酚醛/环氧过渡层固化特性及复合材料性能

为满足固体火箭发动机复合材料壳体的结构功能一体化要求，研究了两种树脂的过渡层配方、工艺及性能，重点研究了在酚醛树脂B30、环氧树脂TDE-85和固化剂甲基六氢苯酐（MHHPA）体系中，三者不同质量分数下的性能特点，采用了数显旋转黏度计和数显恒温水浴锅对树脂黏度测量，使用差示扫描量热仪（DSC）对不同质量分数的树脂进行热分析，求解多相体系反应机理的动力学参数，验证过渡层树脂固化工艺及性能，并与未使用过渡层的树脂配方进行性能对比。结果表明:过渡层体系中，最先反应的是B30和固化剂MHHPA，最后是B30的自固化；环氧树脂TDE-85的力学性能与酚醛树脂B30耐烧蚀性能满足结构层与功能层性能需求；与未使用过渡层的树脂相比，使用过渡层的树脂耐烧蚀性变化不大，但是弯曲强度提高了67.8%，拉伸强度提高了56.1%；与未使用过渡层的复合材料相比，使用过渡层的复合材料层间剪切强度提高了94.9%，但耐烧蚀性变化不大。综上所述，该过渡层可以满足固体火箭发动机复合材料壳体的结构功能一体化要求。 

Curing characteristics of phenolic and epoxy transition layer and properties of composites

In order to meet the requirements of structural and functional integration of composite shell of solid rocket motor，the formula，process and performance of the transition layer of the two resins were studied.The performance characteristics of the transition layer content distribution in the system of phenolic resin B30，epoxy resin TDE-85 and curing agent methylhexahydrophthalic anhydride （MHHPA） were mainly studied.The digital display rotary viscometer and digital display constant temperature water bath were used to measure the viscosity of the resin，and differential scanning calorimetry （DSC） was used for thermal analysis of the resin with gradient content.The kinetic parameters of the mechanism of multiphase reaction system were solved.The curing process and properties of the resin with transition layer were verified.The properties of the resin with transition layer were compared with those of the resin without transition layer.The results showed that:in the transition layer system，B30 and curing agent MHHPA reacted first，followed by B30 self-curing；the mechanical properties of epoxy resin TDE-85 and phenolic resin B30 met the performance requirements of structural layer and functional layer；compared with the resin without transition layer，the ablation resistance of the resin with transition layer had little change，but the bending strength increased by 67.8%，and the tensile strength increased by 56.1%；compared with the composite without transition layer，the interlaminar shear strength of the composite with transition layer increased by 94.9%，but the ablation resistance changed little.In conclusion，the transition layer can meet the structural and functional integration requirements of composite shell of solid rocket motor.