The Orion vehicle is being designed to provide nominal crew transport to the lunar transportation stack in low Earth orbit, crew abort prior during transit to the moon, and crew return to Earth once lunar orbit is achieved. Design of guidance and navigation algorithms to perform maneuvers in support of these functions is dependent on the support provided by navigation infrastructure, the performance of the onboard GN&C system, and the choice of trajectory maneuver methodology for outbound and return mission phases. This paper documents the preliminary integrated analyses performed by members of the Orion Orbit GN&C System team investigating the navigation update accuracy of a modern equivalent to the Apollo era ground tracking network and the expected onboard dispersion and navigation errors during a lunar mission using a linear covariance error analysis technique.


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    Title :

    Orion Cislunar Guidance and Navigation


    Contributors:

    Conference:

    AIAA Guidance Navigation and Control Conference ; 2007 ; Hilton Head, SC, United States


    Publication date :

    2007-08-20


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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