摘要
针对圆形柔性太阳翼的结构、功能特点,提出一种轻量化的碳纤维复合材料平面网格翼梁,该翼梁由M40J碳纤维/氰酸酯树脂采用缠绕工艺自动化成型,通过背靠背的双模模具结构设计、选用可膨胀的聚四氟乙烯模具材料、连续化的缠绕路径设计,解决了平面网格结构可回转缠绕成型、复材成型尺寸精度控制等难题,并对制备的工程样件进行静力试验考核,分析其力学承载性能。研究结果表明:采用自动化缠绕工艺成型的翼梁,具有较高的力学性能,能够承载太阳毯结构重量载荷,破坏形貌为下肋条断裂,多向肋条交叉节点未出现拔出脱粘,节点性能满足使用要求。
According to the structural and functional characteristics of circular solar array,the wing spar molding technology of light weight carbon fibre compositeplane lattice is proposed.The wing spar is automatically formed by M40J carbon fiber/cyanate resin winding process,through back-to-back double mold structure design,selection of expandable PTFE mold material,and continuous winding path design.It solves the rotary winding forming of plane mesh structure and dimensional precision control of composite forming problems.And it also analyzes its mechanical bearing performance by carrying out the static test of the prepared engineering sample.The results show that the wing spar formed by automatic winding process has higher mechanical performance and can bear the weight load of the solar blanket structure.In addition,the failure morphology is the lower riblet fracture,the multi-direction riblet cross node does not appear pull-out and debunking,and the performance of the node meets the use requirements.
作者
孙天峰
武海生
吴跃民
肖伟
刘佳
杨庆君
赵磊
Sun Tianfeng;Wu Haisheng;Wu Yuemin;Xiao Wei;Liu Jia;Yang Qingjun;Zhao Lei(Beijing Spacecraft Manufacturing Factory Co.,Ltd.,Beijing 100094;Beijing Institute of Spacecraft System Engineering,Beijing 100094)
出处
《航天制造技术》
2021年第4期55-59,67,共6页
Aerospace Manufacturing Technology
关键词
碳纤维复合材料
圆形太阳翼
翼梁
平面网格
纤维缠绕
carbon fiber composites
circular solar array
wing spar
plane lattice
filament winding
