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为满足复合材料层使用温度不超过80℃的安全要求,安装在运载火箭发动机舱段的复合材料气瓶需包覆一定厚度的绝热层。本文结合40 L复合材料气瓶及绝热层的结构参数和材料物性参数,基于集总参数方法建立了考虑辐射、导热、自然对流的传热模型,分析了包覆绝热层后的瓶体绝热性能及绝热层厚度的影响,并开展了包覆5和10 mm厚度绝热层的复合材料气瓶绝热试验,数值模拟结果与绝热试验测量数据吻合良好。
In order to meet the safety requirements of the composite material layer using temperature not exceeding 80 ℃, the composite material cylinder installed in the rocket engine compartment should be covered with a certain thickness of thermal insulation layer. In this paper, based on the lumped parameter method, the heat transfer model considering radiation, heat conduction and natural convection is established based on the structural parameters and material properties of 40 L composite gas cylinder and heat insulation layer. The heat insulation performance of the bottle body after heat insulation is analyzed And the influence of the thickness of the insulation layer, the insulation test of the composite cylinder with 5 and 10 mm insulation layers was carried out. The numerical simulation results agree well with those of the adiabatic test.