Telemetry data from three 445 N engine burns of the Cassini spacecraft are used to characterize the high-g slosh characteristics of bipropellants in cylindrical tanks with spherical end domes. Comparisons between flight data and theoretical results indicate that high-g clean tank slosh frequency and high-g sector mode frequency could be predicted with errors of 3–5%. However, at lower tanks’ fill fractions of <35%, when most of the propellants reside in the spherical end domes of the tanks, the prediction errors deteriorated to >5%. Also, high-g full-tank slosh mode in a tank with an eight-panel propellant management device could be modeled using an annular cylindrical tank. Again, prediction error of full-tank slosh frequency degraded with decreasing fill fractions. Based on these results, the high-g sector and full-tank propellant slosh frequencies could be well predicted using simple analytical techniques before these predictions are refined by liquid slosh computer modeling tools. A set of small-amplitude oscillatory motions of the spacecraft attitude was detected during 13 science observations conducted in 2007–2008. Their frequencies matched well the low-g slosh frequency predicted analytically for uncompartmented tank. The root cause and analytical prediction of the observed spacecraft oscillatory motion in low-g condition is an interesting topic for future research.


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    Titel :

    In-Flight Characterization of the Cassini Spacecraft Propellant Slosh Modes


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2017




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :

    Klassifikation :

    Lokalklassifikation TIB:    770/7040
    BKL:    55.60 Raumfahrttechnik