宁波大学硕士专业论文
CFRP帽型加筋壁板薄壁芯模辅助热压共固化成型技术研究
摘要
碳纤维增强复合材料(CFRP)作为一种性能优异的新型材料，具有其高比模、高比强、耐腐蚀、耐高温、耐疲劳、阻尼减震性好、破损安全性好、可设计性和多功能一体化等一系列优点，CFRP帽型加筋结构因具有结构稳定性好、传递周向载荷效率相对较高和屈曲强度高等优点，在新型飞机的曲面结构中得到大量的应用。在帽型加筋壁板的热压罐成型制造工艺中，共固化成型工艺因入罐次数少，极大降低了成本；且共固化也不需要胶接胶黏剂，界面力学性能好，制件重量轻，变形小，这对于对重量大和外形尺寸要求精确的大型客机承重力结构，具有相当大的优势。
针对过去帽型加筋壁板共固化方案中，真空袋芯模易在成型过程中发生真空袋破损、褶皱造成表面质量不好；金属芯模在曲面的壳型件成型应用中常常出现脱模困难的问题；水溶性芯模本身易在实验过程中出现破损现象；带预制孔硅胶芯模在压力传递过程中，无法保证压力均匀性问题。本文提出了基于薄壁硅胶气囊芯模辅助热压罐共固化成型碳纤维增强树脂基复合材料帽型加筋壁板的新工艺。
文章通过建立热压罐共固化CFRP帽型加筋壁板的热-力-流动多场耦合的数学模型，并基于COMSOL Mul
tiphysics有限元软件对薄壁硅胶气囊芯模辅助成型帽型加筋壁板的热压罐共固化过程进行了建模。根据材料特性、固化度建立了热压工艺曲线，通过有限元模拟仿真研究了不同壁厚的硅胶气囊芯模，不同框架模具对制件压力及壁厚的影响。分析得到新工艺制造过程中制件的压力与壁厚都比较均匀，且1mm壁厚的硅橡胶与帽型框架的成型效果相对较好。通过对热压罐共固化实验成型制件的检测，验证了有限元模型的正确性。并结合制件界面结合的力学拉伸实验检测结果，研究了不同壁厚的硅胶气囊芯模和不同框架模具对帽型长桁与蒙皮之间的力学性能的影响。结果显示1mm壁厚的硅橡胶与帽型框架的界面强度效果很好。
综上所述，经过帽型加筋壁板制件的成型质量研究说明基于硅胶气囊芯模辅助CFRP帽型加筋壁板的热压罐共固化成型的新工艺是可行的。
关键词：CFRP帽型加筋壁板；硅胶气囊；厚度；压力；界面结合
CFRP帽型加筋壁板薄壁芯模辅助热压共固化成型技术研究
Rearch on New Core-die Auxiliary Hot Pressing
英语励志短文
Co-curing Technology for CFRP Hat-stiffened Panels
Abstract
As a new type of material with excellent performance,carbon fiber reinforced composite (CFRP)has high specific modulus,high specific strength,corrosion resistance,high temperature resistance,fatigue resistance,good damping and shock absorption,good damage safety,designability and A ries of advantages such as multi-functional integration,CFRP hat-shaped reinforced structure has a large number of applications in the curved structure of new aircraft due to its structural stability,relatively high transmission circumferential load efficiency and high buckling strength.In the autoclave forming process of the hat-shaped reinforced wall panel,the co-curing molding process has a small number of cans,which greatly reduces the cost;and the co-curing does not require a glue adhesive,and the interface mechanical properties are good.The light weight and small amount of deformation have considerable advantages for the weight-bearing structure of a large pasnger aircraft that requires a large weight and a preci size.
In the past co-cure scheme of the hat-shaped stiffened wall panel,the vacuum bag core mold is easy to be damaged during the forming process,and the surface quality is not good due to the wrinkles;the metal core mold often appears to be demolded in the curved shell molding application.Difficult problem;the water-soluble core mold itlf is easy to break during the experiment;the silicone core mold with pre-formed hole can not guarantee the pressure uniformity du
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ring the pressure transmission process.In this paper,a new process for forming a carbon fiber reinforced resin matrix composite hat-stiffened panel bad on thin-walled silica gel airbag core mold assisted autoclave is propod.
The paper establishes a mathematical model of thermo-force-flow multi-field coupling of CFRP hat-stiffened panel siding by co-curing the autoclave,and bad on the COMSOL Multiphysics finite element software,the hat-shaped reinforced siding is assisted by the thin-walled silicone airbag core mold.The autoclave co-cure process was modeled.According to the material characteristics and curing degree,the hot pressing process curve was established.The effects of different frame molds on the pressure and wall thickness of the
宁波大学硕士专业论文
shell were studied by finite element simulation.The pressure and wall thickness of the parts in the new process manufacturing process are relatively uniform,and the forming effect of the silicone rubber and the hat-shaped frame with a wall thickness of1mm is relatively good. The correctness of the finite element model was verified by testing the autoclave experimental molded parts.Combined with the mechanical tensile test results of the interface of the workpiece,the effects of different wall th古铜色英文
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ickness silicone airbag core molds and different frame molds on the mechanical properties between the hat-shaped long raft and the skin were studied.The results show that the interface strength of the silicone rubber of1mm wall thickness and the hat frame is very good.
In summary,the rearch on the molding quality of the hat-stiffened panel plate parts shows that the new process of co-curing of the autoclave bad on the silicone air bag core mold assisted CFRP hat-stiffened panel plate is feasible.
Key words:CFRP Hat-stiffened Panel，silicone balloon，thickness，pressure，interface bonding
CFRP帽型加筋壁板薄壁芯模辅助热压共固化成型技术研究
evolution是什么意思目录
1绪论 (1)
1.1研究背景 (1)
1.2热压罐工艺 (3)
1.2.1基本原理 (3)
1.2.2工艺特点 (3)
1.3碳纤维复合材料成型国内外研究现状 (4)
1.3.1整体化成型方案 (4)
1.3.2加筋壁板成型方式 (5)
1.3.3力学性能现状 (6)麻省理工公开课
1.4课题来源及意义 (6)
correct用法1.5课题研究内容 (7)
2复合材料固化过程建模 (8)administration是什么意思
2.1结构简化 (8)
2.2复合材料固化变形数学模型 (8)
2.2.1热传导模型 (9)
2.2.2树脂粘度模型 (10)
站姿妖娆成网红2.2.3固化动力学模型 (10)
2.2.4流动压实模型 (11)
2.3工艺原理 (12)
2.4复合材料固化过程仿真 (13)
2.4.1几何建模 (13)
2.4.2模块参数定义 (15)
2.4.3网格划分 (16)
2.5固化度成型结果 (17)
2.6有限元模拟仿真对比 (17)
2.7本章小结 (19)
3实验原理与方法 (20)
3.1概述 (20)
3.2实验材料与设备 (20)
3.2.1主要材料 (20)
3.2.2辅助材料 (20)
宁波大学硕士专业论文
3.2.3实验设备 (21)
3.3模具的设计与制造 (22)
3.3.1硅胶气囊芯模与模具的制造 (22)
3.3.2框架模具 (23)
3.4试样制备 (24)
3.4.1碳纤维帽型件的预制件制备 (24)
3.5.2界面结合强度测试试样制备 (25)
3.6实验结果缺陷分析 (26)
3.7实验对比 (27)
3.8仿真与实验验证 (28)
3.9本章小结 (29)
4硅胶气囊芯模壁厚对CFRP帽型加筋壁板的成型质量影响 (30)
4.1壁厚对制件变形的影响 (30)
4.2壁厚对制件内部成型压力的影响 (32)
4.3壁厚对制件成型尺寸的影响 (33)
4.4壁厚对制件界面强度的影响 (36)
4.5本章小结 (38)
5不同框架模具对CFRP帽型加筋壁板的成型质量影响 (40)
5.1不同框架模具对制件变形的影响 (40)
5.2不同框架模具对制件内部成型压力的影响 (41)
5.3不同框架模具对制件成型尺寸的影响 (43)
5.4不同框架模具对制件界面强度的影响 (45)
5.5本章小结 (47)
6结论与展望 (48)
6.1结论 (48)
6.2展望 (48)
参考文献 (50)
在学研究成果 (54)
介词练习题
致谢 (55)
