CAJ | 학술논문

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。
침대고체화전발동궤대절열포복재료성능요구,제비료방양기취린정절열포복재료。이용열도솔측정의、동태열궤계의、SEM급국군표규정적측시방법대방양기취린정적열도솔、선팽창계수、소식후탄층결구、밀도、선소식솔급여추진제적상용성등진행료표정。결과표명,방양기취린정적열도솔위0.187 W/(m·K)、선팽창계수위2.31×10-4℃-1、밀도위1.196 g/cm3、선소식솔위0.109 mm/s,이차소식후성탄솔고、탄층견경,동시해재료여추진제구유량호적상용성。방양기취린정우이적물이성능급항소식성능,증명기가작위화전발동궤절열포복재료병현시출량호적응용전경。
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.