Analytical Structural Efficiency Studies of Borsic/aluminum Compression Panels PDF Download
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Author: Robert R. McWithey
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Languages : en
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Author: Robert R. McWithey
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Robert R. McWithey
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Category : Plates (Engineering)
Languages : en
Pages : 36
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Category :
Languages : en
Pages : 586
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Category : Aeronautics
Languages : en
Pages : 784
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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
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Category : Science
Languages : en
Pages : 98
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Category : Astronautics
Languages : en
Pages : 466
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Category :
Languages : en
Pages : 72
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Category : Aeronautics
Languages : en
Pages : 736
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Author: Technology Reports Centre (Great Britain)
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Category :
Languages : en
Pages : 612
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723436673
Category :
Languages : en
Pages : 24
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Results of analytical and experimental studies are summarized for titanium, boron fiber reinforced aluminum matrix composite, Borsic fiber reinforced aluminum matrix composite, and titanium sheathed Borsic fiber reinforced aluminum matrix composite stiffened panels. The results indicate that stiffened panels with continuous joints (i.e., brazed, diffusion bonded or adhesive bonded joints) are more structurally efficient than geometrically similar panels with discrete joints (i.e., spotwelded or bolted joints). In addition, results for various types of fiber reinforced aluminum matrix stiffened panels indicate that titanium sheathed Borsic fiber reinforced aluminum matrix composite panels are the most structurally efficient. Analytical results are also presented for graphite fiber reinforced polyimide matrix composite stiffened panels and superplastically formed and diffusion bonded titanium sandwich panels. Mcwithey, R. R. and Royster, D. M. and Ko, W. L. Langley Research Center NASA-TP-1617, L-13525, NAS 1.60:1617
