Analysis On Stability Of Coulomb Two-satellite Formation And Method Of Configuration Control

The promising and new conceptual technology of satellites formation flying,Coulomb Formation is one of the most effective methods on solving some very thornyproblems like avoidance of collision and contamination of nearby satellites. Thecoulomb satellite formation is especially suited for close formation flying in high Earthorbits which need a wide field of view to perform interferometry. Based on coulombSatellite Formation Conception, this dissertation investigates the orbit dynamics forcoulomb formation, the stability of system and the reconfiguration of formation.Firstly, this dissertation analyses the environment of space plasma and thephenomenon of Debye shielding for coulomb satellites formation. Then this thesisinvestigates the formation’s applicability in GEO and discusses the impacts which thedisturbing force makes on in the process of charging. Founded by Hill frame, this paperutilizes the Lagrange’s equation to establish the orbital dynamics model of CoulombSatellite Formation.Through simplification, this thesis derives the equation ensuring the stability of theformation and investigates the elementary conditions for stable formation system.Moreover, this thesis studies three kinds of configurations of two-spacecraft formation.Further, this dissertation also analyses three types of three-spacecraft formation of linearthree-spacecraft formation and equilateral triangle formation and derives theconfiguration function.Concerning the possible perturbation in the process of formation, this thesischooses orbital direction and along-track direction to analyze the stability of formationsystem. By designing and applying feedback control method, this dissertationsuccessfully controls the error of relative position.For two-satellite coulomb formation, this paper also devises a plan of maneuveringthe formation orbit basing on PD control method. These series of plan can maneuver theformation from a distance of25meters to35m or backward, which is very promising onthe engineering field of separated spacecraft interferometry.Finally, this dissertation designs the blueprint for two-craft reconfiguration. Basedon optimal control theory and three types of objective functions and utilizing Legendrepseudo-spectrum method, this paper separately devises schemes for optimal orbit maneuvering and optimal orbit transfer and compares cons and pros of different transferthemes.