Dynamical Issues in Rendezvous operations with Third Body Perturbation

The paper presents the complete 6-DOF set of equations of relative motion that describes the dynamics and the kinematic of two spacecraft in non inertial reference frames under the restricted three body problem hypotheses. The work was motivated by the increasing interest in missions that require the modelling of the third body perturbation to lead to an accurate synthesis if Guidance Navigation and Control systems, for this reason also the linearized models of the complete coupled translational-rotational dynamics are provided.