Artemis II Inertial Sensor Failure & Abort Condition Study

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 studie...

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Hauptverfasser:	Hoen, Nicholas Harrison, Leggett, Jared O, Anzalone, Evan John, Park, Thomas Reed
Format:	Tagungsbericht
Sprache:	eng
Schlagworte:	Spacecraft Design, Testing And Performance
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creator	Hoen, Nicholas Harrison Leggett, Jared O Anzalone, Evan John Park, Thomas Reed
description	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.
format	Conference Proceeding
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subjects	Spacecraft Design, Testing And Performance
title	Artemis II Inertial Sensor Failure & Abort Condition Study
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