一种空间有源太阳翼铰链机构设计与研究

Design and Study on a Hinge Mechanism of Space Active Solar Wing

针对某空间微纳卫星太阳翼铰链机构的任务需求,设计了一种采用空间步进电机、无刷旋变、减速机构、微动开关、可重复部署展收和锁定的适应空间应用环境的轻质小型化、高可靠太阳翼铰链机构,开展了整机模态参数分析,并完成了工程样机试验验证。试验结果表明,该机构具有较高的定位精度、较大的负载能力和较好的环境适应性,可为后续空间有源微纳卫星太阳翼铰链机构研制提供参考。

According to some mission requirements of the space micro-nano satellite solar wing hinge mechanism, a lightweight miniaturization and high reliability active solar wing hinge mechanism is designed in this paper by employing the space stepper motor, brushless rotary transformer, retarding mechanism, micro switch, repeatable deployment, folding and locking mechanism, which adapts to the space application. The modal parameter analysis of the whole machine is carried out. The engineering prototype test verification is completed. The experimental results show that the mechanism has higher positioning accuracy, larger load capacity and better environmental adaptability, which can provide reference for the development of the active solar wing hinge mechanism of the follow-up space micro-nano satellite.