Control Orbital Autónomo Restringido de Bajos Empujes y Filtrado de Elementos Orbitales

Abstract

Current navigation and control technologies are used to perform a feasibility analysis of continuous and semi-continuous orbit control. In particular, a strategy based on filtered Relative Orbit Elements is proposed for an autonomous low thrust orbit control algorithm. An Earth Observation constellation with Sinthetic Aperture Radar for Differential Interferometry is taken as a reference mission for the simulations. The filter significantly reduces the variance of the relative orbit elements. This reduction, in combination with the use of current Precise Point Positioning navigation, enables the continuous low thrust control compatible with high performance electric propulsion. The same control and filtering strategies may also be implemented for formation flying.