Propellant tank slosh damping models for launch vehicle ascent analysis typically employ linear models for bare-wall damping, or assume a single, low-amplitude wave height for baffled configurations. A higher fidelity damping model would incorporate nonlinear effects to increase damping as slosh wave amplitude increases. This paper provides an overview of a technical assessment performed by the NASA Engineering and Safety Center (NESC) to evaluate lateral slosh damping as a function of lateral force (or wave) amplitude for multiple tank configurations. The increased fidelity of nonlinear slosh damping models, if leveraged, has the potential to reduce over-conservatism associated with the use of linear slosh damping models. This can provide design flexibility to enhance launch vehicle flight control performance, reduce baffle design requirements and/or increase robustness in targeted areas such as control-structure interaction during ascent.


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    Titel :

    Nonlinear Slosh Damping Testing and Analysis for Launch Vehicle Propellant Tanks


    Beteiligte:
    Tannen S VanZwieten (Autor:in) / Jacob M Brodnick (Autor:in) / Shane Reese (Autor:in) / Michael Ruth (Autor:in) / Brandon Marsell (Autor:in) / Russel A Parks (Autor:in)

    Kongress:

    AIAA SciTech Exhibition and Forum ; 2020 ; Orlando, FL, US



    Erscheinungsdatum :

    2020-01-06




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch