VSCMG簇的操纵律优化设计
发布时间：2018-09-08 10:54
【摘要】：变速控制力矩陀螺(variable speed control moment gyro,VSCMG)簇相对于单框架控制力矩陀螺簇仅增加了飞轮转速可调自由度,实现难度不大,但能够缓解奇异问题。基于线性代数理论,从机理上分析了已有的添加零运动的加权伪逆操纵律不能规避VSCMG簇内所有奇异点。针对添加零运动的加权伪逆操纵律不能规避奇异点的问题,采用优化方法,设计出一种新型的VSCMG簇操纵律,能够规避采用传统添加零运动的加权伪逆操纵律不能规避的奇异点。最后搭建整个航天器姿态控制系统,仿真验证了所设计的新型操纵律奇异规避的有效性。
[Abstract]:The variable speed control moment gyroscope (variable speed control moment gyro,VSCMG) can only increase the freedom of the flywheel rotational speed in comparison with the single frame control torque gyroscope. It is not difficult to realize, but it can alleviate the singularity problem. Based on the theory of linear algebra, the existing weighted pseudo-inverse manipulation law with zero motion can not avoid all singular points in VSCMG cluster. In order to solve the problem that the weighted pseudo inverse manipulation law with zero motion can not avoid singularity points, a new VSCMG cluster manipulation law is designed by using optimization method, which can avoid the singular points that can not be evaded by traditional weighted pseudo inverse manipulation law with zero motion. Finally, the whole spacecraft attitude control system is built, and the effectiveness of the new control law is verified by simulation.
【作者单位】： 哈尔滨工业大学控制与仿真中心;
【基金】：国家自然科学基金(61427809,61203191)资助课题
【分类号】：V448.2
，
本文编号：2230310
[Abstract]:The variable speed control moment gyroscope (variable speed control moment gyro,VSCMG) can only increase the freedom of the flywheel rotational speed in comparison with the single frame control torque gyroscope. It is not difficult to realize, but it can alleviate the singularity problem. Based on the theory of linear algebra, the existing weighted pseudo-inverse manipulation law with zero motion can not avoid all singular points in VSCMG cluster. In order to solve the problem that the weighted pseudo inverse manipulation law with zero motion can not avoid singularity points, a new VSCMG cluster manipulation law is designed by using optimization method, which can avoid the singular points that can not be evaded by traditional weighted pseudo inverse manipulation law with zero motion. Finally, the whole spacecraft attitude control system is built, and the effectiveness of the new control law is verified by simulation.
【作者单位】： 哈尔滨工业大学控制与仿真中心;
【基金】：国家自然科学基金(61427809,61203191)资助课题
【分类号】：V448.2
，
本文编号：2230310
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