Design optimization of aircraft engine-mount systems for vibration isolation is presented. The engine is modeld as a rigid body connected to a flexible base representing the nacelle. The base is modeled with mass and stiffness matrices and structural damping using finite element modeling. The mounts are modeled as three-dimensional springs with hysteresis damping. The objective is to select the stiffness coefficients and orientation angles of the indiviudal mounts to minimize the transmitted forces from the engine to the base. Meanwhile, the mounts have to be stiff enough not allowing engine deflection to exceed its limits under static and low frequency loadings. It is shown that with an optimal system the transmitted forces may be reduced significantly particularly when mount orientation angles are also treated as design variables. The optimization problems are solved using a Constraint Variable Metric approach. The closed form derivatives of the engine vibrational amplitudes with respect to design variables are derived in order to achieve a more efffective optimization search technique.


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    Title :

    Design optimization of aircraft engine-mount systems


    Additional title:

    Optimierung der Konstruktion von Fundamenten für die Schwingungsdämpfung von Flugtriebwerken


    Contributors:


    Publication date :

    1993


    Size :

    6 Seiten, 9 Bilder, 2 Tabellen, 8 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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