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Composite fuselage shell structures research at NASA Langley Research CenterFuselage structures for transport aircraft represent a large portion of both the weight and cost of these aircraft primary structures. Composite materials offer the potential for reducing both the weight and cost of these structures, but only limited studies of the response and failure of composite fuselage structures have been conducted. The research is described which is being conducted and planned at NASA Langley to understand the critical behavior of composite fuselage structures and to validate the structural mechanics methodology being developed for stiffened composite fuselage shell structure subjected to combined internal pressure and mechanical loads. Stiffened shell and curved stiffened panel designs are currently being developed and analyzed, and these designs will be fabricated and then tested to study critical fuselage behavior and to validate structural analysis and design methodology. The research includes studies of the effects of combined internal pressure and mechanical loads on nonlinear stiffened panel and shell behavior, the effects of cutouts and other gradient producing discontinuities on composite shell response, and the effects of local damage on pressure containment and residual strength. Scaling laws are being developed that relate full scale and subscale behavior of composite fuselage shells.
Document ID
19940028618
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Starnes, James H., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Shuart, Mark J.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1992
Publication Information
Publication: Second NASA Advanced Composites Technology Conference
Subject Category
Composite Materials
Accession Number
94N33124
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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