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

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.

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