A methodology is outlined for optimization of airframe structures under dynamic constraints to maximize service life of specified fatigue-critical components. For practical airframe structures, this methodology describes the development of sensitivity analysis and computational procedures for constraints on the steady-state dynamic response displacements and stresses. Strain energy consideration is used for selection of structural members for modification. Development of a design model and its relation to an analysis model, as well as ways to reduce the dimensionality of the problem via approximation concepts, are described. This methodology is demonstrated using an elastic stick model for the MH-53J helicopter to show service life improvements of the hinge fold region.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Airframe Structural Optimization for Maximum Fatigue Life


    Contributors:

    Conference:

    The Third Air Force/NASA Symposium on Recent Advances in Multidisciplinary Analysis and Optimization ; 1990 ; San Francisco, CA, US



    Publication date :

    1990-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    Calendar Fatigue Life of Airframe Materials

    Wang, B. / Fan, J. / Sun, Q. et al. | British Library Conference Proceedings | 2000


    Rotorcraft airframe structural optimization for combined vibration and fatigue constraints

    Sareen, Ashish K. / Schrage, Daniel P. / Murthy, T. S. | NTRS | 1991


    Fatigue Life Enhancement for Metallic Airframe Materials

    Molent, L. / Barter, S. A. | Springer Verlag | 2016


    Outlook on airframe fatigue

    Tye, W. | Engineering Index Backfile | 1955