Abstract In this paper, formation flying between a chief spacecraft moving in an elliptic orbit and a deputy spacecraft is studied. First, by using a state transition matrix (STM) of the Tschauner-Hempel equations, which describe the relative motion between the chief and deputy spacecraft, two formation trajectories that suppress relative distance variations are obtained. These trajectories are extensions of an along-track formation and a general circular orbit wherein the chief spacecraft moves in a circular orbit. The effects of the J2 perturbation on the trajectories are considered in the initial conditions. Further, the solution of the formation reconfiguration that minimizes the L2-norm of the deputy control forces is derived. A control law that realizes the reconfiguration trajectory by using a finite number of impulses is also derived. Finally, numerical examples of the construction of the formation trajectories are shown.


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    Title :

    Spacecraft Formation Design and Control in Keplerian Elliptic Orbits


    Contributors:


    Publication date :

    2011




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    Local classification TIB:    770/7040
    BKL:    55.60 Raumfahrttechnik




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