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Fabrication and evaluation of advanced titanium structural panels for supersonic cruise aircraftFlightworthy primary structural panels were designed, fabricated, and tested to investigate two advanced fabrication methods for titanium alloys. Skin-stringer panels fabricated using the weldbraze process, and honeycomb-core sandwich panels fabricated using a diffusion bonding process, were designed to replace an existing integrally stiffened shear panel on the upper wing surface of the NASA YF-12 research aircraft. The investigation included ground testing and Mach 3 flight testing of full-scale panels, and laboratory testing of representative structural element specimens. Test results obtained on full-scale panels and structural element specimens indicate that both of the fabrication methods investigated are suitable for primary structural applications on future civil and military supersonic cruise aircraft.
Document ID
19790010149
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Payne, L. (Lockheed-California Co. Burbank, CA, United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1977
Publication Information
Publisher: NASA
Subject Category
Mechanical Engineering
Report/Patent Number
SP-4508
NASA-CR-2744
Accession Number
79N18320
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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