Abstract Sun–Earth/Moon L 4 and L 5 axial orbits provide ideal locations to monitor and search for near Earth asteroids. In this paper, an unstable L 5 axial orbit is selected as the target orbit, and then we first investigate transfers from the Earth to the target axial orbit in the ephemeris model. Based on the dynamical structure, we employ stable manifolds associated with the target axial orbit and lunar flyby technique in the preliminary design process. Then, we implement the multiple-shooting differential correction to refine the lunar flyby transfer orbit in the ephemeris model based on the preliminary design. Through a refinement strategy we proposed, a four-impulse lunar flyby transfer orbit from the initial low Earth orbit to the target axial orbit is obtained in the ephemeris model. Finally, we apply the optimal control method to design a low-thrust transfer for a small satellite to the target axial orbit based on the four-impulse transfer orbit. We obtain a low-thrust end-to-end transfer orbit with three thrust arcs via the optimization piece by piece. Numerical results indicate that the lunar flyby plays an important role in the low-thrust transfer orbit, and helps us efficiently decrease the fuel consumption.

    Highlights An unstable L 5 axial orbit is selected as the target orbit. We first study transfers from the Earth to the axial orbit in the ephemeris model. The lunar flyby technique is introduced in the design to reduce the fuel cost. We apply the optimal control method to design a low-thrust transfer to the axial orbit.


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    Titel :

    Lunar flyby transfers to L 5 axial orbit


    Beteiligte:
    Qi, Yi (Autor:in) / de Ruiter, Anton (Autor:in)

    Erschienen in:

    Acta Astronautica ; 180 ; 516-526


    Erscheinungsdatum :

    2021-01-03


    Format / Umfang :

    11 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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