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Structural testing of the technology integration box beamA full scale section of a transport aircraft wing box was designed, analyzed, fabricated, and tested. The wing box section, which was called the technology integration box beam, contained blade stiffened covers and T-stiffened channel spars constructed using graphite-epoxy materials. Covers, spars, and the aluminum ribs were assembled using mechanical fasteners. The box beam was statically tested for several loading conditions to verify the stiffness and strength characteristics of the composite wing design. Failure of the box beam occurred at 125 pct. of design limit load during the combined unbending and torsion ultimate design load test. It appears that the failure initiated at a stiffener runout location in the upper cover which resulted in rupture of the upper cover and portions of both spars.
Document ID
19940028619
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Griffin, C. F.
(Lockheed Aeronautical Systems Co. Marietta, GA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1992
Publication Information
Publication: NASA. Langley Research Center, Second NASA Advanced Composites Technology Conference
Subject Category
Composite Materials
Accession Number
94N33125
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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