The invention provides a center bearing cylinder for an integrated star structure of a load platform. The center bearing cylinder solves the problem of optimal and reasonable distribution of space resources in the integrated design process of the satellite load platform. The central bearing cylinder adopts a spatial configuration of corner box reinforced point type connection and notch type sinking, and structurally comprises a cylinder body, an upper end frame, a laminate flange assembly, a stringer, a bottom plate flange assembly, a lower end frame assembly, a storage box mounting plate flange assembly and an opening reinforcing piece. The cylinder body is of a variable-thickness skin honeycomb sandwich structure, and the upper end frame, the laminate flange assembly, the stringer, the bottom plate flange assembly and the storage box mounting plate flange assembly are connected with the cylinder body. And the opening reinforcing piece is of a U-shaped structure with a pi-shaped section and is embedded into the opening of the cylinder body. According to the design of the variable-thickness skin laying layer, the design of the variable-cross-section flanging lower end frame, the design of the lower end frame corner box reinforcement and the design of the force-bearing cylinder opening reinforcement piece, the overall bending resistance and torsion resistance of the force-bearing cylinder and the strength and rigidity of satellite-rocket connection can be improved.
本发明提供了一种用于载荷平台一体化星体结构的中心承力筒,解决卫星载荷平台一体化设计过程中空间资源优化合理分配的难题。中心承力筒采用角盒加强的点式连接与缺口式下沉的空间构型,结构包括:筒体、上端框、层板法兰组件、桁条、底板法兰组件、下端框组件、贮箱安装板法兰组件和开口补强件。筒体采用变厚度的蒙皮蜂窝夹层结构,上端框、层板法兰组件、桁条、底板法兰组件和贮箱安装板法兰组件与筒体相连。开口补强件为截面是π状的U型结构,嵌入筒体开口处。本发明的变厚度蒙皮铺层设计、变截面翻边下端框设计、下端框角盒加强及承力筒开口补强件设计,可提升承力筒整体抗弯曲、抗扭转性能及星箭连接的强度和刚度。
Central bearing cylinder for load platform integrated star structure
用于载荷平台一体化星体结构的中心承力筒
2024-03-01
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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