Fractionated isomerized spacecraft cluster incompact formation design

An incompact formation design method is proposed for a low earth orbit fractionated spacecraft cluster, the differential drag is considered. The relative distance of any two satellites in the incompact formation is required to be within a certain bound in a long time. The relative eccentricity vector and the relative orbit inclination are used to describe the incompact formation, and the relative semi-axis bias and the relative angular of latitude are considered as the optimal variables. A fictitious space circle formation is used to design the relative orbit for collision avoidance. The relative distance of the two isomerized satellites can be satisfied when considering the aerodynamic force. Simulation results manifest that while the satellite orbit is 500 km, and the area mass ratio of two satellites is 0.0030 m²/kg and 0.0032 m²/kg respectively, the relative distance of the two satellites can be within from 200 m to 20 km in 50 days.