Influences of Carbon Fiber/Epoxy Prepreg Pre-Heating and Storage Aging on Composite Mechanical Properties

CHEN Ping; ZHAO Yueqing; LI Hongfu

doi:10.16080/j.issn1671-833x.2017.16.084

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Influences of Carbon Fiber/Epoxy Prepreg Pre-Heating and Storage Aging on Composite Mechanical Properties

更新时间：2025-10-30

- Influences of Carbon Fiber/Epoxy Prepreg Pre-Heating and Storage Aging on Composite Mechanical Properties
- Aeronautical Manufacturing Technology Vol. 60, Issue 16, Pages: 84-89(2017)
- 作者机构：
  
  1. 北京航空航天大学材料科学与工程学院,北京,100191
  2. 北京航空航天大学交通科学与工程学院,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.16080/j.issn1671-833x.2017.16.084
  CLC：
- Published：2017
- 稿件说明：
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陈萍1,2，赵月青1，李宏福3，张博明1. 碳纤维环氧预浸料前热处理及储放老化对复材力学性能的影响[J]. 航空制造技术, 2017, 60(16): 84-89.

CHEN Ping1,2, ZHAO Yueqing1, LI Hongfu3, ZHANG Boming1. Influences of Carbon Fiber/Epoxy Prepreg Pre-Heating and Storage Aging on Composite Mechanical Properties. Aeronautical Manufacturing Technology, 2017, 60(16): 84-89.
陈萍1,2，赵月青1，李宏福3，张博明1. 碳纤维环氧预浸料前热处理及储放老化对复材力学性能的影响[J]. 航空制造技术, 2017, 60(16): 84-89. DOI： 10.16080/j.issn1671-833x.2017.16.084.

CHEN Ping1,2, ZHAO Yueqing1, LI Hongfu3, ZHANG Boming1. Influences of Carbon Fiber/Epoxy Prepreg Pre-Heating and Storage Aging on Composite Mechanical Properties. Aeronautical Manufacturing Technology, 2017, 60(16): 84-89. DOI： 10.16080/j.issn1671-833x.2017.16.084.

摘要

基于DSC 测试数据，采用非模型拟合动力学方法Flynn-Wall-Ozawa （FWO）对碳纤维环氧预浸料的固化过程进行研究，并将试验结果与模型预测进行对比。结果表明，采用FWO 法能很好地预测预浸料的固化行为。同时，结合热隔膜成型工艺特点，将预浸料分别置于80℃和室温中进行分段处理，将经不同预处理的预浸料采用相同的固化工艺制作成复合材料板并进行力学测试。结果显示，随着80℃预加热时间的延长，层合板剪切强度逐渐降低，试样厚度增加，弯曲模量略微低，弯曲强度出现小幅度波动。室温老化结果表明，随着老化时间的延长，层合板的层间剪切性能和弯曲性能都存在小的波动，但无明显规律。

Abstract

The curing behavior was firstly characterized through different scanning calorimetry (DSC) using modelfree kinetic method (Flynn-Wall-Ozawa

FWO). The results show that FWO is suitable to describe and predict the curing process. At the same time

combining with the characteristic of diaphragm forming

prepreg pre-treated at different time and temperatures were used to product composite laminates. Then the interlaminar shear and bending properties were tested. The results show that with the increase of pre-heating time at 80℃

the shear strength gradually decreases while the thickness of the specimens increases. The flexural modules decrease slightly compared with that of specimens without preheating. For specimens aging at room temperature

the shear strength and flexural properties show small fluctuation with no obvious regularity as the prolongation of aging time.

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