基于预浸料-树脂传递模塑成型工艺的复合材料纵横加筋舱段一体化制备与验证  

Integration manufacturing and testing verification for composite cross stiffened cabin via hybrid prepreg-resin transfer moulding process

作　　者：李伟东 温小雪 马征峥 罗楚养 包建文 钟翔屿 胡晓兰[3] 程功[4] LI Weidong;WEN Xiaoxue;MA Zhengzheng;LUO Chuyang;BAO Jianwen;ZHONG Xiangyu;HU Xiaolan;CHENG Gong(National Key Laboratory of Advanced Composites,AVIC Composite Technology Center,AVIC Composite CO.LTD.,Beijing 101300,China;Collaborative Innovation Center for Civil Aviation Composites,Donghua University,Shanghai 201620,China;College of Materials,Xiamen University,Xiamen 361005,China;Aviation Key Laboratory of Science and Technology on Airborne Guided Weapon,China Airborne Missile Academy,Luoyang 471009,China)

机构地区：[1]中航复合材料有限责任公司航空工业复合材料技术中心,先进复合材料重点实验室,北京101300 [2]东华大学民用航空复合材料协同创新中心,上海201620 [3]厦门大学材料学院,厦门361005 [4]中国空空导弹研究院,航空制导武器航空科技重点实验室,洛阳471009

出　　处：《复合材料学报》2023年第5期2628-2638,共11页Acta Materiae Compositae Sinica

基　　金：青年人才托举工程(2016 QNRC001);中央高校基本科研业务费专项资金(2232022D-28)。

摘　　要：针对舱段的结构特点设计了一种预浸料-树脂传递模塑(RTM)成型工艺。研究了预浸料树脂(AC631)与RTM树脂(6421A)的流变特性,结果表明两种树脂体系具有良好的共成型工艺基础。结合舱段结构设计、铺层设计、模具设计,开展了基于预浸料-RTM共成型技术的复合材料纵横加筋舱段一体化制备工艺验证,结果表明舱段结构具有良好的表观质量、尺寸精度及内部质量。常温、高温两种条件静强度试验验证了其使用强度,高温破坏试验研究了其失效机制与破坏模式。常温力学试验结果表明:在125%严酷机械载荷下,复合材料舱段能够保持良好的结构完整性,其最大应变仅为-1283×10^(-6),满足常温静强度设计要求。100℃下静强度试验结果显示,舱段在125%严酷机械载荷下未出现失稳、破坏等异常状态,最大应变仅为-1315×10^(-6),满足热力耦合工况条件下的强度设计要求。150℃高温破坏试验结果显示,舱段在143.2%严酷机械载荷下,加载侧纵向加强筋发生断裂破坏,裂纹向两侧延伸,舱段丧失承载能力,破坏模式为轴向筋条断裂导致蒙皮局部屈曲失稳破坏。A hybrid prepreg-resin transfer moulding(Prepreg-RTM)process was proposed to realize the integration manufacturing of composite cross stiffened composite cabin.The rheological properties of prepreg resin(AC631)and RTM resin(6421A)were studied.The results show that the two resin systems have good co-forming processes basis.Combined with cabin structure design,layup design and mould design,the integrated preparation process of composite cross stiffened cabin based on hybrid Prepreg-RTM technology was verified.The results show that the cabin structure has good surface quality,dimensional accuracy and internal quality.The service strength of cabin was verified by static strength tests at room temperature and high temperature,and its failure mechanism and failure mode were studied by high temperature failure test.The results of static strength test at room temperature show that the cabin maintains good structural integrity under 125%service load,and the maximum strain of the cabin is−1283×10^(−6) which meets the static strength design requirements.The static strength test results at 100℃reveal that the maximum strain of the cabin is−1315×10^(−6).There is no abnormal state such as instability and failure occurred in the cabin,which meets the requirements of thermal-mechanical coupling condition design.The high temperature failure experiment results demonstrated that the cross stiffened composite cabin failed under 143.2%service load at high temperature of 150℃,caused by the fracture of the longitudinal stiffener in loading side,where the crack propagated to both sides.The failure model of the cabin is local buckling of skin due to the fracture of the longitudinal stiffener.

关 键 词：复合材料 纵横加筋舱段 预浸料-树脂传递模塑共成型工艺 力学响应 破坏机制 

分 类 号：TB332[一般工业技术—材料科学与工程] V214.8[航空宇航科学与技术—航空宇航推进理论与工程]