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Design and evaluation of a bolted joint for a discrete carbon-epoxy rod-reinforced hat sectionThe use of prefabricated pultruded carbon-epoxy rods has reduced the manufacturing complexity and costs of stiffened composite panels while increasing the damage tolerance of the panels. However, repairability of these highly efficient discrete stiffeners has been a concern. Design, analysis, and test results are presented in this paper for a bolted-joint repair for the pultruded rod concept that is capable of efficiently transferring axial loads in a hat-section stiffener on the upper skin segment of a heavily loaded aircraft wing component. A tension and a compression joint design were evaluated. The tension joint design achieved approximately 1.0% strain in the carbon-epoxy rod-reinforced hat-section and failed in a metal fitting at 166% of the design ultimate load. The compression joint design failed in the carbon-epoxy rod-reinforced hat-section test specimen area at approximately 0.7% strain and at 110% of the design ultimate load. This strain level of 0.7% in compression is similar to the failure strain observed in previously reported carbon-epoxy rod-reinforced hat-section column tests.
Document ID
19960041468
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Rousseau, Carl Q. (Bell Helicopter Co. Fort Worth, TX United States)
Baker, Donald J. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
August 29, 1996
Subject Category
Mechanical Engineering
Report/Patent Number
NASA-TM-111622
NAS 1.15:111622
Meeting Information
Meeting: DoD/NASA/FAA Conference on Fibrous Composites in Structural Design.
Location: Fort Worth, TX
Country: United States
Start Date: August 26, 1996
End Date: August 29, 1996
Sponsors: Federal Aviation Administration, NASA Headquarters, Department of Defense
Accession Number
96N31411
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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