Periodic Orbit-Attitude Solutions in the Planar Elliptic Restricted Three-Body Problem

摘要

The pitch motion of spacecraft in the planar elliptic restricted three-body system is studied. Previous studies laid the foundation for spacecraft stability analysis with a small perturbation to the zero pitch motion. In this study, a cellmapping approach that combines analytical and numerical techniques is used to study the global behavior of the full nonlinear spacecraft attitude in which coupling between orbital dynamics and attitude occurs. Spacecraft placed at the Lagrangian points and some of the reference trajectories are considered to study the effect of varying gravity gradient torque to pitch motion in the three-body system. The spacecraft configuration and orbital eccentricity are also taken into account as parameters for the study. Multiple-period periodic solutions and invariant surfaces are presented for different cases.