Structural design and material usage of airframe and dynamic components are investigated with regard to reducing vulnerability from small arms fire and improving crash-worthiness; design flight operating conditions and relationship to critical structural loadings are investigated; it is found possible to reduce flight loadings to 50% static level for airframe, 85% fatigue level for main rotor, and to 50% fatigue level for control system; use of material having high fracture toughness can appreciably improve damaged strength so that order of 70% residual strength is attained for critical areas; schematic structural diagram of these areas and design features that can reduce vulnerability and improve crashworthiness. (08697)


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    Title :

    Vulnerability and crashworthiness in design of rotary wing vehicle structures


    Additional title:

    SAE Paper


    Contributors:
    Rich, M.J. (author)

    Conference:

    SAE Meeting ; 1968 Military


    Published in:

    Publication date :

    1968


    Size :

    20 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English


    Keywords :




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