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Study of advanced composite structural design concepts for an arrow wing supersonic cruise configurationBased on estimated graphite and boron fiber properties, allowable stresses and strains were established for advanced composite materials. Stiffened panel and conventional sandwich panel concepts were designed and analyzed, using graphite/polyimide and boron/polyimide materials. The conventional sandwich panel was elected as the structural concept for the modified wing structure. Upper and lower surface panels of the arrow wing structure were then redesigned, using high strength graphite/polyimide sandwich panels, retaining the titanium spars and ribs from the prior study. The ATLAS integrated analysis and design system was used for stress analysis and automated resizing of surface panels. Flutter analysis of the hybrid structure showed a significant decrease in flutter speed relative to the titanium wing design. The flutter speed was increased to that of the titanium design by selective increase in laminate thickness and by using graphite fibers with properties intermediate between high strength and high modulus values.
Document ID
19780012173
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Turner, M. J. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Grande, D. L. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1978
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
D6-42438-5
NASA-CR-2825
Accession Number
78N20116
Funding Number(s)
CONTRACT_GRANT: NAS1-12287
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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