The invention provides a mechanical-thermal integrated carbon fiber surface plate honeycomb structure, and belongs to the technical field of spacecraft structure design. The structure comprises an upper panel, a honeycomb core, a lower panel, a transition layer and a heat pipe, wherein the upper panel and the lower panel are made of a carbon fiber composite material; wherein the upper panel, the lower panel and the honeycomb core form a honeycomb sandwich structure, the heat pipe is pre-arranged in the honeycomb core in the honeycomb sandwich structure in the form of an embedded part, and thetransition layer is located between the upper panel and/or the lower panel and the heat pipe and used for reducing curing residual stress caused by mismatching of thermal expansion of the pre-embeddedheat pipe and the panel. The transition layer is added between the carbon fiber surface plate and the heat pipe, and the high-modulus carbon fibers and the high-strength fibers are combined and matched for use, so that engineering application of the carbon fiber honeycomb plate embedded heat pipe with high dimensional stability in a wide temperature range is realized.
本发明提供了一种机热一体化碳纤维表板蜂窝结构,属于航天器结构设计技术领域。该结构包括上面板、蜂窝芯子、下面板、过渡层和热管,其中:上面板和下面板采用碳纤维复合材料制成;上面板、下面板与蜂窝芯子形成蜂窝夹层结构,热管以预埋件的形式预置在蜂窝夹层结构内的蜂窝芯子中,过渡层位于上面板和/或下面板与热管之间,用于降低预埋热管与面板由于热膨胀不匹配带来的固化残余应力。本发明在碳纤维表板与热管之间增加过渡层、将高模量碳纤维与高强度纤维组合匹配使用的方法,实现了具有高尺寸稳定性的碳纤维蜂窝板预埋热管在较宽温度范围内的工程应用。
Mechanical-thermal integrated carbon fiber surface plate honeycomb structure
一种机热一体化碳纤维表板蜂窝结构
2021-01-22
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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