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  • 1
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    Advances in metals processing (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: Research on metals processing being conducted to develop improved forming and joining methods with the potential of reducing the weight and cost of future aerospace structures is discussed. The approach followed is to assess the state of the art for fabricating a given structural system, define candidate methods for improving processing, evaluate the merits of each, fabricate and test subelement components, and then scale up the process to demonstrate validity. The development and the state of the art of weldbrazing, superplastic forming (SPF), superplastic forming and codiffusion bonding and superplastic forming and weldbrazing for titanium and the SPF of aluminum is discussed.
    Keywords: METALLIC MATERIALS
    Type: Advan. Mater. Technol.; p 201-218
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Evaluation of Superplastic Forming and Weld-brazing for Fabrication of Titanium Compression Panels (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The two titanium processing procedures, superplastic forming and weld brazing, are successfully combined to fabricate titanium skin stiffened structural panels. Stiffeners with complex shapes are superplastically formed using simple tooling. These stiffeners are formed to the desired configuration and required no additional sizing or shaping following removal from the mold. The weld brazing process by which the stiffeners are attached to the skins utilize spot welds to maintain alignment and no additional tooling is required for brazing. The superplastic formed/weld brazed panels having complex shaped stiffeners develop up to 60 percent higher buckling strengths than panels with conventional shaped stiffeners. The superplastic forming/weld brazing process is successfully scaled up to fabricate full size panels having multiple stiffeners. The superplastic forming/weld brazing process is also successfully refined to show its potential for fabricating multiple stiffener compression panels employing unique stiffener configurations for improved structural efficiency.
    Keywords: MECHANICAL ENGINEERING
    Type: Welding, Bonding and Fastening, 1984; p 253-270
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Weld-brazing - a new joining process (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A joining process designated weld brazing which combines resistance spot welding and brazing has been developed. Resistance spot welding is used to position and align the parts as well as to establish a suitable faying surface gap for brazing. Fabrication is then completed by capillary flow of the braze alloy into the joint. The process has been used successfully to fabricate Ti-6Al-4V titanium alloy joints using 3003 aluminum braze alloy. Test results obtained on single overlap and hat-stiffened structural specimens show that weld brazed joints are superior in tensile shear, stress rupture, fatigue, and buckling than joint fabricated by spotwelding or brazing. Another attractive feature of the process is that the brazed joints is hermetically sealed by the braze material.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: Proc. of the Symp. on Welding, Bonding, and Fastening; 22 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Fabrication and evaluation of advanced titanium and composite structural panels (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Advanced manufacturing methods for titanium and composite material structures are being developed and evaluated. The focus for the manufacturing effort is the fabrication of full-scale structural panels which replace an existing shear panel on the upper wing surface of the NASA YF-12 aircraft. The program involves design, fabrication, ground testing, and Mach 3 flight service of full-scale structural panels and laboratory testing of representative structural element specimens.
    Keywords: METALLIC MATERIALS
    Type: Proc. of the SCAR Conf., Pt. 2,; 15 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Fabrication and evaluation of superplastically formed/weld-brazed corrugated compression panels with beaded webs (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was made to investigate the feasibility of superplastically forming corrugated panels with beaded webs and to demonstrate the structural integrity of these panels by testing. The test panels in the study consist of superplastically formed titanium alloy Ti-6Al-4V half-hat elements that are joined by weld-brazing to titanium alloy Ti-6Al-4V caps to form either single-corrugation compression panels or multiple-corrugation compression panels. Stretching and subsequent thinning of the titanium sheet during superplastic forming is reduced by approximately 35 percent with a shallow half-hat die concept instead of a deep die concept and results in a more uniform thickness across the beaded webs. The complete panels are tested in end compression at room temperature and the results compared with analysis. The heavily loaded panels failed at loads approaching the yield strength of the titanium material. At maximum load, the caps wrinkled locally accompanied with separation of the weld-braze joint in the wrinkle. None of the panels tested, however, failed catastrophically in the weld-braze joint. Experimental test results are in good agreement with structural analysis of the panels.
    Keywords: METALLIC MATERIALS
    Type: NASA-TP-2512 , L-15988 , NAS 1.60:2512
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Thoriated nickel bonded by solid-state diffusion method (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Solid-state diffusion bonding in an inert-gas atmosphere forms high-strength joints between butting or overlapping surfaces of thoriated nickel. This method eliminates inert-phase agglomeration.
    Keywords: MATERIALS
    Type: LAR-116
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Fabrication of structural components from commercial aluminum alloys using superplastic forming (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: SPF technology was used to fabricate structural components from the 7475 Al and 8090 Al-Li commercial alloys. Gas-pressurization cycles were established for SPF three-hat stiffener configurations on the basis of uniaxial data and component-geometry considerations. It is established that higher forming rates than the optimum strain rates selected from the uniaxial data for each alloy could be used in the later stages of forming without reducing SPF components' dimensional conformity. Cavitation was precluded through the use of back pressure during forming.
    Keywords: MECHANICAL ENGINEERING
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Curved cap corrugated sheet (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The report describes a structure for a strong, lightweight corrugated sheet. The sheet is planar or curved and includes a plurality of corrugation segments, each segment being comprised of a generally U-shaped corrugation with a part-cylindrical crown and cap strip, and straight side walls and with secondary corrugations oriented at right angles to said side walls. The cap strip is bonded to the crown and the longitudinal edge of said cap strip extends beyond edge at the intersection between said crown and said side walls. The high strength relative to weight of the structure makes it desirable for use in aircraft or spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NAS 1.71:LAR-12884
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Metal matrix composite structural panel construction (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Lightweight capped honeycomb stiffeners for use in fabricating metal or metal/matrix exterior structural panels on aerospace type vehicles and the process for fabricating same are disclosed. The stiffener stringers are formed in sheets, cut to the desired width and length and brazed in spaced relationship to a skin with the honeycomb material serving directly as the required lightweight stiffeners and not requiring separate metal encasement for the exposed honeycomb cells.
    Keywords: COMPOSITE MATERIALS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    "Sandwich" Stiffener for Composite Structural Panels (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Concept uses commercial titanium honeycomb core brazed to cap material and panel skin. In fabrication of stringers, large sheets of cap material are brazed to pieces of honeycomb core of desired height. After brazing, individual stringers are cut by electrical-discharge machining, and stringers are subsequently brazed to skin. Sandwich beam stringer is light-weight, structurally-efficient, low-cost stiffener for metal-matrix composite structural panels.
    Keywords: FABRICATION TECHNOLOGY
    Type: LAR-12807 , NASA Tech Briefs (ISSN 0145-319X); 6; 4; P. 463
    Format: text
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    NASA TECHNICAL REPORTS
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