Future NASA Artemis missions will require complex docking plans between the Orion capsule and Lunar Gateway that meet predetermined safety constraints while minimizing fuel usage and state uncertainty at rendezvous. In this paper, linear covariance analysis is applied to a first order relative form of Near-Rectilinear Halo Orbit dynamics to determine the nominal trajectories and state dispersions associated with various maneuver profiles in the Sun-referenced Local Vertical Local Horizontal reference frame of the lunar Gateway. These maneuver profiles are optimized using a particle swarm optimizer and direct search algorithm to find trajectories that satisfy approach corridor, free drift, velocity magnitude, under-burn, and maneuver transfer time safety constraints to 3-sigma certainty.


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    Title :

    Robust Trajectory Design for Rendezvous in a Near Rectilinear Halo Orbit


    Contributors:

    Conference:

    Rocky Mountain AAS GN&C Conference ; 2023 ; Breckenridge, CO, US


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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