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We aim at providing a preliminary approach on the dynamics of a spacecraft inorbit about the asteroid (99942) Apophis during its Earth close approach. Thephysical properties from the polyhedral shape of the target are derivedassigning each tetrahedron to a point mass in its center. That considerablyreduces the computation processing time compared to previous methods toevaluate the gravitational potential. The surfaces of section close to Apophisare build considering or not the gravitational perturbations of the Sun, theplanets, and the SRP. The Earth is the one that most affects the invisticatedregion making the vast majority of the orbits to collide or escape from thesystem. Moreover, from numerical analysis of orbits started on March 1, 2029,the less perturbed region is characterized by the variation of the semimajoraxis of 40-days orbits, which do not exceed 2 km very close to the central body($a < 4$ km, $e < 0.4$). However, no regions investigated could be a possibleoption for inserting a spacecraft into natural orbits around Apophis during theclose approach with our planet. Finally, to solve the stabilization problem inthe system, we apply a robust path following control law to control the orbitalgeometry of a spacecraft. At last, we present an example of successfuloperation of our orbit control with a total $\bigtriangleup v$ of 0.495 m/s for60 days. All our results are gathered in the CPM-ASTEROID database, which willbe regularly updated by considering other asteroids.

First approximation for spacecraft motion relative to (99942) Apophis