A hybrid control scheme for attitude and vibration suppression of a flexible spacecraft using energy-based actuators switching mechanism

A novel energy-based switching logic scenario to design a hybrid thruster/reaction wheel (RW) system is investigated for active vibration suppression of a flexible spacecraft embedded with collocated and Non-collocated configuration of Piezoelectric patches. The system model is obtained using Lagrangian formulation and the finite element method. The control system includes the attitude and vibration controller, designed by Extended Lyapunov Design (ELD)/Strain Rate Feedback (SRF) control technique to take advantage of the globally stabilized feedback control strategy. An attractive feature of the proposed dual-stage system is the switching time, which is model-based and depends on the rigid-flexible body dynamics including PZT actions. Based on this approach, the Multi-objective Genetic Algorithm (MGA) determines the switching point concerning fuel consumption, settling time and vibration energy. The obtained results using a comparative study show the capabilities of the combination of the RWs and thrusters for cost-effective, high precise attitude control and residual vibration suppression of flexible spacecraft in future missions.