某战术弹热防护件的制备工艺及性能研究

Study on Preparation Technology and Performance of Thermal Protection Parts of A Tactical Missile

针对高承载能力的异形树脂基防热复合材料结构件在航空航天领域的应用需求,以高硅氧/酚醛胶布为原材料,采用模压成型制备了某长时间飞行战术弹热防护件,讨论了该热防护件的模具结构设计、铺层设计及模压工艺参数设计。采用扫描电镜(SEM)、梅特勒天平、电子万能材料试验机、激光导热仪和热膨胀仪,对热防护件的结构及性能进行了表征。结果表明:上凹、下凸的组合式模具可操作性强,能保证产品基本尺寸且加工成本低;采用交替铺层的方式能保证产品强度并避免聚胶;模压压力14MPa、模压温度170℃、模压时间30min的工艺参数下,制备的某战术弹热防护件性能优异,测试结果分别为:密度1.83g/cm^(3)、拉伸强度85.2MPa、压缩强度280MPa、比热容1.46kJ/(kg·K)、热导率0.65W/(m·K)、平均线膨胀系数6.17×10^(-6)/℃,满足设计和使用要求。

In this study,the thermal protection part of long-time flight weapon was prepared by molding technology with high silica/phenolic tape as raw materials.The mould structural design,ply design and molding process parameter design of the thermal protection part were discussed.The microstructure and properties of the thermal protection part were characterized by scanning electron microscope(SEM),Mettler balance,electronic universal material testing machine,laser thermal conductivity meter and thermal dilatometer.The results show that the basic size of the product can be guaranteed by adopting the upper concave and lower convex combined mold with strong operability and low processing cost.Product strength and no poly-adhesive can be achieved by alternately laying a variety of specifications of cloth.Under the process parameters of molding pressure of 14MPa,molding temperature of 170℃,and molding time of 30min,the thermal protection part prepared by compression molding has excellent performance and meets the design requirements.The test results were:density 1.83g/cm^(3),tensile strength 85.2MPa,compressive strength 280MPa,and specific heat capacity 1.46kJ/(kg·K),thermal conductivity 0.65W/(m·K),average linear expansion coefficient 6.17×10^(-6)/℃.