CN117644363A - Manufacturing method of explosive welding lamellar metal composite material interface shear sample - Google Patents
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- CN117644363A CN117644363A CN202311714502.6A CN202311714502A CN117644363A CN 117644363 A CN117644363 A CN 117644363A CN 202311714502 A CN202311714502 A CN 202311714502A CN 117644363 A CN117644363 A CN 117644363A
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- 239000002905 metal composite material Substances 0.000 title claims abstract description 38
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 24
- 238000003466 welding Methods 0.000 title claims abstract description 20
- 239000002360 explosive Substances 0.000 title claims abstract description 9
- 238000012545 processing Methods 0.000 claims abstract description 47
- 238000012360 testing method Methods 0.000 claims abstract description 31
- 239000000463 material Substances 0.000 claims abstract description 16
- 238000000034 method Methods 0.000 claims abstract description 14
- 238000005520 cutting process Methods 0.000 claims abstract description 13
- 239000000523 sample Substances 0.000 claims description 55
- 239000002131 composite material Substances 0.000 claims description 27
- 238000003754 machining Methods 0.000 claims description 9
- 238000010030 laminating Methods 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- 238000004880 explosion Methods 0.000 abstract description 11
- 238000005253 cladding Methods 0.000 abstract description 3
- 238000004021 metal welding Methods 0.000 abstract description 2
- 239000002184 metal Substances 0.000 description 6
- 229910052751 metal Inorganic materials 0.000 description 6
- 238000003801 milling Methods 0.000 description 6
- 238000005096 rolling process Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
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Abstract
The invention relates to the technical field of explosion welding of metal composite plates, in particular to a manufacturing method of an explosion welding layered metal composite material interface shear sample. A method for manufacturing an explosive welding lamellar metal composite interface shear sample comprises the steps of cutting the sample, preliminarily processing two opposite surfaces of a base layer and a cladding layer, processing a cladding layer step and processing a pre-split. The manufacturing method of the explosive welding lamellar metal composite interface shear sample has the advantages that a sample batch is firstly cut at a designated position of the lamellar metal composite, then the sample batch is processed into a shear sample, a pre-split is processed, and finally the sample manufacturing is completed. The interface processing is accurately controlled, the influence on test result judgment is avoided, and the material utilization rate is improved.
Description
Technical Field
The invention relates to the technical field of explosion welding of metal composite plates, in particular to a manufacturing method of an explosion welding layered metal composite material interface shear sample.
Background
Layered metal composites are materials composed of two or more layers of different metals. The metal laminated composite material has excellent performances, and is widely applied in the fields of wear resistance, corrosion resistance, impact resistance, high heat conductivity, electromagnetic performance, strength, toughness and the like. Layered metal composites typically employ shear or tensile shear specimens to determine interfacial shear strength. The existing layered metal composite material is mainly prepared by adopting processing methods such as explosion welding, rolling, overlaying welding, diffusion welding, casting, explosion rolling, overlaying welding rolling, diffusion rolling, casting rolling and the like, and interfaces exist, particularly, different metals are subjected to explosion welding.
The interface shear strength test is an important index for judging the interface bonding strength of the composite board, and the shear test is to apply the tensile stress of a sample to two different points so as to deform the material in the vertical direction. In this way, we can understand the performance of the composite under torsional and shear stresses. Shear testing can provide a variety of information about the composite, such as failure mode, strength and stiffness of the composite, etc. For example, chinese patent publication No. CN112229705a discloses a method for testing interfacial shear strength of a marine clad steel plate, which is tested by using a split Hopkinson compression bar, and the dynamic test method mainly includes: firstly, designing a sample, a loading piece and a clamping piece, then respectively connecting the loading piece and the clamping piece with an incidence rod and a transmission rod of a separated Hopkinson pressure bar in a threaded manner, and placing the sample in a sample mounting block; adjusting the punch to be coaxial with the multi-layer of the sample, and erecting a high-speed camera system, wherein the punch is taken as an observation area; and starting a loading system of the separated Hopkinson pressure bar to perform a test, and recording the dynamic shear strain rate and the dynamic shear strength at the interface by strain information through strain sheets stuck on the incident bar and the transmission bar. However, in the conventional shear sample processing process, the interfaces are combined in a corrugated manner, are not in the same horizontal plane, and are not processed to the interfaces or too deep interfaces, so that the interface processing is not easy to accurately control, the shear failure surface is not usually at the interfaces, and the judgment of the test result is finally influenced; the tensile shear test sample needs to be large in size and low in material utilization rate.
Disclosure of Invention
In view of the above, the present invention aims to provide a method for manufacturing an explosive welding layered metal composite interface shear sample, which comprises the steps of firstly cutting a sample batch at a specified position of a layered metal composite, then processing the sample batch into a shear sample, processing a pre-split, and finally completing sample manufacturing. The problem that in the conventional shear sample processing process, interfaces are combined in a corrugated manner and are not in the same horizontal plane, the interface is not processed to the interface or is too deep, the interface processing is not easy to accurately control, the shear failure surface is not usually at the interface, and finally the test result judgment is influenced; the tensile shear test sample needs larger size and has lower material utilization rate.
In order to solve the problems, the invention provides a manufacturing method of an explosive welding lamellar metal composite material interface shear sample, which comprises the following steps:
s100, selecting a test sample material, wherein the sample material is a layered metal composite material formed by laminating and connecting a base layer and a multi-layer formed by two metal materials;
cutting the sample material according to the test requirement, and performing rough machining on each surface of the sample material;
s200, processing two surfaces of the base layer and the multiple layers which are opposite to each other, and ensuring that the two surfaces are parallel, wherein the thickness of the multiple layers is smaller than or equal to 3mm;
s300, machining a multi-layer step:
s310, determining the position of a prefabricated multi-layer step close to a first side edge of a first end of a sample, processing the multi-layer surface from the first side edge to the first end part of the sample, removing the multi-layer surface material until corrugation appears between the multi-layer and a base layer, obtaining the removal ac of the multi-layer, and determining the length of the step according to W=2ac;
continuing the thickness direction processing until the corrugation disappears, and recording the processing thickness h;
s320, determining the position of a second side edge of the multi-layer step according to the W size, processing the multi-layer surface on one side of the second side edge, and removing the multi-layer surface material until corrugation appears between the multi-layer and the base layer;
continuing to process in the thickness direction, wherein the processing thickness is 0.5h;
s400, processing the root part of the connection between the multi-layer step and the composite material to form a pre-split.
Further, in step S100, the method includes:
after cutting sample materials, deburring, and press-correcting the blank by a press to ensure that the unevenness of the two opposite surfaces of the composite layer and the base layer is less than 0.5mm.
Further, in step S200, the surface of the base layer is processed with the surface of the clad layer as a reference, and the surface of the base layer is processed with the surface of the base layer as a reference, so that the parallelism of the two opposite surfaces of the clad layer and the base layer is ensured to be less than or equal to 0.05mm.
Further, in step S300, a tolerance range of W is ensured to be between ±0.1 mm.
Further, in step S310, the clad layer is finally processed to have a thickness ac.ltoreq.3 mm.
Further, in step S320, further includes: and (5) after removing the material on the surface of the composite layer until the corrugation appears, continuing to process the composite layer for 0.5h in the thickness direction.
Further, in step S400, a groove is machined at the second side of the multi-layered step, and the machining depth is set to be flush with the bottom surface of the groove at the first side.
Further, the pre-split cross section is in the shape of one or a combination of a plurality of rectangle, triangle, trapezoid, arc and U-shape extending from the second side surface to the inside of the multi-layer step.
Further, the length of the pre-crack extending to the inside of the multi-layer step is 0.5ac, and the height is 0.5h.
Further, the pre-split is machined by wire cutting.
Compared with the prior art, the manufacturing method of the explosive welding lamellar metal composite material interface shear test sample has the following advantages:
the technical scheme has the advantages that the method comprises the steps of firstly cutting a sample batch at a designated position of the layered metal composite material, then processing the sample batch into a shearing sample, processing a pre-split and finally completing sample manufacture. The interface processing is accurately controlled, the influence on test result judgment is avoided, and the material utilization rate is improved.
Drawings
FIG. 1 is a flow chart of a method for fabricating a layered metal composite interfacial shear test sample according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view of a layered metal composite interfacial shear sample according to an embodiment of the present invention;
FIG. 3 is a top view of a layered metal composite interfacial shear sample according to an embodiment of the present invention;
fig. 4 is an enlarged view of section a of fig. 2 of a layered metal composite interfacial shear test piece according to an embodiment of the present invention.
Reference numerals illustrate:
1-multiple layers, 2-base layer.
Detailed Description
In order that the above objects, features and advantages of the invention will be readily understood, a more particular description of the invention will be rendered by reference to specific embodiments thereof which are illustrated in the appended drawings.
The description of "first," "second," "upper," "lower," etc. in this disclosure is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or the number of technical features indicated. Thus, a feature defining "first", "second", "upper", "lower" may include at least one such feature, either explicitly or implicitly. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to be based on the fact that those skilled in the art can implement the combination between the embodiments, and all the technical solutions are within the scope of protection claimed by the present invention.
The invention will be described in detail below with reference to the drawings in connection with embodiments.
As shown in fig. 1, a method for manufacturing an explosive welding laminar metal composite interface shear sample comprises the following steps:
s100, selecting a test sample material, wherein the test sample material is a layered metal composite material formed by laminating and connecting a base layer 2 and a composite layer 1 which are formed by two metal materials; after cutting the sample material, removing burrs, and performing press correction on the blank through a press to ensure that unevenness of two opposite surfaces of the composite layer 1 and the base layer 2 is less than 0.5mm. The sample material is cut according to the test requirements and rough machining is performed on each side of the sample material.
And S200, processing two opposite surfaces of the base layer 2 and the composite layer 1, and ensuring that the two surfaces are parallel, wherein the thickness of the composite layer is smaller than or equal to 3mm. And processing the surface of the base layer 2 by taking the surface of the composite layer 1 as a reference, and processing the surface of the composite layer 1 by taking the surface of the base layer 2 as a reference, so that the parallelism of the two opposite surfaces of the composite layer 1 and the base layer 2 is less than or equal to 0.05mm.
S300, machining a multi-layer step:
s310, determining the position of a first side edge of the prefabricated multi-layer step close to the first end of the sample, machining the multi-layer surface from the first side edge to the first end of the sample, and removing the multi-layer surface material to obtain the removal quantity ac of the multi-layer, wherein ac is less than or equal to 3mm. Determining the length of the step according to w=2ac±0.1 mm; the thickness direction processing was continued until the waviness disappeared, and the processing thickness h was recorded.
S320, determining the position of the second side edge of the multi-layer step according to the W size, processing the multi-layer surface on one side of the second side edge, removing the multi-layer surface material until the corrugation appears between the multi-layer and the base layer, and continuing to process in the thickness direction until the processing thickness is 0.5h.
S400, processing the root part of the connection between the multi-layer step and the composite material to form a pre-split. And processing a groove at the second side edge of the multi-layer step until the processing depth is equal to the level of the bottom surface of the groove and the first side edge. The pre-split section is in the shape of one or a combination of more than one of rectangle, triangle, trapezoid, arc and U-shaped extending from the surface of the second side edge to the inside of the multi-layer step. The length of the pre-split extending to the inside of the multi-layer step is 0.5ac, and the height is 0.5h. The pre-split is machined by wire cutting.
The method for producing the layered metal composite interfacial shear test piece according to the present invention is described in detail below with reference to a specific example.
Explosion welding the layered metal composite material, wherein the base layer is 30mmSA516Gr70, and the cladding layer is 3mmGr1.
S100, cutting a sample batch at a designated position of the layered metal composite material, wherein the number of the sample batch is 33 x 30 x 70mm, removing burrs around the sample batch after the completion, and selecting a press to press and calibrate the blank, wherein the unevenness of the upper surface and the lower surface of the blank is less than 0.5mm;
s200, milling four side faces, upper end faces and lower end faces of the sample by a milling machine, wherein the width is 25+/-0.2 mm, the parallel difference of the two sides is less than or equal to 0.05, and the roughness is less than or equal to Ra12.5. Size assurance: the length is 65 plus or minus 0.2mm, the verticality is less than or equal to 0.05, and the roughness is less than or equal to Ra12.5; the thickness of the composite layer is less than or equal to 3mm, and the thickness of the base layer is more than or equal to 6mm.
S300, machining a multi-layer step:
s310, taking a multi-layer Gr1 as a bottom, determining that the ab size is more than or equal to 10mm (at least ensuring that ab is more than or equal to 2W) by referring to the total thickness delta of the blank and the multi-layer thickness ac, and processing the lower end face (a base SA516Gr 70), wherein the processing amount is 1-3 mm, ensuring that the lower end face is perpendicular to 4 side faces, the perpendicularity is less than or equal to 0.05, and the roughness is less than or equal to Ra3.2;
processing the upper end surface (a multi-layer Gr 1) by using the base SA516Gr70 as a bottom, wherein the processing amount is 0.1mm, the roughness is less than or equal to Ra12.5, and the parallelism difference is less than or equal to 0.05;
s320, deburring, namely sequentially scribing from one end by using a height scribing ruler, marking the positions of a sample step and a groove, milling or planing a right side short step surface until waves (obvious metal mixed spots are formed on the joint surface of the multilayer Gr1 and the base layer SA516Gr70, namely the wave crest position of the waves of an explosion welding interface) appear, and processing the multilayer thickness ac (3 mm) required by shearing the sample;
s400, processing a pre-split:
milling or planing the right small step surface is continued until the corrugation of the combination surface of the composite layer Gr1 and the base layer SA516Gr70 just disappears (the spot shape of the metal mixture disappears, and the position of the trough of the explosion welding interface wave) and the thickness processing amount h (0.40 mm) in the process is recorded.
Milling or planing the long step surface on the left side until the combination surface of the composite layer Gr1 and the base layer SA516Gr70 has the waved (obvious metal mixed spots are the waved wave crest positions of the explosion welding interface), and then continuously processing the thickness for 0.5h (0.20 mm), wherein the thickness is parallel to the lower end surface, and the parallel difference is less than or equal to 0.05. The W size is ensured to be 6 plus or minus 0.1mm, and meanwhile, the left end face of the step is ensured to be 20 plus or minus 0.15mm away from the right side face of the sample, and the roughness is less than or equal to Ra3.2.
Milling a 3mm plus or minus 0.1 end face groove, and processing the thickness for 0.5h (0.20 mm plus or minus 0.1mm and being flush with the right small step face).
And (3) demarcating parallel lines on the steps of the multi-layer Gr1 by taking the left long step surface as a reference.
And (3) carrying out linear cutting processing on the V-shaped pre-split by taking a parallel line defined by the steps of the multi-layer Gr1 as a reference, wherein the width is 0.5 ac+/-0.1 mm (1.5+/-0.1 mm), and the thickness is 0.5 h+/-0.1 (0.2+/-0.1 mm), and the V-shaped pre-split is flush with the end face groove after processing.
Although the present invention is disclosed above, the present invention is not limited thereto. Various changes and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention, and the scope of the invention should be assessed accordingly to that of the appended claims.
Claims (10)
1. The manufacturing method of the explosive welding lamellar metal composite material interface shear sample is characterized by comprising the following steps of:
s100, selecting a test sample material, wherein the sample material is a layered metal composite material formed by laminating and connecting a base layer and a multi-layer formed by two metal materials;
cutting the sample material according to the test requirement, and performing rough machining on each surface of the sample material;
s200, processing two surfaces of the base layer and the multiple layers which are opposite to each other, and ensuring that the two surfaces are parallel to each other so that the thickness of the multiple layers is less than or equal to 3mm;
s300, machining a multi-layer step:
s310, determining the position of a prefabricated multi-layer step close to a first side edge of a first end of a sample, processing the multi-layer surface from the first side edge to the first end part of the sample, removing the multi-layer surface material until corrugation appears between the multi-layer and a base layer, obtaining the removal ac of the multi-layer, and determining the length of the step according to W=2ac;
continuing the thickness direction processing until the corrugation disappears, and recording the processing thickness h;
s320, determining the position of a second side edge of the multi-layer step according to the W size, processing the multi-layer surface on one side of the second side edge, and removing the multi-layer surface material until corrugation appears between the multi-layer and the base layer;
s400, processing the root part of the connection between the multi-layer step and the composite material to form a pre-split.
2. The method for producing a layered metal composite interfacial shear test piece according to claim 1, wherein,
in step S100, it includes:
after cutting sample materials, deburring, and press-correcting the blank by a press to ensure that the unevenness of the two opposite surfaces of the composite layer and the base layer is less than 0.5mm.
3. The method for producing a layered metal composite interfacial shear test piece according to claim 1, wherein,
in step S200, the surface of the base layer is processed by taking the surface of the composite layer as a reference, and the surface of the base layer is processed by taking the surface of the base layer as a reference, so that the parallelism of the two opposite surfaces of the composite layer and the base layer is less than or equal to 0.05mm.
4. The method for producing a layered metal composite interfacial shear test piece according to claim 1, wherein,
in step S300, a W tolerance range of ±0.1mm is ensured.
5. The method for producing a layered metal composite interfacial shear test piece according to claim 1, wherein,
in step S310, the composite layer is finally processed to have a thickness ac of 3mm or less.
6. The method for producing a layered metal composite interfacial shear test piece according to claim 1, wherein,
the step S320 further includes: and (5) after removing the material on the surface of the composite layer until the corrugation appears, continuing to process the composite layer for 0.5h in the thickness direction.
7. The method for producing a layered metal composite interfacial shear test piece according to claim 1, wherein,
in step S400, a groove is machined at the second side of the multi-layer step to a depth at which the bottom surface of the groove is flush with the first side.
8. The method for producing a layered metal composite interfacial shear test piece as defined in claim 8, wherein,
the pre-split section is in the shape of one or a combination of more than one of rectangle, triangle, trapezoid, arc and U-shaped extending from the surface of the second side edge to the inside of the multi-layer step.
9. The method for producing a layered metal composite interfacial shear test piece as defined in claim 9, wherein,
the length of the pre-split extending to the inside of the multi-layer step is 0.5ac, and the height is 0.5h.
10. The method for producing a layered metal composite interfacial shear test piece as defined in claim 9, wherein,
the pre-split is machined by wire cutting.
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| CN202311714502.6A CN117644363A (en) | 2023-12-14 | 2023-12-14 | Manufacturing method of explosive welding lamellar metal composite material interface shear sample |
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