CN111272650A - Joint for testing failure criterion of composite material bonding structure - Google Patents
Joint for testing failure criterion of composite material bonding structure Download PDFInfo
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- CN111272650A CN111272650A CN202010134416.8A CN202010134416A CN111272650A CN 111272650 A CN111272650 A CN 111272650A CN 202010134416 A CN202010134416 A CN 202010134416A CN 111272650 A CN111272650 A CN 111272650A
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- 239000002131 composite material Substances 0.000 title claims abstract description 136
- 238000012360 testing method Methods 0.000 title claims abstract description 78
- 239000012790 adhesive layer Substances 0.000 claims abstract description 124
- 229910052751 metal Inorganic materials 0.000 claims abstract description 38
- 239000002184 metal Substances 0.000 claims abstract description 38
- 239000010410 layer Substances 0.000 claims abstract description 34
- 239000003292 glue Substances 0.000 claims abstract description 33
- 239000000853 adhesive Substances 0.000 claims description 16
- 239000000463 material Substances 0.000 claims description 16
- 230000001070 adhesive effect Effects 0.000 claims description 14
- 239000000835 fiber Substances 0.000 abstract description 12
- 238000000034 method Methods 0.000 description 6
- 239000000805 composite resin Substances 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000003365 glass fiber Substances 0.000 description 2
- 229910052755 nonmetal Inorganic materials 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 229920006231 aramid fiber Polymers 0.000 description 1
- 239000010425 asbestos Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052796 boron Inorganic materials 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 239000011151 fibre-reinforced plastic Substances 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 230000003137 locomotive effect Effects 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 229910052895 riebeckite Inorganic materials 0.000 description 1
- 239000005060 rubber Substances 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
- 239000000057 synthetic resin Substances 0.000 description 1
- 229920003002 synthetic resin Polymers 0.000 description 1
- 238000004154 testing of material Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N19/00—Investigating materials by mechanical methods
- G01N19/04—Measuring adhesive force between materials, e.g. of sealing tape, of coating
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- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a joint for testing the failure criterion of a composite material bonding structure, which comprises: a first metal test bar; a second metal test bar; the first adhesive layer is used for bonding the first metal test bar and the first composite material plate; the first non-adhesive layer frame is adhered to the outer side of the first composite material plate in a matching mode; the second adhesive layer is used for bonding the second metal test bar and the second composite material plate; the second non-adhesive layer frame is bonded on the outer side of the second composite material plate in a matching mode; a third glue layer for bonding the first composite sheet and the second composite sheet; and the third non-stick adhesive layer frame is adhered to the outer side of the third adhesive layer in a matching manner. The composite material bonding joint can test failure loads in different stress states, meanwhile, the tearing influence of two layers of composite material plates is considered, the influence of fiber tearing and layering in the boundary area of the composite material plates can be avoided, and the testing precision of failure criteria is improved.
Description
Technical Field
The invention relates to the technical field of mechanical property testing of composite material bonding structures, in particular to a joint for testing failure criteria of a composite material bonding structure.
Background
The composite material is a new material formed by optimizing and combining material components with different properties by applying an advanced material preparation technology. The base materials of the composite material are divided into two main categories of metal and nonmetal, and the common metal base materials include aluminum, magnesium, copper, titanium and alloys thereof; the non-metal matrix mainly comprises synthetic resin, rubber, ceramic, graphite, carbon and the like; the reinforced material mainly comprises glass fiber, carbon fiber, boron fiber, aramid fiber, silicon carbide fiber, asbestos fiber, whisker and metal.
In the fields of automobiles, locomotives, airplanes and the like, the existing composite materials are widely applied to carbon fiber reinforced resin composite materials, glass fiber reinforced resin composite materials, basalt reinforced resin composite materials and the like, and the application of the composite materials in automobiles is one of effective methods for realizing light weight.
In the manufacturing industry, as components made of fiber reinforced plastics are increasingly used, particularly in the aircraft and automobile industries, there is an increasing demand for component repair, and bonding technology is a primary means of composite joining and repair.
The composite material is an anisotropic layered material, is sensitive to the form and direction of load, and has important significance in researching failure prediction of the composite material adhesive joint in a complex stress state.
The invention provides a failure criterion test joint between composite materials and composite materials under different stress states, which not only considers the stress states of different tensile-shear ratios, but also considers the tearing or analysis failure of composite material plates at two sides of an adhesive layer, and simultaneously can avoid the influence of boundary effect and residual adhesive on the tearing or layering of fibers, and improve the test precision of the failure criterion of the composite materials and the composite materials.
Disclosure of Invention
The invention aims to design and develop a joint for testing the failure criterion of a composite material bonding structure, and the failure strength of the composite material bonding joint in different stress states can be obtained through testing the bonding joint in different directions;
the joint for testing the failure criterion of the composite material bonding structure is designed and developed, and is used for solving the tearing and layering influence of two composite material plates by the fact that the bonding performance of a third adhesive layer is smaller than that of a first adhesive layer and that of a second adhesive layer, and the failure strength of the third adhesive layer is smaller than that of the first composite material plate and that of the second composite material plate.
The technical scheme provided by the invention is as follows:
a joint for testing composite bonded structural failure criteria, comprising:
a first metal test bar;
a second metal test bar disposed opposite to the first metal test bar;
the first adhesive layer is used for bonding the first metal test bar and the first composite material plate;
the first non-adhesive layer frame is adhered to the outer side of the first composite material plate in a matching mode;
the second adhesive layer is used for bonding the second metal test bar and the second composite material plate;
the second non-adhesive layer frame is bonded on the outer side of the second composite material plate in a matching mode;
a third glue layer for bonding the first composite sheet and the second composite sheet;
and the third non-stick adhesive layer frame is adhered to the outer side of the third adhesive layer in a matching manner.
Preferably, the first adhesive layer and the second adhesive layer are made of the same material.
Preferably, the thickness of the third glue layer is 0.1 mm-0.5 mm.
Preferably, the first metal test bar and the second metal test bar are made of the same material, and the thickness of the first composite material plate and the second composite material plate is not less than 2 mm.
Preferably, the bonding areas of the first adhesive layer and the second adhesive layer are the same.
Preferably, the bonding area of the third glue layer does not exceed the bonding area of the first glue layer and the second glue layer.
Preferably, the thickness of the first glue layer and the second glue layer does not exceed the thickness of the third glue layer.
Preferably, the thickness of the third layer of non-stick glue is the same as the thickness of the third layer of glue.
Preferably, the cross-sectional profile of the joint is square or circular and the squares or circles are arranged coaxially.
Preferably, the properties of the first glue layer, the second glue layer and the third glue layer satisfy:
wherein S is1α is the adhesive layer area of the first adhesive layer or the second adhesive layer, the test angle of different positive stress and shear stress is 8932 degrees or more, 90 degrees or more is α degrees or more is 0 degrees or more, sigma degree is more than or equal to1Is the failure strength, tau, of the first or second adhesive layer under positive stress1The failure strength of the first adhesive layer or the second adhesive layer in a shear stress state, K is a safety factor, and K is more than or equal to 1.05, S3Is the glue line area, σ, of the third glue line3Is the failure strength, tau, of the third glue layer under positive stress3The failure strength of the third adhesive layer in a shear stress state is shown;
the performance of the first composite material plate and the third adhesive layer meets the following requirements:
wherein S is4Is the area, σ, of the first composite sheet4Is the interlaminar tensile failure strength, tau, of the first composite panel4The interlaminar shear failure strength of the first composite plate is defined as the interlaminar shear failure strength of the first composite plate;
the performance of the second composite material plate and the third adhesive layer meets the following requirements:
wherein S is5Is the area, σ, of the second composite sheet5Is the interlaminar tensile failure strength, tau, of the second composite sheet5And the interlaminar shear failure strength of the second composite plate is obtained.
The invention has the following beneficial effects:
(1) the failure strength of the composite material bonding joint in different stress states (pure shear, pure tension and any tension-shear ratio) can be tested, and because the bonding performance of the third adhesive layer is smaller than that of the first adhesive layer and the second adhesive layer and the failure strength of the third adhesive layer is smaller than that of the first composite material plate and that of the second composite material plate, the fiber tearing or layering effect of the composite material plates on the two sides of the adhesive layer can be considered, and a more accurate failure criterion is established;
(2) the non-stick adhesive layer is adopted to control the thickness of the adhesive layer of the composite material, so that the adhesive process is simplified, the fiber tearing or layering influence caused by the fact that the adhesive layer is close to the edge of the composite material plate can be avoided, and the testing precision of failure strength is improved;
(3) the non-stick glue layer is wrapped around the composite material plate, so that the influence of residual glue on fiber tearing or layering of the composite material plate can be avoided, and the testing precision of failure strength is improved;
(4) and the thickness of a bonding glue layer between the composite material plate and the metal does not need to be accurately controlled, so that the thickness can be as small as possible, and the bonding process can be simplified.
Drawings
FIG. 1 is a schematic cross-sectional view of a joint for testing failure criteria of a composite bonded structure according to the present invention.
FIG. 2 is an exploded view of a joint for testing failure criteria of a composite bonded structure according to the present invention.
Fig. 3 is a side view of two metal rods according to the embodiment of the present invention.
Fig. 4 is a schematic front dimension view of two metal rods according to the embodiment of the present invention.
Fig. 5 is a schematic size diagram of the adhesive layer in the embodiment of the invention.
Fig. 6 is a schematic size diagram of a composite material according to an embodiment of the present invention.
Fig. 7 is a schematic size view of the first non-stick layer in the embodiment of the invention.
Fig. 8 is a schematic size view of a second layer of non-stick adhesive in accordance with an embodiment of the present invention.
Fig. 9 is a schematic view of the testing principle of the joint of the present invention under different stress states.
Detailed Description
The present invention is described in further detail below in order to enable those skilled in the art to practice the invention with reference to the description.
The joint provided by the invention considers the failure of the composite materials on two sides, can test a multi-stress state, and solves the problem that the prior art only has one function, so that the joint provided by the invention has higher test precision and is more reasonable.
As shown in fig. 1 and fig. 2, the joint for testing the failure criteria of the composite material bonding structure provided by the invention comprises: the composite material testing device comprises a first metal test bar 110, a second metal test bar 120, a first adhesive layer 130, a first composite material plate 140, a second composite material plate 150, a second adhesive layer 160, a third adhesive layer 170, a first non-adhesive layer 171, a second non-adhesive layer 180 and a third non-adhesive layer 190, wherein the third adhesive layer 170 adheres the first composite material plate 140 and the second composite material plate 150 together for testing the adhesion strength of the first composite material plate 140 and the second composite material plate 150, and the composite material plate needs to fail in the testing process; the first adhesive layer 130 is disposed on the other side of the first composite material plate 140, and is used for bonding the first composite material plate 140 and the first metal test bar 110 together, and the first metal test bar 110 has a first through hole 111 for connecting with a testing device; the second adhesive layer 160 is disposed on the other side of the second composite material plate 150, and is used to adhere the second composite material plate 150 and the second metal test bar 120 together, the second metal test bar 120 has a second through hole 121, which is also used to connect with a testing device, and the first metal test bar 110 and the second metal test bar 120 are made of the same material; the first adhesive layer 130 and the second adhesive layer 160 are respectively bonded to the first composite material plate 140, the first metal test bar 110, the second composite material plate 150, and the second metal test bar 120 by using a second adhesive (not shown), which is used for assisting a test and cannot fail during the test.
The first non-stick layer 171 is a frame-shaped structure, and the first non-stick layer 171 covers the outer side of the frame of the third adhesive layer 170; the second non-stick adhesive layer 180 is of a frame-type structure, the second non-stick adhesive layer 180 is arranged on the outer side of the frame of the first composite material plate 140, the third non-stick adhesive layer 190 is of a frame-type structure and is arranged on the outer side of the frame of the second composite material plate 150, and the non-stick adhesive layers are adopted in multiple positions, so that the thickness of the adhesive layers can be accurately controlled, the influence of fiber tearing and layering in the boundary area of the composite material plates can be avoided, and the test precision of the composite material adhesive joint failure criterion is improved.
In the joint of the present invention, the thickness of the third adhesive layer 170 is 0.1mm to 0.5mm, the thickness of the first non-stick adhesive layer 171 is the same as the thickness of the third adhesive layer 170, the thickness of the first adhesive layer 130 and the second adhesive layer 160 does not exceed the thickness of the third adhesive layer 170, the bonding area of the first adhesive layer 130 and the second adhesive layer 160 is the same, the bonding area of the third adhesive layer 170 does not exceed the bonding area of the first adhesive layer 130 and the second adhesive layer 160, and the cross-sectional profile of the joint is square or circular, and the square or circular shapes are concentric.
In another embodiment, the first metal test bar 110 and the second metal test bar 120 are made of aluminum alloy, the first composite material plate 140 and the second composite material plate 150 are made of carbon fiber reinforced resin composite material, and the third adhesive layer 170 is made of adhesive
2015, the first adhesive layer 130 and the second adhesive layer 160 use adhesive
AV138M/HV998, the bonding areas of the first adhesive layer 130, the second adhesive layer 160, and the third adhesive layer 170 are the same, the thicknesses of the first adhesive layer 130, the second adhesive layer 160, and the third adhesive layer 170 are the same, the thickness of the first non-stick layer 171 is the same as that of the third adhesive layer 170, the second non-stick layer 180 is disposed outside the frame of the first adhesive layer 130, the third non-stick layer 190 is disposed outside the frame of the second adhesive layer 160, the cross-sectional profile of the joint is square, the specific dimensions are shown in fig. 3-8, and the first metal test bar 110 and the second metal test bar 120 are connected with a testing device through the first through hole 111 and the second through hole 121 for testing, as shown in fig. 9, the joint can test the failure loads under different stress states, and simultaneously considers the tearing influence of the first composite material plate 140 and the second composite material plate 150.
The performances of the first adhesive layer 130, the second adhesive layer 160 and the third adhesive layer 170 satisfy:
wherein S is1α shows different testing angles of normal stress and shear stress, wherein the testing angles are equal to or larger than α DEG and equal to or larger than 0 DEG, and the adhesive area of the first adhesive layer 130 or the second adhesive layer 160 is equal to or larger than 90 DEG1The failure strength, τ, of the first adhesive layer 130 or the second adhesive layer 160 under positive stress1The failure strength of the first adhesive layer 130 or the second adhesive layer 160 in a shear stress state, K is a safety factor, and K is more than or equal to 1.05, S3Is the glue line area, σ, of the third glue line 1703Failure Strength, τ, of the third glue layer 170 under positive stress3The failure strength of the third adhesive layer 170 in a shear stress state;
the properties of the first composite material plate 140 and the third glue layer 170 satisfy:
wherein S is4Is a first composite board140 area, σ4Tensile failure strength, τ, between layers of the first composite sheet 1404Interlaminar shear failure strength of the first composite panel 140;
the performance of the second composite material plate 150 and the third glue layer 170 satisfies:
wherein S is5Is the area, σ, of the second composite sheet 1505Is the interlaminar tensile failure strength, τ, of the second composite sheet 1505Interlaminar shear failure strength of the second composite sheet 150.
In another embodiment, the adhesive of the first adhesive layer 130 or the second adhesive layer 160 has a failure strength under positive stress of σ1The failure strength of the adhesive of the first adhesive layer 130 or the second adhesive layer 160 under the shear stress state is 33MPa1The first adhesive layer 130 or the second adhesive layer 160 has an adhesive layer area S of 28MPa1＝625mm2；
The adhesive of the third adhesive layer 170 has a failure strength of σ under normal stress3The failure strength of the adhesive of the third adhesive layer 170 under the shear stress state is tau under 25MPa325MPa, the adhesive layer area of the third adhesive layer 170 is S3＝625mm2；
The interlaminar tensile failure strength of the first composite sheet 140 is σ427MPa, interlaminar shear failure Strength τ of the first composite sheet 140450MPa, the area of the first composite sheet 140 is S4＝1225mm2；
The interlaminar tensile failure strength of the second composite sheet 150 is sigma527MPa, interlaminar shear failure Strength τ of the second sheet of composite 150550MPa, the area of the second composite sheet 150 is S5＝1225mm2；
The safety coefficient is K which is more than or equal to 1.05, the testing angle of different normal stress and shear stress is α, and the angle of 90 degrees is more than or equal to α degrees and more than or equal to 0 degree;
therefore, the performance of the first adhesive layer 130, the second adhesive layer 160, the third adhesive layer 170, and the first composite material plate 140 and the second composite material plate 150 all satisfy the above condition.
The joint for testing the failure criterion of the composite material bonding structure can test the failure strength of the composite material bonding joint in different stress states (pure shear, pure tension and any tension-shear ratio), and can establish a more accurate failure criterion by considering the fiber tearing or layering effect of the composite material plates on two sides of the adhesive layer; the non-stick adhesive layer is adopted to control the thickness of the adhesive layer of the composite material, so that the adhesive process is simplified, and the fiber tearing or layering influence caused by the fact that the adhesive layer is close to the edge of the composite material plate can be avoided; the non-stick glue layer is wrapped around the composite material plate, so that the influence of residual glue on the fiber tearing or layering of the composite material plate can be avoided; the thickness of the adhesive layer between the composite material plate and the metal does not need to be accurately controlled, the adhesive layer can be as small as possible, and the adhesive process can be simplified.
While embodiments of the invention have been described above, it is not limited to the applications set forth in the description and the embodiments, which are fully applicable to various fields of endeavor for which the invention may be embodied with additional modifications as would be readily apparent to those skilled in the art, and the invention is therefore not limited to the details given herein and to the embodiments shown and described without departing from the generic concept as defined by the claims and their equivalents.
Claims (10)
1. A joint for testing failure criteria of a composite bonded structure, comprising:
a first metal test bar;
a second metal test bar disposed opposite to the first metal test bar;
the first adhesive layer is used for bonding the first metal test bar and the first composite material plate;
the first non-adhesive layer frame is adhered to the outer side of the first composite material plate in a matching mode;
the second adhesive layer is used for bonding the second metal test bar and the second composite material plate;
the second non-adhesive layer frame is bonded on the outer side of the second composite material plate in a matching mode;
a third glue layer for bonding the first composite sheet and the second composite sheet;
and the third non-stick adhesive layer frame is adhered to the outer side of the third adhesive layer in a matching manner.
2. The joint for testing composite bond structure failure criteria of claim 1, wherein the first bondline and the second bondline are the same material.
3. The joint for testing composite bonded structural failure criteria of claim 2, wherein the thickness of the third bondline is between 0.1mm and 0.5 mm.
4. A joint for testing composite bonded structural failure criteria according to claim 3 wherein the first and second metal coupons are of the same material and the first and second composite plates have a thickness of not less than 2 mm.
5. The joint for testing composite bond structure failure criteria of claim 4, wherein the bond areas of the first bondline and the second bondline are the same.
6. The joint for testing composite bond structure failure criteria of claim 5, wherein the bond area of the third bondline does not exceed the bond area of the first bondline and the second bondline.
7. The joint for testing composite adhesive structural failure criteria of claim 6, wherein the thickness of the first bondline and the second bondline does not exceed the thickness of the third bondline.
8. The joint for testing composite bonded structural failure criteria of claim 7, wherein the thickness of the third layer of non-stick glue is the same as the thickness of the third layer of glue.
9. A joint for testing composite material bonding structural failure criteria as set forth in claim 8 wherein the cross-sectional profile of the joint is square or circular and the squares or circles are coaxially disposed.
10. The joint for testing composite bond structure failure criteria of claim 9, wherein the first bondline, the second bondline, and the third bondline have properties that satisfy:
wherein S is1α is the adhesive layer area of the first adhesive layer or the second adhesive layer, the test angle of different positive stress and shear stress is 8932 degrees or more, 90 degrees or more is α degrees or more is 0 degrees or more, sigma degree is more than or equal to1Is the failure strength, tau, of the first or second adhesive layer under positive stress1The failure strength of the first adhesive layer or the second adhesive layer in a shear stress state, K is a safety factor, and K is more than or equal to 1.05, S3Is the glue line area, σ, of the third glue line3Is the failure strength, tau, of the third glue layer under positive stress3The failure strength of the third adhesive layer in a shear stress state is shown;
the performance of the first composite material plate and the third adhesive layer meets the following requirements:
wherein S is4Is the area, σ, of the first composite sheet4Is the interlaminar tensile failure strength, tau, of the first composite panel4The interlaminar shear failure strength of the first composite plate is defined as the interlaminar shear failure strength of the first composite plate;
the performance of the second composite material plate and the third adhesive layer meets the following requirements:
wherein S is5Is the area, σ, of the second composite sheet5Is the interlaminar tensile failure strength, tau, of the second composite sheet5And the interlaminar shear failure strength of the second composite plate is obtained.
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| CN202010134416.8A CN111272650A (en) | 2020-03-02 | 2020-03-02 | Joint for testing failure criterion of composite material bonding structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111751272A (en) * | 2020-07-03 | 2020-10-09 | 北京理工大学 | Ultrasonic detection and tensile calibration test method for bonding strength grade |
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| 中华人民共和国国家质量监督检验检疫总局，中国国家标准化管理委员会: "《GBT 4944-2005 玻璃纤维增强塑料层合板层间拉伸强度试验方法》", 18 May 2005, pages: 1 - 8 * |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111751272A (en) * | 2020-07-03 | 2020-10-09 | 北京理工大学 | Ultrasonic detection and tensile calibration test method for bonding strength grade |
| CN111751272B (en) * | 2020-07-03 | 2021-09-07 | 北京理工大学 | Ultrasonic detection and tensile calibration test method for bonding strength grade |
| US11733210B2 (en) | 2020-07-03 | 2023-08-22 | Beijing Institute Of Technology | Ultrasonic detection and tensile calibration test method for bonding strength grade |
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