【摘要】 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。更多还原

【Abstract】 Aiming at the performance requirements of thermal insulation material for solid rocket motor,Poly(aryloxyphosphazene) 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 propellant 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(aryloxyphosphazene) can be used as thermal insulation coating material for new advanced rocket engines due to its excellent physical properties and anti-erosion ability.更多还原