Precise Autonomous Orbit Control in Low Earth Orbit

This paper analyses the problem of the autonomous absolute orbit control of a space- in low Earth orbit using different on-board feedback control systems. Three types of are compared. The first implements an analytical control algorithm. The second third controllers considered are the linear and the quadratic optimum regulator from classical control theory. For the implementation of the linear regulators the problem been formulated as a two spacecraft formation keeping in which one of the spacecraft is and not affected by non-gravitational orbit perturbations. The relative Earth-fixed have been introduced as a set of parameters which can express the relative mo- of two spacecraft in an Earth-fixed reference frame. These relative elements allow the formalization of the requirements of an absolute orbit control system design and formulation as a particular case of spacecraft formation flying control problem. A direct between the relative Earth-fixed and orbital elements enables the direct transla- of absolute to formation control requirements and the straightforward use of classical theory techniques for the orbit control of distributed spacecraft systems. The val- , performance estimation and comparison of the control algorithms are realized by of numerical simulations with a high level of realism.