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Nonlinear Analysis and Preliminary Testing Results of a Hybrid Wing Body Center Section Test ArticleA large test article was recently designed, analyzed, fabricated, and successfully tested up to the representative design ultimate loads to demonstrate that stiffened composite panels with through-the-thickness reinforcement are a viable option for the next generation large transport category aircraft, including non-conventional configurations such as the hybrid wing body. This paper focuses on finite element analysis and test data correlation of the hybrid wing body center section test article under mechanical, pressure and combined load conditions. Good agreement between predictive nonlinear finite element analysis and test data is found. Results indicate that a geometrically nonlinear analysis is needed to accurately capture the behavior of the non-circular pressurized and highly-stressed structure when the design approach permits local buckling.
Document ID
20160006275
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Przekop, Adam
(NASA Langley Research Center Hampton, VA, United States)
Jegley, Dawn C.
(NASA Langley Research Center Hampton, VA, United States)
Rouse, Marshall
(NASA Langley Research Center Hampton, VA, United States)
Lovejoy, Andrew E.
(NASA Langley Research Center Hampton, VA, United States)
Wu, Hsi-Yung T.
(Boeing Research and Technology Huntington Beach, CA, United States)
Date Acquired
May 16, 2016
Publication Date
September 28, 2015
Subject Category
Structural Mechanics
Report/Patent Number
NF1676L-20692
Meeting Information
Meeting: American Society for Composites Technical Conference
Location: East Lansing, MI
Country: United States
Start Date: September 28, 2015
End Date: September 30, 2015
Sponsors: American Society for Composites
Funding Number(s)
WBS: WBS 338881.02.22.07.01.01
Distribution Limits
Public
Copyright
Public Use Permitted.
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