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Advanced fabrication technology for high speed aircraft structuresAn overview of the development of the weld-brazing process for fabricating Ti-6Al-4V skin-stiffened panels, a brazing process for fabricating Bsc/Al titanium honeycomb core panels, and the enhanced diffusion bonding (EDB) process for fabricating Ti-14Al-21Nb titanium aluminide structural elements are presented. Data presented include the shear strengths of full-scale weldbrazed Ti-6Al-4V skin stiffened and Bsc/Al titanium honeycomb core sandwich panels designed to meet the requirements of an upper wing panel on the NASA YF-12. These results verified that the materials, fabrication processes, and structural concepts were qualified for Mach 3 flight. Shear strengths of each of the panel concepts following flight service evaluation are also reported. Comparisons made with the cost and weight of the original wing panel indicated that the weldbrazed titanium panels resulted in a 15-20 percent cost savings and the brazed Bsc/Al panel showed a 30 percent weight savings. It was also shown that the strengths of the EDB joints were sufficient to develop stresses in the Ti-14Al-21Nb face sheets of the sandwich structure which were above the yield strength of the material.
Document ID
19910039834
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bales, T. T.
(NASA Langley Research Center Hampton, VA, United States)
Hoffman, E. K.
(NASA Langley Research Center Hampton, VA, United States)
Bird, R. K.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1990
Subject Category
Aeronautics (General)
Accession Number
91A24457
Distribution Limits
Public
Copyright
Other

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