斜装匀速对日驱动的卫星太阳电池阵入射角计算方法

Method for Calculating Sunlight Incident Angle of Solar Array Slanted Mounted and Driving with Uniformly Angular Velocity

某遥感卫星在轨长期工作时姿态处于斜飞状态,受总体构型布局约束,卫星双翼太阳电池阵相对星体倾斜安装;为降低对姿态稳定度的影响,太阳电池阵在轨采用匀速对日定向驱动的工作方式。针对上述特点,提出了一种太阳电池阵入射角的计算方法,考虑了卫星姿态斜飞、偏航导引、地球J_2项摄动、地影影响等因素,采用坐标变换方法,将太阳矢量和太阳电池阵法线矢量转换到同一坐标系下,计算两者方向余弦,进而得到太阳电池阵入射角。选取一年4个典型时间点给出了算例,计算结果与安装在卫星太阳翼上的模拟式太阳敏感器在轨实测结果进行了比较,验证了该计算方法的有效性和精度。

A remote satellite which attitude are biased in long time operation,and constrainted by the general configuration, the double solarry array mounted slanted to the satellite body coordi- nate,meanwhile,in order to depress the influence to attitude stability, the solar array was drived toward Sun vector with the uniformly angular velocity. Aim to those feature,the method to calcu- late solar array panel incident angle is presentated in this paper. It has considered the attitude off- set,yaw steering,J2 pertubation of earth and the effect of earth shadow,applying the transform of corordinate,the sun vector and the normal line of solar array are transformed in the same coordi- nate, calculated the orientation cosine number of value, accordingly, obtained the solar array sun- light incident angle. The four special point being selected, the calculate example is given, compare to the telemetry data obtained by coarse sun sensor on-orbital, the result indicate that they are well consistent.