A methodology for characterizing the thermo-tribomechanical response of an aircraft landing gear shock absorber is presented. Structural damage has been reported as a consequence of heat generated by high loads induced by rough runways on the shock absorber bearings and by the high sliding velocities of the shock absorber piston. Therefore, a model that reveals the characteristics of the thermal behavior, and identifies heat sources and sinks in the landing gear shock absorber is developed. The thermo-tribomechanical model framework is presented with representative development of each component. In addition, a sensitivity study of the maximum heat flux to variations of key input parameters is investigated. The numerical results indicate that the runway amplitude dominates the landing gear thermal response.


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    Titel :

    Aircraft Landing Gear Thermo-Tribomechanical Model and Sensitivity Study


    Beteiligte:
    Heirendt, Laurent (Autor:in) / Liu, Hugh H. T. (Autor:in) / Wang, Phillip (Autor:in)

    Erschienen in:

    Journal of Aircraft ; 51 , 2 ; 511-519


    Erscheinungsdatum :

    2014-02-21


    Format / Umfang :

    9 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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