The invention provides an offset solar wing configuration design method and system for an inclined orbit satellite. The method comprises the steps that S1, the power of a satellite platform, the size of a solar wing mounting surface and a carrying envelope are determined; s2, obtaining a solar elevation angle change range of an orbit where the satellite is located; s3, calculating a solar wing fixed offset angle and a solar wing substrate area; s4, selecting a proper solar wing configuration; s5, under the constraint that a solar wing SADA driving shaft passes through the mass center of a solar wing substrate, the root hinge unfolding angle of the solar wing configuration is calculated in combination with the solar wing offset angle, and the solar wing configuration with the root hinge unfolding angle larger than 30 degrees is selected; s6, calculating the shielding area of the satellite body to the solar wing body when the solar altitude is maximum; and S7, increasing the area of the solar wing substrate equal to the shielding area, and repeating the steps S4 and S5 to obtain the solar wing configuration meeting the requirements. The design of the solar wing is optimized, and the light energy utilization efficiency of the solar wing on the inclined orbit is remarkably improved.
本发明提供了一种倾斜轨道卫星的偏置太阳翼构型设计方法及系统,包括:步骤S1:确定卫星平台的功率、太阳翼安装面尺寸、运载包络;步骤S2:得到卫星所处轨道的太阳高度角变化范围;步骤S3:计算太阳翼固定偏置角度和太阳翼基板面积;步骤S4:选取合适的太阳翼构型;步骤S5:在太阳翼SADA驱动轴过太阳翼基板质心的约束下,结合太阳翼偏置角度计算太阳翼构型的根铰展开角度,选取根铰展开角度大于30°的太阳翼构型;步骤S6:计算太阳高度角最大时卫星本体对太阳翼本体的遮挡面积;步骤S7:增加与遮挡面积相等的太阳翼基板面积,重复步骤S4、步骤S5,得到符合要求的太阳翼构型。本发明优化了太阳翼设计,显著提高了倾斜轨道上太阳翼的光能利用效率。
Offset solar wing configuration design method and system of inclined orbit satellite
一种倾斜轨道卫星的偏置太阳翼构型设计方法及系统
2022-11-01
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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