关键词: 温度场;喷管喉部;固体火箭发动机;喷管烧蚀计算

Abstract: This paper presents a model of numerical calculation for the tempreture distribution on nozzle throat inserter of solid rocket under moving boundery conditions related to the ablating recession,deposition of solid particles from the exhaust gases,and blowing process of deposit. The model is based on the principles of finite-volume energy coservation.The finite-difference method and the alternative direction implicit scheme which is of good stability are used to get numerical solution.To ensure the stability of the numerical solution when boundary recession is so much that near-boundary-cell will drop,the complete implicit interpolative-iterative method is introduced to calculate "the temprature on inner wall and at nodes of surface-cell. The feature of multilayer structure of nozzle throat, aniso-tropy of material, and the variable thermophysical properties with temprature of material are considered in the scheme so that the model is of certain generality and may be applied to the engineering design and research.Several experiments for the solid motor show that the model and the method proposed in this paper could mainly conform to the real working conditions of nozzle inserter and are of quite satisfactory accuracy.

Key words: Temperature field;Nozzle throat;Solid rocket engine;Nozzle abla-tion;Calculation