According to the flexible solar wing combined pressing structure and the forming method, a carbon fiber composite material curing tool is adopted, and thermal expansion matching in the heating and curing process is guaranteed; certain machining allowance is reserved in the important interface part state, and the high-precision requirement of the flexible solar wing combined pressing structure interface is guaranteed through combined machining; a multi-surface interface embedded part is optimized into a combined embedded part structure form, so that the interface bearing performance of the combined compression structure of the flexible solar wing structure is ensured; the machining height tolerance of all the embedded parts is finely controlled, a special combined embedded part gluing positioning tool is designed, and the flatness of a reference working face is guaranteed; and a pressing state evaluation tool is designed, so that the stable long-period rebound mechanical performance is ensured. The problems that in the forming process of an existing flexible solar wing combined pressing structure, the interface precision is out of tolerance, the bearing capacity of a local interface is insufficient, the flatness of a reference working face is insufficient, and the flexible pressing state cannot be quantitatively evaluated are solved.
本发明提供了一种柔性太阳翼组合压紧结构及成型方法,采用碳纤维复合材料固化工装,保证升温固化过程热膨胀匹配;重要接口零件状态下预留一定机加余量,组合加工保证柔性太阳翼组合压紧结构接口高精度要求;多面接口埋件优化为组合预埋件结构形式,保证柔性太阳翼结构组合压紧结构接口承载性能;全部预埋件机加高度公差精细化控制、设计专用组合预埋件胶接定位工装,保证基准工作面平面度;设计压紧状态评价工装,确保长周期回弹机械性能稳定。本发明解决了现有柔性太阳翼组合压紧结构成型过程中出现的接口精度超差、局部接口承载力不足、基准工作面平面度不足、无法定量评价柔性压紧状态等问题。
Flexible solar wing combined pressing structure and forming method
一种柔性太阳翼组合压紧结构及成型方法
2025-02-14
Patent
Electronic Resource
Chinese
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