计算中考虑了对流换热系数沿喷管轴向的变化及材料的方向性.所编程序通用性较好.

Abstract:

In this paper,the finite element method which was extensively and effectively used was also applied to predict the transient temperature field of the composite nozzle in a cylindrical solid rocket motor. The differences of convective heat transfer coefficient along the nozzle axix and the anisotropy of the material were considered in the computation. The program can be easy generalized. The method and model for computation provided in this paper is practical in engineering.