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Test and Analyses of a Composite Multi-Bay Fuselage Panel Under Uni-Axial CompressionA composite panel containing three stringers and two frames cut from a vacuum-assisted resin transfer molded (VaRTM) stitched fuselage article was tested under uni-axial compression loading. The stringers and frames divided the panel into six bays with two columns of three bays each along the compressive loading direction. The two frames were supported at the ends with pins to restrict the out-of-plane translation. The free edges of the panel were constrained by knife-edges. The panel was modeled with shell finite elements and analyzed with ABAQUS nonlinear solver. The nonlinear predictions were compared with the test results in out-of-plane displacements, back-to-back surface strains on stringer flanges and back-to-back surface strains at the centers of the skin-bays. The analysis predictions were in good agreement with the test data up to post-buckling.
Document ID
20040058115
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Li, Jian
(Boeing Co. Mesa, AZ, United States)
Baker, Donald J.
(Army Research Lab. Hampton, VA, United States)
Date Acquired
August 21, 2013
Publication Date
March 10, 2004
Subject Category
Structural Mechanics
Report/Patent Number
AIAA Paper 2004-2056
Meeting Information
Meeting: 45th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
Location: Palm Springs, CA
Country: United States
Start Date: April 19, 2004
End Date: April 22, 2004
Sponsors: American Inst. of Aeronautics and Astronautics, American Society of Mechanical Engineers, American Society for Composites, American Society of Civil Engineers, American Helicopter Society, Inc.
Funding Number(s)
OTHER: 762-55-LE
CONTRACT_GRANT: DAAH10-02-2-0002
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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