STP893

    Bolted Composite Repairs Subjected to Biaxial or Shear Loads

    Published: Jan 1986


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    Abstract

    The methodology to analyze bolted composite repairs subjected to biaxial or shear loads was developed. The methodology was incorporated into an existing McDonnell Aircraft Company (MCAIR) interactive computer program, BREPAIR, which was initially developed for uniaxial loading. The analysis determines bolt loads while accounting for hole clearances and determines patch and laminate strains for doubly symmetric finite regions where the damage is represented as a circular cutout. The analysis was verified by comparing predicted results to industry-recognized solutions for laminates containing circular holes (unrepaired), and to test results of an unrepaired and repaired shear panel. Results of this investigation verified that the methodology developed was a viable analytical tool for determining bolted repair designs for damaged laminates subjected to biaxial or shear loads.

    Keywords:

    composite materials, bolted repair, biaxial loading, circular damage, composite repair, finite plate, infinite plate, metal patch, orthotropic materials, repair methodology, shear loading


    Author Information:

    Bohlmann, RE
    Technical specialist, lead engineer, and branch chief, Technology, McDonnell Douglas Corporation, McDonnell Aircraft Company, St. Louis, MO

    Renieri, GD
    Technical specialist, lead engineer, and branch chief, Technology, McDonnell Douglas Corporation, McDonnell Aircraft Company, St. Louis, MO

    Riley, BL
    Technical specialist, lead engineer, and branch chief, Technology, McDonnell Douglas Corporation, McDonnell Aircraft Company, St. Louis, MO


    Paper ID: STP35340S

    Committee/Subcommittee: D30.04

    DOI: 10.1520/STP35340S


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