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固体火箭发动机喷管与燃气接触的表面常常喷涂一层绝热材料,如氧化铝.在燃气的冲刷作用之下,氧化铝涂层具有两个明显的特征:其一,涂层的热物性参数随温度变化;其二,涂层各部受到不同程度的烧蚀,因此,该状态下的传热分析属于变物性变边界的不稳定导热问题. 本文针对上述事实利用数值计算方法(有限元)进行了分析计算.算例表明,数值计算方法的结果与实际工作状态比较吻合.
Solid rocket engine nozzles come into contact with the gas surface is often sprayed with a layer of thermal insulation material, such as alumina .Oil gas erosion, alumina coating has two distinct characteristics: First, the thermal properties of the coating parameters Temperature, and secondly, the various parts of the coating are ablated by different degrees, therefore, the heat transfer analysis in this state belongs to the problem of unstable thermal conductivity with variable boundary.Based on the above facts, numerical calculation method (FEA) The results show that the numerical results are in good agreement with the actual working conditions.