SYMPOSIA PAPER Published: 01 January 1986
STP35340S

Bolted Composite Repairs Subjected to Biaxial or Shear Loads

Source

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.

Author Information

Bohlmann, RE
Technology, McDonnell Douglas Corporation, McDonnell Aircraft Company, St. Louis, MO
Renieri, GD
Technology, McDonnell Douglas Corporation, McDonnell Aircraft Company, St. Louis, MO
Riley, BL
Technology, McDonnell Douglas Corporation, McDonnell Aircraft Company, St. Louis, MO
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Details
Developed by Committee: D30
Pages: 34–47
DOI: 10.1520/STP35340S
ISBN-EB: 978-0-8031-4963-2
ISBN-13: 978-0-8031-0447-1