固体火箭发动机壳体干法缠绕成型技术研究  

Research on Dry Winding Forming Technology for Solid Rocket Engine Shell

作　　者：王英超 黄泽勇 郭文波 黄凯 靳康康 Wang Yingchao;Huang Zeyong;Guo Wenbo;Huang Kai;Jin Kangkang(Hubei Sangjiang Space Jiangbei Mechanical Engineering Co.,Ltd.,Xiaogan 432000)

机构地区：[1]湖北三江航天江北机械工程有限公司,孝感432000

出　　处：《航天制造技术》2023年第6期30-35,共6页Aerospace Manufacturing Technology

摘　　要：相比传统湿法缠绕成型工艺,干法缠绕环保清洁,无树脂污染,可以解决去手工化问题,提高生产效率,同时精确控制预浸料树脂含量,提高产品质量的可靠性,具有诸多优点,有望成为未来固体火箭发动机复合材料壳体缠绕成型工艺技术的主流方向。本文以T700丝束预浸纱为原料,通过干法缠绕制备了单向板及NOL环试样,与湿法缠绕试样相比,拉伸性能略低,层间剪切强度较高。最后在固体缩比发动机壳体上进行了干法缠绕应用,壳体爆破压力达到12.15MPa,纤维强度发挥率达到85%。Compared to traditional wet winding molding technology,dry winding has a clean environment and no resin pollution,which can solve the problem of manual processing,improve production efficiency,accurately control the resin content,improve the reliability of product quality,and have many advantages.It is expected to become the mainstreamof future solid rocket engine composite material shell winding molding technology.This article uses the prepreg silk of T700 as the raw material to prepare unidirectional plate and NOL ring samples through dry winding.Compared with wet winding samples,the tensile performance is inferior,but the interlayer shear strength is superior.Finally,dry winding was applied on the solid scaled engine shell,and burst pressure of the shell reached 12.15MPa,with a fiber strength utilization rate of 85%.

关 键 词：干法缠绕 预浸纱 缩比壳体 爆破压力 

分 类 号：TB33[一般工业技术—材料科学与工程]