尾翼盒段主承力结构用高温固化碳纤维复合材料性能应用研究

Properties of High Temperature Cured Carbon Fiber Composite Used for Tail Box Main Load Structure

为了获得成套材料性能数据,为制件工艺性提供支持,并确定是否满足民用飞机设计和使用要求等,针对两组各三个批次的高温固化环氧树脂碳纤维复合材料,采用热压罐工艺制备,并对预浸料及层合板物理性能和3种环境条件下的基本层合板力学性能进行了研究。结果表明,两组预浸料树脂挥发份小,树脂流动度和凝胶时间适中,工艺性良好;该两组复合材料孔隙率小,纤维体积分数适中,耐温、耐湿热和界面粘结性能均较好,且M21体系复合材料的综合性能稍优于CYCOM 977-2体系复合材料,其结果均基本能满足某型民机尾翼盒段设计和使用要求,为该类材料的后续应用发展提供了依据。

In order to obtain a complete set of materials performance data, and provide support for part manufacturability, and determine whether to meet the requirements of the civil aircraft design and application, the high temperature cured epoxy resin impregnated carbon fiber composites were fabricated by hot press process with two groups of three batches respectively. The prepreg and composite physical properties, basic mechanical properties under three different environment conditions were investigate. The results show that the resin volatiles of this two group prepregs are small, the resin flow and gel time are moderate,so the processes are good. The porosities of two group composites are small, and the fiber volumes are moderate, the temperature resistance, humidity resistance and interface adhesion property of this two group composites are relatively good. The overall mechanical property under three different environment conditions of M21 system composite are better than these of CYCOM 977-2 system composite. The results are all basic to satisfy a certain type of civil aircraft tail box’s design and use requirements, and it provide the basis for the subsequent application of this composites development.