Geometrical methods for formation flying design based on the analytical solution to Hill's equations have been previously developed and used to specify desired relative motions in near circular orbits. By generating relationships between the vehicles that are intuitive, these approaches offer valuable insight into the relative motion and allow for the rapid design of satellite configurations to achieve mission specific requirements, such as vehicle separation at perigee or apogee, minimum separation, or a specific geometrical shape. Furthermore, the results obtained using geometrical approaches can be used to better constrain numerical optimization methods; allowing those methods to converge to optimal satellite configurations faster. This paper presents a set of geometrical relationships for formations in eccentric orbits, where Hill.s equations are not valid, and shows how these relationships can be used to investigate formation designs and how they evolve with time.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Analysis of Formation Flying in Eccentric Orbits Using Linearized Equations of Relative Motion


    Contributors:


    Publication date :

    2004-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English






    Formation flying control in eccentric orbits

    Tillerson, Michael / How, Jonathan | AIAA | 2001


    Spacecraft Formation-Flying in Eccentric Orbits

    Zhang, Heng / Sun, Lan | AIAA | 2003


    The study of relative dynamics for spacecraft formation flying in eccentric orbits

    Wang, Pengji / Yang, Di | Emerald Group Publishing | 2003