PW-Sat2立方星离轨帆研制及在轨验证  

Development of PW-Sat2 CubeSat’s deorbiting sail and the on-orbit verification

作　　者：李懿德 范鑫 LI Yide;FAN Xin(Aerospace System Engineering Shanghai,Shanghai 201109,China;Students’Space Association,Warsaw University of Technology,Warsaw 00-665,Poland;Shanghai Academy of Spaceflight Technology,Shanghai 201109,China)

机构地区：[1]上海宇航系统工程研究所,上海201109 [2]华沙理工大学学生太空协会,华沙00-665 [3]上海航天技术研究院,上海201109

出　　处：《航天器环境工程》2020年第4期414-420,共7页Spacecraft Environment Engineering

摘　　要：针对当前的空间碎片减缓要求,轻小型、模块化、通用化离轨装置的研发成为研究热点。其中薄膜帆离轨装置具有成本低、质量小、发射体积小、面质比大等优点。文章以波兰PW-Sat2立方星离轨帆为例,总结其研制、试验过程,特别是对于帆面和非火工锁紧/释放机构;分析其在轨实验期间的离轨效能和故障模式,并提出可靠性提升方案,以期为我国后续离轨帆产品的研制提供参考。In response to the current space debris mitigation requirements both at home and abroad,the development of light,small,modular,and generalized deorbiting devices has become a research hotspot.Among them,the deorbiting sail has the advantages of low cost,light weight,small launch volume,and large surfacequality ratio.This paper,by taking the deorbiting sail of the Polish PW-Sat2 CubeSat as an example,introduces its development and test process,as well as a summary of the experiences,with focus on the sail surface and the non-pyrotechnic lock&release mechanism.The deorbiting efficiency and the failure modes during the orbit test are analyzed,and a corresponding reliability improvement program is proposed,to provide some reference for developing subsequent deorbiting sail products in China.

关 键 词：空间碎片减缓 立方星 锁紧/释放机构 离轨帆 

分 类 号：V476.9[航空宇航科学与技术—飞行器设计]