双翼箱式航天器太阳光压干扰力矩模型

Model of Sunlight Pressure Disturbance Torque on Cubical Spacecraft with a Pair of Solar Sails

在设计航天器姿控系统时,需要充分考虑各种光照条件下航天器所受到的太阳光压干扰力矩。本文针对双翼太阳帆板、面板式天线阵、箱式主体构型航天器,采用几何方法,详细讨论了航天器各表面的受晒情况,推导了不同太阳光入射条件下航天器各面所受到的太阳光压力矩数学模型。为验证模型有效性,将其应用于某三轴稳定对地定向卫星姿态动力学仿真中,得到了相应的太阳光压干扰力矩曲线。

When designing the attitude control system of spacecraft, it is necessary to take account of the sunlight pressure disturbance torques under various sunlight incident conditions. In this paper, a typical spacecraft with a cubical body, a planar antenna array and a pair of symmetrical solar sails are introduced. And then the mathematical models of the exposed area of each facet and the sunlight pressure torques acted on the spacecraft are derived according to the relative angle of incidence of sunlight and the spacecraft＇s geometry. As illustration, these models are applied to an attitude control dynamics simulation of a three-axis stability satellite and the corresponding toques were plotted in curves.