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Evaluation of a Metallic Repair on a Rod-Stiffened Composite PanelA design and analysis of a repair concept applicable to a stiffened composite panel based on the pultruded rod stitched efficient unitized structure was recently completed.The damage scenario considered was a midbay-to-midbay saw-cut with a severed stiffener, flange, and skin. Advanced modeling techniques such as mesh-independent definition of compliant fasteners and elastic-plastic material properties for metal parts were used in the finite-element analysis supporting the design effort. A bolted metallic repair was selected so that it could be easily applied in the operational environment. The present work describes results obtained from a tension panel test conducted to validate both the repair concept and finite element analysis techniques used in the design effort. The test proved that the proposed repair concept is capable of sustaining load levels that are higher than those resulting from the current working stress allowables. This conclusion enables upward revision of the stress allowables that had been kept at an overly conservative level due to concerns associated with repairability of the panels. Correlation of test data with finite-element analysis results is also presented and assessed.
Document ID
20150001217
Acquisition Source
Langley Research Center
Document Type
Reprint (Version printed in journal)
External Source(s)
Authors
Przekop, Adam
(NASA Langley Research Center Hampton, VA, United States)
Jegley, Dawn C.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
February 3, 2015
Publication Date
February 26, 2014
Publication Information
Publication: Journal of Aircraft
Volume: 51
Issue: 3
Subject Category
Aircraft Design, Testing And Performance
Composite Materials
Structural Mechanics
Report/Patent Number
NF1676L-16663
Funding Number(s)
WBS: WBS 699959.02.22.07.01.01
Distribution Limits
Public
Copyright
Other

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