The Integrated Adaptive Wing Technology Maturation wind-tunnel test is the culmination of a cooperative effort between NASA and Boeing to develop control techniques that can improve the performance and safety of higher aspect ratio flexible transport aircraft. The wind-tunnel test article, to be tested at the NASA Langley Research Center Transonic Dynamics Tunnel, is a semispan model of a modern transport configuration with an aspect ratio 13.5 wing based on the NASA Common Research Model. Multiobjective control laws have been developed targeting drag optimization, maneuver load alleviation, gust load alleviation, and modal suppression. In this paper, the integrated model design, active control system, and sensor suite will be presented, and pretest modeling and characterization activities will be described. A summary of the planned wind-tunnel test entries will provide an overview of the experimental approach and expected outcomes.


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    Titel :

    Overview of the Integrated Adaptive Wing Technology Maturation Wind-Tunnel Test Objectives


    Beteiligte:
    P. S. Heaney (Autor:in) / J. F. Quindlen (Autor:in)

    Erscheinungsdatum :

    2023


    Format / Umfang :

    35 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch