Recent advances in computational speed have made aircraft and spacecraft crash simulations using an explicit, nonlinear, transient-dynamic, finite element analysis code more feasible. This paper describes the development of a simple landing gear model, which accurately simulates the energy absorbed by the gear without adding substantial complexity to the model. For a crash model, the landing gear response is approximated with a spring where the force applied to the fuselage is computed in a user-written subroutine. Helicopter crash simulations using this approach are compared with previously acquired experimental data from a full-scale crash test of a composite helicopter.


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    Titel :

    Simulation of Aircraft Landing Gears with a Nonlinear Dynamic Finite Element Code


    Beteiligte:

    Kongress:

    Modeling and Simulation Technologies ; 2000 ; Denver, CO, United States


    Erscheinungsdatum :

    2000-01-01


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch




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