分体组合式双自由度对日定向系统构型及布局设计

Configuration and Layout Design of Split Combined Double-Degree-of-Freedom Solar-Oriented System

为解决空间站在不同的构型及飞行姿态下,因太阳入射角变化大引起的太阳电池翼难以对日定向的难题,提出分体组合式双自由度对日定向系统构型。研究空间站构型及飞行姿态,确定采用A轴与B轴2个轴独立运转、单独控制的对日定向方式,2个轴通过桁架结构实现正交连接。在梦天实验舱单舱飞行时,A轴不动,B轴根据轨道周期跟踪太阳,通过飞行器姿态调整补偿太阳入射角的变化。组合体飞行时,B轴补偿太阳高度角,A轴根据轨道周期带动B轴与太阳电池翼共同跟踪太阳,实现双自由度对日定向。在轨飞行结果表明:在不同的舱段构型及飞行姿态下,功率通道输出功率波动幅度由60%减小到7%,分体组合式双自由度对日定向系统构型能够适应空间站复杂的飞行工况。

In order to solve the problem that the solar cell wing is difficult to orient to the sun due to the large variation of the incidence angle of the sunlight under different configurations and flight attitudes of the space station,a configuration of split combined double-degree-of-freedom solar-oriented system is proposed.The configuration and flight attitude of the space station are studied,by which the solar-oriented mode to independently operate and separately control the A-and B-axes is determined.The two axes are orthogonally connected through the truss structure.During the single cabin flight of the Mengtian lab module,the A-axis does not move,the B-axis tracks the sun according to the orbital period,and the change of the sunlight incidence angle is compensated by adjusting the attitude of the aircraft.When the combined body flies,the B-axis is used to compensate for the solar altitude angle,and the A-axis drives the B-axis and the solar cell wing to track the sun together according to the orbital period so as to achieve the double-degree-of-freedom orientation to the sun.The in-orbit flight results show that under different module configurations and flight attitudes,the fluctuation amplitude of the power channel output power is reduced from 60%to 7%,and the configuration of split combined double-degree-of-freedom solar-oriented system can adapt to the complex flight conditions of the space station.