Abstract This paper presents two ways to transfer a spacecraft to distant periodic orbits in the Earth–Moon system. These unstable periodic orbits of the restricted three-body problem reveal a rich phase-portrait structure that can be used by space missions. Through the perspective of dynamical system theory, distant periodic orbits' invariant manifolds can be exploited to design novel low-energy trajectories in the Earth–Moon framework. Interior and exterior transfers are presented. The latter use impulsive, high-thrust propulsion to target the stable manifold from the exterior. Interior transfers are instead formulated with continuous, low-thrust propulsion. The attainable sets are used in both cases to handle families of either coast arcs or low-thrust orbits. First guess solutions are optimized in the framework of the Sun–Earth–Moon–Spacecraft restricted four-body problem through direct transcription and multiple shooting. The novelty of the presented solutions, as well as their efficiency, is demonstrated through examples.

    Highlights ► Extend the invariant manifold technique to the case of final distant periodic orbit around the Moon. ► Study low-thrust propulsion in the restricted three-body problem. ► Design low-thrust, stable-manifold interior trajectories to final DPO around the Moon.


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    Titel :

    Transfers to distant periodic orbits around the Moon via their invariant manifolds


    Beteiligte:
    Mingotti, G. (Autor:in) / Topputo, F. (Autor:in) / Bernelli-Zazzera, F. (Autor:in)

    Erschienen in:

    Acta Astronautica ; 79 ; 20-32


    Erscheinungsdatum :

    2012-04-12


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch