Prediction of Distortion in Flanged Composite Laminates Using Viscoelastic Models
This paper presents an investigation into the flange angle distortion of flanged carbon-epoxy composite laminates using finite element analysis.Tests are conducted to determine material models of the composites at elevated temperatures.A thermo-mechanically coupled and viscoelastic finite element model is developed to predict the deformation of the composite laminates during and after cure and subsequent reheating and/or assembly processes respectively.Comparison is made between the predicted and measured angle distortion of the laminates under both static and transient conditions,and good agreement is obtained.It is shown both experimentally and numerically that due to viscoelasticity of the composite laminates,significant amount of spring-in angle distortion is locked in the laminates manufactured using the standard autoclave process,in which the laminates are constrained to the mould by the applied autoclave pressure and vacuum.The “locked-in distortion is released if the laminates are subsequently thermal-loaded and cooled,resulting in an increase of the spring-in angle for the flanged laminates.
Composite laminate Spring-in Viscoelasticity Finite Elements
Xiaolin Liu Paul Falzon
Advanced Composite Structures Australia Pty Ltd,1/320 Lorimer Street,Port Melbourne,VIC 3207,Australia
国际会议
2014 Asia-Pacific International Symposium on Aerospace Technology(2014亚太航空航天技术学术会议)
上海
英文
1-8
2014-09-24（万方平台首次上网日期，不代表论文的发表时间）