太阳同步轨道卫星帆板对日定向控制与仿真

Simulation of Sun Synchronous Orbit Satellite Solar Panel Control

航天器所需能源由太阳能帆板提供。针对单翼、单自由度、匀速驱动的太阳同步轨道卫星帆板的对日定向控制问题,研究了轨道偏心率、地球非球形摄动、日月引力、大气阻力、太阳光压等因素对卫星帆板对日定向精度的影响作用规律,为了提高对日帆板的定位控制精度,提出了在摄动影响下,采用线性拟合的方法,通过合理设置卫星帆板的驱动速度,延长卫星对日定向姿态的稳定时间。仿真结果表明,提出的方法简单易行,能够确保卫星帆板对日定向精度较长时间保持在允许范围内,在提高卫星帆板受晒效率的同时,减少了卫星帆板调整的次数。

Solar panel control problem for a sun synchronous orbit satellite,which has one degree freedom single solar panel droved by a constant velocity to point to the sun,is investigated in this paper.First of all,the rules are found out by simulation to express how the perturbations of orbit eccentricity,nonspherical acceleration,sun and lunar gravity,air drag and sun radiation pressure affect the solar panel attitude.Then,the changing rule of solar panel attitude angle is analyzed with integrated conditions considering all perturbations,and a linear fitting method is obtained.Then,the solar panel theoretic driving velocity is compensated with this method in order to keep solar panel in the optimal position for solarization.Simulation results indicate that the proposed method can keep the panel pointing to the sun for a relative long time,and reduce times to adjust the solar panel attitude.