C_f/E预浸料先进拉挤固化工艺  

Advanced Pultrusion Curing Process of Cf/E Prepreg

作　　者：齐俊伟[1] 宋伟[1] 肖军[1] 邓磊明[1] 罗鹏[1] 

机构地区：[1]南京航空航天大学,南京210016

出　　处：《宇航材料工艺》2011年第5期44-49,共6页Aerospace Materials & Technology

基　　金：国家04重大专项(2010ZX04016-013)

摘　　要：为探索与预浸料先进拉挤成型技术相适应的工艺方案,采用DSC研究了碳纤维/环氧预浸料USN12500的固化放热过程,对USN12500的典型固化工艺进行改进,以此为基础设计了不同压力和加压时机下的试验方案,采用实验室现有设备模拟先进拉挤过程制备了试样,以制品的孔隙率作为考察指标优选了的拉挤成型固化的工艺参数。结果表明:制品在110℃下处理20 min,热压阶段130℃下处理15 min同时保持0.4MPa的工艺压力,后固化150℃下处理1.5 h为工艺试验的优化方案,并且能够制得孔隙率<1.1%的制品。To explore prepreg curing process which adjust to advanced pultrusion technology,curing exothermic process of carbon fiber/epoxy prepreg was studied in this work with differential scanning calorimetry（DSC） to improve the typical curing process of prepreg USN12500.Then the process schemes were designed and conducted with pressure values and the time to apply pressures as variables.Based on the available equipments in the laboratory,the curing process of prepreg adopt with advanced pultrusion was simulated and samples were prepared.With void content as investigation index we optimized the curing process parameters of advanced pultrusion.The results of the test indicate that final process scheme was optimized with pretreating the prepreg at 110℃ for 20 min,then curing at 130℃ for 15 min under pressure of 0.4 MPa,and finally postcuring at 150℃ for 1.5 h.The test verificated that void content less than 1.1% in composites profiles can be prepared.

关 键 词：预浸料 先进拉挤 DSC 压力 孔隙率 

分 类 号：TQ327.106[化学工程—合成树脂塑料工业]