Abstract
Low-energy escaping trajectories in the Hill three-body problem are investigated numerically using a Poincare map that relates the crossing of a plane containing one of the collinear libration points back to the first periapsis passage. This set of periapsis points is confined in a small region that determines some conditions for escape from any planetary satellite. In particular, the minimum energy to escape from a given circular orbit is obtained together with restrictions on the initial conditions (inclination, argument of periapsis, and longitude of the ascending node). This leads to a new optimal transfer criterion for the class of directly escaping trajectories. Savings on the order of 130 m/s in the case of Europa are obtained when compared to a classic two-body model. The results are also extended to the problem of low-energy capture. Numerical applications are given for the cases of Miranda, Europa, Titan, and Triton.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
