Given Artemis II as the first crewed lunar mission in decades, significant effort is directed towards understanding Space Launch System (SLS) response to failures of the three inertial sensors: two Ring-Laser Gyro Assemblies (RGAs) and the Redundant Inertial Navigation Unit (RINU). Parametric studies identify Loss of Mission (LOM) or Loss of Crew (LOC) sensitive mission phases. Fault Detection & Isolation (FDI) algorithms’ thresholds’ performance is assessed with respect to detecting LOM or LOC causing sensor failures. Monte Carlo studies are performed targeting specific trajectory phases for insight into re-optimizing FDI thresholds and improving knowledge of SLS sensor failure response statistics.


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    Title :

    Artemis II Inertial Sensor Failure & Abort Condition Study


    Contributors:

    Conference:

    44th Annual AAS Guidance, Navigation, and Control Conference ; 2021 ; Breckenridge, US


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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