Dynamics, control and reconfiguration of satellite formation flight around Lagrangian points

Abstract

The concept of Satellite Formation Flying (SFV) means having two or more satellites in orbit, with their relative positions remain constant or obeying a configuration eventually dynamics along the trajectory This concept involves control over the movement of a group of vehicles, with the goal of maintaining a certain geometry configuration between the elements of the set. It allows a group of small and cheap satellites operating like a single "virtual large satellite" , providing an ability to obtain unique data. Thus, using the Earth-Moon system, this project aims to present a methodology that meets the desired effectiveness and efficiency, supported by the concepts from the application of the Theory of Dynamical Systems and exploitation of the unique features of the Circular Restricted Three Body Problem, basic model for the scenario Earth-Moon-particle, where the gravitational iterations between the Satellites in Formation Flight are neglected. In this project, the satellites are located around the L4 and L5 Lagrangian points which form an equilateral triangles with the Earth and the Moon. In Earth-Moon system, L4 and L5 are stable equilibrium points (centers), i.e there exist a family of periodic orbits around them. It is therefore necessary to find an optimal control strategy for Satellites in Formation Flight to keep fixed the configuration in the direction in which it is more stable. Finally, depending on the type of applications, such as space telescopes may be necessary to reconfigure the geometrical arrangement of the formation. We must therefore find a set of maneuvers that minimize the spent fuel to change the geometry and avoid collision between the satellites. (AU)