Constructing ballistic capture orbits in the real Solar System model

• DOI: 10.1007/s10569-014-9580-5
• Publication Date: 2014-10-20T05:53:11Z
• Authors: Z.-F. Luo; F. Topputo; F. Bernelli-Zazzera; G.-J. Tang
• Keywords: Ephemeris; Celestial mechanics; Orbital mechanics

A method to design ballistic capture orbits in the real Solar System model is presented, so extending previous works using the planar restricted three-body problem. In this generalization a number of issues arise, which are treated in the present work. These involve reformulating the notion of stability in three-dimensions, managing a multi-dimensional space of initial conditions, and implementing a restricted $$n$$ -body model with accurate planetary ephemerides. Initial conditions are categorized into four subsets according to the orbits they generate in forward and backward time. These are labelled weakly stable, unstable, crash, and acrobatic, and their manipulation allows us to derive orbits with prescribed behavior. A post-capture stability index is formulated to extract the ideal orbits, which are those of practical interest. Study cases analyze ballistic capture about Mercury, Europa, and the Earth. These simulations show the effectiveness of the developed method in finding solutions matching mission requirements.