PDF《炭纤维 / 聚醚醚酮复合材料的》

第42 卷第

2 期固体火箭技术Journal of Solid Rocket Technology Vol.

42 No.2

2019 炭纤维 / 聚醚醚酮复合材料的 激光原位成型工艺探究 ① 沈镇,秦滢杰,陈书华,韩建平 (西安航天复合材料研究所,西安 710025) 摘要:为扩大热塑性树脂基复合材料在航空航天领域的应用,选择了一种具有优异力学性能和热性能的聚醚醚酮树脂 作为基体,对激光原位成型技术在热塑性树脂基复合材料成型的可行性进行探索. 采用溶液浸渍法制备 T700 炭纤维/ 聚 醚醚酮预浸胶带(预浸带),通过激光原位成型方式缠绕制备 T700 炭纤维/ 聚醚醚酮复合材料 NOL 环(NOL 环),探索不同 成型工艺条件下 NOL 环的层间剪切性能,优化出适宜的激光原位成型工艺参数. 结果表明,预浸胶带在含胶量为 33.6% 时韧性好,并且具有较好的拉伸性能;

通过层间剪切性能测试,当缠绕速度为

3 m/ min、激光输出电流为

40 A、芯模温度为

290 ℃ 、压辊压力为

150 N 时,激光原位成型的 NOL 环层间剪切性能较为优异,这为激光原位成型热塑性树脂基复合材料 在固体火箭发动机复合材料壳体上的应用提供了工艺参考. 关键词:激光;

原位成型;

聚醚醚酮;

复合材料 中图分类号:V258;

TB332 文献标识码:A 文章编号:1006?2793(2019)02?0229?05 DOI:10.7673/ j.issn.1006?2793.2019.02.015 Study on the laser in?situ winding process of carbon fiber reinforced PEEK composite SHEN Zhen,QIN Yingjie,CHEN Shuhua,HAN Jianping (Xi'

an Aerospace Composite Research Institute,Xi'

an 710025,China) Abstract:To expand the application of thermoplastic resin matrix composites in the aerospace field, a polyether?ether-ketone (PEEK)resin with excellent mechanical properties and thermal properties has been selected as the matrix,and the feasibility of in- situ laser winding technology in thermoplastic resin matrix composites has been determined.T700 carbon fiber/ PEEK prepreg tape was prepared by solution impregnation method,and T700 carbon fiber/ PEEK composite NOL ring was prepared by a laser in?situ winding process under different mold processing conditions. Moreover,the interlaminar shear properties of the NOL ring with the ap? propriate in?situ laser molding parameters have been optimized.The results show that the prepreg presented good toughness and ten? sile properties as the mass fraction of the resin in the composite was 33.6%.The NOL ring shows good interlaminar shear perform? ance when the processing parameters including winding velocity,the laser output current,the mandrel temperature and roller consoli? dation force were

3 m/ min,40 A,290 ℃ and

150 N,respectively.These results provide a feasibility analysis for the application of in? situ laser winding process on the solid rocket motor composite shell. Key words:laser;

in?situ winding process;

PEEK;

composite

0 引言 热塑性复合材料是未来武器装备和航天器、飞行 器发展的理想耐温、抗冲击、轻质化材料. 连续炭纤 维/ PEEK 复合材料具有力学性能优异、耐空间环境条 件好、损伤容限高以及层间断裂韧性好等特性,且能够 在250 ℃条件下连续使用,现已应用于机身、卫星部件 和其他空间结构,解决了目前传统热固性复合材料存 在的脆性大和断裂韧性低等问题[1] . 不过,聚醚醚酮 成型温度最高可达

400 ℃ ,这种高温环境接近了传统 热固化设备的极限,采用传统的基于热压罐、固化炉 或热压模等热固化方式进行成型时,存在能耗高、成 型时间长等缺陷[2] . ―