This paper presented the numerical and experimental activities related to the design and manufacturing of a wind-tunnel wing model, equipped with four control surfaces, to be installed in the XDIA aeroelastic demonstrator. The design of the wing model is based on a constant Froude scaling with respect to a reference full-scale target aircraft. Each control surface is driven by an electric motor embedded into the central part of the wing. The aeroservoelastic model was tuned on the basis of wind-tunnel results, where both frequency response functions and wing loads were measured by means of accelerometers embedded into the model and by using an aerodynamic balance used to clamp the root of the wing main spar. The experimentally correlated aeroservoelastic model was used to predict the flutter behavior of the wing and to design the control system for modal control purpose. A generalization of the original ILAF control architecture was developed and implemented, where control forces are not proportional to local velocity but to modal velocity. In particular, two mode shapes of the wing model were initially controlled, first bending and torsion modes. The ILAF control methodology demonstrated a good capability of shaping wing modes already at 30 m/s (and up to 42 m/s, which, by chance, is the maximum speed tested), with good performances related both to bending and torsion. Indeed, a reduction of 10 and 12 dB on the acceleration peak related to first bending and torsion modes, respectively, was experimentally verified. The adopted control architecture appears as noticeably robust: even by switching off the single control surfaces the capability to damp first bending and torsion modes remains remarkable, even if the best performance is obtained by using all four control surfaces. Finally, from the user point of view, the experimental activity demonstrated that ILAF control architecture can be easily tuned, using a limited number of control gains having a clear physical meaning. Future developments will include at first a complete characterization of the modal control here proposed for the whole range of wind-tunnel speeds, then an extension of the aeroservoelastic model so to take into account in a more precise way the presence offree play, especially connected with actuators gear heads, and their effects on control performances. Finally, the modal control system here presented will be coupled to a roll maneuver enhancement control system, now under development, so to be able to optimize the aircraft roll performances in terms of both static and dynamic structural requirements, taking advantage of the presence of redundant control surfaces.


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    Title :

    Active aeroelastic control over a multisurface wing: modeling and wind-tunnel testing


    Additional title:

    Aktive aeroelastische Steuerung über einen Multi-Oberflächen-Flügel: Modellierung und Windkanaltest


    Contributors:
    Gaspari, A. de (author) / Ricci, S. (author) / Riccobene, L. (author) / Scotti, A. (author)

    Published in:

    AIAA Journal ; 47 , 9 ; 1995-2010


    Publication date :

    2009


    Size :

    16 Seiten, 24 Bilder, 6 Tabellen, 34 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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