An approach to simulate the characteristics of the payload/orbiter interfaces for the payload modal survey was developed. The flexure designed for this approach is required to provide adequate stiffness separation in the free and constrained interface degrees of freedom to closely resemble the flight boundary condition. Payloads will behave linearly and demonstrate similar modal effective mass distribution and load path as the flight if the flexure fixture is used for the payload modal survey. The potential non-linearities caused by the trunnion slippage during the conventional fixed base modal survey may be eliminated. Consequently, the effort to correlate the test and analysis models can be significantly reduced. An example is given to illustrate the selection and the sensitivity of the flexure stiffness. The advantages of using flexure fixtures for the modal survey and for the analytical model verification are also demonstrated.


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    Titel :

    Simulating flight boundary conditions for orbiter payload modal survey


    Beteiligte:
    Chung, Y. T. (Autor:in) / Sernaker, M. L. (Autor:in) / Peebles, J. H. (Autor:in)


    Erscheinungsdatum :

    1993-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    SIMULATING FLIGHT BOUNDARY CONDITIONS FOR ORBITER PAYLOAD MODAL SURVEY

    SERNAKER, M. / PEEBLES, J. / CHUNG, Y. | AIAA | 1993


    Orbiter Boundary Layer Stability Analysis at Flight Entry Conditions

    Johnson, Heath / Candler, Graham | AIAA | 2010




    Orbiter Entry Boundary Layer Flight Testing

    Campbell, Charles / Garske, Michael / Kinder, Jerry et al. | AIAA | 2008