中国空间科学技术

中国空间科学技术 ›› 2024, Vol. 44 ›› Issue (6): 64-71.doi: 10.16708/j.cnki.1000-758X.2024.0091

• 空间太阳能电站专题 • 上一篇    下一篇

薄膜电池阵透镜式薄壁支撑杆自展开方法研究

张恩杰1,2,3,*，王治易1,2,3，谢超1,2,3，房光强1,2,3，侯欣宾4   

  1. 1.上海宇航系统工程研究所，上海201108
    2.宇航空间机构全国重点实验室，上海201108
    3.上海市空间飞行器机构重点实验室，上海201108
    4.中国空间技术研究院 钱学森空间技术实验室，北京100094
  • 收稿日期:2024-03-12 修回日期:2024-04-29 录用日期:2024-06-08 发布日期:2024-12-03 出版日期:2024-12-05

Passive deployment of lenticular thin-walled supporting boom for thin-film solar array

ZHANG Enjie1,2,3,*，WANG Zhiyi1,2,3，XIE Chao1,2,3，FANG Guangqiang1,2,3，HOU Xinbin4   

  1. 1.Shanghai Institute of Aerospace System Engineering, Shanghai 201108, China
    2.National Key Laboratory of Aerospace Mechanism, Shanghai 201108, China
    3.Shanghai Key Laboratory of Spacecraft Mechanism, Shanghai 201108, China
    4.Qian Xuesen Laboratory of Space Technology, China Academy of Space Technology, Beijing 100094, China
  • Received:2024-03-12 Revision received:2024-04-29 Accepted:2024-06-08 Online:2024-12-03 Published:2024-12-05

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摘要： 透镜式薄壁杆是空间太阳能电站薄膜电池阵的主支撑杆，目前常用的控制其展开的有源驱动机构的收拢包络及质量均较大。优化支撑结构展开控制方法，提升薄膜电池阵收藏效率，是实现超大型、轻量化空间电站建设目标的重要途径之一。鉴于此，充分利用复合材料薄壁支撑杆的弹性自恢复特性，开展无源自驱动展开方法研究。首先，建立透镜式薄壁杆的仿真模型，分析薄壁杆的压扁与卷绕收拢过程力学响应，得到其收拢后的应力应变数据；然后，选用柔性粘扣作为薄壁杆的展开约束控制单元，通过仿真分析得到其剥离过程的力位移曲线；最后，采用数据传递方法，建立带预应力的薄壁杆展开动力学模型，并在此基础上构建柔性粘扣模拟单元，分析柔性粘扣的力学性能对薄壁杆展开过程的影响。结果表明，通过调节柔性粘扣连接力，可以实现透镜式薄壁杆的无源自驱动有序展开。薄膜电池阵主支撑结构的无源自驱动有序展开，为进一步降低电池阵机构复杂度与质量、提升收纳比提供了方向指引。

关键词: 空间太阳能电站, 薄膜电池阵, 透镜式薄壁杆, 自驱动, 展开动力学

Abstract: Lenticular boom is used as the main supporting rod of the thin-film solar array of space solar power station. The envelope volume and weight of active driving mechanism commonly used to control the deployment of the boom are relatively large. The control approach of boom deployment is a decisive factor of the storage ratio, which can significantly reduce the envelope volume and weight of the solar array through optimization. It is regarded as a promising method for establishing the ultra-large and light-weight space solar power station. In view of this, the passive deployment of composite thin-walled lenticular boom (CTLB) with full utilization of the elastic recovery characteristics of its cross-section is investigated in this paper. With the explicit dynamics finite element (FE) method, the mechanical responses of CTLB during flattening and coiling are analyzed in terms of the elastic stress and strain. Then the peel force of the flexible fastener during detachment is numerically obtained. The flexible fastener is chosen as the control unit for CTLB deployment. By inheriting the deformed shape and material state from the proceeding FE analysis and simulating the flexible fastener using cohesive element, a dynamic model is established for the deployment of CTLB. Then the influence of the mechanical properties of flexible fasteners on the unfolding characteristic of CTLB is numerically studied. The results show that the orderly deployment of CTLB can be achieved by adjusting the detachment force of flexible fastener, which provides a solution for further reducing the complexity and weight as well as improving the storage ratio of ultra-large thin-film solar array.

Key words:  , space solar power station, thin-film solar array, lenticular boom, elastic energy-powered passive deployment, deployment dynamics