国产高模碳纤维/环氧复合材料在太阳翼基板上的应用研究  

Research on Application of Domestic High-modulus Carbon Fiber/Epoxy Composites on Substrates for Spacial Solar Array

作　　者：杨淑利[1] 濮海玲[1] 邵立民 罗盼 任守志[1] 高鸿[3] YANG Shuli;PU Hailing;SHAO Limin;LUO Pan;REN Shouzhi;GAO Hong(Beijing Institute of Spacecraft System Engineering,Beijing 100094;Beijing Spacecrafts limited Company,Beijing 100094;China Academy of Space Technology,Beijing 100094)

机构地区：[1]北京空间飞行器总体设计部,北京100094 [2]北京卫星制造厂有限公司,北京100094 [3]中国空间技术研究院,北京100094

出　　处：《宇航材料工艺》2023年第2期117-122,共6页Aerospace Materials & Technology

摘　　要：基板是空间太阳电池阵电池电路的安装基础,“上下碳纤维复合材料网格面板+铝蜂窝芯+聚酰亚胺膜”是基板的典型结构。高模量碳纤维作为太阳翼核心关键原材料,必须实现自主可控,避免受制于人。为此,开展了国产高模碳纤维CCM40J-6K/环氧复合材料在太阳翼基板上的应用试验研究,提出了CCM40J-6K/环氧复合材料在产品应用上的宏观力学、微观网格抗拉脱、聚酰亚胺膜粘贴等三个关键环节,针对性地设计并实施了常温和高低温交变力学性能、网格面板节点结合力、聚酰亚胺膜粘贴性能以及基板结构热循环性能等5个方面的测试验证。验证结果表明:CCM40J-6K太阳翼基板各项力学性能与进口M40JB-6K相当,可以沿用原M40JB-6K相关基板成型工艺,单层及多层铺层基板试验件能够经受高低温交变及热循环恶劣环境,试验件试验前后力学性能无明显变化,且聚酰亚胺膜无脱粘现象,网格节点拉伸强度国产碳纤维网格面板相比进口碳纤维网格面板高18.9%。说明国产碳纤维CCM40J-6K能够应用于太阳翼基板结构研制。The substrate was the installation basis of solar cell for spacial solar array."Upper and lower grid panel of carbon fiber composite+aluminum honeycomb core+polyimide film"was a typical structure of the substrate.As the key raw material of the solar array,high-modulus carbon fiber must be autonomous and controllable.To this end,the research of domestic high-modulus carbon fiber CCM40J-6K/epoxy composite applied to solar array's substrate had been carried out.And three key links,including macro mechanics,pull-off resistance of micro mesh,and adhesion performance of polyimide film of CCM40J-6K/epoxy composites in substrate applications,had been proposed.Five aspects of testing and verification items,including mechanical properties,bonding force of mesh panel node,bondingperformance of polyimide film,and thermal-cycle performance of substrate structures,had been carried out.The verification results show that the mechanical properties of solar array's substrate using the domestic carbon fiber-CCM40J-6K are equivalent to those of the imported M40JB-6K,and the original related molding process of substrate by M40JB-6K can be followed.Test pieces of single-layer and multi-layer laminate substrate can withstand thermal shock and thermal cycling tests,whose mechanical properties have no obvious change before and after the test,and the polyimide film has no debonding phenomenon.The tensile strength of the grid node of the domestic carbon fiber is 18.9%higher than that of the imported carbon fiber.It shows that the domestic carbon fiber CCM40J-6K can be applied to the development of the substrate structure for solar array.

关 键 词：国产高模量碳纤维 太阳翼 基板 应用试验 

分 类 号：TB33[一般工业技术—材料科学与工程]