摘要
为获取复合材料在温度影响下的力学性能,提出了理论预示模型,分析并讨论了模型中的相关参数,建立了满足固体火箭发动机壳体用炭纤维/环氧树脂复合材料及基体材料随温度变化的数学模型。应用该预示方法获取的数据与实验结果吻合较好,能够获得材料在任意温度下的性能变化规律,可作为工程应用中材料设计的计算手段和选材基本依据,对评价和应用复合材料耐热性有一定的指导意义。同时,利用网格理论及混合定律,分析了平衡型纤维缠绕复合材料壳体随温度变化的规律,将该方法扩展到对复合材料壳体爆破压强随温度变化的性能预示。
To obtain mechanical properties of composite material under the influence of temperature, the model of theory predic- tion was put forward and dependent parameters in the model were analyzed and discussed.Mathematic models of composite material and epoxy resin material were established. The results of prediction and test coincided well. Performance variation laws of material under the arbitrary temperature were obtained,which can be used as the calculation methods and material design and basic founda- tion of material selection.Finally, the variation laws of composite material ease with temperature were analyzed by using grid theory and mixing laws.This method was expanded to predict the performance of composite material ease burst pressure with temperature variation.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2013年第6期831-835,共5页
Journal of Solid Rocket Technology
关键词
复合材料
强度
模量
力学性能
性能预示
composite material
strength
modulus
mechanical properties
performance prediction
