高轨卫星角动量管理的太阳电池阵转角控制  

Solar array angle control for high-orbit satellite angular momentum management

作　　者：何益康 林书宇 杨森 王振华[3] 何闻[1] HE Yikang;LIN Shuyu;YANG Sen;WANG Zhenhua;HE Wen(Key Laboratory of Advanced Manufacturing Technology of Zhejiang Province,Zhejiang University,Hangzhou 310027,China;Shanghai Institute of Spaceflight Control Technology,Shanghai 201109,China;School of Astronautics,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]浙江大学浙江省先进制造技术重点实验室,浙江杭州310027 [2]上海航天控制技术研究所,上海201109 [3]哈尔滨工业大学航天学院,黑龙江哈尔滨150001

出　　处：《系统工程与电子技术》2024年第11期3835-3843,共9页Systems Engineering and Electronics

基　　金：国家自然科学基金(62373125,52027808)资助课题。

摘　　要：为了延长高轨卫星的角动量卸载周期,提出一种用于高轨卫星角动量管理的太阳电池阵转角控制方法。首先,构建出太阳电池阵转角控制作用模型,并将用于卫星角动量管理的太阳电池阵转角控制转化为约束优化问题。然后,从工程实用的角度出发,根据常用的两翼太阳电池阵对称布局的特点,简化用于角动量管理的太阳电池阵转角控制问题,提出简单实用的太阳电池阵转角控制律。最后,通过数值仿真和某遥感卫星的在轨环境干扰数据对所提方法进行验证。结果表明,所提方法可以显著降低卫星角动量的积累,延长角动量卸载周期。To extend the angular momentum unloading period of high-orbit satellites,a solar array angle control method for high-orbit satellite angular momentum management is proposed.Firstly,a solar array angle control model is constructed,and the solar array angle control used for satellite momentum management is transformed into a constrained optimization problem based on the solar array angle control model.Then,from an engineering perspective,the solar array angle control problem for momentum management is simplified based on the characteristics of commonly-used symmetric configuration of two-wing solar array panels,and a simple and practical control law for solar array angle is proposed.Finally,the proposed method is verified by numerical simulation and on-orbit environmental disturbance data of a remote sensing satellite.Simulation results show that the proposed method can significantly reduce the accumulation of satellite angular momentum and extend the momentum unloading period.

关 键 词：高轨卫星 太阳电池阵 角动量管理 控制律 约束优化 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]