NDLI: Design and analysis of a stiffened composite fuselage panel

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Design and analysis of a stiffened composite fuselage panel

Content Provider	NASA Technical Reports Server (NTRS)
Author	Dickson, J. N. Biggers, S. B.
Copyright Year	1980
Description	A 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.
File Size	1749802
Page Count	54
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19960025808
Archival Resource Key	ark:/13960/t2x39kz8m
Language	English
Publisher Date	1980-08-01
Access Restriction	Open
Subject Keyword	Aircraft Design, Testing And Performance Panels Rigid Structures Aircraft Construction Materials Skin Structural Member Graphite-epoxy Composites Fuselages Stiffening Composite Structures Buckling Aircraft Structures Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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