Artemis II Inertial Sensor Failure & Abort Condition Study

Nicholas Harrison Hoen; Jared O Leggett; Evan John Anzalone; Thomas Reed Park

NASA NTRS · 20205006557

Artemis II Inertial Sensor Failure & Abort Condition Study

Nicholas Harrison Hoen·Jared O Leggett·Evan John Anzalone·Thomas Reed Park

Abstract

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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BibTeX RIS

Nicholas Harrison Hoen, Jared O Leggett, Evan John Anzalone, Thomas Reed Park. Artemis II Inertial Sensor Failure & Abort Condition Study. https://ntrs.nasa.gov/citations/20205006557

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