Systems and methods for attitude fault detection based on integrated GNSS/inertial hybrid filter residuals are provided. In one embodiment, a fault detection system for aircraft attitude measurement system comprises: a sensor monitor coupled to a first inertial measurement unit, the sensor monitor comprising: a navigation error model for the first inertial measurement unit, the model configured to model a plurality of error states including at least an attitude error state vector, an velocity error state vector, and a position error state vector determined from data generated by the first inertial measurement unit; and a propagator-estimator configured to propagate and update error states based on GNSS data; and a residual evaluator configured to input measurement error residual values generated by the propagator-estimator, wherein the residual evaluator outputs an alert signal when the measurement error residual values exceed a threshold.


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    Titel :

    SYSTEMS AND METHODS FOR ATTITUDE FAULT DETECTION BASED ON INTEGRATED GNSS-INERTIAL HYBRID FILTER RESIDUALS


    Weitere Titelangaben:

    SYSTEME UND VERFAHREN ZUR LAGEFEHLERDETEKTION AUF GRUNDLAGE VON RESTEN INTEGRIERTER GNSS- / INTERTIALHYBRIDFILTER
    SYSTÈMES ET PROCÉDÉS DE DÉTECTION DE DÉFAUT D'ATTITUDE SUR LA BASE DE RESIDUS DE FILTRE HYBRIDE GNSS/INERTIEL


    Beteiligte:

    Erscheinungsdatum :

    2021-02-24


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    G01C Messen von Entfernungen, Höhen, Neigungen oder Richtungen , MEASURING DISTANCES, LEVELS OR BEARINGS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / G07C TIME OR ATTENDANCE REGISTERS , Zeit- oder Anwesenheitskontrollgeräte



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