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Application of Interface Technology in Nonlinear Analysis of a Stitched/RFI Composite Wing Stub BoxA recently developed interface technology was successfully employed in the geometrically nonlinear analysis of a full-scale stitched/RFI composite wing box loaded in bending. The technology allows mismatched finite element models to be joined in a variationally consistent manner and reduces the modeling complexity by eliminating transition meshing. In the analysis, local finite element models of nonlinearly deformed wide bays of the wing box are refined without the need for transition meshing to the surrounding coarse mesh. The COMET-AR finite element code, which has the interface technology capability, was used to perform the analyses. The COMET-AR analysis is compared to both a NASTRAN analysis and to experimental data. The interface technology solution is shown to be in good agreement with both. The viability of interface technology for coupled global/local analysis of large scale aircraft structures is demonstrated.
Document ID
19970019491
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Wang, John T. (NASA Langley Research Center Hampton, VA United States)
Ransom, Jonathan B. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1997
Publication Information
Publisher: American inst. of Aeronautics and Astronautics
Subject Category
Structural Mechanics
Report/Patent Number
NASA-TM-112837
NAS 1.15:112837
AIAA Paper 97-1190
Meeting Information
Meeting: Structures, Structural Dynamics, and Materials
Country: United States
Start Date: April 7, 1997
End Date: April 11, 1997
Sponsors: American Helicopter Society, Inc., American Society for Composites, American Society of Mechanical Engineers, American Inst. of Aeronautics and Astronautics, American Society of Civil Engineers
Accession Number
97N21204
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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