绝热层烧蚀性能的理论预示

A THEORETICAL PREDICTION FOR ABLATION OF LINER INHIBITORS

关键词:  火箭发动机绝热层  烧蚀性能  气体分析  温度场  固体火箭发动机

Key words:  Pocket engine insolutor  Ablation Proporty  Gas analysis  Temperature field  Solid rocket engine

摘要:

本文在多次绝热层烧蚀实验所得物理模型的基础上,建立了在低燃气流速下的烧蚀表面质量和能量控制方程,以及某发动机绝热层在烧蚀时形成的炭化层、热解层和基体的温度响应控制方程,求得了该发动机内弹道环境条件下绝热层烧蚀过程中炭化面和热解面的退移速率.所得数值解与实验结果比较一致.

Abstract:

On the hasis of many ablation experiments of liner inhibitors,the physical and mathematical model is established. Mass and energy equations at the charring surface, the carbon process layer, the pyrolysis layer and the basis are solved under the condition of low gas velocity. The retreat rates on carbon process face and pyrolysis face and the internal temperature response are obtained under the same condition as in full scale motor.The calculation results are in accordance with ablation experiments adequately.