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。
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.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2015年第2期278-280,共3页
Journal of Solid Rocket Technology
基金
总装备部预先研究项目
关键词
芳氧基聚磷腈
性能表征
包覆层
polyaryloxyphosphazene
performance characterization
coating material
作者简介
王建中（1961一），男，高级工程师，研究方向为功能高分子材料。E-mail：zfwang772@163．com
