Fabricating aluminum matrix composites

Toth, I. J.; Brentnall, W. D.; Menke, G. D.

doi:10.1007/bf03355795

Cited by 5 publications

(3 citation statements)

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“…However, the fracture toughness, K~, which is the important parameter for structural design, shows a substantial increase with increased matnx yield strength. These data, combined with the well-established [11,12] increase in off-axis mechanical properties with increased matrix yield strength, lead to the conclusion that a significant overall benefit can be derived from heat treating B-6061 Al composites.…”

Section: Discussionmentioning

confidence: 90%

“…This series will be used to illustrate the effect of matrix yield strength (and hence composite yield strength) on toughness at a constant composite strength. A simple rule-of-mixtures calculation was used to calculate the effective yield strength of the matrix as a function of heat treatment: yield strengths of 5.7 ksi (3913 MPa) for the 0 condition, 12 [6,7] indicates that the thickness used is sufficient to assure plane strain conditions at the notch tip, that the fracture behavior of this material is not dependent on notch tip radii over the range employed in this study, and that crack propagation is colinear with the notch. 1.…”

Section: The Critical Energy Release Rate Criterionmentioning

confidence: 99%

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Crack Initiation in B-Al Composites

Hoover¹

1976

Journal of Composite Materials

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The toughness of notched, unidirectional B-Al composites under three-point bending has been examined as a function of filament volume fraction, filament diameter and matrix yield strength. The results illustrate that the work-of-fracture, 1/, criterion for composite toughness has only limited utility since yf was found to be a strong function of notch length. The linear elastic fracture toughness, K,, was observed to be independent of both notch length and filament diameter. However, the K, values increased significantly as the yield strength of the matrix increased. The critical energy release rate, L,, was shown to be independent of crack length, filament diameter and matrix yield strength. It has been proposed that L, is a reflection of the strain energy stored in the filaments at crack initiation and is thus a measure of the parameter which controls composite crack initiationstrain in the filaments at the notch root.

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Section: Discussionmentioning

confidence: 90%

Section: The Critical Energy Release Rate Criterionmentioning

confidence: 99%

Crack Initiation in B-Al Composites

Hoover¹

1976

Journal of Composite Materials

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“…Variation of the B4C-Ti composite property ratios a~ s /az 2 ande, , /E2 2 with B4 C ribbon cross-section dimensions. titanium alloy matrix composite [5]. The corresponding wlt value for the fiber cross-section was taken as 1.…”

Section: Table L Properties Of Boron Carbide Ribbon-titanium Compositesmentioning

confidence: 99%

Tensile Properties of Boron Carbide Ribbon in Titanium Matrix

Hordon

1973

Journal of Composite Materials

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In the mechanical analysis of fiber-reinforced composite structures, the effect of reinforcement geometry, in particular, the effect of ribbon-shaped reinforcement elements on composite properties, has been treated by Foye [ I ] and by Halpin and Thomas [2]. Analysis has shown that the mechanical properties transverse to the ribbon axis increase with an increase in ribbon width/thickness (wlt) ratio, gradually approaching isotropy with the axial properties in the limit for extremely large w/t ratios. Experimental data to support the analysis has been limited, however, due to the difficulty in preparing suitable ribbon geometries for reinforcement materials. The present note reports some recent measurements on the mechanical properties of titanium composites reinforced by boron carbide ribbon elements with varying cross-section dimensions to provide experimental corroboration of the theory. EXPERIMENTALThe preparation of composite laminates containing alternate layers of boron or boron carbide and aluminum or titanium phases up to 25 jum in thickness has been previously reported [ 3,4]. The laminates were fabricated by depositing B or B4C onto thin Ti or Al foil sheets and subsequently diffusion bonding arrays of bi-phase sheet elements.Extending this work, the B4C-Ti laminate process was modified to produce uniaxial arrays of bi-phase ribbon elements by grooving the titanium core foils prior to boron carbide deposition. Using a standard coated sheet thickness of 0.0011 in., ribbon widths were varied from 0.05 to 3.0 in. with the inter-ribbon spacing or groove width maintained at 0.020 in. The ribbon arrays were subsequently diffusion bonded at 700°C with additional titanium intermediate sheets to produce multi-layer composite plates containing 20-43 percent B4C volume fraction in the form of uniaxially aligned sets of ribbons with cross-section w/t values ranging from 50 to 3000, the latter corresponding to a continuous laminate.

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