Risk reduction is the objective of the X-57 Maxwell aeroelasticity team. The X-57, NASA’s experimental electric propulsion aircraft, has a long thin wing with primary propulsion systems located at the wing tips and high lift motors distributed along the span. Many of the classical aeroelastic concerns associated with such a configuration were addressed through early design decisions. The as-designed intermediate flight vehicle configurations show flutter mechanisms associated with flexible models of control surface systems –the stabilator, flaps and ailerons. Improvements to the analytical models, based on ground test data and project decisions about flight operations, show improved prospects of the vehicle being aeroelastically stable throughout the flight envelope. On-going ground testing and further analyses will lend credibility to the flutter predictions and vehicle safety.


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    Titel :

    Status Report on Aeroelasticity in the Vehicle Development for X-57 Maxwell


    Beteiligte:
    J. Heeg (Autor:in) / B. K. Stanford (Autor:in) / C. D. Wieseman (Autor:in) / S. J. Massey (Autor:in) / J. Moore (Autor:in) / R. Truax (Autor:in) / K. Miller (Autor:in)

    Erscheinungsdatum :

    2018


    Format / Umfang :

    18 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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    Status Report on Aeroelasticity in the Vehicle Development for X-57 Maxwell

    Heeg, Jennifer / Stanford, Bret / Wieseman, Carol D. et al. | AIAA | 2018


    Status Report on Aeroelasticity in the Vehicle Development for X-57 Maxwell (AIAA 2018-3487)

    Heeg, Jennifer / Stanford, Bret / Wieseman, Carol D. et al. | British Library Conference Proceedings | 2018



    Aeroelasticity Supplement Report

    Batt, J. R. / Bilz, J. L. | NTRS | 1959