Spacecraft Attitude Control with Fully Actuated System and Particle Swarm Optimization Approaches

In this paper, attitude tracking control of spacecraft is studied. Firstly, the fully actuated system models of rigid body satellite is established, and then the linear sliding mode controller is designed by direct parameterization method. One of the key problems in direct parameterization is the tuning of matrix parameters. Aiming at the difficulty of parameter setting of spacecraft attitude controller based on fully actuated system approach, a parameter setting method based on particle swarm optimization algorithm was proposed. Particle swarm optimization is used to adjust matrix parameters more quickly and accurately. At the same time, inertia weight factor is introduced to avoid the early local optimal phenomenon of particle swarm optimization algorithm. Simulation results reveal the effect of the proposed control approach.