Abstract

Abstract In this paper we study the manoeuvres to be done by a spacecraft in order to correct the error in the execution of the injection manoeuvre in the transfer trajectory. We will consider the case where the nominal trajectory is a halo orbit around the collinear equilibrium point L 1 . The results can be easily extended to the L 2 point and to other kinds of libration point orbits, such as Lissajous and quasi-halo orbits. For our study we use simple dynamical systems concepts related with the invariant manifolds of the target orbit, and we compare our results with those obtained by Serban et al. (Automatica, 38(2002) 571) using optimal control.

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