碳/碳蜂窝制备工艺及压缩与剪切行为

Preparation process,compression and shear behavior of carbon/carbon honeycomb

为了满足高分辨率航天器承载平台对尺寸稳定性、轻量化和高承载空间结构的多重需求,采用热压成型和树脂浸渍-碳化组合工艺制备了4种不同规格的碳/碳(C/C)蜂窝。以碳纤维预浸料为原料,通过热压工艺成型波纹片,用无机胶粘剂粘合片材形成蜂窝,经过浸渍-碳化工艺成型C/C蜂窝。对不同规格C/C蜂窝在不同加载方式下的力学行为进行了研究。结果表明,采用所提出组合工艺制备的C/C蜂窝未发生节点脱粘。边长5 mm蜂窝的压缩强度为8.2 MPa。在面外压缩、L向与W向剪切载荷下,C/C蜂窝的主要失效模式是双层壁脱粘分层。C/C蜂窝结构具有较高的抗压强度和良好可设计性,可能满足未来轻质高强航天器承载平台结构要求。

To meet the multiple requirements of dimensional stability,light weight,and high load-bearing capacity for the high resolution spacecraft bearing platform,four different sizes of carbon/carbon(C/C)honeycomb were prepared by the combination of hot pressing and resin impregnation-carbonization processes.Carbon fiber prepreg was used as the raw material to form corrugated sheets by hot pressing,and inorganic adhesive was used to bond the corrugated sheets to form the honeycomb.C/C honeycomb was formed by the impregnation-carbonization process.The mechanical behaviors of different sizes of C/C honeycomb under different load modes were investigated.The results show that the C/C honeycombs prepared by the proposed combined process do not experience nodal debonding,and the compressive strength of the 5 mm edge length honeycomb is 8.2 MPa.The main failure mode of C/C honeycomb is double wall debonding delamination under out-of-plane compression,L and W direction shear process loads.The C/C honeycombs show high compressive strength and good designability and may meet the requirements of future lightweight and high strength spacecraft bearing platforms.