The control method for satellites formation-keeping based on J₂ term perturbation and atmosphere drag

It's important to make use of J₂ term and atmospheric drag perturbations in low-orbit formation flying, for they are main disturbing forces in those kinds of orbits. Three-axis orbit-drifts caused by J₂ term perturbation and differences in classical orbit elements due to atmospheric drag perturbation are concerned in this paper. Considering both J₂ term and atmospheric drag Perturbations, an analytic relation between in-track drift Δx and relative semi-major axis perturbation Δa is demonstrated. Based on it, a single side limit cycle control method is designed. The simulation has demonstrated the validity and feasibility of this method. The control period is nearly 2.8 days and Δv is 0.00631 m/s each time.