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目前,已使用一种环氧树脂和浸润过的碳纤维来制造轻质的航天飞机纤维缠绕壳体。使用浸润剂处理过的纤维作增强材料,由于纤维的予浸作用,改变了树脂的总含量,从而也改变了复合材料的最终机械性能。美国 Naval Ordnance 实验室缠绕了环形试件用以研究浸润剂含量对纤维束吸收树脂的影响;研究复合材料的最终拉伸性能以及燃烧时可观察到的破坏形式。该环形试件研究的树脂含量范围为总量的20％～40％之间,浸润剂含量为O％～6％。结果表明,浸润剂含量是确定纤维吸收树脂总量的一个临界参数。复合材料的最终拉伸强度取决于浸润剂的总含量,当树脂含量低而浸润剂含量高的时候,拉伸强度可增加到60％之多。爆破时的破环形式是树脂含量的函数,而不是浸润剂含量的函数。
At present, an epoxy resin and infiltrated carbon fiber have been used to make the lightweight space shuttle fiber wound housing. The use of sizing treated fibers as a reinforcing material changes the total content of the resin due to the pre-impregnation of the fibers, thereby changing the final mechanical properties of the composite. The Naval Ordnance laboratory in the United States wrapped a toroidal test piece to study the effect of sizing agent on the fiber bundle-absorbing resin. The ultimate tensile properties of the composite and the observed forms of damage during combustion were investigated. The resin content of the annular specimen ranges from 20% to 40% of the total amount, and the sizing agent content is from 0% to 6%. The results show that the content of sizing agent is a critical parameter to determine the total amount of fiber absorbent resin. The ultimate tensile strength of the composites depends on the total content of the sizing agent. The tensile strength can be increased to as much as 60% when the resin content is low and the sizing agent is high. The broken ring form at blasting is a function of resin content, not a function of sizing content.