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Testing and Analysis of a Composite Non-Cylindrical Aircraft Fuselage Structure The Environmentally Responsible Aviation Project aimed to develop aircraft technologies enabling significant fuel burn and community noise reductions. Small incremental changes to the conventional metallic alloy-based 'tube and wing' configuration were not sufficient to achieve the desired metrics. One airframe concept identified by the project as having the potential to dramatically improve aircraft performance was a composite-based hybrid wing body configuration. Such a concept, however, presented inherent challenges stemming from, among other factors, the necessity to transfer wing loads through the entire center fuselage section which accommodates a pressurized cabin confined by flat or nearly flat panels. This paper discusses a finite element analysis and the testing of a large-scale hybrid wing body center section structure developed and constructed to demonstrate that the Pultruded Rod Stitched Efficient Unitized Structure concept can meet these challenging demands of the next generation airframes. Part II of the paper considers the final test to failure of the test article in the presence of an intentionally inflicted severe discrete source damage under the wing up-bending loading condition. Finite element analysis results are compared with measurements acquired during the test and demonstrate that the hybrid wing body test article was able to redistribute and support the required design loads in a severely damaged condition.
Document ID
20160007728
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)
Lovejoy, Andrew E.
(NASA Langley Research Center Hampton, VA, United States)
Rouse, Marshall
(NASA Langley Research Center Hampton, VA, United States)
Wu, Hsi-Yung T.
(Boeing Co. Huntington Beach, CA, United States)
Date Acquired
June 20, 2016
Publication Date
January 4, 2016
Subject Category
Structural Mechanics
Report/Patent Number
NF1676L-21714
Meeting Information
Meeting: AIAA SciTech 2016
Location: San Diego, CA
Country: United States
Start Date: January 4, 2016
End Date: January 8, 2016
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 338881.02.22.07.01.01
Distribution Limits
Public
Copyright
Public Use Permitted.
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