大尺寸CFRP固体火箭发动机壳体湿法缠绕用树脂配方研制

针对大尺寸炭纤维增强复合材料(CFRP)固体火箭发动机壳体的制备要求,研制了一种具有良好粘度-温度及粘度-时间特性的炭纤维复合材料湿法缠绕成型树脂配方A.采用差示扫描量热法(DSC)、傅立叶红外光谱(FT-IR)等分析技术对树脂基体的固化反应进行了系统地研究,并测试了配方的粘度、力学性能及容器爆破强度.结果表明,该树脂配方A的反应表观活化能为41.71 kJ/moL,室温下粘度低(≤0.5390 Pa·s),适用期较长(＞48 h),不仅完全满足大尺寸CFRP固体火箭发动机壳体的湿法缠绕成型工艺要求,而且其树脂基体及其炭纤维复合材料表现出优良的力学性能.炭纤维复合材料界面粘接良好,缠绕的Φ150 mm容器的PV/W均大于48 km,纤维强度转化率达到89.0%以上.

Research on Resin Formula of CFRP Solid Rocket Engine Shell with big Dimension for Wet Winding

To meet a demand for CFRP solid rocket shell engine with big dimension,a new resin formula A with good properties of viscosity vs temperature and viscosity vs time for carbon composites with wet wingding process was developed.The curing action was systematically studied by means of DSC and FT-IR.The viscosity and mechanical properties as well as composite blast strength were tested. The results show that the surface active energy of the curing resin system A get to 41.7 kJ/mol.The resin matrix has a low viscosity(≤0.5390Pa·s)at room temperature and long pot life(＞48 h) and that it meets a demand for wet winding process of CFRP solid rocket engine shell with big dimension.The cast and the composite have excellent mechanical properties.Through the properties of the resultant carbon fibre based composite,the matrix is proved that it could cohere well with the carbon fibre.The PV/W values of Φ150 mm pressure vessels are over 48km and their strength conversion rate of cyclic fibre is up to 89.0%.