In this paper the problem of spacecraft orbit transfer with minimum fuel consumption is considered. The main goal is to study the effect of errors in the propulsive system in an orbit transfer problem. After a search in the literature and a analysis of the resutls available, we selected a method developed by Altman and Pistiner to be the base of the algorithm developed. The spacecraft is supposed to be in Keplerian motion controlled by the thrusts, that are assumed to be impulsive with errors in magnitude and direction. Resutls of simulations are also presneted, to show the extra fuel and time required to complete the maneuver.
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