NDLI: Design and analysis of a stiffened composite fuselage panel (Document No: 19800023313)

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Design and analysis of a stiffened composite fuselage panel (Document No: 19800023313)

Content Provider	NASA Technical Reports Server (NTRS)
Author	Dickson, J. N. Biggers, S. B.
Copyright Year	1980
Description	The design and analysis of stiffened composite panel that is representative of the fuselage structure of existing wide bodied aircraft is discussed. 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	15319147
Page Count	52
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19800023313
Archival Resource Key	ark:/13960/t55f3mz67
Language	English
Publisher Date	1980-08-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Stress Analysis Aircraft Construction Materials Skin Structural Member Airframe Materials Compressive Strength Stiffening Laminates Composite Materials Rectangular Panels Fuselages Elastic Properties Buckling Tensile Properties 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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