复合材料叠层板固化成型后的变形分析计算  

Composite Laminates Deformation Analysis and Calculation After Curing

作　　者：官霆[1] 孙良新[1] 邢丽英[2] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016 [2]北京航空材料研究院,北京100095

出　　处：《宇航材料工艺》2006年第1期34-37,共4页Aerospace Materials & Technology

摘　　要：文摘分析复合材料铺层的微观结构,研究复合材料成型过程变形特点,以此建立两类针对性的有限元模型,并采用典型复合材料叠层板固化成型温度载荷,进行叠层板翘曲变形和板内应力的计算分析。在此基础上,将计算结果与实际试验制件实测结果进行对比。结果表明,本文所提供的有限元分析计算模型可对实际情况进行简便和较为精确的模拟。The micro composition and the deforming theorem of composite laminates are analyzed. Accordingly, the special finite element models are built, and the residual deformation and the stress are calculated and analyzed with the composite curing temperature load. The analysis of the results of the finite element model is completed. Moreover, the calculating results are compared with that of test specimen. The difference between calculation and test are analyzed. The result shows that the composite deforming finite element analyzing method is simple and effective.

关 键 词：复合材料 叠层板 残余应力 残余变形 

分 类 号：TB33[一般工业技术—材料科学与工程]