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Article(id=1251480538993869133, tenantId=1146029695717560320, journalId=1251234078029037663, issueId=1251480531381207309, articleNumber=null, orderNo=null, doi=10.11887/j.issn.1001-2486.23090005, pmid=null, cstr=null, oa=null, hot=null, price=null, onlineType=0, articleFormat=0, articleType=null, articleTypeStr=null, receivedDate=1694448000000, receivedDateStr=2023-09-12, revisedDate=null, revisedDateStr=null, acceptedDate=null, acceptedDateStr=null, onlineDate=1776305811879, onlineDateStr=2026-04-16, pubDate=1766851200000, pubDateStr=2025-12-28, doiRegisterDate=null, doiRegisterDateStr=null, onlineIssueDate=1776305811879, onlineIssueDateStr=2026-04-16, onlineJustAcceptDate=null, onlineJustAcceptDateStr=null, onlineFirstDate=null, onlineFirstDateStr=null, sourceXml=null, magXml=null, createTime=1776305811879, creator=13701087609, updateTime=1776305811879, updator=13701087609, issue=Issue{id=1251480531381207309, tenantId=1146029695717560320, journalId=1251234078029037663, year='2025', volume='47', issue='6', pageStart='1', pageEnd='306', issueExtLink='null', onlineDate='null', pubDate='null', beforeIssueId=null, nextIssueId=null, price=null, status=1, issueComplete=1, articleOrder=1, issueType=1, specialIssue=null, createTime=1776305810065, creator=13701087609, updateTime=1776305899308, updator=13701087609, preIssue=null, nextIssue=null, ext={EN=IssueExt(id=1251480905865446141, tenantId=1146029695717560320, journalId=1251234078029037663, issueId=1251480531381207309, language=EN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=), CN=IssueExt(id=1251480905865446142, tenantId=1146029695717560320, journalId=1251234078029037663, issueId=1251480531381207309, language=CN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=)}, issueFiles=null}, startPage=199, endPage=207, ext={EN=ArticleExt(id=1251480539807564122, articleId=1251480538993869133, tenantId=1146029695717560320, journalId=1251234078029037663, language=EN, title=Effect of mode Ⅱ interlaminar fracture toughness on the tensile properties of carbon/glass hybrid composites, columnId=1251480533906178319, journalTitle=Journal of National Niversity of Defense Technology, columnName=Aeronautical and Astronautical Science and Technology·Materials Science and Engineering, runingTitle=null, highlight=null, articleAbstract=

To investigate the effect of interlaminar properties on the tensile properties of fiber hybrid composites, two kinds of epoxy resins with different toughness, 7901 and 9A16, were used as the matrix.Interlayer carbon/glass hybrid composites with different numbers of carbon fiber layers were designed and manufactured.The effects of mode Ⅱ interlaminar fracture toughness(GⅡC)on the failure mode and mechanical properties of carbon/glass hybrid composites were investigated through both theoretical and experimental investigation.The results show that, the higher mode Ⅱ interlaminar fracture toughness is, the more the carbon layer tends to fail in fragmentation, achieving a higher critical thickness for fragmentation, which is beneficial for achieving pseudo-ductility.In addition, the GⅡC on the modulus and strength of hybrid composites is marginal, as the variation is within 5%.However, the GⅡCdemonstrates a significant impact on the pseudo-ductility strain, which is decreased by 40.7% when the GⅡC is increased from 1.75 N/mm to 2.08 N/mm.

, correspAuthors=Jun TANG, authorNote=null, correspAuthorsNote=null, copyrightStatement=null, copyrightOwner=null, extLink=null, articleAbsUrl=null, sourceXml=null, magXml=null, pdfUrl=null, pdf=null, pdfFileSize=null, pdfExtLink=null, richHtmlUrl=null, mobilePdfUrl=null, reviewReport=null, pdfFirstPage=null, abstractGraph=null, abstractGraphContent=null, abstractVideo=null, citation=null, cebUrl=null, magXmlContent=null, mapNumber=null, authorCompany=null, fund=null, authors=null, authorsList=Fahao ZHANG, Changping YIN, Longjie SONG, Suli XING, Dingding CHEN, Jun JIANG, Jun TANG), CN=ArticleExt(id=1251480549097947895, articleId=1251480538993869133, tenantId=1146029695717560320, journalId=1251234078029037663, language=CN, title=Ⅱ型层间断裂韧性对碳/玻混杂复合材料拉伸性能的影响, columnId=1251480534057173265, journalTitle=国防科技大学学报, columnName=航空宇航科学与技术·材料科学与工程, runingTitle=null, highlight=null, articleAbstract=

为探究纤维混杂复合材料层间性能对其拉伸力学性能的影响，采用7901和9A16两种不同韧性的环氧树脂作为基体，设计和制备了含不同碳纤维铺层数的碳/玻混杂复合材料。并通过理论推导和实验相结合的方式探究了Ⅱ型层间断裂韧性（GⅡC）对碳/玻混杂复合材料失效机理和力学性能的影响规律。结果表明，Ⅱ型层间断裂韧性越大，碳纤维层越趋向于碎片化断裂，具有更高地实现碎片化断裂的临界厚度，有利于伪延展行为的实现。此外，Ⅱ型层间断裂韧性对混杂复合材料模量、强度的影响不显著，变化均在5%以内；但其对伪延展应变有较大影响，当Ⅱ型层间断裂韧性由1.75 N/mm增加到2.08 N/mm时，伪延展应变下降了40.7%。

, correspAuthors=唐俊, authorNote=null, correspAuthorsNote=
唐俊（1990—），男，四川绵阳人，讲师，博士，E-mail：
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张发豪（1999—），男，山东潍坊人，硕士研究生，E-mail：

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张发豪（1999—），男，山东潍坊人，硕士研究生，E-mail：

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张发豪（1999—），男，山东潍坊人，硕士研究生，E-mail：

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figureFileBig=ag4l/G+a3dghuLlsp8a32A==, tableContent=null), ArticleFig(id=1251480560573563206, tenantId=1146029695717560320, journalId=1251234078029037663, articleId=1251480538993869133, language=EN, label=Tab.1, caption=

Experimental raw materials

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原材料名称型号厚度/mm
碳纤维/环氧预浸料T300/79010.02
玻璃纤维/环氧预浸料S4/79010.12
碳纤维/环氧预浸料T300/9 A160.02
玻璃纤维/环氧预浸料S4/9 A160.12
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实验原材料

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原材料名称型号厚度/mm
碳纤维/环氧预浸料T300/79010.02
玻璃纤维/环氧预浸料S4/79010.12
碳纤维/环氧预浸料T300/9 A160.02
玻璃纤维/环氧预浸料S4/9 A160.12
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Basic properties of 9A16 resin and 7901 resin castings

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树脂浇铸体性能（120℃固化）9 A16树脂7901树脂
玻璃化转变温度/℃146115
树脂密度/（g/cm3）1.201.20
拉伸强度/MPa6591
拉伸模量/GPa3.13.0
弯曲强度/MPa124104
弯曲模量/GPa3.33.0
), ArticleFig(id=1251480560896524631, tenantId=1146029695717560320, journalId=1251234078029037663, articleId=1251480538993869133, language=CN, label=表2, caption=

9A16树脂和7901树脂浇铸体基本性能

, figureFileSmall=null, figureFileBig=null, tableContent=
树脂浇铸体性能（120℃固化）9 A16树脂7901树脂
玻璃化转变温度/℃146115
树脂密度/（g/cm3）1.201.20
拉伸强度/MPa6591
拉伸模量/GPa3.13.0
弯曲强度/MPa124104
弯曲模量/GPa3.33.0
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Parameters used for critical thickness calculation

, figureFileSmall=null, figureFileBig=null, tableContent=
基体类型E1/GPaE2/GPaScarbon/MPaGⅡC/（N/mm）
9 A164513521501.75
79014513521502.08
), ArticleFig(id=1251480561106239847, tenantId=1146029695717560320, journalId=1251234078029037663, articleId=1251480538993869133, language=CN, label=表3, caption=

临界厚度计算所用参数

, figureFileSmall=null, figureFileBig=null, tableContent=
基体类型E1/GPaE2/GPaScarbon/MPaGⅡC/（N/mm）
9 A164513521501.75
79014513521502.08
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Ⅱ型层间断裂韧性对碳/玻混杂复合材料拉伸性能的影响
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张发豪 , 尹昌平 , 宋龙杰 , 邢素丽 , 陈丁丁 , 蒋俊 , 唐俊 *
国防科技大学学报 | 航空宇航科学与技术·材料科学与工程 2025,47(6): 199-207
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国防科技大学学报 | 航空宇航科学与技术·材料科学与工程 2025, 47(6): 199-207
Ⅱ型层间断裂韧性对碳/玻混杂复合材料拉伸性能的影响
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张发豪 , 尹昌平, 宋龙杰, 邢素丽, 陈丁丁, 蒋俊, 唐俊*
作者信息
  • 国防科技大学　空天科学学院，湖南　长沙　410073

    • 张发豪（1999—），男，山东潍坊人，硕士研究生，E-mail：

通讯作者:

唐俊（1990—），男，四川绵阳人，讲师，博士，E-mail：
Effect of mode Ⅱ interlaminar fracture toughness on the tensile properties of carbon/glass hybrid composites
Fahao ZHANG , Changping YIN, Longjie SONG, Suli XING, Dingding CHEN, Jun JIANG, Jun TANG*
Affiliations
  • College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
出版时间: 2025-12-28 doi: 10.11887/j.issn.1001-2486.23090005
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摘要
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为探究纤维混杂复合材料层间性能对其拉伸力学性能的影响，采用7901和9A16两种不同韧性的环氧树脂作为基体，设计和制备了含不同碳纤维铺层数的碳/玻混杂复合材料。并通过理论推导和实验相结合的方式探究了Ⅱ型层间断裂韧性（GⅡC）对碳/玻混杂复合材料失效机理和力学性能的影响规律。结果表明，Ⅱ型层间断裂韧性越大，碳纤维层越趋向于碎片化断裂，具有更高地实现碎片化断裂的临界厚度，有利于伪延展行为的实现。此外，Ⅱ型层间断裂韧性对混杂复合材料模量、强度的影响不显著，变化均在5%以内；但其对伪延展应变有较大影响，当Ⅱ型层间断裂韧性由1.75 N/mm增加到2.08 N/mm时，伪延展应变下降了40.7%。

纤维混杂复合材料  /  基体  /  Ⅱ型层间断裂韧性  /  失效模式  /  拉伸性能

To investigate the effect of interlaminar properties on the tensile properties of fiber hybrid composites, two kinds of epoxy resins with different toughness, 7901 and 9A16, were used as the matrix.Interlayer carbon/glass hybrid composites with different numbers of carbon fiber layers were designed and manufactured.The effects of mode Ⅱ interlaminar fracture toughness(GⅡC)on the failure mode and mechanical properties of carbon/glass hybrid composites were investigated through both theoretical and experimental investigation.The results show that, the higher mode Ⅱ interlaminar fracture toughness is, the more the carbon layer tends to fail in fragmentation, achieving a higher critical thickness for fragmentation, which is beneficial for achieving pseudo-ductility.In addition, the GⅡC on the modulus and strength of hybrid composites is marginal, as the variation is within 5%.However, the GⅡCdemonstrates a significant impact on the pseudo-ductility strain, which is decreased by 40.7% when the GⅡC is increased from 1.75 N/mm to 2.08 N/mm.

fiber hybrid composite  /  matrix  /  mode Ⅱ interlaminar fracture toughness  /  failure modes  /  tensile properties
张发豪, 尹昌平, 宋龙杰, 邢素丽, 陈丁丁, 蒋俊, 唐俊. Ⅱ型层间断裂韧性对碳/玻混杂复合材料拉伸性能的影响. 国防科技大学学报, 2025 , 47 (6) : 199 -207 . DOI: 10.11887/j.issn.1001-2486.23090005
Fahao ZHANG, Changping YIN, Longjie SONG, Suli XING, Dingding CHEN, Jun JIANG, Jun TANG. Effect of mode Ⅱ interlaminar fracture toughness on the tensile properties of carbon/glass hybrid composites[J]. Journal of National Niversity of Defense Technology, 2025 , 47 (6) : 199 -207 . DOI: 10.11887/j.issn.1001-2486.23090005
正文
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纤维增强聚合物基复合材料具有比强度高、比模量高、结构可设计性强等优点，已广泛应用于航空航天、汽车、能源等领域。然而其一般呈现强而脆的特点，在使用过程中，容易在过载条件下发生脆性断裂[1]问题，严重影响构件的安全性。纤维混杂[2-4]是解决该问题的有效手段之一。通过对不同纤维种类、纤维比例、铺层形式等的设计，混杂复合材料[5]能够实现类似于金属屈服的力学行为，从而有效提高纤维增强树脂基复合材料韧性和延展性[6]，解决脆性断裂问题。
复合材料的伪延展性不同于金属材料的屈服，它的本质是混杂复合材料中低失效应变纤维层的渐进、离散的损伤。Jalalvand等[7-9]研究者发现，碳/玻混杂复合材料存在4种典型的失效模式，如图1所示。只有当碳纤维层发生碎片化断裂时（如图1（c）～（d）所示），碳/玻混杂复合材料才展现出伪延展性。而碳纤维层碎片化断裂的条件为：①碳纤维层断裂后玻璃纤维层能够继续承载，不发生过早的整体断裂（如图1（a）所示），为此，外部的玻璃纤维层需足够厚或强以满足承载要求；②碳纤维层断裂后无如图1（b）所示的大面积分层损伤，因此，能否抑制层间大面积分层损伤的萌生是碳/玻混杂复合材料是否呈现伪延展性的关键。
提高层间断裂韧性能够有效增加复合材料抗分层损伤的能力[10-13]。对于拉伸载荷下的碳/玻混杂复合材料，由于碳纤维失效应变小于玻璃纤维，因此，碳纤维层首先发生断裂。碳纤维层断裂后，碳纤维层和玻璃纤维层之间发生平行于拉伸载荷方向的相对位移，层间受剪切应力的作用，此时，形成的分层损伤为Ⅱ型（剪切型）分层损伤。因此，决定碳/玻混杂复合材料层间分层损伤扩展难易程度的性能参数是Ⅱ型层间断裂韧性（GⅡC）。
Ⅱ型层间断裂韧性受树脂基体类型[14-15]以及树脂中增韧影响。Srivastava等[16]以多壁碳纳米管（multi-walled carbon nanotube，MWCNT）为填料置于碳纤维织物复合材料层间，结果表明，GⅡC提升了115%，这是由于碳纳米管桥接基体提高了裂纹尖端生长的阻力，从而有效抑制了分层损伤的萌生。Marino等[17-18]通过在碳纤维层和玻璃纤维层之间增加ABS树脂薄膜（filminterleaving）的方式改变了混杂复合材料的层间断裂韧性。他们发现由于两种不同树脂接触界面生成了新的相界面，能够有效增加纤维层与树脂薄膜的黏合程度，从而有效抑制了大面积分层裂纹的扩展，实现了碳纤维层的碎片化断裂，得到了含有非线性段的拉伸应力-应变曲线，同时，混杂复合材料的模量与强度并没有发生改变。此外，Marino等[19]通过在标准厚度铺层之间加入尼龙-6纳米纤维层，提高了混杂复合材料的层间断裂韧性，更易实现碳/玻混杂复合材料中的碳纤维层的碎片化断裂，从而实现伪延展性。
目前有关复合材料层间断裂韧性的研究，主要聚焦于如何提高层间断裂韧性，并未系统探究层间断裂韧性与混杂复合材料失效机理以及力学行为之间的关系。针对这一问题，本文拟通过建立Ⅱ型层间断裂韧性与混杂复合材料失效模式之间的量化关系，系统探究Ⅱ型层间断裂韧性对混杂复合材料力学行为的影响规律，并对给定Ⅱ型层间断裂韧性混杂复合材料的失效模式进行预测。为了对预测结果进行验证，选取了两种力学性能相当但韧性不同的常用双酚A型环氧树脂（7901和9A16）作为基体来制备不同Ⅱ型层间断裂韧性的混杂复合材料，并对其拉伸性能和失效机理进行了分析。
1　原材料及试样制备
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1.1　原材料
实验所用的原材料如表1所示。其中，9 A16树脂和7901树脂均为双酚A型环氧树脂，其基本性能见表2。由表2可知，两种牌号的环氧树脂除了玻璃化转变温度（Tg）和拉伸强度存在一定差异，其他性能基本相当。但是二者所使用的增韧剂类型和含量均不相同，故其断裂韧性存在显著差异。由于生产厂商并未对相关性能参数进行表征，表2中无断裂韧性具体数值，因此后续对层间断裂韧性进行了实验表征。
1.2　试样制备
本节设计和制备了基于不同树脂基体的Ⅱ型层间断裂韧性试样以及混杂复合材料拉伸试样这两类试样。
1.2.1　Ⅱ型层间断裂韧性试样制备
虽然层间断裂韧性主要由基体性能决定，但是由于碳纤维和玻璃纤维与树脂基体的界面结合性能不同，混杂复合材料层间断裂韧性与单一纤维增强的复合材料的层间断裂韧性存在一定的差异性。为了具体探究此差异性，针对不同的树脂体系，分别设计了三种层间断裂韧性的试样，如图2所示，分别为纯玻璃纤维（GG）构型、纯碳纤维（CC）构型以及碳/玻混杂（C/G）构型，其中，CF表示碳纤维铺层，GF表示玻璃纤维铺层。按照图2所示的具体铺层顺序在模具上对预浸料进行铺覆。在铺覆过程中，于中间位置插入厚度为0.01 mm的聚四氟乙烯（polytetrafluoroethylene，PTFE）薄膜来预制分层，如图3所示。铺覆完成后，采用模压工艺制备试样，固化制度为120℃、1.5MPa下保温、保压2h。待试样冷却至室温后脱模，而后通过水切割设备对层合板进行切割。切割后的试样尺寸为140 mm×24 mm。为观测分层损伤的扩展情况，在试样一侧喷涂一层白色光亮涂层并标记刻度。此外，由于聚四氟乙烯薄膜的厚度为0.01 mm，预制分层损伤尖端较钝，与实际裂纹尖端存在一定的差异，故通过特定工装将预制分层损伤的一侧顶开，从而引入长度为2～5mm的端部较为尖锐的预制裂纹，如图4所示。
1.2.2　混杂复合材料拉伸试样制备
为了系统地探究层间断裂韧性对碳/玻混杂复合材料力学性能的影响，设计了两种不同碳纤维层厚度和体积分数的混杂构型，分别是[G4/C4/G4]（C4）和[G4/C8/G4]（C8），如图5所示。按照所设计的铺层顺序进行预浸料铺覆，并通过模压工艺制备层合板，固化制度为120℃、1. 5 MPa下保温、保压2 h。通过水切割设备对层合板进行切割得到碳/玻混杂复合材料拉伸试样，试样尺寸为240 mm×15 mm，并在试样夹持部分粘贴了50 mm×15 mm的玻璃纤维增强环氧树脂加强片。
2　性能测试方法
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2.1　Ⅱ型层间断裂韧性测试
Ⅱ型层间断裂韧性测试根据JIS K7086—1993标准执行，测试方法为端部缺口三点弯曲实验。加载速度为0.5 mm/min，并通过电荷耦合器件（charge coupled device，CCD）相机拍照记录裂纹尖端移动距离，拍照频率为2 Hz。为保证实验结果可靠性，每类试样至少平行测试5次。
2.2　拉伸性能测试
依据ASTM D3039进行拉伸性能测试，实验采用的设备为力试万能试验机LE5105，加载速率为2 mm/min。每个混杂复合材料构型测试至少测试5个试样。
测试前，对试样表面进行了散斑处理，测试过程中采用CCD相机记录试样变形情况，其采样频率为4 Hz。通过数字图像相关（digital image correlation）技术对图片进行处理，计算得到测试过程中的应变。
对于在拉伸载荷下的混杂复合材料，其典型力学性能指标包括：屈服应力、屈服应变、伪延展应变、拉伸模量、拉伸强度等。各性能指标在应力-应变曲线上的定义见图6。
3　结果分析与讨论
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3.1　基体类型对层间断裂韧性的影响
不同构型复合材料的Ⅱ型层间断裂韧性如图7所示。由图可知，对于同种树脂基体、不同构型试样，从玻璃纤维层到碳纤维层再到碳/玻混杂层，层间断裂韧性呈下降趋势。这表明碳/玻混杂复合材料的层间性能要低于单一的纤维增强复合材料的层间性能，因而，在混杂复合材料层间更容易产生分层损伤。而对于同种构型、不同基体类型的试样，无论是碳纤维层间、玻璃纤维层间还是碳/玻混杂层间，以9A16为基体的复合材料的层间断裂韧性均小于以7901为基体的复合材料的层间断裂韧性，且这种差异在碳纤维层间和碳/玻混杂层间更加显著。这表明7901树脂具有更高的层间断裂韧性，分层损伤更难在7901树脂基体中扩展。
3.2　碳纤维层临界厚度的计算分析
由于碳纤维的失效应变小于玻璃纤维的失效应变，在拉伸载荷下，碳纤维层首先发生断裂。假设碳纤维层断裂释放的能量全部由分层损伤所消耗，那么，可以通过应变能释放率G（单位面积所消耗的应变能）与Ⅱ型层间断裂韧性GⅡC[8，20-21]的大小关系来判断是否产生分层损伤。当G≥ GⅡC时，表明碳纤维层断裂释放的应变能足以引起层间分层损伤的萌生与扩展，此时，碳纤维层不会发生碎片化断裂；当G＜GⅡC时，表明碳纤维层断裂释放的应变能不足以引起分层损伤，此时，碳纤维层在应力重新分布的条件下，趋向于碎片化断裂。
图8所示为碳/玻混杂复合材料的层间分层损伤示意图，玻璃纤维层和碳纤维层的厚度分别是tglass、tcarbon，模量为Eglass、Ecarbon，试样的宽度为W。
碳纤维层断裂前混杂复合材料的初始模量E1可由式（1）计算得到。
其中，混杂复合材料总厚度ttot=2tglass+tcarbon，则碳/玻混杂复合材料初始模量可表示为：
碳纤维层断裂引发分层损伤时，混杂复合材料的等效弹性模量E2可由式（3）计算得到。
在拉伸载荷下，单位长度混杂复合材料的应变能U可由式（4）进行计算，其中σ、ε分别是混杂复合材料的应力和应变，E是混杂复合材料的模量。
单位长度混杂复合材料分层损伤前后所释放的应变能可由式（5）进行计算，其中U1表示分层损伤产生前的应变能，U2表示分层损伤产生后的应变能。
此时，能量释放率G可表示为：
将式（2）～（5）代入式（6）中可得：
由于碳纤维断裂前，混杂复合材料沿厚度方向变形一致，则中间碳纤维层的应力σcarbon可由式（8）得到。
将σcarbon代入式（7），得到能量释放率G表达式的另一种形式。
式（9）中，碳纤维断裂时所受应力σcarbon等于碳纤维复合材料的强度Scarbon。由此，便可计算得到不同玻璃纤维层厚度下的应变能释放率G与碳纤维层厚度tcarbon之间的关系如图9所示。计算时所用的性能参数见表3。
由图9可知，在特定玻璃纤维层厚度下，随着碳纤维层厚度的增加，其断裂时应变能释放率呈上升趋势；随着玻璃纤维层厚度的增加，应变能释放率呈下降趋势。
此外，对于所设计的玻璃纤维层厚度为0.48 mm的混杂复合材料，令G=GⅡC，便可计算特定层间断裂韧性条件下实现碳纤维层碎片化断裂的临界厚度tcarbon-c，tcarbon-c与GⅡC的关系如图10所示。由图可知，该曲线将区间分为两部分，曲线上下两部分分别对应着不同的失效模式。在曲线上方的部分，碳纤维层断裂后引发大面积分层，而下方部分则是对应着碳纤维层碎裂的失效模式。实现碎片化断裂的碳纤维层临界厚度与Ⅱ型层间断裂韧性呈正相关关系，这说明更大的GⅡC意味着混杂复合材料可在更厚的碳纤维层下实现碳纤维的碎片化断裂，从而使混杂复合材料呈现伪延展性。
3.3　Ⅱ型层间断裂韧性对失效机理的影响
图11所示为C4（9 A16）碳/玻混杂复合材料的应力-应变曲线和对应的失效过程图。图11中的浅灰色区域表示碳纤维层和玻璃纤维层之间的分层损伤。加载前的试样如图11中①所示。当加载到一定载荷时，碳纤维层发生断裂，即②点，而后断裂成离散的、较小的碎片，在碳纤维层断裂处均产生局部的分层损伤，而外部半透明的玻璃纤维层保持完整，如图11中的③所示。随着载荷继续增加，局部分层损伤发生扩展，如图11中的④所示。碳纤维层的碎片化以及局部分层损伤的逐渐扩展起到消散应变能的作用，因此，碳/玻混杂复合材料表现出显著的伪延展性。继续加载，碳纤维层碎片化断裂趋近于饱和，离散的局部分层损伤汇聚成贯穿整个试样的大面积分层，如图11中的④所示。而当玻璃纤维层无法继续承受拉伸载荷时，试样开始发生劈裂，从而导致整个混杂复合材料的失效，如图11中的⑤所示。
图12所示为C4（7901）碳/玻混杂复合材料的应力-应变曲线和对应的失效过程图，与C4（9 A16）类似，同样表现出良好的伪延展性。不同的是，C4（7901）试样中碳纤维层碎片更加细小、离散。当碳纤维层开始断裂后，应力相比于C4（9 A16）保持不变，C4（7901）复合材料应力仍然以较高的速率在增大，这主要是由于局部分层损伤扩展较小，未分层的碳纤维层仍能够承受一定的载荷。
图13与图14分别为C8（9 A16）和C8（7901）碳/玻混杂复合材料的应力-应变曲线和对应的失效过程图。二者的失效模式均为碳纤维断裂后引起大面积分层损伤。在应力-应变曲线上呈现应力掉落，没有呈现伪延展性。不同的是C8（7901）构型的分层扩展较为缓慢，应力掉落速率和幅度都低于C8（9 A16）的。C8（7901）虽然也没有表现出伪延展性，但其拉伸行为所表现出的延展性要比C8（9A16）更好，这是由于C8（7901）具有更高的Ⅱ型层间断裂韧性。这意味着C8（7901）吸收相同应变能后会产生更小的分层损伤，并且分层损伤扩展速率也更加缓慢。
根据3.1节中的测试结果，结合前述理论推导，可以计算得到以9A16树脂为基体的碳/玻混杂复合材料中碳纤维实现碎片化断裂的临界厚度为130 μm，而以7901树脂为基体的混杂复合材料的临界厚度为157 μm。由于碳纤维单层厚度为20 μm，则分别需要6层和8层碳纤维的堆叠以达到其临界厚度。图15所示为理论预测的碳纤维层临界厚度与实验测量值的对比。由图可知，在特定的GⅡC下，通过理论计算得到的混杂复合材料碳纤维层的临界厚度与实际构型中的碳纤维层厚度的比较，可以预测碳/玻混杂复合材料的失效模式，经对比，理论预测与实验测量结果具有良好的一致性。
3.4　Ⅱ型层间断裂韧性对拉伸性能的影响
图16所示为不同构型碳/玻混杂复合材料的力学性能，包括模量、强度、碳纤维层断裂起始点应变、碳纤维层断裂起始点应力、伪延展应变。
从模量来看，相同构型下，将混杂复合材料环氧9A16基体替换为环氧7901基体，C4、C8构型的模量基本一致，但有小幅度的下降，分别下降了4.98%、1.83%。树脂基体对于单向复合材料模量的贡献较小，造成这种差别的主要原因可能是两种树脂基体预浸料中纤维体积分数的差异性。
对于强度而言，相同构型下，两种基体混杂复合材料的拉伸强度基本一致。C4（7901）的强度相对于C4（9A16）略有提高。这表明改变基体类型，即改变层间断裂韧性，对于碳/玻混杂复合材料的强度影响不大。
而对于碳纤维层断裂起始点，无论是C4还是C8构型，9A16树脂混杂复合材料中碳纤维层发生断裂时的应变均高于7901树脂混杂复合材料的，碳纤维层第一次断裂应变分别高了1. 12%、7.98%。由于两种基体混杂复合材料的模量基本一致，相较于7901树脂混杂复合材料，9A16树脂混杂复合材料中碳纤维层发生断裂时的应力也略高，分别高了4.62%、5.93%。相较于C4构型，C8构型的碳纤维层断裂起始点应变和应力提高更明显。
从伪延展应变来看，将混杂复合材料环氧9A16基体替换为环氧7901基体，C4构型的伪延展应变降低了40.7%。根据前面层间断裂韧性测量结果，9A16树脂混杂复合材料的层间断裂韧性要低于7901树脂混杂复合材料的层间断裂韧性。因此，分层损伤更容易在9A16树脂混杂复合材料的层间进行扩展。这表明，分层损伤的扩展有利于混杂复合材料高延展性的实现，由于分层损伤的扩展受Ⅱ型层间断裂韧性的控制，因此，在碳纤维层厚度低于临界厚度的前提条件下，适当降低Ⅱ型层间断裂韧性能够提高碳/玻混杂复合材料延展性。
4　结论
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1）实现碎片化断裂的碳纤维层临界厚度与Ⅱ型层间断裂韧性呈正相关关系，这表明具有更大Ⅱ型层间断裂韧性的混杂复合材料可在更厚的碳纤维层下实现伪延展性。
2）通过理论计算碳纤维层临界厚度，并以此预测的混杂复合材料失效模式与实验测量结果具有良好的一致性。Ⅱ型层间断裂韧性代表层间分层损伤扩展需要的能量，更大的Ⅱ型层间断裂韧性意味着分层损伤的萌生与扩展更难，从而使碳/玻混杂复合材料的失效模式更加倾向于碳纤维层的碎片化断裂。
3）Ⅱ型层间断裂韧性对混杂复合材料模量、强度的影响不明显；而其对伪延展应变有明显影响，在临界厚度以下，适当降低Ⅱ型层间断裂韧性能够提高碳/玻混杂复合材料延展性。
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2025年第47卷第6期
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doi: 10.11887/j.issn.1001-2486.23090005
  • 接收时间：2023-09-12
  • 首发时间：2026-04-16
  • 出版时间：2025-12-28
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    国防科技大学　空天科学学院，湖南　长沙　410073

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唐俊（1990—），男，四川绵阳人，讲师，博士，E-mail：
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2种不同金属材料的力学参数
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Number of
species		 占总种数比例
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total species (%)		 属
Genus		 种数
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鹅膏菌科Amanitaceae 2 11 5.26 鹅膏菌属 Amanita 10 4.78
小菇科 Mycenaceae 2 12 5.74 丝盖伞属 Inocybe 5 2.39
多孔菌科 Polyporaceae 8 14 6.70 蜡蘑属 Laccaria 5 2.39
红菇科 Russulaceae 3 23 11.00 小皮伞属 Marasmius 6 2.87
小菇属 Mycena 11 5.26
光柄菇属 Pluteus 5 2.39
红菇属 Russula 17 8.13
栓菌属 Trametes 5 2.39
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