基于感应耦合式无线能量传输的微纳聚合体航天器电源系统设计与验证  

Design and verification of micro-nano polymer spacecraft power system based on magnetic coupled wireless power transfer

作　　者：张龙龙 杨志[2] 张严[2] 赵晓静 张勤荣 ZHANG Longlong;YANG Zhi;ZHANG Yan;ZHAO Xiaojing;ZHANG Qinrong(China University of Petroleum(East China),Qingdao 266555,China;DFH Satellite Co.,Ltd.,Beijing 100094,China)

机构地区：[1]中国石油大学(华东),青岛266555 [2]航天东方红卫星有限公司,北京100094

出　　处：《空间电子技术》2024年第3期79-85,共7页Space Electronic Technology

基　　金：国家预先研究课题项目(编号:30508020304);泰山学者青年专家项目(编号:ZX20230241);中国空间技术研究院杰出青年基金项目(编号:2021399)。

摘　　要：微纳聚合体航天器是一种以机械或电磁锁紧机构实现各模块化基本单元航天器连接的新型航天器架构,可以灵活实现在轨组装与自重构以满足不同任务需求。但是,基于传统电连接器的电气互联方式无法适应模块化航天器间灵活交汇对接与快速分离需求。针对上述问题,文章建立了基于感应耦合式双向无线能量传输的微纳聚合体航天器电源系统架构,根据地面演示验证需求分别设计了能源核航天器和载荷任务航天器电源系统参数,然后根据各模块化航天器间非接触供电需求,设计了双向无线能量传输单元参数,最后通过地面演示试验验证了基于双向无线能量传输的微纳聚合体航天器电源系统架构可行性,单级无线能量传输功率在20W~30W时传输效率稳定在75.8%以上,通过效率优化提升至95%以上,将可实现四个基本单元航天器的多级功率传输。Micro-nano polymer spacecraft is a new type of spacecraft architecture that uses mechanical or electromagnetic locking mechanisms to connect modular spacecraft.It can flexibly achieve in orbit assembly and self-restructuring to meet different mission requirements.However,the electrical interconnection method based on traditional electrical connectors cannot meet the application requirements of flexible intersection,docking,and rapid separation between modular spacecrafts.In response to the above issues,this paper establishes power supply system architecture for micro-nano polymer spacecraft based on inductive coupled wireless power transfer.According to the ground demonstration verification requirements,the power supply system parameters for energy spacecraft module and payload spacecraft module are designed respectively.Then,based on the non-contact power supply requirements between modular spacecraft,the parameters of the bidirectional wireless energy transmission unit are designed.Finally,the feasibility of the power supply system architecture for micro-nano polymer spacecraft based on bi-directional wireless power transfer was verified through ground demonstration experiments.The transmission efficiency of the single-stage wireless energy transfer power remained stable at 75.8%or above when it reached 20-30W.By optimizing the efficiency to over 90%,multi-stage power transfer of four basic unit spacecraft could be achieved.

关 键 词：微纳聚合体航天器 电源系统 近场无线能量传输 设计验证 

分 类 号：TN253[电子电信—物理电子学] V443[航空宇航科学与技术—飞行器设计]