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Design and Analysis of a Stiffened Composite Fuselage PanelA stiffened composite panel has been designed that is representative of the fuselage structure of existing wide bodied aircraft. The panel is a minimum weight design, based on the current level of technology and realistic loads and criteria. Several different stiffener configurations were investigated in the optimization process. The final configuration is an all graphite epoxy J-stiffened design in which the skin between adjacent stiffeners is permitted to buckle under design loads. Fail-safe concepts typically employed in metallic fuselage structure have been incorporated in the design. A conservative approach has been used with regard to structural details such as skin frame and stringer frame attachments and other areas where sufficient design data was not available.
Document ID
19960025808
Acquisition Source
Langley Research Center
Document Type
Contractor Report (CR)
Authors
Dickson, J. N. (Lockheed-Georgia Co. Marietta, GA United States)
Biggers, S. B. (Lockheed-Georgia Co. Marietta, GA United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1980
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.26:159302
AD-A301599
LG80ER0137
NASA-CR-159302
Accession Number
96N71579
Funding Number(s)
CONTRACT_GRANT: NAS1-15949
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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