NASA's Artemis campaign plans to send astronauts to the lunar surface for the first time since 1972. The campaign relies on the Orion crew capsule to ferry the crew from Earth to an L2 9:2 lunar synodic resonant Near-Rectlinear Halo Orbit (NRHO) before descent to the lunar surface. This investigation examines a process to construct various abort families during transit from Earth to the NRHO using the Earth-Moon Circular Restricted Three-Body Problem (CR3BP). The initial trajectories are constructed using the CR3BP and categorized in families. A process is then summarized to transcribe and converge trajectories from the CR3BP into a higher-fidelity model. Ultimately, an effective methodology to develop, classify and converge these aborts in higher-fidelity is critical to the Artemis program in the event of an anomaly during the crew transit.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Abort Trajectory Design Strategies for the Artemis Missions


    Contributors:
    B. McCarthy (author) / J. Geiser (author) / M. Bolliger (author) / D. Owen (author) / D. Henry (author)

    Publication date :

    2024


    Size :

    20 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Artemis II Inertial Sensor Failure & Abort Condition Study

    Nicholas Harrison Hoen / Jared O Leggett / Evan John Anzalone et al. | NTRS


    Abort planning for Apollo missions

    Diamant, L. S. / Foggatt, C. E. / Gerbracht, R. J. et al. | NTRS | 1970


    Abort planning for Apollo missions

    DIAMANT, L. / FOGGATT, C. / GERBRACHT, R. et al. | AIAA | 1970


    Enabling Near-term Artemis Missions

    J. C. Mcphee | NTIS | 2022