Abstract: Based on the heat transfer theory,a solution is obtained to predict the change of the deposit thickness of alumina with time on the nozzle wall of a solid rocket motor.The temperature distribution and the thickness of the deposit layer along the nozzle wall have been calculated.The deposition rate,which is not a constant at the initial period of the deposition process,can also be calculated. The trend of the theoretical results agree with the experiment data from the engine interrupteed tests.

Key words: Combustion deposit;Solid rocket engine;Rocket engine nozzle;Temperature distribution;Mathematical model

摘要： 本文根据传热理论建立了固体火箭发动机喷管三氧化二铝沉积规律的数学模型,并求得了喷管壁内和沉积层内的温度分布。又根据沉积层厚度的定义确定了沉积层厚度随时间变化的解析解。数值计算结果与实验的比较表明,理论计算得到的基本规律和实验相符。

关键词: 燃烧室沉积灰;固体火箭发动机;火箭发动机喷管;温度分布;数学模型