基于多尺度的固体火箭发动机复合材料壳体及其缠绕纤维强度精确预示  

Accurate prediction of winding fibre strength of solid rocket motor composite case based on multi-scale method

作　　者：颜勇 牟星 张骞 祖磊 张桂明 王立强 扶建辉 陈世军 YAN Yong;MOU Xing;ZHANG Qian;ZU Lei;ZHANG Guiming;WANG Liqaing;FU Jianhui;CHEN Shijun(Key Laboratory of National Defense Science and Technology of Combustion,Thermal Structure and Internal Flow Field,The 41st Institute of the Fourth Academy of CASC,Xi'an 710025,China;School of Mechanical Engineering,Hefei University of Technology,Hefei 230009,China)

机构地区：[1]中国航天科技集团有限公司四院四十一所,燃烧、热结构与内流场国防科技重点实验室,西安710025 [2]合肥工业大学机械工程学院,合肥230009

出　　处：《固体火箭技术》2022年第6期817-829,共13页Journal of Solid Rocket Technology

摘　　要：针对纤维缠绕成型过程中存在纤维交叉起伏结构,导致纵向缠绕层纤维发挥强度不理想问题。构建了考虑复合材料多尺度结构特征的宏-细-微观跨尺度模型,开展了基于纤维细观尺度的渐进损伤实效行为研究,实现了结构失效状态及强度折减系数在不同尺度间的传递,最终预示了纤维缠绕壳体损伤失效。制备了直径300 mm的纤维缠绕壳体并开展水压打爆测试,测试结果表明,该跨尺度方法预测爆压值与实验测试值误差为1.4%,且所得整体应力分布较传统层合建模方法和实验值更为吻合。该分析方法可以为纤维缠绕复合材料壳体精细化设计分析提供参考价值,提升了纤维缠绕复合材料壳体工艺-设计一体化技术应用水平。The undulation and cross-over flaws of the fiber during fiber-wound fabrication process can lead to the unsatisfactory strength of the longitudinal winding fiber.A macro-fine-micro cross-scale model considering multi-scale structural characteristics of the composite was established.The progressive damage failure behavior at the meso-scale was investigated,moreover the structure failure state and transmitting strength reduction coefficient between different scales was realized.Finally,the damage failure of the fiber-wound case was predicted.A 300 mm diameter composite case was fabricated and subjected to a hydro-burst test.The test results show that the error between the predicted burst pressure of the cross-scale model method and the experimental test value is 1.4%.Compared with traditional laminated modeling method,the obtained overall stress distribution with this method is more consistent with the experimental value,this method could provide a theoretical reference for accurate design of fiber wound composite cases,which could improve the fabrication process and design integration level of fiber-wound composite case.

关 键 词：复合材料壳体 多尺度模型 渐进失效 纤维发挥强度 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] TB332[一般工业技术—材料科学与工程]