Method for manufacturing a conjugate

Abstract

To provide a method for manufacturing a joined body which contributes to simplification of manufacture of a joined body.SOLUTION: A method for manufacturing a joined body according to one form of the present disclosure that is a method for manufacturing a joined body joined by heating composite materials in which fibers are impregnated with a resin including the steps of: heating a plurality of molding dies so that the composite materials fit to each of the plurality of molding dies, and semi-curing the resin of the plurality of composite materials; combining and heating the plurality of molding dies into which the composite materials are fit after semi-curing the resin of the plurality of composite materials, and joining the plurality of composite materials. The plurality of molding dies used when the resin of the composite material is semi-cured and the plurality of molding dies used when the plurality of composite materials are joined are common.SELECTED DRAWING: Figure 4

Description

Technical Field

[0001] The present disclosure relates to a method for manufacturing a bonded body.

Background Art

[0002] Molded articles of composite materials (for example, prepregs) in which resin is impregnated into fibers are widely used for parts of flying bodies such as aircraft because they have high hardness and low weight. When manufacturing such molded articles, for example, composite materials are joined to form a bonded body.

[0003] For example, the method for manufacturing a bonded body of Patent Document 1 is to perform a surface treatment on a first composite material obtained by curing a resin-impregnated fiber to impart a polar functional group, and on the surface of the first composite material to which the polar functional group is imparted, a second composite material in which uncured resin is impregnated into fibers is laminated and heated together with the first composite material, and the first composite material and the second composite body are joined to manufacture a bonded body.

[0004] Here, the method for manufacturing a bonded body of Patent Document 2 is to place a first composite material in which a semi-cured resin is impregnated into fibers by an RTM (Resin Transfer Molding) molding method on a second composite material in which uncured resin is impregnated into fibers via an adhesive, and heat the first composite material and the second composite material to join them via the adhesive to manufacture a bonded body.

Prior Art Documents

Patent Documents

[0005]

Patent Document 1

Patent Document 2

Summary of the Invention

Problems to be Solved by the Invention

[0006] The applicant of the present application has found the following problems. In recent years, in order to shorten the manufacturing period of a joined body, as in the manufacturing method of the joined body of Patent Document 2, the resin of the composite material may be brought into a semi-cured state as a pretreatment of the joining process.

[0007] In such a case, generally, the mold used when bringing the resin of the composite material into a semi-cured state is different from the mold used in the joining process. Therefore, there is a problem that the manufacture of the joined body becomes complicated.

[0008] The present disclosure has been made in view of such problems, and realizes a manufacturing method of a joined body that contributes to simplification of the manufacture of the joined body.

Means for Solving the Problems

[0009] A method for manufacturing a joined body according to an aspect of the present disclosure is a method for manufacturing a joined body in which a composite material in which a resin is impregnated in fibers is heated and joined, a step of heating a plurality of molds while aligning the composite material along each of the plurality of molds to bring the resins of the plurality of composite materials into a semi-cured state; a step of combining and heating the plurality of molds in a state where the composite materials are aligned after bringing the resins of the plurality of composite materials into a semi-cured state to join the plurality of composite materials; comprising the plurality of molds used when bringing the resins of the plurality of composite materials into a semi-cured state are common to the plurality of molds used when joining the plurality of composite materials.

Advantages of the Invention

[0010] According to the present disclosure, it is possible to realize a method for manufacturing a joined body that contributes to simplification of the manufacture of the joined body.

Brief Description of the Drawings

[0011]

Figure 1

Figure 2

Figure 3

Figure 4

Embodiments for Carrying Out the Invention

[0012] Hereinafter, specific embodiments to which the present disclosure is applied will be described in detail with reference to the drawings. However, the present disclosure is not limited to the following embodiments. Also, for clarity of explanation, the following description and drawings are simplified as appropriate.

[0013] First, the configuration of the joined body manufactured by the method for manufacturing a joined body of the present embodiment will be described. In the present embodiment, a wing of an aircraft is manufactured as the joined body. In the following description, for clarity of explanation, a three-dimensional (XYZ) coordinate system will be used.

[0014] FIG. 1 is a view of the wing manufactured by the method for manufacturing a joined body of the present embodiment as seen from the +Z side. FIG. 2 is a cross-sectional view taken along line II-II of FIG. 1. As shown in FIGS. 1 and 2, the wing 1 includes a first outer skin 2, a second outer skin 3, a spar 4, a sleeve 5, and an adhesive member 6.

[0015] The first outer skin 2 is made of a composite material obtained by curing a resin impregnated with fibers, and as shown in FIGS. 1 and 2, it constitutes the outer skin on the +Z side of the wing 1. A notch 2a is formed at the end of the first outer skin 2 on the -X side. The notch 2a is curved convexly on the -X side when viewed from the Y-axis direction.

[0016] The second outer skin 3 is made of a composite material obtained by curing a resin impregnated with fibers, and as shown in FIG. 2, it constitutes the outer skin on the -Z side of the wing 1. A protrusion 3a that fits with the notch 2a of the first outer skin 2 protrudes on the +Z side from the end of the second outer skin 3 on the -X side. The protrusion 3a has a shape corresponding to the notch 2a and is curved convexly on the -X side when viewed from the Y-axis direction.

[0017] The spar 4 is composed of, for example, a composite material obtained by curing a resin impregnated in fibers, and constitutes a reinforcing member of the wing 1. As shown in FIG. 2, the spar 4 has a substantially rectangular columnar shape that is hollow when viewed from the Y-axis direction. The sleeve 5 is fixed to the end portion of the spar 4 on the Y-axis side as shown in FIG. 1, and is, for example, a connecting portion for connecting the spar 4 to the drive shaft of the wing 1. The sleeve 5 has, for example, a cylindrical shape, and the hollow portion of the spar 4 and the hollow portion of the sleeve 5 are continuous in the Y-axis direction.

[0018] The adhesive member 6 is, for example, an adhesive sheet as shown in FIG. 2. The adhesive member 6 is disposed between the notch portion 2a of the first outer skin 2 and the protruding portion 3a of the second outer skin 3, and joins the notch portion 2a of the first outer skin 2 and the protruding portion 3a of the second outer skin 3.

[0019] The adhesive member 6 is disposed between the end portion of the first outer skin 2 on the +X-axis side and the end portion of the second outer skin 3 on the +X-axis side, and joins the end portion of the first outer skin 2 on the +X-axis side and the end portion of the second outer skin 3 on the +X-axis side. Further, the adhesive member 6 is disposed between the first outer skin 2 and the spar 4 and between the second outer skin 3 and the spar 4, and joins the first outer skin 2 and the second outer skin 3 via the spar 4 and the adhesive member 6.

[0020] Next, a method for manufacturing the wing 1 of the present embodiment will be described. In the present embodiment, a first mold used when the resin impregnated in the fibers of the first composite material forming the first outer skin 2 is brought into a semi-cured state and a second mold used when the resin impregnated in the fibers of the second composite material forming the second outer skin 3 is brought into a semi-cured state, and while curing the resin in the semi-cured state in the first composite material and curing the resin in the semi-cured state in the second composite material, the adhesive member 6 is cured, and the first mold and the second mold used when joining the first composite material and the second composite material are commonly used.

[0021] First, a process of bringing the resin of the first composite material forming the first outer skin 2 and the resin of the second composite material forming the second outer skin 3 into a semi-cured state will be described. Here, the first composite material and the second composite material are, for example, general prepregs, and the resin is impregnated in the fibers.

[0022] The fibers are formed as a fabric, woven fabric, or knitted fabric, such as carbon fibers, aramid fibers, nylon fibers, polyester fibers, or glass fibers, or any combination thereof. The resin includes a thermosetting resin, such as, for example, an epoxy resin, a bismaleimide resin, a vinyl ester resin, an unsaturated polyester resin, a phenolic resin, or a silicone resin.

[0023] Figure 3 is a cross-sectional view showing the state when the resin of the first composite material and the resin of the second composite material are in a semi-cured state. In Figure 3, for clarity, the hatching indicating the cross-sectional portions of the first mold and the second mold is omitted.

[0024] First, as shown in Figure 3, while aligning the first composite material 11 along the cavity surface 12a of the first mold 12, a portion 11a forming the notch 2a of the first outer skin 2 is formed. At this time, the cavity surface 12a of the first mold 12 has a concave portion with a shape substantially equal to the outer surface shape of the first outer skin 2. And the first mold 12 incorporates a heating part 12b.

[0025] The heating part 12b includes, for example, a through-hole 12c penetrating the first mold 12 as shown in Figure 3, and a heated liquid or gas as a heat medium is supplied to the through-hole 12c. Therefore, the heating part 12b directly heats the first mold 12 with the heat medium supplied to the through-hole 12c.

[0026] In this way, with the first composite material 11 in a state along the cavity surface 12a of the first mold 12, as shown in Figure 3, the peripheral portion on the Z-axis - side of the first composite material 11 is arranged to substantially coincide with the peripheral portion on the Z-axis - side of the cavity surface 12a of the first mold 12.

[0027] Next, as shown in Figure 3, the first composite material 11 is covered with a packing sheet 13 and packed. At this time, the peripheral portion of the packing sheet 13 may be fitted into a groove 12d formed in the first mold 12 so as to surround the cavity surface 12a of the first mold 12 via a packing 14.

[0028] On the one hand, as shown in FIG. 3, while aligning the second composite material 15 along the cavity surface 16a of the second mold 16, a portion 15a that forms the protruding portion 3a of the second outer skin 3 is formed. At this time, the cavity surface 16a of the second mold 16 is provided with a recess having a shape substantially equal to the outer surface shape of the second outer skin 3. And the second mold 16 incorporates a heating portion 16b.

[0029] The heating portion 16b includes, for example, as shown in FIG. 3, a through portion 16c that penetrates the second mold 16, and a liquid or gas heated as a heat medium is supplied to the through portion 16c. Therefore, the heating portion 16b directly heats the second mold 16 by the heat medium supplied to the through portion 16c.

[0030] In this way, with the second composite material 15 along the cavity surface 16a of the second mold 16, as shown in FIG. 3, the portion 15a that forms the protruding portion 3a of the second outer skin 3 in the second composite material 15 protrudes in the +Z axis direction from the end portion on the -X axis side of the second mold 16, and the peripheral portion on the +Z axis side of the portion that forms the outer surface of the second outer skin 3 in the second composite material 15 is arranged to substantially coincide with the peripheral portion on the +Z axis side of the cavity surface 16a of the second mold 16.

[0031] Next, as shown in FIG. 3, the second composite material 15 is covered with a packing sheet 17 and packed. At this time, it is preferable to fit the peripheral edge portion of the packing sheet 17 into a groove 16d formed in the second mold 16 so as to surround the cavity surface 16a of the second mold 16 via a packing 18.

[0032] Also, when packing the second composite material 15, in order to hold the portion 15a that forms the protruding portion 3a of the second outer skin 3 in the second composite material 15 in a predetermined shape, as shown in FIG. 3, it is preferable to support the portion 15a that forms the protruding portion 3a of the second outer skin 3 in the second composite material 15 with a pressing member 19 such as a mandrel from the +X axis direction.

[0033] At this time, as shown in FIG. 3, when packing the second composite material 15, the packing sheet 17 covers the portion 15a forming the protruding portion 3a of the second outer skin 3 in the second composite material 15, the pressing member 19, and the region where the pressing member 19 is not disposed on the outer surface of the second outer skin 3 in the second composite material 15.

[0034] Next, as shown in FIG. 3, the cavity surface 12a of the first mold 12 and the cavity surface 16a of the second mold 16 are arranged and combined (i.e., clamped) so as to face each other in the Z-axis direction.

[0035] Then, a heat medium is supplied to the through-hole 12c of the heating portion 12b in the first mold 12 and the through-hole 16c of the heating portion 16b in the second mold 16 to heat the first mold 12 and the second mold 16, and the resin of the first composite material 11 and the resin of the second composite material 15 are brought into a semi-cured state.

[0036] As described above, since the first mold 12 and the second mold 16 of the present embodiment incorporate the heating portions 12b and 16b, they can be heated directly as compared with the case where the first mold 12 and the second mold 16 are indirectly heated (i.e., heated from the outside of the first mold 12 and the second mold 16) such as autoclave molding. Therefore, temperature control of the first mold 12 and the second mold 16 is easy.

[0037] Here, the semi-cured state is a state in which functional groups remain on the surfaces of the first composite material 11 and the second composite material 15. For example, the degree of curing of the resin of the first composite material 11 and the resin of the second composite material 15 is about 60 to 80% (preferably 70%).

[0038] However, the degree of curing of the resin of the first composite material 11 and the resin of the second composite material 15 can be appropriately set in consideration of the materials of the resin of the first composite material 11, the resin of the second composite material 15, and the adhesive member 6, and the occurrence of wrinkles in the first composite material 11 and the second composite material 15. The degree of curing can be measured, for example, based on the heat flow curve obtained by differential scanning calorimetry (DSC).

[0039] At this time, the packing sheets 13 and 17 may be vacuumed through vacuum holes (not shown) formed in the first mold 12 and the second mold 16, respectively. Thereby, generation of voids or the like in the first composite material 11 and the second composite material 15 can be suppressed.

[0040] Also, by pressurizing the space S1 surrounded by the first composite material 11, the second composite material 15, and the pressing member 19 and pushing the pressing member 19 toward the X-axis - side, displacement of the pressing member 19 toward the X-axis + side can be suppressed. Thereby, the portion 15a forming the protruding portion 3a of the second outer skin 3 in the second composite material 15 can be held in a predetermined shape. Note that an inner back or the like may be disposed in the space S1, and the pressing member 19 may be pushed toward the X-axis - side by supplying gas to the inner back.

[0041] Thereafter, when the state in which the first mold 12 and the second mold 16 are combined is released and the packing sheets 13 and 17 are removed, the process of semi-curing the resin of the first composite material 11 and the resin of the second composite material 15 is completed.

[0042] Next, the process of joining the first composite material 11 and the second composite material 15 will be described. FIG. 4 is a cross-sectional view showing a state of joining the first composite material and the second composite material. In FIG. 4, for clarity, the hatching indicating the cross-sectional portions of the first mold and the second mold is omitted.

[0043] First, separately, a third composite material 20 in which resin is impregnated into fibers is formed into the shape of the spa 4 and heated to semi-cure the resin of the third composite material 20. Then, a sleeve 5 is fixed to the end portion on the Y-axis - side of the third composite material 20.

[0044] Next, as shown in FIG. 4, a packing 14 is fitted into a groove 12d of a first mold 12 in a state where a first composite material 11 in a semi-cured state of resin is along a cavity surface 12a, and a packing 18 is fitted into a groove 16d of a second mold 16 in a state where a second composite material 15 in a semi-cured state of resin is along a cavity surface 16a. Then, while combining the first mold 12 and the second mold 16, a third composite material 20 is interposed at a predetermined position between the first composite material 11 and the second composite material 15. However, either the packing 14 or the packing 18 may be omitted.

[0045] At this time, the third composite material 20 extends in the Y-axis direction between the first composite material 11 and the second composite material 15. For example, an end portion on the Y-axis + side of the third composite material 20 is arranged in an open state within a space surrounded by the first composite material 11 and the second composite material 15. And the sleeve 5 is accommodated in an accommodation portion formed in the first mold 12 and the second mold 16.

[0046] Also, a portion 15a forming a protruding portion 3a of the second outer skin 3 in the second composite material 15 is fitted into a portion 11a forming a notch portion 2a of the first outer skin 2 in the first composite material 11, and an adhesive member 6 is interposed between the portion 11a forming the notch portion 2a of the first outer skin 2 in the first composite material 11 and the portion 15a forming the protruding portion 3a of the second outer skin 3 in the second composite material 15.

[0047] At the same time, an adhesive member 6 is interposed between a portion on the X-axis + side of the first composite material 11 and a portion on the X-axis + side of the second composite material 15. Also, an adhesive member 6 is interposed between the first composite material 11 and the third composite material 20, and between the second composite material 15 and the third composite material 20.

[0048] Here, the adhesive member 6 preferably has functional groups equal to the resins of the first composite material 11, the second composite material 15, and the third composite material 20. Further, the regions in the first composite material 11 that come into contact with the adhesive member 6, the regions in the second composite material 15 that come into contact with the adhesive member 6, and the regions in the third composite material 20 that come into contact with the adhesive member 6 are preferably subjected to a surface treatment for imparting functional groups, such as plasma treatment or corona treatment.

[0049] Next, a heat medium is supplied to the through-hole 12c of the heating portion 12b in the first mold 12 and the through-hole 16c of the heating portion 16b in the second mold 16 to heat the first mold 12 and the second mold 16. While completely curing the resins of the first composite material 11 and the second composite material 15, the adhesive member 6 is cured to join the first composite material 11, the second composite material 15, and the third composite material 20. However, in the present embodiment, the step of completely curing the resins of the first composite material 11 and the second composite material 15 and the step of curing the adhesive member 6 are carried out simultaneously. However, as a separate step, for example, the step of completely curing the resins of the first composite material 11 and the second composite material 15 may be carried out after the step of curing the adhesive member 6.

[0050] Thereby, the wing 1 in which the first outer skin 2, the second outer skin 3, and the spar 4 are joined can be manufactured. Thus, in the present embodiment, after the resins of the first composite material 11, the second composite material 15, and the third composite material 20 are in a semi-cured state, the third composite material 20 is interposed between the first composite material 11 and the second composite material 15 and joined.

[0051] Therefore, for example, compared with the case of molding and joining the first composite material 11, the second composite material 15, and the third composite material 20 by autoclave molding or the like, the generation of wrinkles in the first composite material 11, the second composite material 15, and the third composite material 20 can be suppressed.

[0052] Also, when the resins of the first composite material 11, the second composite material 15, and the third composite material 20 are in a semi-cured state, functional groups remain on the surfaces of the first composite material 11, the second composite material 15, and the third composite material 20. Therefore, compared with the case where the resins of the first composite material 11, the second composite material 15, and the third composite material 20 are in a fully cured state, the first composite material 11 and the second composite material 15, the first composite material 11 and the third composite material 20, and the second composite material 15 and the third composite material 20 can be firmly joined through fewer adhesive members 6, and as a result, the wing 1 can be lightened.

[0053] Moreover, since the resin of the third composite material 20 is in a semi-cured state, it can be deformed when the third composite material 20 is interposed between the first composite material 11 and the second composite material 15, and errors such as molding errors and dimensional errors of the third composite material 20 can be absorbed.

[0054] Also, as described above, since the first mold 12 and the second mold 16 have built-in heating parts 12b and 16b, the first mold 12 and the second mold 16 can be directly heated as compared with the case of indirectly heating the first mold 12 and the second mold 16 such as autoclave molding. Therefore, temperature control of the first mold 12 and the second mold 16 is easy.

[0055] Also, when the adhesive member 6 has functional groups equal to those of the resin of the first composite material 11, the resin of the second composite material 15, and the resin of the third composite material 20, the bonding force between the first composite material 11 and the second composite material 15, between the first composite material 11 and the third composite material 20, and between the second composite material 15 and the third composite material 20 can be improved as compared with the case where the functional groups of the adhesive member 6 and the resin of the first composite material 11, the resin of the second composite material 15, and the resin of the third composite material 20 are different.

[0056] In addition, when a surface treatment such as plasma treatment or corona treatment is performed on the regions in the first composite material 11 that come into contact with the adhesive member 6, the regions in the second composite material 15 that come into contact with the adhesive member 6, and the regions in the third composite material 20 that come into contact with the adhesive member 6, the bonding strength between the first composite material 11 and the second composite material 15, between the first composite material 11 and the third composite material 20, and between the second composite material 15 and the third composite material 20 can be further improved.

[0057] Here, as shown in FIG. 4, an inner back 21 is disposed in the space S2 on the X-axis - side surrounded by the first composite material 11, the second composite material 15, and the third composite material 20. By pressing the inner back 21, a portion 15a that forms the protruding portion 3a of the second outer skin 3 in the second composite material 15 can be pressed against a portion 11a that forms the notch portion 2a of the first outer skin 2 in the first composite material 11.

[0058] Thereby, the occurrence of peeling of the adhesive member 6 between the portion 11a that forms the notch portion 2a of the first outer skin 2 in the first composite material 11 and the portion 15a that forms the protruding portion 3a of the second outer skin 3 in the second composite material 15 can be suppressed.

[0059] At this time, it is preferable to pressurize the space S3 inside the third composite material 20 and the space S4 on the X-axis + side surrounded by the first composite material 11, the second composite material 15, and the third composite material 20 to suppress the displacement of the third composite material 20 in the X-axis + direction accompanying the pressurization of the inner back 21.

[0060] Incidentally, gas may be supplied to the spaces S3 and S4 from a gas supply hole formed in the first mold 12 or the second mold 16 so as to communicate with the accommodating portion in the first mold 12 and the second mold 16 where the sleeve 5 is accommodated, via the sleeve 5 and the third composite material 20.

[0061] Thus, the manufacturing method of the wing 1 according to this embodiment commonly uses the first mold 12 and the second mold 16 used when the resin of the first composite material 11 and the resin of the second composite material 15 are in a semi-cured state, and the first mold 12 and the second mold 16 used when joining the first composite material 11 and the second composite material 15. Therefore, compared with the case of using different molds in the process of making the resin in a semi-cured state and the process of joining the composite materials, the manufacturing of the wing 1 can be simplified.

[0062] Moreover, when the first mold 12 and the second mold 16 incorporate the heating parts 12b and 16b, the first mold 12 and the second mold 16 can be directly heated as compared with the case of indirectly heating the first mold 12 and the second mold 16 such as autoclave molding. Therefore, the temperature control of the first mold 12 and the second mold 16 is easy, and the manufacturing of the wing 1 can be facilitated.

[0063] Also, when the adhesive member 6 has functional groups equal to those of the resin of the first composite material 11, the resin of the second composite material 15, and the resin of the third composite material 20, the bonding force between the first composite material 11 and the second composite material 15, between the first composite material 11 and the third composite material 20, and between the second composite material 15 and the third composite material 20 can be improved as compared with the case where the functional groups of the adhesive member 6 and the resin of the first composite material 11, the resin of the second composite material 15, and the resin of the third composite material 20 are different.

[0064] The present disclosure is not limited to the above-described embodiment, and can be appropriately changed without departing from the gist. For example, in the above-described embodiment, the resin of the third composite material 20 is in a semi-cured state and interposed between the first composite material 11 and the second composite material 15, but the resin of the third composite material 20 may be in a completely cured state and interposed between the first composite material 11 and the second composite material 15. For example, in the above-described embodiment, the form in which the inner back 21 is disposed in the space S2 when joining the first composite material 11, the second composite material 15, and the third composite material 20 was described. However, a pressing member such as a mandrel having a larger coefficient of thermal expansion than the first mold 12 and the second mold 16 may be disposed in the space S2. For example, the adhesive member 6 in the above-described embodiment is configured by an adhesive sheet. However, not limited to the adhesive sheet, an adhesive member used when joining molded articles of the composite can be used, and it may be in a paste form or a film form. Further, when the composite materials can be joined with the resin of the composite material, the adhesive member 6 may be omitted. For example, in the above-described embodiment, the heating portions 12b of the first mold 12 and the heating portions 16b of the second mold 16 are configured to be heated by supplying a gas or a liquid as a heat medium. However, any configuration may be used as long as the first mold 12 and the second mold 16 can be directly heated. For example, a heater including heating wires embedded in the first mold 12 and the second mold 16 may be used. For example, in the above-described embodiment, the wing 1 was manufactured as the joined body. However, any joined body manufactured by joining composite materials to each other may be used. Therefore, the number of composite materials and molds can be appropriately changed according to the shape of the joined body. Further, depending on the shape of the joined body, it may not be necessary to combine a plurality of molds when bringing the resin of the composite material into a semi-cured state.

Explanation of Reference Numerals

[0065] 1 Wing, 2 First outer skin, 3 Second outer skin, 4 Spar, 6 Adhesive member, 11 First composite material, 12 First mold, 15 Second composite material, 16 Second mold, 19 Pressing member, 20 Third composite material

Claims

1. A method for manufacturing a joined body in which a composite material impregnated with resin is heated and joined, comprising: aligning a first composite material along a first mold and a second composite material along a second mold, opposing the first mold and the second mold, clamping them, and heating to make the resin of the first composite material and the resin of the second composite material in a semi-cured state; after making the resin of the first composite material and the resin of the second composite material in a semi-cured state, releasing the clamping state between the first mold and the second mold; after making the resin of the first composite material and the resin of the second composite material in a semi-cured state, opposing the first mold with the first composite material along it and the second mold with the second composite material along it, clamping them, and heating to join the first composite material and the second composite material; characterized by comprising: the joined body is a wing of a flying object; a method for manufacturing a joined body, wherein the first mold and the second mold used when making the resin of the first composite material and the resin of the second composite material in a semi-cured state are common to the first mold and the second mold used when joining the first composite material and the second composite material.

2. Each of the first mold and the second mold has a built-in heating part; When heating the first mold and the second mold, the first mold and the second mold are heated by their respective heating parts. The method for manufacturing a joined body according to Claim 1.

3. A step of interposing a reinforcing member including a third composite material in which a resin impregnated with fibers is preformed into a preset shape in a semi-cured state or a fully cured state between the first composite material and the second composite material when joining the first composite material and the second composite material is provided, When heating the first mold and the second mold to join the first composite material and the second composite material, the first composite material, the second composite material, and the reinforcing member are joined. The method for manufacturing a joined body according to Claim 1 or 2.

4. A step of interposing an adhesive member between the first composite material and the second composite material to be joined is provided, The resin of the first composite material, the resin of the second composite material, and the adhesive member have equal functional groups. The method for manufacturing a joined body according to Claim 1 or 2.

5. When the resin of the first composite material and the resin of the second composite material are in a semi-cured state, with the portion forming the protruding part that fits into the notch of the first composite material when the first composite material and the second composite material are joined in the second composite material protruding from the second mold, while supporting the portion forming the protruding part of the second composite material with a pressing member disposed inside the second mold, the first mold and the second mold are clamped, and the resin of the portion forming the protruding part of the second composite material is brought into a semi-cured state. The method for manufacturing a joined body according to claim 1 or 2.

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