微重力空间下微纳遥感卫星太阳翼构型仿真分析  

Simulation Analysis on the Solar Panel of Remote Sensing CubeSat with Different Structures in Microgravity Space

作　　者：董怡泽 付春雨[2] 王超[1] 孔祥磊 邢哲 高冀[1] DONG Yize;FU Chunyu;WANG Chao;KONG Xianglei;XING Zhe;GAO Ji(China Academy of Space Technology Institute of Spacecraft Application System Engineering,Beijing 100094,China;Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China)

机构地区：[1]中国空间技术研究院卫星应用总体部,北京100094 [2]北京卫星环境工程研究所,北京100094

出　　处：《计算机测量与控制》2022年第8期218-223,共6页Computer Measurement &Control

摘　　要：针对微纳遥感卫星从技术试验阶段到业务化应用的转型发展,如何缓解其能量来源的受限条件,获取更高的太阳能充电效能,对微纳遥感卫星未来星座构建的发展需求有重要作用;通过设计不同构型的微纳卫星太阳翼,构造太阳电池阵列的仿真模型,根据太阳能电池阵列在微重力空间下的工作特性,仿真分析微重力空间下不同构型太阳翼的充电性能和充电效率,并对不同构型的使用性能进行了分析比较;结果表明,选择最优太阳翼构型能够为微纳遥感卫星提供更好的能源和动力支撑,为后续微纳遥感卫星开展更多商业应用提供有效参考。Aiming at the transformation stage of remote sensing CubeSat from technical test to business application,how to alleviate the energy limitation and obtain higher solar charging efficiency is important to the development of constellation construction.By designing the solar panel of CubeSat with different configurations,the simulation model of solar array is constructed.According to the performance of solar cell sequence in microgravity space,the charging performance and efficiency of different configurations of solar wings in microgravity space are simulated and analyzed,and the service performance of different configurations is simulated and compared.The results show that selecting the optimal configuration of solar array can provide better energy and power support for the remote sensing CubeSat,an effective reference for the follow-up remote sensing CubeSat is provided to carry out more commercial applications.

关 键 词：微纳卫星 微重力环境 太阳翼 建模仿真 

分 类 号：TP391[自动化与计算机技术—计算机应用技术]