针对固体火箭发动机对绝热包覆材料性能要求,制备了芳氧基聚磷腈绝热包覆材料。利用热导率测定仪、动态热机械仪、SEM及国军标规定的测试方法对芳氧基聚磷腈的热导率、线膨胀系数、烧蚀后碳层结构、密度、线烧蚀率及与推进剂的相容性等进行了表征。结果表明,芳氧基聚磷腈的热导率为0.187 W/(m·K)、线膨胀系数为2.31×10-4℃-1、密度为1.196 g/cm3、线烧蚀率为0.109 mm/s,而且烧蚀后成碳率高、碳层坚硬,同时该材料与推进剂具有良好的相容性。芳氧基聚磷腈优异的物理性能及抗烧蚀性能,证明其可作为火箭发动机绝热包覆材料并显示出良好的应用前景。%Aiming at the performance requirements of thermal insulation material for solid rocket motor,Poly(aryloxyphosp-hazene)based thermal insulation coating materials were prepared.Performances of the Poly(aryloxyphosphazene)thermal insulation coating materials,such as thermal conductivity,linear expansion coefficient,density,linear ablation rate and compatibility with pro-pellant were characterized by using thermal conductivity measuring device , dynamic thermal analysis, SEM and the measuiring methods regulated by military standard.The results show that,the thermal conductivity of polyaryloxyphosphazene is 0.187 W/(m· K),the linear expansion coefficient is 2.31×10-4℃-1,the density is 1.196 g/cm3,the linear ablation rate is 0.109 mm/s,and the layer is hard with high char yield after ablation. The materials present good compatibility with propellant. The poly ( aryloxyphosp-hazene) can be used as thermal insulation coating material for new advanced rocket engines due to its excellent physical properties and anti-erosion ability.
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