Satellite Constellation Reconfiguration Using the Approximating Sequence Riccati Equations

Abstract

In this work we study the reconfiguration of a constellation of satellite. In this work we consider the non-linear
feedback optimal control of the motion of a spacecraft under the influence of the gravitational attraction of a central
body, the Earth in our case, and we would like to transfer the spacecraft from lower circular orbit to a higher one. Both
orbits around the Earth are assumed to be circular and coplanar. We use both radial and tangential thrust control. The
nonlinear dynamics of the system will be factorized in such a way that the new factorized system is accessible. The
problem is tackled using the Approximating Sequence Riccati Equations (ASRE) method. The technique is based on
Linear Quadratic Regulator (LQR) with fixed terminal state, which guarantees closed loop solution. The method is
tested through GNSS circular constellation.