The pitch motion of a 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 cell mapping 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. The effect of gravity gradient torques, orbital eccentricity, and the spacecraft configuration at different Lagrangian points is analyzed. Multiple-period periodic solutions and invariant surfaces are presented for different cases. Reference trajectories around the Lagrangian points are also considered to study coupled dynamics.


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    Title :

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


    Contributors:

    Conference:

    AIAA/AAS Astrodynamics Specialist Conference ; 2016 ; Long Beach, CA, United States


    Publication date :

    2016-09-12


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English