An autonomous spacecraft propellant-gauging system, the system including a propellant tank, one or more heating devices, at least one temperature sensor and a processor. The heating devices are used to heat up the propellant tank, and the temperature sensors sense the temperature of the propellant content of the propellant tank. The processor controls operations of the heating devices and the temperature sensor. The processor further executes an algorithm to automate gauging of the propellant content of the propellant tank based on a reduced order model (ROM) and a number of parameters, and reports out an estimate of the mass of the remaining propellant of the propellant tank.


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    Titel :

    Autonomous spacecraft propellant gauging


    Beteiligte:

    Erscheinungsdatum :

    06.12.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / G01F Messen des Volumens, des Durchflussvolumens, des Massendurchflusses oder des Füllstandes , MEASURING VOLUME, VOLUME FLOW, MASS FLOW, OR LIQUID LEVEL / G06N COMPUTER SYSTEMS BASED ON SPECIFIC COMPUTATIONAL MODELS , Rechnersysteme, basierend auf spezifischen Rechenmodellen



    Modeling of Spacecraft Propellant Gauging System

    Yendler, Boris / Ambrose, Jay / Collicott, Steven H. | SAE Technical Papers | 1999


    Error Analyses for Spacecraft Propellant Gauging Techniques

    Chang, Y. K. / Young, M. B. / Chae, Y. S. et al. | British Library Conference Proceedings | 1994


    Error analysis of spacecraft propellant gauging techniques

    Chang, Young / Chae, Yeon / Young, Marc et al. | AIAA | 1994