空间站复合材料收紧装置刚度及静力试验分析  

Stiffness and Static Test Analysis of Composite Material Tightening Device for Space Station

作　　者：王梓桥 周秀燕 许文彬 汤亮 刘甲秋 朱楠 杨永生 刘芳芳 WANG Ziqiao;ZHOU Xiuyan;XU Wenbin;TANG Liang;LIU Jiaqiu;ZHU Nan;YANG Yongsheng;LIU Fangfang(Harbin FRP Institute Co.,Ltd.,Harbin 150028,Heilongjiang,China;Shanghai Aerospace Systems Engineering Institute,Shanghai 201109,China)

机构地区：[1]哈尔滨玻璃钢研究院有限公司,黑龙江哈尔滨150028 [2]上海宇航系统工程研究所,上海201109

出　　处：《上海航天（中英文）》2023年第6期144-151,共8页Aerospace Shanghai（Chinese&English）

基　　金：国家自然科学基金(U22B20128)。

摘　　要：针对空间站柔性翼在展开及收拢状态,通过地面结构试验,对复合材料收紧装置试验件刚度及强度进行试验摸底。对试验项目进行设计,分别对面外刚度、面内刚度、0°工况强度、90°工况强度6个工况条件进行测试,获取了复合材料收紧装置试验件的刚度、强度数据。通过强度试验可知,Y向位移最大,X方向位移最小,且理论与实际偏差小于12%,证明复合材料收紧装置理论预测方法有效,可以为后续复合材料收紧装置结构优化及工艺制造提供有效理论支撑。According to the deployment and retraction state of the flexible wing of the space station,the stiffness and strength of the composite tightening device test piece were tested through the ground structure test.The test items are designed,and the external stiffness,the internal stiffness,the 0°working condition strength,and the 90°working condition strength are measured,by which the stiffness and strength data of the composite tightening device test pieces are obtained.The strength test results show that the Y-direction displacement is the largest,the X-direction displacement is the smallest,and the theoretical and actual deviation is less than 12%.These indicate that the theoretical prediction method for composite material tightening devices is effective,and can provide effective theoretical support for the subsequent structural optimization and process manufacturing of composite material tightening devices.

关 键 词：复合材料 收紧装置 空间站 柔性翼 静力试验 

分 类 号：TB332[一般工业技术—材料科学与工程]