摘要
针对热固性复合材料存在较为严重的固化变形问题,通过数值分析的方法对热固性树脂基复合材料加筋壁板的固化变形进行研究。选取热压罐成型复合材料加筋壁板构件做为研究对象,建立了热固性树脂基复合材料反应动力学模型、热压罐内复合材料温度场和固化变形场的时变模型,利用ABAQUS有限元分析软件Heat transfer模块计算热传递、General static模块分析变形场,计算分析温度、压力等典型工艺参数对T型加筋壁板固化变形的影响。结果表明:升温速率取3 K/min,罐内压力取0.4~0.6MPa,即可满足制件的加工精度要求也能够满足经济性要求;保温温度的提高和保温时间的延长均导致了本例固化变形的减小;双平台固化的结果不如单平台固化的;铺层一致性越高,对称性越好,固化变形越小。
Aiming to solve the problem of serious curing deformation of the thermoset resin matrix composite material,the curing deformation of stiffened composite panel was numerically studied. Reaction kinetics model of thermosetting resin matrix composites and the time-varying models of temperature field and solidification deformation field of the composite material in autoclave were established.ABAQUS Heat transfer module was used to calculate the heat transfer and ABAQUS General static module was used to analyze the deformation field. The impacts of different processing parameters such as temperature and pressure to the curing deformation of the composite panel with T shape stiffener were studied. The results show that while the heating rate is 3 K/min and the autoclave pressure is 0.4 to 0.6MPa both accuracy and economic requirements can be met. The increase of holding temperature and holding time leads to the reduction of curing deformation. The one-step temperature profile curing can achieve a better result than the two-step temperature profile curing. The improvement in the uniformity and symmetry of the layup will reduce the curing deformation.
作者
徐碧娥
XU Bi-e(AECC Commercial Aircraft Engine Co.,LTD,Shanghai 200241)
出处
《航空发动机》
北大核心
2022年第6期71-76,共6页
Aeroengine
基金
航空动力基础研究项目资助。
关键词
固化变形
热固性树脂基复合材料
时变模型
数值分析
航空发动机
curing deformation
thermoset resin matrix composite
time-varying model
numerical analysis
aeroengine
