Recent catastrophic airframe failures and near failures has led to a strong impetus to design new airframe primary structure to damage tolerant criteria requirements. Generally, this reflects a recognition that inadvertent or inherent flaws can be introduced in manufacturing of primary aircraft components that cannot be detected by existing NDI techniques. The current version of this criteria is the proposed revision to MIL-A-008866A, dated 18 August 1972, Revision 'D'. This version of the damage tolerant criteria was considered a design requirement by Northrop in this Advanced Metallic Structures/Advanced Development Program. Information regarding the impact this criteria could have on a thin, high load factor, aircraft wing is very limited. Of particular concern are the effects deviations in nominal analysis variables can have on crack growth service life and damage tolerant design stress predictions. This damage tolerant criteria sensitivity study investigates these effects on an aircraft designed prior to the existence of these requirements. (Modified author abstract)


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    Title :

    Advanced Metallic Structure: Air Superiority Fighter Wing Design for Improved Cost, Weight and Integrity. Volume II. Criteria Sensitivity Study


    Contributors:
    F. A. Figge (author)

    Publication date :

    1973


    Size :

    155 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English