利用太阳光压的大偏心率伴飞卫星轨道控制

Orbit Control of Fly-around Satellite with Highly Eccentric Orbit by Using Solar Radiation Pressure

提出了利用太阳帆进行大偏心率伴飞卫星轨道控制的方法.伴飞卫星围绕其惯量主轴做角速度恒定的自转,其惯量主轴在惯性系内指向保持不变.对伴飞卫星的控制分为轨道面的控制和轨道面内控制两部分.在控制过程中,优先考虑轨道面内的控制,在轨道面内控制不能进行(或者因为几何原因不能进行轨道面内控制)时,进行轨道面的控制.通过滑膜控制方法(Sliding Mode Control)计算轨道面内控制需要的控制力的方向和大小.得到需求的控制力要求后,推算出在控制过程中太阳帆相对于伴飞卫星主体的角度解析表达式.通过控制太阳帆的方向得到所需的不同的控制力.整个控制过程只针对伴飞卫星,主星处于自然飞行状态.最后对于这种控制方法进行数值验证.在无摄运动状态下通过控制系统进行伴飞轨道的轨道调整和误差消除,在考虑4阶非球形引力和第三体引力摄动情况下进行伴飞轨道的轨道维持.数值结果表明通过这种控制方法伴飞轨道能够保持轨道误差小于5 m.

The method of controlling highly eccentric fly-around orbit using the solar wing is designed in this paper. The formation is maintained by controlling the follower. The in-plane and the out-of-plane control are separated. The follower is rotating around the inertial principal axis with a constant angular velocity. The controlling of the angular between the solar wings and satellite body is obtained. The orbit is controlled by adjusting the geometrical orientation. The in-plane control is prior to the out-of- plane control. The out-of-plane control force is applied when the error of in-plane is eliminated or the in-plane control force can not be supplied. Three different kinds of numerical simulations including the orbit reconfiguration, the error elimination, and the orbit maintenance are performed. It is shown that the method can keep the error less than 5 m, and it is feasible for the space formation.