航空材料学报2024，Vol.44Issue(6)：72-81,10.DOI:10.11868/j.issn.1005-5053.2023.000204
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
摘要
Abstract
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Key words
curing deformation/core material/laying-up sequence/frontal structure/finite element simulation分类
航空航天引用本文复制引用
陈林杰,成艳娜,刘向阳,李尧,闫超,滕薛蓓,许英杰..芳纶铺层夹层结构U型前缘固化变形计算与分析[J].航空材料学报,2024,44(6):72-81,10.基金项目
国家重点研发项目(2021YFF0500100) （2021YFF0500100）
