利用太阳光压的大偏心率伴飞卫星轨道控制
发布时间：2018-11-23 10:07
【摘要】：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.
[Abstract]:A method for orbit control of satellite with large eccentricity by using solar sail is presented. The satellite has a constant rotation of angular velocity around its inertial spindle, and the direction of the inertial spindle remains unchanged. The control of the satellite is divided into two parts: the control of orbit surface and the control of orbit plane. In the control process, priority is given to the in-plane control of the track, and when the in-plane control of the track cannot be carried out (or can not be controlled in the track for geometric reasons), the control of the track surface is carried out. The direction and magnitude of the control force needed for the in-plane control of the track are calculated by the synovial control method (Sliding Mode Control). After the required control force is obtained, the analytical expression of the angle of the solar sail relative to the satellite body during the control process is deduced. Different control forces are obtained by controlling the direction of the solar sail. The whole control process is only for the companion satellite, and the host satellite is in a natural flight state. Finally, the numerical verification of the control method is carried out. The orbit adjustment and error elimination of the tracking orbit are carried out by the control system in the state of non-perturbation motion, and the orbit maintenance of the tracking orbit is carried out considering the perturbation of the fourth order non-spherical gravity and the third body gravity. The numerical results show that the trajectory error can be kept less than 5 m by this control method.
【作者单位】： 中国科学院紫金山天文台;中国科学院空间目标与碎片观测重点实验室;中国科学院大学;
【基金】：国家自然科学基金项目(11125315,11173056)资助
【分类号】：P173.1
本文编号：2351203
[Abstract]:A method for orbit control of satellite with large eccentricity by using solar sail is presented. The satellite has a constant rotation of angular velocity around its inertial spindle, and the direction of the inertial spindle remains unchanged. The control of the satellite is divided into two parts: the control of orbit surface and the control of orbit plane. In the control process, priority is given to the in-plane control of the track, and when the in-plane control of the track cannot be carried out (or can not be controlled in the track for geometric reasons), the control of the track surface is carried out. The direction and magnitude of the control force needed for the in-plane control of the track are calculated by the synovial control method (Sliding Mode Control). After the required control force is obtained, the analytical expression of the angle of the solar sail relative to the satellite body during the control process is deduced. Different control forces are obtained by controlling the direction of the solar sail. The whole control process is only for the companion satellite, and the host satellite is in a natural flight state. Finally, the numerical verification of the control method is carried out. The orbit adjustment and error elimination of the tracking orbit are carried out by the control system in the state of non-perturbation motion, and the orbit maintenance of the tracking orbit is carried out considering the perturbation of the fourth order non-spherical gravity and the third body gravity. The numerical results show that the trajectory error can be kept less than 5 m by this control method.
【作者单位】： 中国科学院紫金山天文台;中国科学院空间目标与碎片观测重点实验室;中国科学院大学;
【基金】：国家自然科学基金项目(11125315,11173056)资助
【分类号】：P173.1
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