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Testing and Analysis Validation of a Metallic Repair Applied to a PRSEUS Tension 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 utilized 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
20130012900
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Przekop, Adam (Analytical Services and Materials, Inc. Hampton, VA, United States)
Jegley, Dawn C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 27, 2013
Publication Date
April 8, 2013
Subject Category
Structural Mechanics
Report/Patent Number
NF1676L-15210
AIAA Paper 2013-1735
Meeting Information
Meeting: 54th AIAA/ASME/ASCE/AHS/ASC, Structures, Structural Dynamics, and Materials Conference
Location: Boston, MA
Country: United States
Start Date: April 8, 2013
End Date: April 11, 2013
Sponsors: American Helicopter Society, Inc., American Society of Civil Engineers, American Society of Mechanical Engineers, American Inst. of Aeronautics and Astronautics, American Society for Composites
Funding Number(s)
WBS: WBS 699959.02.08.07.02.02
Distribution Limits
Public
Copyright
Public Use Permitted.

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