Structure preserving method of isomerism multiple satellites formation under impulsive maneuvers

In near earth orbit, the initial state of two satellites formation configuration parameters is usually designed to achieve a controlled long-term stable relative motion. Focusing on the coupling relative motion caused by multiple satellites formation, an analysis method of relative motion was proposed on the basis of the Hill coordinates and trigonometric function formulas. Based on the definition of sensing baseline of synthetic aperture radar (SAR) load, combining with the relative motion character of formation configuration parameters, a design method of configuration parameter was put forward to find the maximum effective baselines combination. The long term effect of J2 term and air drag perturbation was analyzed, based on which the relative motion of isomerism multiple satellites formation was studied and a leader-follower form of bias control was proposed under impulse maneuver to preserve the designed formation configuration. The control method was validated in a four satellites formation with isomerism area-mass ratios.