具有SGCMG系统的挠性卫星姿态机动控制及验证

针对挠性卫星在轨姿态快速机动的需求，开展了星体姿态机动控制方法及控制实现研究。基于建立的挠性卫星姿态跟踪控制误差方程，给出了PD控制与补偿控制相结合的姿态跟踪控制器形式；考虑系统实现的时延影响，利用经典频率分析方法选择了兼顾系统稳定性及宽带控制的控制参数；在控制具体实现中，采用一种新型的基于力矩矢量调节奇异规避操纵策略，克服常规鲁棒奇异规避操纵存在的框架“锁死”现象，在解决奇异规避的同时避免激发挠性振动。所提出方法的有效性通过了在轨验证。

Maneuver Attitude Control Method and In Orbit Verification for Flexible Satellites with Single Gimbal Control Moment Gyros

The problems of the attitude maneuver control method and its actual application realization for flexible satellites are investigated. An attitude tracking controller which combines the PD control with compensation strategy is proposed, and the controller parameters, which can guarantee both system stability and wide-band control, are achieved by employing the classical frequency-domain design technique for a flexible satellite system in case of time lag. In the control system implementation based on the control moment gyros (CMG), a novel CMG steering strategy by directly adjusting torque command vector is adopted to overcome the gimbal locked phenomenon of the traditional singularity robust steering law, as well as to avoid the singularity without exciting the flexible mode vibration. The effectiveness of the proposed method is sufficiently verified by an in-orbit flexible satellite.