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  • 1
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    Laboratory Produced P/M Aluminum 2XXX + Zr Sheet (1988)
    Springer
    Details
    Publication Date: 1988-11-01
    Print ISSN: 1047-4838
    Electronic ISSN: 1543-1851
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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    PAPER CURRENT
  • 2
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    Laboratory produced P/M aluminum 2XXX + Zr sheet (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A laboratory-scale batch of aluminum alloy sheeting samples in the 2XXX + Zr system has been produced by P/M techniques in the T8X temper and subjected to tensile and Kahn tear property tests in both the longitudinal and long-transverse directions. The results obtained were compared to those of a NASA study concerning the same alloy powders; it appears that laboratory production-scale sheet-sample properties are good to excellent predictors of pilot-scale process products' tensile and tear notch toughness properties. The tear resistance toughness of the laboratory samples was not predictive of the pilot-scale products, however.
    Keywords: METALLIC MATERIALS
    Type: Journal of Metals (ISSN 0148-6608); 40; 40-43
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Material characterization of superplastically formed titanium (Ti-6Al-2Sn-4Zr-2Mo) sheet (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerospace industry has focused considerable interest on the near-alpha titanium alloy Ti-6Al-2Sn-4Zr-2Mo (Ti-6242) because of both its high-temperature properties and its superplastic forming (SPF) capabilities. This paper describes current research to characterize selected mechanical properties of Ti-6242 sheet in the SPF-strained condition, both with and without heat treatment, and compares the results with those obtained on as-received material. Tensile and creep tests were conducted, and metallographic analysis was performed to show the effect of 100 to 700 percent SPF strain on titanium properties. Analysis shows that as a result of SPF processing, both tensile and yield strengths, as well as elongation, are moderately reduced. Creep tests at 800 F and 1000 F show that the SPF processed material displays superior creep resistance compared with the as-received material. A post-SPF duplex-anneal heat treatment had no beneficial effect on tensile and creep properties.
    Keywords: METALLIC MATERIALS
    Type: NASA-TP-2674 , L-16115 , NAS 1.60:2674
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Analysis and test of superplastically formed titanium hat-stiffened panels under compression (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Four hat-stiffened titanium panels with two different stiffener configurations were fabricated by superplastic forming/weld brazing and tested under a moderately heavy compressive load. The panels had the same overall dimensions but differed in the shape of the hat-stiffener webs; three panels had stiffeners with flat webs and the other panel had stiffeners with beaded webs. Analysis indicated that the local buckling strain of the flat stiffener web was considerably lower than the general panel buckling strain or cap buckling strain. The analysis also showed that beading the webs of the hat stiffeners removed them as the critical element for local buckling and improved the buckling strain of the panels. The analytical extensional stiffness and failure loads compared very well with experimental results.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-88989 , NAS 1.15:88989
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Test of superplastically formed corrugated aluminum compression specimens with beaded webs (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Corrugated wall sections provide a highly efficient structure for carrying compressive loads in aircraft and spacecraft fuselages. The superplastic forming (SPF) process offers a means to produce complex shells and panels with corrugated wall shapes. A study was made to investigate the feasibility of superplastically forming 7475-T6 aluminum sheet into a corrugated wall configuration and to demonstrate the structural integrity of the construction by testing. The corrugated configuration selected has beaded web segments separating curved-cap segments. Eight test specimens were fabricated. Two specimens were simply a single sheet of aluminum superplastically formed to a beaded-web, curved-cap corrugation configuration. Six specimens were single-sheet corrugations modified by adhesive bonding additional sheet material to selectively reinforce the curved-cap portion of the corrugation. The specimens were tested to failure by crippling in end compression at room temperature.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-104119 , NAS 1.15:104119
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Superplastically Formed Titanium Hat-Stiffened Panels (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Recent advances in superplastic forming of some metals make it possible to fabricate new shapes. Superplastic forming enables design of structures using mass more efficiently. Parts having intersecting compound contour surfaces made; impossible to fabricate such parts by more conventional methods. Beaded hat-stiffened panel has higher critical buckling strain than conventional hat-stiffened panel.
    Keywords: FABRICATION TECHNOLOGY
    Type: LAR-13814 , NASA Tech Briefs (ISSN 0145-319X); 14; 1; P. 63
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Characteristics Of Superplastically Formed Ti-6242 Sheet (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Near-alpha titanium alloy candidate for high-temperature structural airframe applications. Research characterizes selected mechanical properties of Ti-6242 sheets in superplastic forming (SPF) condition, both with and without heat treatment, and compares results with those obtained on as-received material. Information derived from research proves useful to aerospace community for designing and manufacturing Ti-6242 structures and structural components.
    Keywords: MATERIALS
    Type: LAR-14304 , NASA Tech Briefs (ISSN 0145-319X); 16; 3; P. 63
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Superplastic forming/weld-brazing of Ti-6Al-4V panels for enhanced structural efficiency (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An account is given of the results obtained by NASA-sponsored studies which exploit the processing advantages of superplastic forming (SPF) and joining by weld-brazing (WB) for the fabrication of Ti-alloy skin-stiffened structural components. The buckling strengths of panels with stiffeners having the geometry of a conventional hat shape are compared with those of panels having advanced-geometry stiffereners. Both single- and multiple-stiffened panels have been evaluated at room temperature; the SPF/WB panels with advanced-geometry stiffeners developed up to 60-percent higher buckling strength than panels with conventional-geometry stiffeners. Selective stiffener reinforcement with a boron-reinforced Al-matrix MMC was also evaluated.
    Keywords: MECHANICAL ENGINEERING
    Type: International SAMPE Metals and Metals Processing Conference; Aug 18, 1987 - Aug 20, 1987; Cherry Hill, NJ; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Experimental Study of a Hot Structure for a Reentry Vehicle (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A large structural model of a reentry vehicle has been built incorporating design concepts applicable to a radiation-cooled vehicle. Thermal-stress alleviating features of the model are discussed. Environmental tests on the model include approximately 100 cycles of loading at room temperature and 33 cycles of combined loading and-heating up to temperatures of 1,6000 F. Measured temperatures are shown for typical parts of the model. Comparisons are made between experimental and calculated deflections and strains. The structure successfully survived the heating and loading environments.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA-TM-X-314
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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