NDLI: Study of advanced composite structural design concepts for an arrow wing supersonic cruise configuration

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Study of advanced composite structural design concepts for an arrow wing supersonic cruise configuration

Content Provider	NASA Technical Reports Server (NTRS)
Author	Grande, D. L. Turner, M. J.
Copyright Year	1978
Description	Based 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.
File Size	6412293
Page Count	124
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19780012173
Archival Resource Key	ark:/13960/t10p5vm9m
Language	English
Publisher Date	1978-04-01
Access Restriction	Open
Subject Keyword	Aircraft Design, Testing And Performance Structural Design Arrow Wings Composite Materials Aerodynamic Configurations Supersonic Cruise Aircraft Research Flutter Analysis Structural Analysis 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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