某大型T800壳体结构精细化建模及损伤失效分析  

Refined modeling and damage failure analysis of a large T800 shell structure

作　　者：喻琳峰 任全彬 宋学宇 张爱华 YU Linfeng;REN Quanbin;SONG Xueyu;ZHANG Aihua(Xi’an Institute of Aerospace Propulsion Technology,China Aerospace Science and Technology Corporation,Xi’an 710025,China;Aerospace Solid Propulsion Technology Institute,China Aerospace Science and Technology Corporation,Xi’an 710025,China)

机构地区：[1]中国航天科技集团有限公司西安航天动力技术研究所,西安710025 [2]中国航天科技集团有限公司航天动力技术研究院,西安710025

出　　处：《航空动力学报》2025年第1期346-358,共13页Journal of Aerospace Power

摘　　要：利用Python对ABAQUS二次开发的方法,建立了精细化的壳体后封头结构模型。针对复合材料壳体封头纤维缠角及厚度不断变化的特点,编制计算程序,精确计算出封头部位每个纵向缠绕层缠绕角的大小以及缠绕层随半径变化的层厚,较真实地建立了固体火箭发动机复合材料壳体后封头结构的有限元分析模型,在一定内压载荷下对其应变情况进行了分析。将分析的结果与试验结果比较,验证了该模型的准确性。使用UMAT(user-defined material)子程序,引入损伤失效准则对壳体结构进行了损伤失效分析,进一步获取了该结构在内压载荷逐渐增加时,其破坏位置,破坏形式,最终得出了该缠绕层结构的最终破坏形式为封头靠近赤道位置处的纤维断裂破坏,对今后的复合材料壳体结构设计提供了依据。Using the method of Python’s secondary development of ABAQUS,a refined shell back head structure model was established.According to the characteristics of the fiber winding angle and thickness of the composite shell head,the calculation program was compiled to accurately calculate the winding angle of each longitudinal winding layer and the thickness of the winding layer varying with the radius.The finite element analysis model of the rear head structure of the solid rocket motor composite shell was established,and the strain was analyzed under certain internal pressure load.The accuracy of the model was verified by comparing the analysis results with the experimental results.The UMAT(userdefined material)subroutine was used to introduce the damage failure criterion to analyze the shell structure,and the failure position and failure form of the structure were further obtained when the internal pressure load gradually increased.Finally,it was concluded that the final failure form of the winding layer structure was the fiber fracture failure near the equatorial position of the head,helping to provide a basis for the design of the composite shell structure in the future.

关 键 词：纤维缠绕 复合材料壳体 精细化模型 损伤力学 渐进损伤 破坏模式 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]