Perturbation Analysis And Control Of Tight Satellite Formation Flying

During the flying of formation satellites,formation configuration could be broken under J2 perturbation and lunisolar gravitational perturbation.This paper analyses perturbations to eliminate the evolution of formation configuration and the solution to long term satellite formation flying is obtained.And the long term stability of formation flying is studied by the evolution of formation configuration.Based on analyses of perturbations,satellites formations are designed to achieve minimal evolution of relative eccentricity vector and trace direction distance.At the same time modified relative elements are used to analyze perturbations on formation satellites to avoid singularity of eccentricity.The J2 perturbation and lunisolar gravitational perturbation are periodic disturbing force.The period of J2 perturbation is orbital period and the period of lunisolar gravitational perturbation is lunar orbital period.Because of the periodicity of perturbations,iterative learning control is used to control the satellite formation in order to take advantage of the periodicity to save fuel and decrease control error.What's more,PID controller is applied as tracking controller in order to decrease influence of nonperiodic disturbing forces.Finally,Some simulations are carried out with iterative learning control,which prove that the ILC control improve the control precision and response speed.