This paper introduces an integrated approach for flexible-aircraft time-domain aeroelastic simulation and controller design suitable for wake encounter situations. The dynamic response of the vehicle, which may be subject to large wing deformations in trimmed flight, is described by a geometrically nonlinear finite-element model. The aerodynamics are modeled using the unsteady vortex lattice method and include the arbitrary time-domain downwash distributions of a wake encounter. A consistent linearization in the structural degrees of freedom enables the use of balancing methods to reduce the problem size while retaining the nonlinear terms in the rigid-body equations. Numerical studies on a high-altitude, long-endurance aircraft demonstrate the reduced-order modeling approach for load calculations in wake vortex encounters over a large parameter space. Closed-loop results finally explore the potential of combining feedforward/feedback H control and distributed control surfaces to obtain significant load reductions.


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    Title :

    Dynamic Load Alleviation in Wake Vortex Encounters


    Contributors:

    Published in:

    Publication date :

    2016-01-08


    Size :

    13 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    Dynamic Load Alleviation in Wake Vortex Encounters

    Hesse, Henrik | Online Contents | 2016


    Wake vortex alleviation

    GREENE, G. | AIAA | 1981


    On wake vortex alleviation

    Roberts, L. | NTRS | 1975


    Wake-Vortex Alleviation Flowfield Studies

    Durston, D.A. | Online Contents | 2005


    Wake Vortex Alleviation Flow Field Studies

    Donald Durston / Stephen Walker / David Driver et al. | AIAA | 2005