宇航材料工艺2011，Vol.41Issue(5)：44-49,6.
Cf/E预浸料先进拉挤固化工艺
Advanced Pultrusion Curing Process of Cf/E Prepreg
摘要
Abstract
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 pullrusion 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 100℃ 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Key words
Prepreg/Advanced pultrution/ DSC/ Pressure/Void content引用本文复制引用
齐俊伟,宋伟,肖军,邓磊明,罗鹏..Cf/E预浸料先进拉挤固化工艺[J].宇航材料工艺,2011,41(5):44-49,6.基金项目
国家04重大专项(2010ZX04016-013) （2010ZX04016-013）
