Lunar capture trajectories in the four-body problem

K. Onozaki, Hiroaki Yoshimura

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    3 Citations (Scopus)

    Abstract

    In this paper, we develop the low energy trajectory design of a spacecraft from the Earth to the Moon in the context of the Planar Restricted Four Body Problem, which may be approximately modeled by coupling two Planar Restricted Three Body Problems, i.e., the Sun-(Earth+Moon)-Spacecraft and the Earth-Moon-Spacecraft systems. The principal idea lies in the so-called tube dynamics, which may patch invariant manifolds of the two PR3BPs to obtain the required lunar capture trajectories. We first model the S-E-M-S/C system by the coupled Planar Restricted Circular Three Body Problem (PRC3BP) and we also analyze the case, in particular, where the E-M-S/C system is modeled by the Planar Restricted Elliptic Three Body Problem (PRE3BP), since the E-M system has the nonnegligible eccentricity. Finally, we develop the low energy lunar capture trajectory in the coupled PRC3B-PRE3BP in comparison with the case of the coupled PRC3BP.

    Original languageEnglish
    Title of host publicationAIAA SPACE 2013 Conference and Exposition
    Publication statusPublished - 2013
    EventAIAA SPACE 2013 Conference and Exposition - San Diego, CA
    Duration: 2013 Sep 102013 Sep 12

    Other

    OtherAIAA SPACE 2013 Conference and Exposition
    CitySan Diego, CA
    Period13/9/1013/9/12

    Fingerprint

    four body problem
    three body problem
    Moon
    moon
    Spacecraft
    spacecraft
    Earth (planet)
    trajectory
    Trajectories
    trajectories
    eccentricity
    Sun
    energy
    sun
    tubes

    ASJC Scopus subject areas

    • Space and Planetary Science
    • Aerospace Engineering

    Cite this

    Onozaki, K., & Yoshimura, H. (2013). Lunar capture trajectories in the four-body problem. In AIAA SPACE 2013 Conference and Exposition

    Lunar capture trajectories in the four-body problem. / Onozaki, K.; Yoshimura, Hiroaki.

    AIAA SPACE 2013 Conference and Exposition. 2013.

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    Onozaki, K & Yoshimura, H 2013, Lunar capture trajectories in the four-body problem. in AIAA SPACE 2013 Conference and Exposition. AIAA SPACE 2013 Conference and Exposition, San Diego, CA, 13/9/10.
    Onozaki K, Yoshimura H. Lunar capture trajectories in the four-body problem. In AIAA SPACE 2013 Conference and Exposition. 2013
    Onozaki, K. ; Yoshimura, Hiroaki. / Lunar capture trajectories in the four-body problem. AIAA SPACE 2013 Conference and Exposition. 2013.
    @inproceedings{b97843f765444e1dad8039a27fcb9ee7,
    title = "Lunar capture trajectories in the four-body problem",
    abstract = "In this paper, we develop the low energy trajectory design of a spacecraft from the Earth to the Moon in the context of the Planar Restricted Four Body Problem, which may be approximately modeled by coupling two Planar Restricted Three Body Problems, i.e., the Sun-(Earth+Moon)-Spacecraft and the Earth-Moon-Spacecraft systems. The principal idea lies in the so-called tube dynamics, which may patch invariant manifolds of the two PR3BPs to obtain the required lunar capture trajectories. We first model the S-E-M-S/C system by the coupled Planar Restricted Circular Three Body Problem (PRC3BP) and we also analyze the case, in particular, where the E-M-S/C system is modeled by the Planar Restricted Elliptic Three Body Problem (PRE3BP), since the E-M system has the nonnegligible eccentricity. Finally, we develop the low energy lunar capture trajectory in the coupled PRC3B-PRE3BP in comparison with the case of the coupled PRC3BP.",
    author = "K. Onozaki and Hiroaki Yoshimura",
    year = "2013",
    language = "English",
    isbn = "9781624102394",
    booktitle = "AIAA SPACE 2013 Conference and Exposition",

    }

    TY - GEN

    T1 - Lunar capture trajectories in the four-body problem

    AU - Onozaki, K.

    AU - Yoshimura, Hiroaki

    PY - 2013

    Y1 - 2013

    N2 - In this paper, we develop the low energy trajectory design of a spacecraft from the Earth to the Moon in the context of the Planar Restricted Four Body Problem, which may be approximately modeled by coupling two Planar Restricted Three Body Problems, i.e., the Sun-(Earth+Moon)-Spacecraft and the Earth-Moon-Spacecraft systems. The principal idea lies in the so-called tube dynamics, which may patch invariant manifolds of the two PR3BPs to obtain the required lunar capture trajectories. We first model the S-E-M-S/C system by the coupled Planar Restricted Circular Three Body Problem (PRC3BP) and we also analyze the case, in particular, where the E-M-S/C system is modeled by the Planar Restricted Elliptic Three Body Problem (PRE3BP), since the E-M system has the nonnegligible eccentricity. Finally, we develop the low energy lunar capture trajectory in the coupled PRC3B-PRE3BP in comparison with the case of the coupled PRC3BP.

    AB - In this paper, we develop the low energy trajectory design of a spacecraft from the Earth to the Moon in the context of the Planar Restricted Four Body Problem, which may be approximately modeled by coupling two Planar Restricted Three Body Problems, i.e., the Sun-(Earth+Moon)-Spacecraft and the Earth-Moon-Spacecraft systems. The principal idea lies in the so-called tube dynamics, which may patch invariant manifolds of the two PR3BPs to obtain the required lunar capture trajectories. We first model the S-E-M-S/C system by the coupled Planar Restricted Circular Three Body Problem (PRC3BP) and we also analyze the case, in particular, where the E-M-S/C system is modeled by the Planar Restricted Elliptic Three Body Problem (PRE3BP), since the E-M system has the nonnegligible eccentricity. Finally, we develop the low energy lunar capture trajectory in the coupled PRC3B-PRE3BP in comparison with the case of the coupled PRC3BP.

    UR - http://www.scopus.com/inward/record.url?scp=84884844033&partnerID=8YFLogxK

    UR - http://www.scopus.com/inward/citedby.url?scp=84884844033&partnerID=8YFLogxK

    M3 - Conference contribution

    AN - SCOPUS:84884844033

    SN - 9781624102394

    BT - AIAA SPACE 2013 Conference and Exposition

    ER -