JP2020199523A - Bonding method and composite material bonded by the same - Google Patents

Abstract

To provide a method for bonding a member in a state of sandwiching a reinforcement member, and a composite material bonded by the same.SOLUTION: A reinforcement member 30 is arranged between a first member 28 and a second member 26, a composite material 60 is formed by energizing the first member and making the first member collide with the second member in a state of sandwiching a reinforcement member, and the composite material has a thickness of 0.01 mm to 1 mm.SELECTED DRAWING: Figure 3

Description

The present invention relates to a joining method and a composite material joined by the joining method.

Patent Document 1 proposes a processing method for obtaining a composite material by crimping two metal members with a reinforcing member including carbon fiber and metal fiber sandwiched between them. The composite material obtained from this processing method has high mechanical strength. Therefore, for example, a structural part of a vehicle is press-molded from this composite material to obtain high mechanical strength.

Patent No. 6124794

On the other hand, there is a demand to reinforce parts by joining composite materials to already molded parts. If the part has a flat surface, it is easy to join the composite to that surface by methods such as welding. However, if the component does not have a flat surface, i.e. only a curved surface, the composite material needs to be deformed to fit the curved surface. Also, for weight optimization, the composite material to be joined is preferably as light as possible. Therefore, the thickness of the composite material to be joined is preferably 1 mm or less so that the composite material to be joined can be easily deformed and is lightweight.

Further, there is a demand for giving a composite material material properties other than mechanical strength, such as a large damping capacity. In response to this request, by joining the two members with the reinforcing member and the viscoelastic material sandwiched between them, a composite material having a large damping ability can be obtained. However, since this viscoelastic material is easily deformed when a force is applied, it is not easy to give the composite material the necessary damping capacity. Therefore, the composite material is preferably formed by a method that does not give a large force to the viscoelastic material.

Therefore, an object of the present invention is to provide a method of joining members with a reinforcing member sandwiched between them, and a composite material to be joined by the method. This composite material is easily joined to other parts and improves the material properties of those parts.

In order to achieve this object, the method of joining the first member and the second member according to claim 1 is
A reinforcing member is arranged between the first member and the second member.
The composite material is formed by urging the first member and colliding the first member with the second member while sandwiching the reinforcing member.
The composite material is characterized by having a thickness of 0.01 mm to 1 mm.

The method of the embodiment according to claim 2 is
It is characterized in that an electromagnetic force is applied to the first member to urge the first member.

The method of the embodiment according to claim 3 is
It is characterized in that an explosive force is applied to the first member to urge the first member.

The method of the embodiment according to claim 4 is
The first member is characterized in that the pressure of the gas generated by irradiating the first member with a laser urges the first member.

Further, the method of joining the first member and the second member according to claim 5 is
A reinforcing member and an adhesive are arranged between the first member and the second member.
A composite material is formed by adhering the first member to the second member while sandwiching the reinforcing member.
The composite material is characterized by having a thickness of 0.01 mm to 1 mm.

The method of the embodiment according to claim 6 is
The adhesive is a thermosetting adhesive,
It is characterized in that the first member is adhered to the second member by applying heat to the thermosetting adhesive.

Further, the composite material of the embodiment according to claim 7 is a composite material formed by the method according to any one of claims 1 to 6.
It is characterized by being joined to other parts.

The composite material of the embodiment according to claim 8 is
The reinforcing member includes carbon fiber or glass fiber.

The composite material of the embodiment according to claim 9 is
The first member and the second member seal the reinforcing member.

The composite material of the embodiment according to claim 10 is
The composite material is characterized by having a thickness of 0.01 mm to 0.2 mm.

The composite material of the embodiment according to claim 11 is
When the first member is joined to the part
The first member and the component are made of the same material.

The composite material of the embodiment according to claim 12 is
When the second member is joined to the part
The second member and the component are made of the same material.

According to the invention of claim 1 of the present application, it is possible to provide a method of colliding and joining members with a reinforcing member sandwiched between them. Composites joined in this way are easily joined to other parts to improve mechanical strength.

According to the invention of claim 2 of the present application, it is possible to provide a method of joining members by electromagnetic molding while sandwiching a reinforcing member. Composites joined in this way are easily joined to other parts to improve mechanical strength.

According to the third aspect of the present application, it is possible to provide a method of joining members by explosive welding while sandwiching a reinforcing member. Composites joined in this way are easily joined to other parts to improve mechanical strength.

According to the invention of claim 4 of the present application, it is possible to provide a method of irradiating a member with a laser in a state where the reinforcing member is sandwiched and generating laser ablation to cause the members to collide and join. Composites joined in this way are easily joined to other parts to improve mechanical strength.

According to the invention of claim 5 of the present application, it is possible to provide a method of bonding and joining the members with the reinforcing members sandwiched between them. Composites joined in this way are easily joined to other components to improve damping.

According to the invention of claim 6 of the present application, it is possible to provide a method of bonding and joining the members with the reinforcing members sandwiched between them. Composites joined in this way are easily joined to other components to improve damping.

According to claim 7 of the present application, it is possible to provide a composite material that can be easily bonded to other parts.

According to the invention of claim 8 of the present application, it is possible to provide a composite material including a reinforcing member having a high mechanical strength and a large elastic modulus.

According to the invention of claim 9 of the present application, it is possible to provide a composite material in which the end portion of the reinforcing member is configured so as not to easily cause electrolytic corrosion with other parts.

According to the invention of claim 10 of the present application, it is possible to provide a composite material which is easily bonded to other parts.

According to the invention according to claim 11 of the present application, it is possible to provide a composite material configured so that electrolytic corrosion does not easily occur between a member of the composite material and other parts.

According to the invention of claim 12 of the present application, it is possible to provide a composite material configured so that electrolytic corrosion does not easily occur between a member of the composite material and other parts.

It is the schematic which shows the electromagnetic molding apparatus in the case of obtaining a composite material by electromagnetic molding which concerns on embodiment of this invention. It is a schematic diagram which shows the state of the 1st member, the 2nd member, and the reinforcing member when the electromagnetic force is not applied to the 1st member in the case of obtaining a composite material by electromagnetic molding. It is a schematic diagram which shows the state of the 1st member, the 2nd member, and the reinforcing member when the electromagnetic force is applied to the 1st member in the case of obtaining a composite material by electromagnetic molding. It is a graph which shows the relationship between the thickness which a 1st member (iron) and a 2nd member (aluminum) have and the energy required for joining in order to obtain a composite material which has a thickness of 1mm or less. It is a side view of the composite material seen from the line V of FIG. It is a schematic diagram which shows the state of a composite material and other parts when an electromagnetic force is applied to a composite material in the case of joining a composite material to another part by electromagnetic molding. An outline showing the states of the first member, the second member, and the reinforcing member when the explosive force is not applied to the first member when the composite material is obtained by explosive welding according to another embodiment. It is a figure. Schematic diagram showing the state of the first member, the second member, and the reinforcing member when the explosive force is applied to the first member when the composite material is obtained by explosive welding according to another embodiment. Is. The first member, the second member, and the reinforcing member when the first member is not urged by the laser ablation when the composite material is obtained by generating the laser ablation according to another embodiment. It is a schematic diagram which shows the state of. The first member, the second member, and the reinforcing member when the first member is urged by the laser ablation when the composite material is obtained by generating the laser ablation according to another embodiment. It is the schematic which shows the state. The state of the first member, the second member, and the reinforcing member when heat is applied to the thermosetting adhesive when a composite material is obtained with the thermosetting adhesive according to another embodiment. It is a schematic diagram which shows.

Hereinafter, embodiments of the joining method according to the present invention will be described with reference to the accompanying drawings together with the composite material obtained from the joining method.

[1. Joining due to collision between members]
[1.1: Electromagnetic molding]
FIG. 1 shows a schematic configuration of an electromagnetic molding apparatus 100 according to an embodiment of the present invention. The electromagnetic molding device 100 is a molding device that joins a conductive member (first member) to a member to be joined (second member).

As shown in FIG. 1, the electromagnetic molding apparatus 100 generally has a lower structure 10 and an upper structure 12 arranged on the lower structure 10.

The lower structure 10 includes a rectangular parallelepiped-shaped conductor 14 extending from the front side to the back side of FIG. The conductor 14 is electrically connected to the pulse generation circuit 16. The pulse generation circuit 16 comprises a general charge / discharge circuit, includes a DC power supply 18, a capacitor 20, and a switch 22, and by opening and closing the switch 22, the electric charge stored in the capacitor 20 is instantaneously flowed to the conductor 14. It is configured to be able to.

The superstructure 12 includes a rectangular parallelepiped-shaped, highly rigid fixing portion 24 extending from the front side to the back side of FIG. Further, the superstructure 12 is a jig (for example, a spacer) arranged below the fixing portion 24 to support the end portion of the joined member 26 so that the joined member (second member) 26 described later does not fall. ) (Not shown).

[1.1.1: Molding method]
An example of a molding method using the electromagnetic molding apparatus 100 having the above-described configuration will be described with reference to FIGS. 1 and 2. In actual molding, the plate-shaped conductive member (first member) 28 extending from the front side to the back side in the drawing is installed above the conductor 14 with a gap between the conductor 14 and the conductor 14. .. In the embodiment, the reinforcing member 30 is composed of a plurality of strands such as ropes or strings, is arranged from the front side to the back side in the drawing, and is placed on a substantially central portion of the upper surface of the conductive member 28. The member to be joined (second member) 26 is a plate-shaped member extending from the front side to the back side in the drawing, and is arranged below the fixing portion 24. In the embodiment, the width of the member to be joined 26 is the same as or substantially the same as the width of the conductive member 28. Therefore, the entire surface of the member to be joined 26 faces substantially the entire surface of the conductive member 28 with the reinforcing member 30 interposed therebetween. For the sake of explanation, the member to be joined 26 and the reinforcing member 30 are shown with a sufficient gap between them, but in actual molding, the distance between the member to be joined 26 and the reinforcing member 30 is both. It is set to the most suitable value for joining.

In the above-mentioned state, the pulse generation circuit 16 connected to the conductor 14 applies a pulse current 40 represented by a long-dotted line, which consists of a single pulse having a pulse width of about 100 μsec or less and about 10 kA to about 200 kA, to the conductor 14.

As a result, as shown in FIG. 1, a momentary magnetic field 42 indicated by the alternate long and short dash line is generated around the conductor 14. At the same time, by electromagnetic induction, the induced current 44 indicated by the alternate long and short dash line flows inside the conductive member 28 in the direction opposite to the pulse current 40 (the direction from the back side to the front side in FIG. 1). As a result, the upward electromagnetic force 46 indicated by the two-point chain line is generated in the direction orthogonal to the magnetic field 42 and the induced current 44, so that the conductive member 28 flies toward the upper member to be joined 26. It is momentarily urged to collide with the member to be joined 26 with a large force, and the conductive member 28 and the member to be joined 26 are joined with the reinforcing member 30 sandwiched between them (see FIG. 3). The impact when the conductive member 28 collides with the member to be joined 26 is absorbed by the fixing portion 24.

In the above-described embodiment, for example, the conductive member 28 is composed of an iron plate having a thickness of about 0.5 mm. The reinforcing member 30 is configured by arranging a plurality of toes having a diameter of about 0.3 mm, which are composed of a large number of filaments of a long fiber bundle in which a large number of carbon fibers (single fibers) are bundled, in parallel. The member 26 to be joined is composed of an aluminum plate having a thickness of about 0.5 mm.

As shown in the graph of FIG. 4, when joining a conductive member 28 having a thickness of about 0.5 mm made of an iron plate and a member 26 having a thickness of about 0.5 mm made of an aluminum plate, a pulse is formed. The generation circuit 16 needs to apply electrical energy of about 12 to 14 kJ to the conductor 14 within the energy region 50. When the applied energy is a region below the energy region 50, that is, less than about 12 kJ, the conductive member 28 and the member to be joined 26 are not sufficiently joined. On the other hand, when the applied energy exceeds the region above the energy region 50, that is, about 14 kJ, either the conductive member 28 or the member to be joined 26 may be damaged.

By applying energy of about 12 to 14 kJ to the conductor 14, the pulse generation circuit 16 makes a conductive member 28 having a thickness of about 0.5 mm made of an iron plate and a thickness of about 0.5 mm made of an aluminum plate. The members to be joined 26 are joined with the reinforcing member 30 sandwiched between them to obtain a composite material 60 having a thickness of about 1 mm. In this case, a characteristic wavy pattern 62 appears at the joining interface between the conductive member 28 made of an iron plate and the joined member 26 made of an aluminum plate (see FIG. 3).

In the above-described embodiment, the conductive member 28 made of an iron plate and the bonded member 26 made of an aluminum plate each have a thickness of about 0.5 mm, but each have a thickness of about 0.1 mm. You may. Further, the toe of the reinforcing member 30 may have a diameter of about 0.06 mm. In this case, the pulse generation circuit 16 applies an energy of about 8 kJ to the conductor 14 to obtain a composite material 60 having a thickness of about 0.2 mm. Therefore, when the conductive member 28 made of an iron plate and the member 26 made of an aluminum plate are joined, the energy applied to the conductor 14 by the pulse generation circuit 16 is appropriately adjusted to be 0.01 mm to 1 mm. A composite material 60 having a desired thickness is obtained in between, preferably between 0.1 mm and 1 mm.

In the above-described embodiment, the conductive member 28 is made of iron, but may be made of a metal material other than iron, for example, the same aluminum as the member to be joined 26. On the other hand, the member 26 to be joined may be a metal material other than aluminum, for example, the same iron or resin as the conductive member 28. In any case, as in FIG. 4, the energy applied to the conductor 14 by the pulse generating circuit 16 based on the relationship between the thickness of the conductive member 28 and the member to be joined 26 and the energy required for joining. Need to be determined. Further, the reinforcing member 30 may be a fiber material other than carbon fiber, for example, glass fiber. Further, when the composite material 60 obtained by the above method is joined to another part described later, the material of the conductive member 28 or the member to be joined 26 is the same as that of the part so that electrolytic corrosion does not easily occur. It is preferable to have.

In the above-described embodiment, the length of the reinforcing member 30 in the direction from the back side to the front side in FIGS. 1, 2 and 3 is preferably shorter than the length of the conductive member 28 and the member to be joined 26. In this case, a composite material 60 is obtained in which the conductive member 28 and the member to be joined 26 seal the reinforcing member 30 (see FIG. 5). Since the reinforcing member 30 is configured so as not to be exposed to the outside, the end portion of the reinforcing member 30 does not easily undergo electrolytic corrosion with other parts.

[1.1.2: Joining to other parts]
The composite material 60 formed by the above method improves the mechanical strength (including both proof stress (breaking strength) and rigidity (deformation strength, Young's modulus)) of the component by being joined to another component. Has the effect of causing.

For example, FIG. 6 shows a situation in which the composite material 60 is joined to another component 70. The component 70 has a curved surface 72 on which stress is easily concentrated. On the other hand, since the composite material 60 has a thickness of 1 mm or less, it can be easily deformed according to the shape of the curved surface 72. Therefore, by deforming the composite material 60 in advance according to the shape of the curved surface 72, the composite material 60 is easily joined to the component 70 without creating a gap between the curved surface 72 and the composite material 60. In FIG. 6, the method of joining the composite material 60 to the component 70 is the above-mentioned electromagnetic molding, but it may be joined by generating explosive welding or laser ablation, which will be described later. Regardless of which method is used, a characteristic wavy pattern 74 appears at the bonding interface between the composite material 60 and the component 70.

[1.2: Explosion welding]
FIG. 7 shows a schematic configuration of the explosion welding device 200 according to another embodiment. The explosive welding device 200 is a molding device that joins a flying member (first member) to a member to be joined (second member).

As shown in FIG. 7, the explosion welding device 200 generally has a lower structure 210 and an upper structure 212 arranged on the lower structure 210.

The lower structure 210 includes a rectangular parallelepiped-shaped highly rigid fixing portion 214 extending from the front side to the back side in FIG. 7. The fixing portion 214 has a jig (for example, a vise) for fixing the end portion of the member to be joined (second member) 216 to be described later, which is arranged on the upper surface of the fixing portion 214 (not shown).

The superstructure 212 includes a rectangular parallelepiped explosive 218 extending from the front side to the back side of FIG. 7. The explosive 218 has an electric detonator 220 located on the left side of the upper surface of the explosive 218. The electric detonator 220 is connected to the detonation control unit 222 and has a structure for detonating the explosive 218 by receiving an electric signal transmitted from the detonation control unit 222. Further, the superstructure 212 has a jig (for example, a spacer) for supporting an end portion of a flying member (first member) 224, which will be described later, arranged on the lower surface of the explosive 218 (not shown). The flying member 224 is supported so as to fly toward the member to be joined 216 after the explosive 218 explodes.

Using the explosive welding device 200 having the above configuration, the plate-shaped member to be joined (second member) 216 extending from the front side to the back side of FIG. 7 is located at a substantially central portion of the upper surface of the fixing portion 214. Will be installed. In the embodiment, the reinforcing member 226 is composed of a plurality of strands such as a rope or a string, is arranged from the front side to the back side in FIG. 7, and is placed on a substantially central portion of the upper surface of the member to be joined 216. The flying member (first member) 224 is a plate-shaped member extending from the front side to the back side in FIG. 7, and is arranged below the explosive 218. In the embodiment, the width of the member to be joined 216 is the same as or substantially the same as the width of the flying member 224. Therefore, the entire surface of the member to be joined 216 faces almost the entire surface of the flying member 224 with the reinforcing member 226 interposed therebetween. For the sake of explanation, the flying member 224 and the reinforcing member 226 are shown with a sufficient gap between them in FIG. 7, but in actual molding, the distance between the flying member 224 and the reinforcing member 226 is both. It is set to the most suitable value for joining.

The electric detonator 220 ignites when the detonator control unit 222 transmits an electric signal with the joined member 216, the flying member 224, and the reinforcing member 226 arranged as described above. As a result, the explosive 218 explodes, and the generated explosive force 228 urges the flying member 224 toward the member to be joined 216 (see FIG. 8). The flying member 224 collides with the member to be joined 216 with a large force, and the flying member 224 and the member to be joined 216 are joined with the reinforcing member 226 sandwiched between them to obtain a composite material 260. The impact when the flying member 224 collides with the member to be joined 216 is absorbed by the fixing portion 214.

In the above embodiment, for example, the flying member 224 is composed of an iron plate. The reinforcing member 226 is configured by arranging a plurality of tows made of a large number of filaments of a long fiber bundle in which a large number of carbon fibers (single fibers) are bundled in parallel. The member to be joined 216 is composed of an aluminum plate.

Therefore, similarly to the above-mentioned electromagnetic molding, the thickness or diameter of the member to be joined 216, the flying member 224, and the reinforcing member 226, and the energy generated when the explosive 218 explodes are appropriately adjusted to be 0.01 mm to 1 mm. In the meantime, a composite material 260 having a desired thickness, preferably between 0.1 mm and 1 mm, is obtained.

Further, similarly to the composite material obtained from the above-mentioned electromagnetic molding, the composite material 260 is deformed in advance according to the shape of the other parts, so that it can be easily joined to the other parts without forming a gap, and the other parts can be easily joined. It has the effect of improving the mechanical strength of parts.

[1.3: Joining by generating laser ablation]
FIG. 9 shows a schematic configuration of the laser irradiation device 300 according to another embodiment. The laser irradiation device 300 is a molding device that joins a flying member (first member) to a member to be joined (second member) by generating laser ablation.

As shown in FIG. 9, the laser irradiation device 300 generally has a lower structure 310 and a superstructure 312 arranged on the lower structure 310.

The lower structure 310 includes a rectangular parallelepiped-shaped highly rigid fixing portion 314 extending from the front side to the back side in FIG. 9. The fixing portion 314 has a jig (for example, a vise) for fixing the end portion of the member to be joined (second member) 316, which will be described later, arranged on the upper surface of the fixing portion 314 (not shown).

The superstructure 312 has a laser irradiator 318. The laser irradiator 318 has a laser oscillator 320, a mirror 322, and a lens 324. The laser output from the laser oscillator 320 may be a YAG laser, a CO ₂ laser, or any other laser. The laser irradiator 318 is configured to irradiate the laser oscillated from the laser oscillator 320 from the lens 324 via the mirror 322. Further, the superstructure 312 has a jig (for example, a spacer) for supporting an end portion of a flying member (first member) 326 which will be described later and is arranged below the laser irradiator 318 (not shown). The flying member 326 is supported so as to fly toward the member to be joined 316 after the laser is irradiated from the laser irradiator 318 to the upper surface of the flying member 326 and laser ablation occurs on the upper surface of the flying member 326. There is.

Using the laser irradiation device 300 having the above configuration, the plate-shaped member to be joined (second member) 316 extending from the front side to the back side of FIG. 9 is located at a substantially central portion of the upper surface of the fixing portion 314. Will be installed. In the embodiment, the reinforcing member 328 is composed of a plurality of strands such as a rope or a string, is arranged from the front side to the back side in FIG. 9, and is placed on a substantially central portion of the upper surface of the member to be joined 316. The flight member (first member) 326 is a plate-shaped member extending from the front side to the back side in FIG. 9, and is arranged below the laser irradiator 318. In the embodiment, the width of the member to be joined 316 is the same as or substantially the same as the width of the flying member 326. Therefore, the entire surface of the member to be joined 316 faces almost the entire surface of the flying member 326 with the reinforcing member 328 interposed therebetween. For the sake of explanation, the flying member 326 and the reinforcing member 328 are shown with a sufficient gap between them in FIG. 9, but in actual molding, the distance between the flying member 326 and the reinforcing member 328 is both. It is set to the most suitable value for joining.

When the laser irradiator 318 irradiates the flying member 326 with the laser in the state where the joined member 316, the flying member 326, and the reinforcing member 328 are arranged as described above, the upper surface of the flying member 326 shown by the one-point chain line is shown. A phenomenon (laser ablation) in which the gas evaporates and is emitted as a gas occurs around the position 330 where the laser is irradiated (see FIG. 10). As a result, the flying member 326 is urged to fly toward the member to be joined 316. The flying member 326 collides with the member to be joined 316 with a large force, and the flying member 326 and the member to be joined 316 are joined with the reinforcing member 328 sandwiched between them to obtain a composite material 360. The impact when the flying member 326 collides with the member to be joined 316 is absorbed by the fixing portion 314.

In the above embodiment, for example, the flying member 326 is composed of an iron plate. The reinforcing member 328 is configured by arranging a plurality of tows made of a large number of filaments of a long fiber bundle in which a large number of carbon fibers (single fibers) are bundled in parallel. The member to be joined 316 is composed of an aluminum plate.

Therefore, similarly to the above-mentioned electromagnetic molding, the thickness or diameter of the member to be joined 316, the flying member 326, and the reinforcing member 328, and the energy of the laser emitted from the laser irradiator 318 are appropriately adjusted to obtain 0. A composite material 360 having a desired thickness between 01 mm and 1 mm, preferably between 0.1 mm and 1 mm is obtained.

Further, similarly to the composite material obtained from the above-mentioned electromagnetic molding or explosive welding, the composite material 360 is deformed in advance according to the shape of the other parts, so that it can be easily joined to the other parts without forming a gap. , Has the effect of improving the mechanical strength of other parts.

[2. Adhesive bonding]
FIG. 11 shows a schematic configuration of the adhesive heating device 400 according to the embodiment of the present invention. The adhesive heating device 400 is a molding device that joins a joining member (first member) to a member to be joined (second member) using a thermosetting adhesive.

As shown in FIG. 11, the adhesive heating device 400 generally has a lower structure 410 and an upper structure 412 arranged on the lower structure 410.

The lower structure 410 includes a rectangular parallelepiped-shaped highly rigid fixing portion 414 extending from the front side to the back side of FIG. The fixing portion 414 has a jig (for example, a vise) for fixing the end portion of the member to be joined (second member) 416 to be described later, which is arranged on the upper surface of the fixing portion 414 (not shown).

The superstructure 412 includes a rectangular parallelepiped-shaped heat transfer portion 418 extending from the front side to the back side of FIG. The heat transfer unit 418 is electrically connected to the power supply 420 and is configured to emit a high temperature at which the thermosetting adhesive described later can be cured. Further, the superstructure 412 is configured to apply a force from above to a joining member (first member) 422 arranged below the heat transfer portion 418.

[2.1: Adhesive method]
Using the adhesive heating device 400 having the above configuration, the plate-shaped member to be joined (second member) 416 extending from the front side to the back side in FIG. 11 is a substantially central portion of the upper surface of the fixing portion 414. Will be installed in. In the embodiment, the reinforcing member 424 is composed of a plurality of strands such as a rope or a string, is arranged from the front side to the back side of FIG. 11, and is placed on a substantially central portion of the upper surface of the member to be joined 416. Further, the thermosetting adhesive 426 is applied to the entire upper surface of the member to be joined 416 so as to cover the reinforcing member 424. The joining member (first member) 422 is a plate-shaped member extending from the front side to the back side in FIG. 11, and is arranged on the lower surface of the heat transfer portion 418 in a state of being in contact with the thermosetting adhesive 426 from above. Will be done. In the embodiment, the width of the member to be joined 416 is the same as or substantially the same as the width of the member 422 to be joined. Therefore, the entire surface of the member to be joined 416 faces almost the entire surface of the joining member 422 with the reinforcing member 424 and the thermosetting adhesive 426 interposed therebetween.

With the members to be joined 416, the joining members 422, and the reinforcing member 424 arranged as described above, the heat transfer portion 418 applies heat to the joining member 422, so that the heat is transferred to the thermosetting adhesive 426. As a result, the thermosetting adhesive 426 is cured, and the joining member 422 and the member to be joined 416 are joined with the reinforcing member 424 and the thermosetting adhesive 426 sandwiched between them to obtain a composite material 460.

In the above-described embodiment, for example, the joining member 422 is composed of an iron plate having a thickness of about 0.3 mm. The reinforcing member 424 is configured by arranging a plurality of tows having a diameter of about 0.2 mm composed of a large number of filaments of a long fiber bundle in which a large number of carbon fibers (single fibers) are bundled in parallel. The member to be joined 416 is composed of an aluminum plate having a thickness of about 0.3 mm. In this case, the resulting composite material 460 has a thickness of about 0.8 mm. By appropriately adjusting the thickness or diameter of the member to be joined 416, the joining member 422, and the reinforcing member 424, the composite material 460 having a desired thickness between 0.01 mm and 1 mm, preferably between 0.1 mm and 1 mm. Is obtained.

Further, the joining member 422 may be made of a metal material other than iron, for example, the same aluminum or resin as the member to be joined 416. On the other hand, the member to be joined may be a metal material other than aluminum, for example, the same iron or resin as the member 422 to be joined. Further, the reinforcing member 424 may be a fiber material other than carbon fiber, for example, glass fiber. Further, when the composite material 460 obtained by the above method is joined to another part described later, the material of the joining member 422 or the member to be joined 416 is the same as that of the part so that electrolytic corrosion does not easily occur. Is preferable.

A thermosetting adhesive 426 is used so that the joining member 422 and the member to be joined 416 are joined with the reinforcing member 424 sandwiched between them, but other adhesives such as pressure-sensitive adhesives (adhesives) are used. It may be used. In this case, it is not necessary to heat the adhesive, and the superstructure 412 may include a pressurizing portion instead of the heat transfer portion 418.

[2.2: Adhesion to other parts]
The composite material 460 molded by the above method has an effect of improving the damping ability of the component by being joined to another component by the elastic modulus of the reinforcing member 424 and the thermosetting adhesive 426.

Similar to the composite material obtained from the above-mentioned electromagnetic molding, explosive welding, or joining by generating laser ablation, the composite material 460 is pre-deformed to the shape of other parts without creating gaps. It is easily joined to other parts and has the effect of improving the damping ability of other parts. In this case, it is preferable to use a thermosetting adhesive as a method for joining the composite material 460 and other parts.

28,224,326,422: First member (conductive member, flying member, joining member)
26,216, 316, 416: Second member (member to be joined)
30,226,328,424: Reinforcing member 60,260,360,460: Composite material 426: Adhesive

Claims (12)

A method of joining a first member and a second member.
A reinforcing member is arranged between the first member and the second member.
The composite material is formed by urging the first member and colliding the first member with the second member while sandwiching the reinforcing member.
A method characterized in that the composite material has a thickness from 0.01 mm to 1 mm. The method according to claim 1, wherein an electromagnetic force is applied to the first member to urge the first member. The method according to claim 1, wherein an explosive force is applied to the first member to urge the first member. The method according to claim 1, wherein the pressure of the gas generated by irradiating the first member with a laser urges the first member. A method of joining a first member and a second member.
A reinforcing member and an adhesive are arranged between the first member and the second member.
A composite material is formed by adhering the first member to the second member while sandwiching the reinforcing member.
A method characterized in that the composite material has a thickness from 0.01 mm to 1 mm. The adhesive is a thermosetting adhesive and
The method according to claim 5, wherein the first member is adhered to the second member by applying heat to the thermosetting adhesive. The composite material formed by the method according to any one of claims 1 to 6.
A composite material characterized by being joined to other parts. The composite material according to claim 7, wherein the reinforcing member includes carbon fiber or glass fiber. The composite material according to claim 7 or 8, wherein the first member and the second member seal the reinforcing member. The composite material according to any one of claims 7 to 9, wherein the composite material has a thickness of 0.01 mm to 0.2 mm. When the first member is joined to the part
The composite material according to any one of claims 7 to 10, wherein the first member and the component are made of the same material. When the second member is joined to the part
The composite material according to any one of claims 7 to 11, wherein the second member and the component are made of the same material.

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