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以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、线烧蚀率以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0．187W／（m·K）、线膨胀系数为2．31×10^-4、密度为1．196g／cm^3、线烧蚀率为0．109mm／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。
Poly （aryloxyphosphazene） based thermal insulation coating materials for solid rocket engine were prepared. Performanees 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. The results show that, thermal conductivity of polyaryloxyphosphazene is 0.187 W/（ m · K）, linear expansion coefficient is 2.31 × 10^-4, density is 1.196 g/cm^3, the linear ablation rate is 0.109 ram/s, and the layer is hard with high char yield after the ablation. The materials present good compatibility with the 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.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2015年第3期407-409,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-），男，高工，研究方向为功能高分子材料。E—mail：zfwang772@163．com
