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Application study of filamentary composites in a commercial jet aircraft fuselageA study of applications of filamentary composite materials to aircraft fuselage structure was performed. General design criteria were established and material studies conducted using the 727-200 forebody as the primary structural component. Three design approaches to the use of composites were investigated: uniaxial reinforcement of metal structure, uniaxial and biaxial reinforcement of metal structure, and an all-composite design. Materials application studies for all three concepts were conducted on fuselage shell panels, keel beam, floor beams, floor panels, body frames, fail-safe straps, and window frames. Cost benefit studies were conducted and developmental program costs estimated. On the basis of weight savings, cost effectiveness, developmental program costs, and potential for early application on commercial aircraft, the unaxial design is recommended for a 5-year flight service evaluation program.
Document ID
19720025911
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Johnson, R. W. (Boeing Co. Seattle, WA, United States)
June, R. R. (Boeing Co. Seattle, WA, United States)
Date Acquired
September 2, 2013
Publication Date
June 1, 1972
Subject Category
Materials, Nonmetallic
Report/Patent Number
NASA-CR-112110
Accession Number
72N33561
Funding Number(s)
CONTRACT_GRANT: NAS1-11162
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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