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Compressive strength of titanium alloy skin-stringer panels selectively reinforced with boron-aluminum composite.Description of a method of selectively reinforcing conventional titanium airframe structure with unidirectional boron-aluminum composite attached by brazing which has been successfully demonstrated based on compression tests of short skin-stringer panels. Improvements in structural performance exceeded 25% on an equivalent weight basis over the range from room temperature to 800 F, both in terms of initial buckling and maximum strengths. Room-temperature performance was not affected by prior exposure at 600 F for 1000 hours in air, or by 400 cycles between -65 and 600 F. The experimental results were generally predictable on the basis of existing analytical procedures. No evidence of failure was observed in the braze bond between the boron-aluminum composite and the titanium alloy.
Document ID
19720041721
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Herring, H. W.
(NASA Langley Research Center Hampton, Va., United States)
Carri, R. L.
(Grumman Aerospace Corp. Bethpage, N.Y., United States)
Date Acquired
August 6, 2013
Publication Date
April 1, 1972
Subject Category
Structural Mechanics
Report/Patent Number
AIAA PAPER 72-359
Meeting Information
Meeting: Structures, Structural Dynamics, and Materials Conference
Location: San Antonio, TX
Start Date: April 10, 1972
End Date: April 12, 1972
Sponsors: AIAA, SAE, ASME
Accession Number
72A25387
Distribution Limits
Public
Copyright
Other

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