翱翔之星电源系统的设计与在轨验证  

DESIGN AND ON-ORBIT VALIDATION OF ELECTRIC POWER SYSTEM FOR AOXIANG-SAT

作　　者：李朋[1] 周军[1] 于晓洲[1] 刘光辉[1] Li Peng;Zhou Jun;Yu Xiaozhou;Liu Guanghui(Institute of Precision Guidance and Control, School of Astronautics, Northwestern Polytechnical University, Xi ＇an 710072, China)

机构地区：[1]西北工业大学航天学院精确制导与控制研究所

出　　处：《太阳能学报》2018年第4期1002-1007,共6页Acta Energiae Solaris Sinica

基　　金：国家自然科学基金重大研究计划(91338202);陕西省自然科学基金(2015JM4125)

摘　　要：针对翱翔之星这一类标准架构立方星体积小、能源紧张的特点,提出一种新颖的微纳卫星集中供电式模块化电源系统拓扑结构,采用最大功率点跟踪设计多路独立的太阳能转换单元以提高太阳能的利用效率。针对电源系统全部采用商业化器件的理念,对系统各主要单元保证软、硬件可靠性的设计方法进行阐述,进而对电源系统的工作流程、状态监测和保护模式进行论述,使系统具有较好的抗故障能力和运行自主性。通过翱翔之星的地面实验和在轨数据分析,验证所设计系统的有效性,具有较好的工程应用价值。Aiming at the characteristics of small size and energy shortage for standard CubeSat architecture such as Aoxiang-Sat, topology for a novel centralized and modular electric power system for nanosatellite was proposed, which used the design of multiple independent solar energy conversion units with maximum power point tracking to increase efficiency of solar energy utilization. With the idea of using Commercial off the shelf devices in the power system, the design method ensuring software and hardware reliability for each major unit of the system was explained, the work process, status monitoring and protection mode of the system were further discussed to make the system have better antifault capability and operation autonomy. The validity of the designed system and the good engineering application value were verified through the ground experiments and on-orbit data analysis of Aoxiang-Sat.

关 键 词：微纳卫星 电源系统 最大功率点跟踪 电源管理 立方星 在轨试验 

分 类 号：V442[航空宇航科学与技术—飞行器设计]