The invention discloses a design method of an on-orbit launch separation mechanism of a miniature spacecraft. The separation mechanism based on the design method mainly comprises a main frame structure, a pull pin unlocking device, a memory alloy pull pin device, a tail charging port support and a protective skin. The main frame comprises a guide rail, a flange plate, a reinforcing ring and a tail baffle. The memory alloy pin puller and the pin pulling unlocking device are used for achieving locking of the miniature spacecraft in the separation mechanism before launching, the influence of vibration on the miniature spacecraft can be effectively reduced through cooperation with a tail baffle, and the miniature spacecraft can be prevented from colliding with a tail charging port of the separation mechanism. The separation mechanism designed through the design method is light in weight and high in space utilization rate, the separation reliability of the miniature spacecraft is high, and the separation guiding precision of the miniature spacecraft can be effectively improved.
本发明公开了一种微型航天器在轨发射分离机构的设计方法,基于该设计方法下的分离机构主要包括主框架结构、拔销解锁器、记忆合金拔销器、尾部充电口支架以及防护蒙皮。主框架包含导轨、法兰盘、加强圈以及尾部挡板。利用记忆合金拔销器以及拔销解锁器实现微型航天器发射前在分离机构内被锁死,配合尾部挡板可有效减小振动对微型航天器的影响,以及可防止微型航天器与分离机构尾部充电口发生碰撞。该设计方法设计的分离机构质量轻,空间利用率高,微型航天器分离可靠性高,并能有效提高微型航天器分离导向精度。
Design method for on-orbit launch separation mechanism of miniature spacecraft
一种微型航天器在轨发射分离机构的设计方法
2025-03-25
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
SPACECRAFT LAUNCH SYSTEM AND LAUNCH METHOD, AND SPACECRAFT
European Patent Office | 2022
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