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Nonlinear Finite Element Analysis of a Composite Non-Cylindrical Pressurized Aircraft Fuselage StructureThe Environmentally Responsible Aviation Project aims 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 are not sufficient to achieve the desired metrics. One of the airframe concepts that might dramatically improve aircraft performance is a composite-based hybrid wing body configuration. Such a concept, however, presents 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 nonlinear finite element analysis of a large-scale test article being developed to demonstrate that the Pultruded Rod Stitched Efficient Unitized Structure concept can meet these challenging demands of the next generation airframes. There are specific reasons why geometrically nonlinear analysis may be warranted for the hybrid wing body flat panel structure. In general, for sufficiently high internal pressure and/or mechanical loading, energy related to the in-plane strain may become significant relative to the bending strain energy, particularly in thin-walled areas such as the minimum gage skin extensively used in the structure under analysis. To account for this effect, a geometrically nonlinear strain-displacement relationship is needed to properly couple large out-of-plane and in-plane deformations. Depending on the loading, this nonlinear coupling mechanism manifests itself in a distinct manner in compression- and tension-dominated sections of the structure. Under significant compression, nonlinear analysis is needed to accurately predict loss of stability and postbuckled deformation. Under significant tension, the nonlinear effects account for suppression of the out-of-plane deformation due to in-plane stretching. By comparing the present results with the previously published preliminary linear analysis, it is demonstrated in the present paper that neglecting nonlinear effects for the structure and loads of interest can lead to appreciable loss in analysis fidelity.
Document ID
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Przekop, Adam
(Analytical Mechanics Associates, Inc. Hampton, VA, United States)
Wu, Hsi-Yung T.
(Boeing Research and Technology Huntington Beach, CA, United States)
Shaw, Peter
(Boeing Research and Technology Huntington Beach, CA, United States)
Date Acquired
June 11, 2014
Publication Date
January 13, 2014
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA Paper-2014-1064
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
Location: National Harbor, MD
Country: United States
Start Date: January 13, 2014
End Date: January 17, 2014
Sponsors: American Society of Civil Engineers, American Inst. of Aeronautics and Astronautics, American Society for Composites, American Society of Mechanical Engineers, American Helicopter Society, Inc.
Funding Number(s)
WBS: WBS 699959.
Distribution Limits
Public Use Permitted.
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