高效湿法缠绕用环氧树脂配方及其复合材料性能

Epoxy resin formulation and its composite properties for high efficiency wet winding

针对高质固体火箭发动机壳体高效的生产要求对不同官能度环氧树脂复配体系的工艺性进行研究,重点开展了多官能团环氧树脂复配体系配方设计及力学性能研究,分别采用DSC(差示扫描分析)、黏度测试进行固化特征温度、固化反应动力学及工艺适用期研究,并最终制备单向层合板及NOL(the Naval Ordnance Laboratory)环进行复合材料性能的测试分析。研究结果表明:三官能度复配的环氧树脂能满足高效湿法缠绕要求。当三官能度的TDE-85质量分数为25%时,综合性能达到最优,适用期仅为120 min,拉伸强度为97.3 MPa,弯曲强度为115 MPa,玻璃化转变温度高达466 K,较最低值分别提高36.3%、15.9%、25.8%。该树脂体系与纤维匹配性好,复合材料性能优良,NOL环拉伸强度与层间剪切强度分别为2.56 GPa、74.4 MPa,纤维强度利用率达76.6%,适用于固体火箭发动机湿法缠绕成形。

According to the requirement for high-efficient production of high quality solid rocket motor shell,the epoxy resin formulation with different functionalities was studied by focusing on its formulation design and mechanical properties.The curing characteristic temperature,curing reaction kinetics and pot life were tested by DSC(differential scanning calorimetry)and viscosity test,respectively,the unidirectional laminates and NOL(the Naval Ordnance Laboratory)rings were prepared to test and analyze the properties of composites.The results showed that the epoxy resin with three functionalities can meet the requirements of high efficient wet winding.When the mass fraction of TDE-85 with three functionalities was 25%,the comprehensive properties reached the optimum,the tensile strength(97.3 MPa),the bending strength(115 MPa)and the glass transition temperature(466 K)increased by 36.3%,15.9%and 25.8%respectively,while the applicable period was 120 min.The resin system had good adaptability to fibers,demonstrated by the excellent properties of composites,about 2.56 GPa in tensile strength and 74.4 MPa in interlaminar shear strength of the NOL rings,respectively.The utilization ratio of fiber strength reached 76.6%,demonstrating that the epoxy resin system was suitable for the wet winding process of the solid rocket motor.