This paper presents the overall trajectory design and optimization process for NASA’s Artemis I mission to send an uncrewed Orion vehicle to a lunar Distant Retrograde Orbit (DRO). The on-orbit trajectory begins at the Space Launch System (SLS) core separation and ends at the Orion service module Earth Entry Interface (EI) point. The details of the trajectory optimization process are presented, including design of nominal and extended mission options, launch windows, and abort options. Novel design techniques are also discussed to account for contingencies, such as using auxiliary thrusters to protect against main engine failure and applying trajectory shaping to mitigate or reduce eclipse durations.


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    Title :

    Artemis I Trajectory Design and Optimization



    Conference:

    2020 AAS/AIAA Astrodynamics Specialist Conference ; 2020 ; Virtual, US


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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