箭上复合材料气瓶绝热性能数值分析和试验研究

Numerical and Experimental Study on the Insulation Performance of A Rocket-Borne COPV

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 demand that working temperature of the composite layer should be below 80℃, an insulation layer is wrapped around the composite overwrapped pressure vessel （COPV） mounted in the engine com- partment of launch vehicles. Based on lumped parameter method, structural parameters and physical property data of a 40 L COPV, a numerical model in consideration of the radiation, conduction and convection process was estab- lished. It analyzed the insulation performance and discussed the influence of the insulation layer thickness. Moreover, insulation tests of the COPV wrapped by an insulation layer with the thickness of 5 mm or 10 mm were carried out. The numerical results agree well with the experiment measurements.