JP5610881B2 - Composite material mold and manufacturing method thereof - Google Patents

Description

  The present invention relates to a composite material mold and a method for producing the same.

In recent years, a molding jig (mold) in which a core material is coated with a composite material has been developed in order to manufacture a structure such as an aircraft or a windmill with the composite material (Patent Document 1).
The composite material is a molding material including a binding material (matrix) and fine particles or a fibrous material. For example, it is composed of a plastic typified by an epoxy resin and hard fibers made of carbon or glass, and is used as a prepreg or the like.

  When the core material is coated with the composite material, a step of curing the matrix of the composite material in a high temperature and high pressure environment is essential. Therefore, a molding jig in which a core material is coated with a composite material is manufactured by being installed inside a high-temperature and high-pressure pot called an autoclave.

Special Table 2007-521987

  Since the components of the main wing class of aircraft are long and large, inevitably, a large jig is required for the forming jig and the autoclave for manufacturing the forming jig. Therefore, a molding jig for a large structure can be manufactured by an aircraft body manufacturer that owns a large autoclave, but cannot be manufactured by a general jig manufacturer that does not have a large autoclave. There is a problem.

  This invention is made | formed in view of such a situation, Comprising: It aims at providing the manufacturing method of the composite material shaping | molding jig which can be manufactured irrespective of the magnitude | size of an autoclave.

  In order to solve the above problems, the present invention provides a step of processing the upper surface of the core material into a shape corresponding to the shape of the molded body, and the other core material of the core material when the core materials are arranged side by side. Forming a step on the side surface facing the surface, laminating an uncured composite material on the surface of the core material and curing it by heating and pressurizing to form a composite material layer, orthogonal to the side surface Forming a taper portion having a thickness gradually reduced toward the side surface on the composite material layer on the other surface of the core material to be formed, and forming an adhesive on the side surface And bonding the constituent members together, laminating an uncured composite material on the tapered portion, placing a heat source on the composite material, and then covering the composite material and the heat source with a packaging material And vacuuming the inside of the packaging material And curing the composite material by heating at the heat source after, to provide a method of manufacturing a composite mold comprising the steps of polishing the surface of the combined components.

  According to the present invention, since a single composite material mold is manufactured by combining a plurality of constituent members, it is possible to manufacture a composite material mold for a large structure even with a small and medium autoclave. By providing a step on the side surface of the coupling portion between the constituent members, the coupling area is increased and the direction of the coupling surface is dispersed, so that the strength of the coupling portion can be increased. The taper portion provided in the composite material layer can be further enhanced in strength by bonding the constituent members and then filling and curing with an uncured composite material. The composite material laminated | stacked on the taper part can be hardened with the heat source arrange | positioned on top, without using an autoclave.

In one aspect of the present invention, the step of creating the constituent member includes a step of forming a hole in the side surface, and the step of connecting the constituent members to each other arranges the two constituent members while abutting the side surface, Preferably, the method includes a step of inserting one end of the guide member into the hole formed in one component member and inserting the other end of the guide member into another hole formed in the other component member.
By providing holes in the abutting surfaces of the constituent members and connecting the holes of the opposing constituent members with a guide member, the positioning of the constituent members is facilitated.

  In one aspect of the present invention, the taper portion is formed in the composite material layer on the upper surface side of the component member, the step is formed on the side surface on the lower surface side of the component member, and the component members are joined to each other. Thereafter, a step of applying a patch to the step and fixing it with an adhesive, laminating an uncured composite material on the surface of the patch, arranging a heat source on the composite material, and then laminating the stacked composite material And curing with the uncured composite material laminated on the tapered portion.

  The upper surface of the composite material mold is a tool surface with which the workpiece is in contact. When a workpiece is placed on the tool surface, a compressive force is applied to the upper surface. By forming a tapered portion in the joint portion of the upper composite material layer and filling the tapered portion with another composite material, the strength of the joint portion of the composite material layer can be increased. Further, by applying the contact material from the lower surface, it becomes a connecting portion having a strength capable of withstanding the weight of each component member and the shearing force when the material to be molded is placed.

In the above aspect, the tapered portion may be formed in the composite material layer on the lower surface side of the constituent member, and an uncured composite material may be laminated on the surface of the pad according to the shape of the tapered portion.
By providing the taper portion on the lower composite layer, the strength of the joint portion of the lower composite layer can be increased.

In one aspect of the present invention, the tapered portion may be formed so that the core material is exposed at an end portion of the component member.
By exposing the core material to the end portion, it is possible to form a flat bottom surface on the surface of the coupling portion when the two constituent members are disposed by abutting the tapered portion. Accordingly, when a plate-like body such as a prepreg is used as the composite material, the composite material can be arranged more in accordance with the shape of the tapered portion.

  In one aspect of the present invention, it is preferable to install a plurality of angle members on the side surface of the component member. By doing so, the fine adjustment at the time of aligning a structural member becomes possible, and structural members can be combined more accurately.

  In one embodiment of the present invention, the core material is preferably a carbon foam. By doing so, the composite material mold can be reduced in weight.

In the present invention, an upper surface is processed into a shape corresponding to the shape of a molded body, and a core material having a step formed on at least one side surface and another surface of the core material orthogonal to the side surface on which at least the step is formed are provided. A composite material layer having a tapered portion which is provided and has a thickness gradually reduced toward the side surface;
A side surface on which a step of one of the constituent members is formed and a side surface on which a step of the other constituent member is formed are bonded via an adhesive layer, and the taper portion In another aspect, the present invention provides a composite mold having a surface of the bonded component member that is formed with another composite material layer and polished.

  Since the composite material shaping | molding die concerning this invention couple | bonds several structural members, it becomes possible to manufacture the composite material shaping | molding die for large structures even if it is a medium-sized autoclave. Since the step is formed on the side surface of the core material, a composite material mold having a high strength of the joint portion between the constituent members is obtained. Since another composite material layer is formed on the tapered portion provided in the composite material layer, a composite material mold having a higher strength of the joint portion is obtained. Since the surface of the composite material layer is polished, it becomes a composite material mold having a smooth surface having accuracy applicable as a tool surface to be contacted with the workpiece.

In one aspect of the invention, it is preferable that the side surface on which the step is formed has a hole, and includes guide members inserted into holes corresponding to each other in the adjacent component members.
The tapered portion is formed on the composite material layer on the upper surface side of the component member, the step is formed on the side surface on the lower surface side of the component member, and the pad is fixed to the step via an adhesive layer. It is preferable that another composite material layer is formed on the surface of the pad.
Moreover, the said taper part may be formed in the composite material layer of the lower surface side of the said structural member, and the said another composite material layer may be formed in the surface of the said contact material according to the shape of the said taper part.
The tapered portion may be formed so that the core material is exposed at an end portion of the component member.
Moreover, it is preferable that a plurality of angle members are installed on the side surfaces of the constituent members.
The core material is preferably a carbon foam.

  According to the present invention, since a plurality of constituent members are assembled and enlarged, a composite material mold for a large structure can be manufactured even for a medium-sized autoclave.

It is an image figure of the manufacturing method of the composite material shaping | molding die concerning this invention. It is a perspective view which shows the coupling | bonding specification of the composite material shaping | molding die in the manufacturing method of the composite material shaping | molding die concerning this embodiment. It is a perspective view which shows the state after the coupling | bonding of the composite material shaping | molding die of FIG. It is the schematic explaining the manufacturing method of the composite material shaping | molding die concerning this embodiment. It is the schematic of the adhesive strength test 1. FIG. It is the schematic of the adhesive strength test 2. FIG. It is a graph which shows the change of the adhesive strength before and after high temperature exposure. It is a graph which shows an example of the hardening cycle of a composite material layer. It is a graph which shows an example of the hardening cycle of a to-be-molded body.

An embodiment of a method for producing a composite mold according to the present invention will be described with reference to the drawings.
In FIG. 1, the image figure of the manufacturing method of the composite material shaping | molding die concerning this invention is shown. The method for manufacturing a composite material mold according to the present invention is characterized by manufacturing a large composite material mold 100 by combining a plurality of constituent members 1.

  The component 1 includes a core material and a composite material layer. The core material is a carbon foam or the like. By providing the core material, it becomes stronger in bending rigidity than a component member made of only a composite material. The composite material layer is made of a fiber-reinforced resin plate (composite material). The resin reinforced with fibers is, for example, an epoxy resin reinforced with carbon fibers. The size of the constituent member 1 can be appropriately set according to the size of the autoclave to be used. In the present embodiment, the constituent member 1 to be coupled is assumed to have a side of about 0.5 to 2 m. These can be assembled into a composite material mold for producing a molded body of about 6 to 30 m.

A method for manufacturing the composite material mold according to this embodiment will be described with reference to FIGS.
FIG. 2 shows the combined specifications of the composite material mold in the method of manufacturing the composite material mold according to this embodiment. FIG. 3 shows a state after the composite material mold of FIG. 2 is joined. FIG. 4 is a schematic diagram for explaining a method for manufacturing a composite material mold according to this embodiment.

(1) Step of producing component member The core material 2 is fixed with a clamp, and NC processing is performed in the order of the lower surface, the side surface, and the upper surface. Here, “NC” means a control method for instructing the position of the tool with respect to the workpiece with numerical information corresponding thereto in the numerically controlled machine tool. When a carbon foam is used as the core material, NC processing may be performed after a plurality of carbon foams are bonded with an inorganic adhesive to obtain a desired size.

Specifically, as shown in FIGS. 2 and 4, at least one step 5 parallel to the lower surface 6 is formed on a predetermined side surface 4 of the core material 2. Two holes 7 may be formed in the side surface 4 at intervals. In that case, the size of the hole 7 is appropriately set depending on the size of the core material 2, the size and weight of the object to be molded, and the like.
In FIG. 2, the step 5 and the hole 7 are formed only on the side surface 4, but when the component member 1 is formed, the step 5 and the hole 7 are similarly formed on the side surface combined with the other component member 1. . Moreover, when forming the step 5 in step shape, it forms so that the step 5 provided in the two structural members 1 to couple | bond together may mutually be fitted.

  The upper surface 3 of the core material is a molding surface (tool surface) with which the workpiece is in contact, and NC processing is performed according to the shape of the workpiece.

Next, the composite material layer 8 is provided on the surface of the core material 2 other than the side surface on which the step 5 is formed.
A prepreg (composite material) made of a resin reinforced with a film adhesive and fibers is sequentially laminated on the surface of the core material 2. At this time, a plurality of film adhesives and prepregs may be laminated as necessary. For example, when the core material 2 is a porous body, it is preferable to laminate two or more film adhesives. For example, it is preferable to laminate a plurality of prepregs on a tool surface that requires rigidity.
After laminating the prepreg, the periphery is covered with a bag film 9 and pressurized while heating in an autoclave to cure the film adhesive and the prepreg (not shown). Between the prepreg and the back film, a peel ply, a release film, a vent mat, and the like may be appropriately disposed. The curing reaction conditions are appropriately set according to the film adhesive and prepreg used.

Next, as shown in FIG. 2, the tapered portion 10 is formed so that the thickness of the composite material layer gradually decreases toward the end portion coupled with the other component 1. The taper is formed at 15: 1, for example. The tapered portion 10 may be provided not only on the upper surface but also on the lower and side composite material layers.
Moreover, you may form the taper part 10 in the state which exposed the core material to the edge part. A flat bottom surface can be formed on the surface of the coupling portion when the two constituent members are arranged by abutting the tapered portion 10. Accordingly, when a plate-like body such as a prepreg is used as the composite material, the composite material can be arranged more in accordance with the shape of the tapered portion.

  Next, the upper surface of the composite material layer 8 is polished using an abrasive or a compound to obtain a smooth surface having accuracy applicable to the tool surface.

  Next, the angle member 11 is attached with a bolt to the side surface of the component 1 where the composite material layer 8 is formed, and the upper surface hole is reamed. In this embodiment, an aluminum angle member 11 is used.

(2) Step of joining the constituent members together (FIG. 4 (i))
First, the adhesive 12 is applied to at least one of the side surfaces 4 of the constituent member 1a and the constituent member 1b. The adhesive is an inorganic adhesive and is preferably cured at room temperature.
Next, the side surface 4 is butted and the constituent member 1a and the constituent member 1b are arranged, and one end of the guide member 13 is inserted into the hole 7a of the one constituent member 1a. Next, the other end of the guide member 13 is inserted into the hole 7b of the other constituent member 1b to join the constituent member 1a and the constituent member 1b.
For the guide member 13, a material having a linear expansion coefficient close to that of the core material 2 may be used. In the present embodiment, a guide pin made of ceramics is used as the guide member 13. If the linear expansion coefficient of the guide pin 13 is lower than the linear expansion coefficient of the core material 2, it is possible to avoid large expansion when exposed to high temperatures and to apply a load to the core material 2.
Next, a reflector is mounted on the angle member 11 provided on the side surface of the core member, and the position of the constituent member is finely adjusted using a three-dimensional measuring instrument.

(3) Adhesion process of the pad 14 (FIGS. 4 (i) and 4 (ii))
An inorganic adhesive is applied to the step 5a and the step 5b provided on the lower surface side of the constituent member 1a and the constituent member 1b combined in the step (2). A pad 14 according to the shape of the steps 5a and 5b is prepared. An inorganic adhesive is appropriately applied also to the surface of the pad 14 and then bonded to the steps 5a and 5b. If necessary, the inorganic adhesive may be cured while applying a load to the pad 14 from the lower surface side.
In addition, when the step 5a and the step 5b are stepped, the adhesive bonding step may be omitted.

(4) Step of curing the composite material at the tapered portion 10 (FIGS. 4 (ii) and 4 (iii))
A film adhesive 15 is laminated on the tapered portion 10 provided on the upper surface 3 side of the coupling portion of the constituent member 1a and the constituent member 1b. Next, the prepreg cut out with the width | variety matched with the shape of the taper part 10 is laminated | stacked on the taper part 10 (FIG. 3). Moreover, an adhesive film and a prepreg are laminated | stacked so that the surface of the contact material 14 adhere | attached on the lower surface side of the structural member 1a and the structural member 1b may be covered. When the taper portion is provided on the lower surface 6 and the side surface 4, the adhesive film and the prepreg are laminated in the same manner as the upper surface 3 side according to the shape of the taper portion.
After the heat source 16 is arranged on the top of the laminated prepreg so as to cover the prepreg, these are covered with the bag film 9. In the present embodiment, the heat source 16 is a heat blanket. Specifically, a silicon rubber heater or the like is used. A heat conductive sheet 17 such as a copper foil is preferably disposed under the heat source 16. Further, a peel ply, a release film, a vent mat, and the like may be sequentially disposed between the prepreg and the back film 9. In this case, the heat blanket and the copper foil are preferably disposed between the release film and the vent mat.
Next, the bag film 9 is evacuated and then heated with a heat blanket to cure the prepreg. The curing reaction conditions are the same as in step (1) above.

(5) Surface treatment process of the composite material layer 8 in the joint (FIG. 4 (iv))
After cutting the surface of the composite material layer 8 cured in the step (4) so as to be smoothly connected to the surface of the composite material layer 8 formed in the step (1), the step (1) Similarly, the surface of the composite material layer 8 is polished and finished to a smooth surface.

(Adhesive strength test between components)
A carbon foam (CFOAM20; available from Touchetone Research Laboratory, Ltd.) was used as the core material. As adhesives, inorganic adhesives (X-Pando; available from X-Pando Products Company) and epoxy adhesives (ER-0 / EH-208-S; available from limited company Plus Plastics) Using. The inorganic adhesive used was a mixture of 300 g of X-Pando and 67 g of water. The epoxy adhesive used was a mixture of ER-0 and EH-208-S at a ratio of 2: 1.

  Test pieces in which the carbon foam was bonded with an inorganic adhesive or an epoxy adhesive were prepared, and the following two types of adhesive strength tests were performed. The inorganic adhesive was cured by heating at 93 ° C. for 240 minutes. The epoxy adhesive was first cured by heating at 40 ° C. for 24 hours, and then secondarily cured at 180 ° C. for 2 hours.

Adhesive strength test 1 (4-point bending test)
FIG. 5 shows a schematic diagram of the adhesive strength test 1. FIG. A bending load was applied to the bonded portion in a state where the test pieces (each 3 pieces) were exposed to room temperature or a high temperature of 180 ° C. for 900 hours. AG-X 100 kN (manufactured by Shimadzu Corp., load capacity ± 100 kN) was used as a testing machine. As the displacement meter, DT-30F (manufactured by Kyowa Denki Co., Ltd., maximum displacement 30 mm) was used.
Using formula (A), the breaking load (P), test piece dimensions (test piece support span (L ₁ ), load span (L ₂ ), test piece width (w), test piece plate thickness (t)), and Bending stress (S _F ) was calculated from the test conditions, and the strengths were compared.
S _F = 3P (L ₁ −L ₂ ) / 2 wt ² (A)

Adhesive strength test 2 (3-point bending test)
FIG. 6 shows a schematic diagram of the adhesive strength test 2. A bending load and a shear load were applied to the bonded portion in a state where the test pieces (3 pieces each) were exposed to room temperature or a high temperature of 180 ° C. for 900 hours. Bending stress (S _F ) was calculated using equation (B) in the same manner as equation (A), and the strengths were compared.
^{_{S F = 3PL 1 / 2wt 2}} ··· (B)

  According to the above test, in the test piece loaded at normal temperature, the carbon foam portion was broken regardless of the type of adhesive. All test pieces using an inorganic adhesive were broken at the load. It is considered that the strength of the bonded portion is higher than the test results because the load portion is locally cracked and fractures. In the test piece using the epoxy adhesive, some of the test pieces were broken from the load part, but most of the test pieces tended to break at the carbon foam part near the adhesive. As a cause of this, the epoxy adhesive generates a residual stress in the carbon foam during bonding, or the adhesive restrains the deformation of the carbon foam during bending load, and is close to the adhesive of the carbon foam. There is a possibility that cracking is likely to occur.

  FIG. 7 shows the change in adhesive strength before and after high temperature exposure. According to FIG. 7, the adhesive strength decreased about 73% to 80% in the test piece using the epoxy adhesive by being exposed to high temperature. On the other hand, in the test piece using the inorganic adhesive, the decrease in the adhesive strength was about 6% to 16%. From the above results, it was confirmed that when the carbon foams were bonded to each other, the adhesive strength was maintained even after high temperature exposure by using an inorganic adhesive.

  In addition, about the film adhesive used in order to adhere | attach a composite material and a carbon foam in the said embodiment, adhesive strength does not fall by high temperature exposure using L-313 (available from JD Lincoln). This has been confirmed by a separate test.

(Example)
A carbon foam (CFOAM20; available from Touchetone Research Laboratory, Ltd.) was used as the core material. An inorganic adhesive (X-Pando; available from X-Pando Products Company) was used as an adhesive for adhering the carbon foams. As the composite material (prepreg), TRK510-270GMP (available from Mitsubishi Rayon Co., Ltd.) with a thick layer (thickness: 0.65 mm) and a coarse layer on the core material side, and a thin layer on the surface side (thickness) 0.22 mm) and fine TRK3110-270GMP (available from Mitsubishi Rayon Co., Ltd.) was used. The fiber direction of the prepreg was suitably 0 °, ± 45 °, and + 90 °. As the film adhesive, an epoxy film adhesive (L-313) was used.

  According to the above embodiment, two constituent members having dimensions of 500 mm × 500 mm × thickness 132 mm were produced and combined to form a 1,000 mm × 500 mm composite material mold (composite material forming jig). In order to fix the structural member during the machining of the carbon foam and the composite material, a clamp plate made of the composite material was added to the side surface of the structural member.

  As a composite layer on the upper surface, 3 ply of TRK510-270GMP was laminated, and 9 ply of TRK3110-270GMP was laminated. As a composite material layer on the lower surface and the side surface, 3 ply of TRK510-270GMP was laminated, and then 2 ply of TRK3110-270GMP was laminated.

  After the composite material layer was cured by the curing cycle shown in FIG. 8, the composite material layer was NC processed. The surface of the composite layer was subjected to # 1000 water sharpening and finishing material Chemlease # 2100 application, and then polished with a compound to finish the surface.

  It was confirmed that the upper surface of the component member produced above had a high shape accuracy with a deviation from the reference surface of less than 0.1 mm.

After the two constituent members were joined together, the contact material was bonded to the step on the lower surface side. Next, a film adhesive and a prepreg were sequentially laminated on the tapered portion. The prepreg was formed by stacking 3 ply of TRK510-270GMP and then stacking 9 ply of TRK3110-270GMP. At this time, every time 3 ply of prepreg was laminated to remove air remaining between the layers, debulk (Full vacuum × 10 minutes) was performed.
Next, a composite material layer was formed on the surface of the patch. As a composite material layer on the lower surface of the backing material, 5 ply of TRK510-270GMP was laminated, and then 4 ply of TRK3110-270GMP was laminated, followed by debulk (Full vacuum × 10 minutes). As a composite material layer on the side surface of the padding material, 3 ply of TRK510-270GMP was laminated, and then 2 ply of TRK3110-270GMP was laminated, followed by debulk (Full vacuum × 10 minutes).

  On the prepreg, a peel ply, a release film, a copper foil, a silicon rubber heater, and a vent mat were laminated and covered with a bag film. After the bag film was evacuated, the composite material layer was cured by heating with a heat blanket at the same temperature cycle as when the composite material layer of the constituent members was cured.

  The composite material layer formed on the taper part and the surface of the backing material and its surroundings are polished in the same procedure as the composite material layer of the constituent member, and the surface treatment is performed so that the surface where the two constituent members are joined is smoothly connected, and the composite A material forming jig was used.

Using the composite material forming jig prepared above, a molded object was prepared.
On the composite material forming jig produced as described above, 16 layers of prepreg were laminated in a quasi-isotropic manner. A peel ply, a release film, and a vent mat were sequentially laminated thereon, covered with a bag film, and then the bag film was evacuated. This composite material forming jig was placed in an autoclave, and the prepreg was cured by a curing cycle shown in FIG.

  In the process of producing the molded body, the bag film was evacuated and then subjected to a leak check. As a result, it was confirmed that the air leakage amount was the same level as that of a metal forming jig, and there was no practical problem.

  The composite material forming jig was not applied or damaged throughout the process of producing the molded body. Moreover, the tool surface of the manufactured to-be-molded body was connected smoothly, and it was confirmed that there was no step or depression at the joint between the constituent members of the composite material forming jig.

DESCRIPTION OF SYMBOLS 1 Constituent member 2 Core material 3 Upper surface 4 Side surface 5 Stage 6 Lower surface 7 Hole 8 Composite material layer, composite material 9 Back film 10 Tapered part 11 Angle material 12 Adhesive 13 Guide member 14 Adhesive material 15 Film adhesive 16 Heat source 17 Thermal conduction Sheet 18 Sealant 100 Composite mold

Claims (14)

A step of processing the upper surface of the core material into a shape corresponding to the shape of the molded body, and a step of forming a step on a side surface facing the other core material when the core materials are arranged side by side; A step of forming a composite material layer by laminating an uncured composite material on the surface of the core material and applying pressure while heating, and a composite material on the other surface of the core material orthogonal to the side surface Forming a taper portion having a thickness gradually reduced toward the side surface in the layer, and creating a component member including:
Applying an adhesive to the side surface and bonding the components together;
After laminating an uncured composite material on the tapered portion and disposing a heat source on the composite material, the composite material and the heat source are covered with a packaging material, and the inside of the packaging material is evacuated and then the heat source is used. Heating and curing the composite material;
Polishing the surfaces of the combined components; and
A method for manufacturing a composite material mold. Creating the component includes forming a hole in the side surface;
In the step of joining the constituent members, two constituent members are arranged by abutting the side surfaces, one end of the guide member is inserted into the hole formed in one constituent member, and the other constituent member is formed. Inserting the other end of the guide member into another hole,
The manufacturing method of the composite material shaping | molding die of Claim 1. The taper portion is formed on the composite material layer on the upper surface side of the component member, the step is formed on the side surface on the lower surface side of the component member, and the step is applied to the step after joining the component members. And fixing with an adhesive,
Laminating an uncured composite material on the surface of the abutting material, placing a heat source on the composite material, and then curing the laminated composite material together with the uncured composite material stacked on the tapered portion;
The manufacturing method of the composite material shaping | molding die of Claim 1 or Claim 2 provided with these.   The composite material molding die according to claim 3, wherein the tapered portion is formed in a composite material layer on a lower surface side of the constituent member, and an uncured composite material is laminated on a surface of the contact material in accordance with the shape of the tapered portion. Manufacturing method.   The manufacturing method of the composite material shaping | molding die in any one of Claim 1 thru | or 4 which forms the said taper part so that the said core material may be exposed to the edge part of the said structural member.   The manufacturing method of the composite material shaping | molding die in any one of Claims 1 thru | or 5 which installs multiple angle materials in the side surface of the said structural member.   The manufacturing method of the composite material shaping | molding die in any one of Claim 1 thru | or 6 which makes the said core material a carbon foam. A core material whose upper surface is processed into a shape corresponding to the shape of the molded body, and a step is formed on at least one side surface;
A composite material layer having a tapered portion that is provided on the other surface of the core material orthogonal to the side surface on which at least a step is formed and whose thickness is gradually reduced toward the side surface;
Comprising structural members,
The side surface on which the step of one of the constituent members is formed and the side surface on which the step of the other constituent member is formed are bonded via an adhesive layer,
Another composite material layer is formed on the tapered portion,
A composite mold having a surface of the bonded component member that has been polished. The side surface on which the step is formed has a hole;
The composite material shaping | molding die of Claim 8 provided with the guide member inserted in the mutually corresponding hole of the said adjacent structural member. The tapered portion is formed in the composite material layer on the upper surface side of the component member,
The step is formed on the side surface on the lower surface side of the component member,
The composite material mold according to claim 8 or 9, wherein a patch is fixed to the step via an adhesive layer, and another composite layer is formed on a surface of the patch.   11. The composite material according to claim 10, wherein the tapered portion is formed in a composite material layer on a lower surface side of the constituent member, and the another composite material layer is formed on a surface of the contact material in accordance with a shape of the tapered portion. Mold.   The composite material molding die according to any one of claims 8 to 11, wherein the tapered portion is formed so that the core material is exposed at an end portion of the component member.   The composite material shaping | molding die in any one of Claims 8 thru | or 12 with which multiple angle materials were installed in the side surface of the said structural member. The composite material mold according to any one of claims 8 to 12, wherein the core material is a carbon foam.

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