挠性航天器姿态机动的主动振动控制

针对挠性航天器三轴姿态同时机动时太阳帆板的振动抑制问题,提出了采用压电智能元件作为致动器的主动振动控制方法,基于Lagrangian方法和四元数参数化建立了航天器姿态动力学和运动学模型.利用航天器姿态控制问题固有的无源性,设计了一种仅利用姿态四元数而无需以角速度测量、挠性变形位移及速率测量作为反馈的控制规律,使得在大角度姿态机动的同时能有效地抑制太阳帆板的振动;基于Lyapunov方法证明了设计的动态控制器能够保证姿态的渐近稳定性和模态振动的衰减性.将该方法的控制效果与PD控制方法进行了比较,仿真验证了所给出的控制方法的可行性和有效性.

Active vibration control of flexible spacecraft during attitude maneuver

An approach is presented for actively suppressing the vibrations of a flexible spacecraft during large angle attitude maneuvers.On the basis of a model obtained using the Lagrangian approach and the unitary quaternion parameterization,a dynamics controller capable of performing maneuvers for the flexible spacecraft by only using attitude measures and piezoelectric actuators,was used to dampen the vibration of flexible booms induced during the maneuvers.The absence of flexible displacement and velocity sensors was compensated for by the presence of appropriate dynamics in the controller.Based on the passivity of the attitude control system,the angular velocity feedback could be replaced by a nonlinear filter of the quaternion.The Lyapunov technique was applied in the design of the dynamics controller,which is able to not only stabilize the spacecraft attitude but also suppress vibrations of the flexible solar panels.The proportional plus derivative(PD) control strategy was adopted and compared with the proposed control approach.Simulation results reveal the interest and practical feasibility of such a control scheme.