应用于立方星的剪叉式可展开太阳电池阵机构

立方星在轨任务期间的能源供给主要依靠蓄电池或体装太阳能电池阵。随着微小航天器技术的发展，立方星功能密度越来越大，星上载荷对功率的需求越来越高，传统的电池板供能方式已很难满足未来空间任务需求。另外，立方星因其特有的尺寸规范和标准，对电池阵的收纳尺寸和展开机构也有特殊应用需求。基于上述背景和立方星的结构特点，设计了一种展开原理简单、扩展性好、折展比大的一维剪叉式空间可展开机构，进行了原理样机的加工制造和地面展开试验，验证了机构设计的功能可行性以及设计参数的合理性。机构展开后阵列发电功率是传统供能方式的3~5倍，且特殊的几何外形可提供被动重力梯度稳定优势，在提升未来立方星载荷能力方面有重要应用价值。

Scissor deployable solar array mechanism for CubeSat

The energy supply of CubeSat during the mission in orbit mainly relies on batteries or body-mounted solar arrays. With the development of micro spacecraft technology, the functional density of CubeSat is increasing, and the power demand of on-board payload is getting higher and higher, it is difficult for the traditional battery panel energy supply method to meet the future space mission requirements. In addition, the CubeSat has special application requirements for the stowage size and deployment mechanism of the battery array due to its unique size specifications and standards. Based on the above background and the structural characteristics of the CubeSat, this paper designs a one-dimensional shear-fork space deployable mechanism with simple deployment principle, good scalability and large folding ratio, and conducts processing and ground deployment tests of the principle prototype to verify the functional feasibility of the mechanism design and the rationality of the design parameters. The power generated by the array after deployment is three to five times higher than the conventional energy supply method, and the special geometry can provide the advantage of passive gravity gradient stabilization, which has important application value in enhancing the future CubeSat load capacity.