Nonlinear Dynamic and Piezoelectric Ply Control Strategies Investigations on Laminated Flexible Spacecraft

A nonlinear dynamic modeling method for active vibration suppression of laminated flexible spacecraft with macro fiber composite (MFC) is presented in this paper. High-order shear deformation theory is utilized to accurately describe the flexible deformations caused by the coupling effect of large overall motions and composite laminated material. Meanwhile, strain feedback control law strategy is established by using MFC as control actuators. According to the experiments results, the correctness of the proposed method has been verified. Depend on the proposed method, the system with different ply control strategies of MFCs is studied for obtaining the optimized control results. Integrated considering the kinematic accuracy, profile accuracy and dynamic character of the spacecraft system, the strategy with double MFCs assembling in the lower surface is superior to others. There are theoretical value and practical significance for the compositive mechanical performance of the spacecraft with laminated piezoelectric plates.