Plate-Like Flexible Spacecraft Modeling and Distribution of Control Moment Gyroscopes

This study investigates the optimization configuration problem of control moment gyroscopes for flexible vibration suppression of large space structures. First, the structural dynamic model of an unconstrained plate-like flexible spacecraft with control moment gyroscopes is established using the Lagrangian method and the finite element method. Second, an optimization problem is established with the positions of control moment gyroscope array as variables and the linear quadratic index of mechanical energy during vibration process as the objective function. Additionally, an improved gray wolf optimizer is used to solve the optimization problem. The optimization results show that the control moment gyroscopes should be primarily placed on the corners of the spacecraft in a symmetrical manner. Finally, the priority of control moment gyroscope installation positions was studied using topological iteration. The results indicate that the control moment gyroscopes should be primarily installed on the corners, followed by the central positions, and then gradually expanded outward.