芳纶铺层夹层结构U型前缘固化变形计算与分析  

Calculation and analysis of curing deformation of U-shaped leading edge of aramid-layer sandwich structures

作　　者：陈林杰 成艳娜 刘向阳 李尧 闫超 滕薛蓓 许英杰[2] CHEN Linjie;CHENG Yanna;LIU Xiangyang;LI Yao;YAN Chao;TENG Xuebei;XU Yingjie(AVIC Xi’an Aircraft Industry Group Corporation,Xi’an 710000,China;School of Mechanical Engineering,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]中航西安飞机工业集团股份有限公司,西安710000 [2]西北工业大学机电学院,西安710072

出　　处：《航空材料学报》2024年第6期72-81,共10页Journal of Aeronautical Materials

基　　金：国家重点研发项目(2021YFF0500100)。

摘　　要：以芳纶铺层U型前缘为研究对象,建立固化温度场模型和固化变形场模型,揭示其固化变形机理,探究夹芯材料、内蒙皮铺层顺序以及前缘结构对整体构件固化变形的影响规律。结果显示,高弹性模量的硬质泡沫可在固化压力下给予内蒙皮良好支撑,并降低芯材内部缺陷和固化变形。相较于芯材材料,内蒙皮铺层顺序和前缘结构对构件的固化变形具有显著影响。综合考虑构件的不对称性带来的固化后收口、扭转变形,采用[0/45/-45/0/0/0/45]内蒙皮铺层顺序可达到最小化固化变形。With the U-shaped leading edge made of aramid laminate as the focus of this study,we have developed models for both the curing temperature field and the curing deformation field,aiming to unravel the underlying mechanisms of its curing deformation.Our investigation delves into the various influence patterns of core materials,the sequence of the inner skin laying-up,and the structure of the leading edge on the overall curing deformation of the component.The findings reveal that rigid foam characterized by a high elastic modulus effectively supports the inner skin under curing pressure,thereby minimizing internal defects and curing deformation within the core material.Compared with the core material,the sequence of the inner skin laying-up and the design of the leading edge structure exert a more profound influence on the curing deformation of the component.Taking into account the post-curing neck-in and torsional deformation stemming from the component’s asymmetry,we have found that employing the[0/45/−45/0/0/0/45]laying-up sequence for the inner skin achieves minimal curing deformation.

关 键 词：固化变形 芯材材料 铺层顺序 前缘结构 有限元仿真 

分 类 号：V261.97[航空宇航科学与技术—航空宇航制造工程]