This Paper presents an efficient algorithm for the nonlinear aeroelastic trim analysis of very flexible aircraft described by detailed models. The algorithm is based on a novel inertia relief technique for large displacements and is applicable to fluid–structure iteration frameworks coupling generic structural and aerodynamic solvers, including high-fidelity commercial solvers. The methodology is tested on a low-order model of the University of Michigan’s X-HALE experimental vehicle in order to compare to reference results for a typical steady rectilinear flight condition. Nonlinear aeroelastic trim analyses conducted at different flight speeds show that the proposed approach gives a smooth and fast convergence to the trim solution, which makes it suitable for high-fidelity aeroelastic design of very flexible aircraft.


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    Title :

    Nonlinear Aeroelastic Trim of Very Flexible Aircraft Described by Detailed Models



    Published in:

    Journal of Aircraft ; 55 , 6 ; 2338-2346


    Publication date :

    2018-08-13


    Size :

    9 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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