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首页> 外文期刊>International journal of aerospace engineering >Development of Pogo Pin-Based Holding and Release Mechanism for Deployable Solar Panel of CubeSat
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Development of Pogo Pin-Based Holding and Release Mechanism for Deployable Solar Panel of CubeSat

机译：基于Pogo Pin的CubeSat可展开太阳能电池板保持和释放机制的开发

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CubeSats are revolutionary to the space industry and are transforming space exploration which enables the next generation of scientists and engineers to complete all phases of space missions. Deployable solar panels have been widely used for the generation of enough power in CubeSats due to their limited volume area for solar cell integration. In general, the cable cutting release mechanism have been used in 1U-3U small satellites because of its simplicity and low cost. However, this mechanism has a low constraint force and is unable to apply constraints along the in-plane and out-of-plane directions. In this study, for the improvement of the conventional cable cutting mechanism, a spring-loaded pogo pin-based nichrome burn wire holding and release mechanism (HRM) was proposed and fabricated. The pogo pin constitutes an immensely attractive function for the holding and release mechanism of solar panels because it works as an electrical interface to provide power, a separation spring to initiate the reaction force to deploy the panels, and a status switch to determine deployments. In addition, the proposed mechanism guarantees the loading capability along the in-plane and out-of-plane directions of solar panels, the synchronous release of multiple panels, and a handling simplicity that differentiates it from the conventional mechanism. The design feasibility, structural safety, and reliability of the mechanism were verified through functionality tests and launch and on-orbit environmental tests. The proposed pogo pin-based holding and release mechanism would be equally applicable for other CubeSat deployable appendages.
机译：CubeSat对太空工业而言是革命性的，并且正在改变太空探索，使下一代科学家和工程师能够完成太空任务的所有阶段。可部署的太阳能电池板因其体积有限的太阳能电池集成而已广泛用于在CubeSats中生成足够的功率。通常，电缆切割释放机构由于其简单性和低成本而被用于1U-3U小型卫星。但是，该机构的约束力低，无法沿平面内和平面外方向施加约束。在这项研究中，为改进传统的电缆切割机制，提出并制造了一种弹簧加载的基于弹簧针的镍铬合金燃烧线固定和释放机构（HRM）。弹簧针构成了太阳能电池板固定和释放机构的一项极具吸引力的功能，因为它充当提供电力的电气接口，用于启动反作用力以展开面板的分离弹簧以及用于确定展开的状态开关。另外，所提出的机构保证了沿太阳能电池板的面内和面外方向的负载能力，多个板的同步释放以及与常规机构不同的操作简便性。该机制的设计可行性，结构安全性和可靠性通过功能测试以及发射和在轨环境测试得到了验证。提议的基于Pogo Pin的保持和释放机制将同样适用于其他CubeSat可部署附件。

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