JP2008055898A - Fiber-reinforced composite component and production process of structure using the same - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a fiber-reinforced composite component for quick and inexpensive production of a fiber-reinforced composite structure and a production process of the structure using the same. <P>SOLUTION: The fiber-reinforced composite structure is produced by aligning and joining separate parts 2 and 3 to a fiber-reinforced composite component 1 based on protrusions 12 and 13; wherein the component 1 is equipped with the protrusions 12 and 13 which have information for identifying the separate components 2 and 3 and locating their joining points. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

  The present invention relates to a fiber reinforced composite material part capable of producing a fiber reinforced composite material structure quickly and inexpensively, and a method for producing a structure using the same.

  Conventionally, when manufacturing a structure such as an aircraft fuselage or wing by combining multiple parts made of fiber reinforced composite material such as carbon fiber reinforced plastic (CFRP), each part is placed in a predetermined position and bonded. ing. However, in order to place each component at an accurate position, a large assembly jig is used, or an optical positioning device (for example, the positional relationship between components is detected based on the hole of the component, and the positional relationship stored in advance. And a device for moving and positioning a component based on the difference between the detected positional relationship and the detected positional relationship, and the manufacturing cost is high.

  Therefore, US Pat. No. 5,560,102 (Patent Document 1) discloses a method of manufacturing an aircraft fuselage using self-locating detail parts that determine the arrangement of each part with reference to an alignment hole. Has proposed. Specifically, the position of the rivet bonding hole in the structure is determined in advance by CAD, and the obtained position of each rivet bonding hole is stored in the CAD / CAM main frame as the position of the hole provided in each part, By controlling the NC drill based on the joint position information downloaded from the CAD / CAM main frame (position information of the joint hole varies depending on each part), through holes (positioning holes) are provided in each part. Each component is arranged with reference to the alignment hole. With this method, a highly accurate structure can be manufactured with a small number of steps. However, when manufacturing an aircraft structure, a large number of parts are combined. Therefore, unless the combination and arrangement position of the parts to be joined can be recognized quickly, it cannot be efficiently manufactured. In the method of Patent Document 1, since only the alignment holes are provided, the combination and arrangement position of the parts to be joined may not be recognized quickly.

U.S. Pat.No. 5,560,102

  Accordingly, an object of the present invention is to provide a fiber reinforced composite part capable of producing a fiber reinforced composite structure quickly and inexpensively.

  Another object of the present invention is to provide a method of manufacturing a structure comprising such a fiber reinforced composite part.

  As a result of diligent research in view of the above object, the inventors of the present invention have provided a fiber reinforced composite material component with a protrusion having identification information and joint position information of other parts to be joined, and thus the fiber reinforced composite material structure can be quickly and The present inventors have found that it can be manufactured at low cost and have come up with the present invention.

  That is, the fiber-reinforced composite material part of the present invention is characterized in that a protrusion having identification information and joining position information of other parts to be joined is provided.

  The method of the present invention for manufacturing a fiber reinforced composite material structure by joining a fiber reinforced composite material part and another part, the identification information and joining position information of the other part to be joined to at least one fiber reinforced composite material part. A protrusion having a protrusion is provided, and the other part is aligned with the fiber-reinforced composite material part using the protrusion.

  Preferably, the information is at least one selected from the group consisting of the shape, size, number and arrangement of the protrusions, and marks provided on the protrusions. It is preferable that the shape, size, number, and arrangement of the protrusions are set so as to engage with the joint portion of the other component. In order to align the other part with the fiber-reinforced composite part having such a protrusion, the protrusion and the joint of the other part may be engaged. It is preferable to provide a stepped portion or a recessed portion that engages with the protrusion of the fiber-reinforced composite material part at the joint part of the other part. Marks corresponding to the protrusions and the other parts may be provided.

  In a preferred embodiment of the present invention, the fiber-reinforced composite part has a pair of I-shaped protrusions, and the other part has a rectangular plate-like joint that engages with the I-shaped protrusions, By engaging the rectangular plate-shaped joint portion with the I-shaped protrusion, the other part is matched with a joint position set in advance with respect to the fiber-reinforced composite part.

  In another preferred embodiment of the present invention, the fiber-reinforced composite part has a pair of L-shaped protrusions, and the other part has a rectangular plate-like joint that engages with the L-shaped protrusions. Then, by engaging the rectangular plate-like joint portion with the L-shaped protrusion, the other part is matched with a joint position set in advance with respect to the fiber-reinforced composite material part.

  According to the present invention, other parts to be joined to the fiber-reinforced composite material part can be quickly identified, and the parts can be accurately and quickly aligned, so that a highly accurate structure can be manufactured with fewer steps. . Therefore, when the fiber-reinforced composite material part of the present invention is used, a fiber-reinforced composite material structure used for an aircraft fuselage, wing, and the like can be manufactured quickly and inexpensively.

[1] Fiber Reinforced Composite Part FIG. 1 shows a beam-like fiber reinforced composite part according to an embodiment of the present invention. This fiber reinforced composite material part 1 is formed by curing a prepreg in which a reinforcing fiber is impregnated with a matrix resin, a trapezoidal flat plate portion 10, flange portions 11 and 11 ′ protruding from both side edges, and a flat plate It has I-shaped projections 12, 12, 13, 13 provided on both sides of the part 10. One flange portion 11 projects perpendicularly to the flat plate portion 10, and the other flange portion 11 ′ projects in a direction inclined with respect to the flange portion 11. The protrusions 12 and 13 have identification information and joining position information of other parts joined to the fiber reinforced composite material part 1. In this embodiment, in order to identify other parts, the length L ₁ between the outer ends of the protrusions 12 and 12 and the length L ₂ between the outer ends of the protrusions 13 and 13 are shown in FIG. It is the same as to 2 (e) and longitudinal length L ₃ and L ₄ of the first additional component 2 and a second other component 3 of the rectangular plate-shaped joints 23 and 33 shown in FIG. 3 .

  As shown in FIG. 2 (e), the first other component 2 includes a flat plate portion 20, flange portions 21, 21 ′ protruding from both side edge portions on both sides, and vertical from each end of the flat plate portion 20. And a rectangular plate-like joint 23 extending in the direction. One flange portion 21 is flat, and the other flange portion 21 ′ is curved. Step portions 23 a and 23 a having the same length as the protrusions 12 are provided at both ends of the rectangular plate-like joint portion 23. As shown in FIGS. 2 (a) to 2 (d), the first other component 2 is attached to the flat plate portion 10 of the fiber reinforced composite component 1 so that the protrusions 12 and 12 and the step portions 23a and 23a are engaged with each other. When the joint part 23 is brought into contact with each other, the positions of the other parts 2 in the X direction and the Y direction with respect to the fiber reinforced composite part 1 are determined, and the other parts 2 are joined to the fiber reinforced composite part 1 in advance. Can be placed in position.

  As shown in FIG. 3, the second other component 3 includes a flat plate portion 30, flange portions 31 and 31 ′ protruding from both side edge portions on both sides, and a rectangular shape extending vertically from each end portion of the flat plate portion 30. And a plate-like joint portion 33. One flange 31 is flat and the other flange 31 'is curved. Similarly to the first other component 2, the rectangular plate-like joint portion 33 of the second other component 3 has step portions 33b and 33b that engage with the projections 13 and 13 at both ends. The other parts 3 are arranged at joint positions set in advance with respect to the fiber-reinforced composite material part 1.

As shown in FIG. 4, if the length L ₃ equal intervals L ₁ and a rectangular plate-like joint 23 between the outer ends of the projections 12 and 12, the first other parts 2 of the junction 23 It is not necessary to have a stepped portion. When the joint portion 23 is brought into contact with the flat plate portion 10 so that the positions of the outer end portions of the protrusions 12 and 12 coincide with the positions of both end portions of the rectangular plate-like joint portion 23, the fiber-reinforced composite material part 1 is contacted. The first other component 2 can be placed at a preset joining position. As will be described later, the alignment in the vertical direction and the horizontal direction is performed in a state where the fiber reinforced composite part 1 and the other part 2 are placed on the surface plate with the flat flange portions 11 and 21 facing downward. Is preferred. When the fiber reinforced composite part 1 and the other part 2 are arranged at a preset joining position, the flange portions 11 and 21 form a single plane. The same applies to the joining of the second other component 3.

  The shape, size, number, and arrangement of the protrusions 12 and 13 can be arbitrarily set as long as the first other component 2 and the second other component 3 can be arranged at preset positions. Further, the shapes and sizes of the joints 23 and 33 of the components 2 and 3 are not limited to those shown in FIGS. As shown in FIG. 5 (a) and FIG. 5 (b), U-shaped recesses 23b and 23b having the same length as the projections 12 and 12 are formed on the edge of the joint 23 of the first other component 2. You may provide in the position engaged with the protrusions 12 and 12. FIG.

  FIG. 6 shows a fiber reinforced composite component according to another embodiment of the present invention. In FIG. 6, the same parts and portions as those in FIG. 1 are denoted by the same reference numerals. This fiber reinforced composite material part 1 is the same as that shown in FIG. 1 except that the letters “A” and “B” are provided as marks on the I-shaped protrusions 12 and 13, respectively. The marks provided on the protrusions 12 and 13 are not limited to characters, and may be numbers, symbols indicating the numbers of other parts, materials, or combinations including them.

  In order to identify other parts to be joined to the fiber-reinforced composite part 1 shown in FIG. 6, a mark 24 made of the letter “A” is provided on the first other part 2 as shown in FIG. A mark consisting of the letter “B” is provided on the other part 3 (see FIG. 3). The method of arranging the first other part 2 and the second other part 3 on the fiber-reinforced composite part 1 shown in FIG. 6 may be the same as described above.

FIG. 8 illustrates a fiber reinforced composite component according to yet another embodiment of the present invention. In FIG. 8, the same parts and portions as those in FIG. 1 are denoted by the same reference numerals. This fiber reinforced composite part is the same as the fiber reinforced composite part shown in FIG. 1 except that the protrusions 12 and 13 are L-shaped. As shown in FIGS. 8 and 9, the shape, size, number and arrangement of the L-shaped protrusions 12 and 13 are adapted to the shape and size of the joint 23 of the first other component 2, and the L-shaped protrusion The distance L ₅ between the parallel portions 12 and 12 is the same as the length L ₃ of the joint 23. Therefore, both corner portions of the joint portion 23 are accurately engaged with the inner corner portions of the L-shaped projections 12 and 12, and the parts 1 and 2 can be adjusted to a preset joint position. Thus, if the protrusions 12 and 12 are L-shaped, the fiber reinforced composite part 1 and the first other part 2 can be provided without providing the step part 23a and the recessed part 23b in the joint part 23 of the first other part 2. The component 2 can be easily adjusted to a preset joining position. The interval L ₆ between the parallel portions of the protrusions 13 and 13 is the same as the length L ₄ of the joint portion 33 of the second other component 3 (see FIG. 3), and the inner side of the L-shaped protrusions 13 and 13 is the same. The corners fit with both corners of the joint 33.

  FIG. 10 shows a fiber reinforced composite component according to yet another embodiment of the present invention. In FIG. 10, the same parts and portions as those in FIG. 1 are denoted by the same reference numerals. This fiber-reinforced composite material part 1 is the same as the fiber-reinforced composite material part shown in FIG. 8 except that four L-shaped projections 12 are provided. Since the shape, size, number and arrangement of the L-shaped projections 12 conform to the shape and size of the rectangular plate-like joint 23 of the first other component 2, the four corners of the joint 23 are four. By engaging with the inner corner of the L-shaped projection 12, the parts 1 and 2 can be precisely matched to a preset joining position.

[2] Manufacturing method of fiber reinforced composite structure A fiber reinforced composite structure is manufactured by aligning other parts to the fiber reinforced composite part 1 and joining or bonding them with fasteners such as rivets and bolts. To do. Although it is not limited, as shown in FIG. 11, when the parts 1 and 2 are aligned on the surface plate 5 with the flat flange portions 11 and 21 facing down, the X direction and Y direction of the parts 1 and 2 will be described. Can be easily and accurately determined. The same applies when the other component 3 is aligned with the fiber-reinforced composite material component 1.

  FIG. 12 shows an example of an aircraft fuselage structure using the fiber-reinforced composite material part of the present invention. The fiber reinforced composite parts 2 and 3 are joined to the flat plate portion 10 of the fiber reinforced composite part 1 having L-shaped protrusions 12 and 13 by fasteners 50, and the L-shaped protrusions 22 of the fiber reinforced composite parts 2 and 3 are joined. , 32, the fiber reinforced composite material part 4 having the joint 43 is joined by the fastener 50. However, other parts to be joined to the fiber reinforced composite material part of the present invention are not limited to fiber reinforced composite parts, and may be aluminum alloy parts or the like. Therefore, the fiber reinforced composite material structure is not limited to a structure composed of only fiber reinforced composite material parts, and may have parts other than the fiber reinforced composite material parts. The structure shown in FIG. 12 can be used on an aircraft floor.

[3] Manufacturing Method of Fiber Reinforced Composite Part Taking the beam-like fiber reinforced composite part 1 shown in FIG. 1 as an example, the manufacturing method of the fiber reinforced composite part of the present invention will be described below.

(1) Mold
(a) Shape FIGS. 13 and 14 show an example of a mold for forming the beam-like fiber-reinforced composite part 1 shown in FIG. The mold includes upper and lower molds 6 and 7 having cavities 60 and 70 that form the flat plate portion 10 and the flange portions 11 and 11 ′ of the fiber reinforced composite part 1, and the upper and lower dies 6 and 7; The side molds 8 and 8 are in close contact with each other.

  As shown in FIGS. 13 (a) and 13 (b), the cavity 60 of the upper mold 6 includes a horizontal portion 60a that forms the flat plate portion 10 of the fiber reinforced composite part 1 and a flange of the fiber reinforced composite part 1. It has a vertical part 60b that forms the part 11 and an inclined part 60c that forms the flange part 11 '. The upper mold 6 is provided with a plurality of holes 66 into which the heads 90a of the pins 90 are inserted. A groove 61 for accommodating the resin leak prevention seal 91 is formed along the outer periphery of the cavity 60, and a flange portion 62 is formed between the cavity 60 and the groove 61. The horizontal portion 60a is provided with recesses 63, 63, 64, 64 for forming the protrusions 12, 12, 13, 13 of the fiber reinforced composite part 1.

  As shown in FIG. 14 (a), in order to remove the molded fiber-reinforced composite material part 1 from the upper mold 6, a flat surface such as a flat-blade screwdriver is provided on the inner surface (end surface 60d of the cavity 60) of the flange portion 62 of the upper mold 6. A shallow groove 65 for inserting a proper tool is appropriately provided.

  As shown in FIG. 13A and FIG. 13C, the lower mold 7 has a shape corresponding to the upper mold 6. The cavity 70 of the lower mold 7 forms a horizontal part 70a that forms the flat plate part 10 of the fiber reinforced composite part 1, a vertical part 70b that forms the flange part 11 of the fiber reinforced composite part 1, and a flange part 11 '. And an inclined portion 70c. Each rectangular convex portion 77a is provided with a plurality of holes 76 into which the pins 90 are inserted. When the pin head 90a is inserted into the hole 66 of the upper mold 6 and the main body of the pin 90 is inserted into the hole 76 of the lower mold 7, the upper mold 6 and the lower mold 7 are accurately positioned. A groove 71 for accommodating the resin leakage prevention seal 91 is formed along the outer periphery of the cavity 70, and a flange portion 72 is formed between the cavity 70 and the groove 71. The horizontal portion 70a is provided with recesses 73, 73, 74, 74 for forming the protrusions 12, 12, 13, 13 of the fiber reinforced composite part 1.

  As shown in FIG. 14B, a flat tool for removing the molded fiber-reinforced composite material part 1 from the lower mold 7 is also inserted into the inner surface of the flange portion 72 of the lower mold 7 (end surface 70d of the cavity 70). A shallow groove 75 is provided.

  Since the cured fiber reinforced composite part 1 tends to be thicker by about 0.1 mm after the mold is opened, the total thickness of the cavities 60 and 70 of the upper mold 6 and the lower mold 7 is about 0.1 mm. It is preferable to make it smaller than the target thickness.

(b) Material Examples of the material constituting the upper mold 6 and the lower mold 7 include cast iron, steel (for example, JIS SS400), carbon steel (for example, JIS S45C-H), and the like. As the cast iron, one having a low linear expansion coefficient marketed under the trade name “Novinite” from Enomoto Casting Co., Ltd. is preferable. Examples of the material constituting the side mold 8 include aluminum.

  Examples of the material for the pin 90 include alloy steel (for example, JIS SCM435H). The material of the seal 91 is preferably rubber having heat resistance that can withstand the curing temperature, and examples thereof include fluorine-containing rubber such as polytetrafluoroethylene (PTFE), silicone rubber, and the like. As a commercial product of PTFE seal, GORE-TEX No.3300 (manufactured by Japan Gore-Tex Co., Ltd.) can be mentioned.

(2) Manufacturing process
(a) Prepreg Lamination Step Resin is filled in the holes 63 and 64 of the upper mold 6 and the holes 73 and 74 of the lower mold 7 in advance. It is preferable to use the same resin as the prepreg matrix resin. A plurality of trapezoidal cloth-like prepregs are stacked on the upper mold 6 and the lower mold 7. As shown in FIG. 15 (a), the prepreg laminates 1a and 1b on the upper die 6 and the lower die 7 each have a surplus.

  The prepreg is formed by impregnating a matrix resin into a cloth made of reinforcing fibers. The reinforcing fiber is not particularly limited and is appropriately selected from carbon fiber, aramid fiber, glass fiber, boron fiber, and the like according to the use. The matrix resin is preferably a thermosetting resin, and is appropriately selected from epoxy resin, polyurethane, unsaturated polyester, bismaleimide resin, phenol resin, and the like according to the use. When the panel-like fiber reinforced composite 1 is used as an aircraft fuselage component, the reinforcing fiber is preferably a carbon fiber, and the matrix resin is preferably an epoxy resin.

(b) Trimming process of surplus thickness As shown in FIG. 15 (b), the surplus thickness of the flange portion 11a of the prepreg laminate 1a is cut along the end surface 60d of the cavity 60 of the upper mold 6 by a trimming tool 92 such as a cutter. Trimming is performed, and the surplus thickness of the flange portion 11b of the prepreg laminate 1b is trimmed along the end surface 70d of the cavity 70 of the lower mold 7. Trimming is usually performed at room temperature. A seal 91 is mounted in the groove 61 of the upper mold 6 and the groove 71 of the lower mold 7. Silicone pieces are filled into the groove 65 of the upper mold 6 and the groove 75 of the lower mold 7. As shown in FIG. 15 (c), the pins 90 are inserted into the holes 76 of the lower mold 7 and their heads 90a are inserted into the holes 66 of the upper mold 6 so that the prepreg laminates 1a and 1b are in contact with each other. The upper mold 6 is placed on the mold 7.

  In the present invention, surplus trimming is performed from the uncured prepreg laminates 1a and 1b that can be easily trimmed, so that a fiber-reinforced composite having a good cut surface can be easily compared with the conventional method of trimming a cured prepreg molded body. Can be manufactured.

(c) Lamination process of flange part prepreg As shown in FIGS. 15 (d) and 15 (e), in order to reinforce the flange parts 11 and 11 ′, the strip-like prepregs 1c and 1c are made of reinforcing fibers and matrix resin The prepreg laminates 1a and 1b are laminated on the flange portions 11a and 11b and the flange portions 11′a and 11′b via the filler 1d. In this way, a prepreg assembly 1 ′ in which the prepreg laminates 1a and 1b, the strip-shaped prepreg 1c, and the filler 1d are integrated is obtained.

(d) Curing Step As shown in FIG. 16, the side molds 8 and 8 are attached to the side surfaces of the combined upper mold 6 and lower mold 7 to support the flange portion of the prepreg assembly 1 ′. As shown in FIG. 17, the entire mold is placed on a base 93 and covered with a bag film 94. The inside of the bag film 94 is depressurized from a pipe 95 connected to a vacuum pump. An adhesive seal 96 is placed between the bag film 94 and the base 93 so that a vacuum state can be maintained.

  The bag film 94 is heated while being kept in a vacuum state (see FIG. 18) to cure the matrix resin. Although heating can be performed in an oven or the like, it is preferably performed while pressurizing in an autoclave. The heating temperature varies slightly depending on the type of thermosetting resin, but is preferably 120 to 180 ° C. When using an autoclave, it is preferable to pressurize to about 3-6 MPa.

(e) Demolding process The molds 6 to 8 are removed from the fiber-reinforced composite part 1 obtained. As shown in FIG. 19, a screw thread is provided in the hole 66 of the upper mold 6. The upper die 6 and the lower die 7 can be easily separated by screwing a bolt 97 into the threaded hole 66 and pushing the head 90a of the pin 90 at its tip. A flat tool 98 such as a flat-blade screwdriver is inserted into the groove 65 provided in the flange portion 62 of the upper mold 6 to separate the fiber reinforced composite material part 1 from the upper mold 6. As shown in FIG. 20, a flat tool 98 is also inserted into the groove 75 provided in the flange portion 72 of the lower mold 7, and the fiber reinforced composite material part 1 is lifted from the lower mold 7 to be separated.

(3) Mold size setting In order to prevent deterioration of dimensional accuracy due to thermal expansion during heat curing, the fiber reinforced composite part 1 (prepreg assembly 1 ') and the mold have a linear expansion coefficient as close as possible. Is preferred. Specifically, the linear expansion coefficient of CFRP used for the fiber-reinforced composite material part 1 is about 2.6 × 10 ⁻⁶ / ° C., so novinite grade CS-5 [linear expansion coefficient: 2.5 × 10 ⁻⁶ / ° C. ( 200 ° C.)] or CN-5 [Linear expansion coefficient: 2.7 × 10 ⁻⁶ / ° C. (200 ° C.)] is preferably used. However, when the difference between the linear expansion coefficients of the two is relatively large, it is preferable to determine the room temperature dimensions of the cavities of the molds 6 and 7 so as to have the same dimensions as the fiber-reinforced composite material part 1 at the curing temperature.

The accuracy of the dimensions of the flat portion 10 of the fiber-reinforced composite member 1 is important to the design length and W _1, the length of the cavity in which the design length is obtained as W _2. When the temperature rises from room temperature to the curing temperature, as shown in FIG. 21, the length W ₁ of the flat plate portion 10 becomes W ₁ + ΔW ₁ (= α ₁ · W ₁ · ΔT), and the cavity length W ₂ becomes W ₂ + ΔW. ₂ (= α ₂ · W ₂ · ΔT). Here, α ₁ is the linear expansion coefficient of the fiber reinforced composite material part 1, α ₂ is the linear expansion coefficient of the lower mold 7, and ΔT is the difference (° C.) between the room temperature and the curing temperature. At the curing temperature, the length of the flat plate portion 10 is the same as the length of the cavity, so that W ₁ + α ₁ · W ₁ · ΔT = W ₂ + α ₂ · W ₂ · ΔT holds. Therefore, W ₂ is represented by the following formula (1).
W ₂ = W ₁ × (1 + α ₁ · ΔT) / (1 + α ₂ · ΔT) (1)

  When the fiber reinforced composite material part 1 is taken out from the molds 6 and 7, the angle between the flat plate portion 10 and the flange portions 11 and 11 'of the fiber reinforced composite material component 1 tends to slightly decrease. The angle formed by the horizontal portions 60a, 70a and the vertical portions 60b, 70b of the cavities 60, 70 and the angle formed by the horizontal portions 60a, 70a and the inclined portions 60c, 70c are made larger than the angle in the final product. It is preferable to leave.

1 is a perspective view showing a fiber-reinforced composite material part according to an embodiment of the present invention. It is a fragmentary perspective view which shows the example of joining of the other components with respect to a fiber reinforced composite material component. It is a fragmentary sectional enlarged view which shows the fiber reinforced composite material components and other components which should be joined. FIG. 3 is an enlarged partial cross-sectional view illustrating a state in which the fiber-reinforced composite material part of FIG. 2B and other parts are joined. It is a fragmentary top view which shows the joined fiber reinforced composite material component and other components. It is the elements on larger scale which show the junction part of the other components in Fig.2 (a). It is a fragmentary perspective view which shows another example which has arrange | positioned another component to the fiber reinforced composite material component of FIG. It is a fragmentary perspective view which shows another example which has arrange | positioned another component to the fiber reinforced composite material component of FIG. It is a fragmentary perspective view which shows an example which has arrange | positioned another component to the fiber reinforced composite material component by another embodiment of this invention. It is the elements on larger scale which show the junction part of the other components of Fig.5 (a). FIG. 6 is a perspective view showing a fiber reinforced composite component according to yet another embodiment of the present invention. It is a fragmentary perspective view which shows the state which has arrange | positioned other components to the fiber reinforced composite material component of FIG. FIG. 6 is a perspective view showing a fiber reinforced composite component according to yet another embodiment of the present invention. It is a fragmentary perspective view which shows an example which has arrange | positioned another component to the fiber reinforced composite material component of FIG. It is a fragmentary perspective view which shows an example which has arrange | positioned other components to the fiber reinforced composite material component by another embodiment of this invention. It is a fragmentary perspective view which shows the other components aligned with the fiber reinforced composite material component of FIG. 1 on a surface plate. It is a perspective view which shows an example of the structure for aircraft fuselages using the fiber reinforced composite material component of this invention. It is a perspective view which shows an example of the shaping | molding die for the fiber reinforced composite material part of FIG. FIG. 14 is a view showing the upper mold of FIG. 13 (a) from various directions. FIG. 14 is a view showing the lower mold of FIG. 13 (a) from various directions. FIG. 14 is an enlarged perspective view showing a portion A of FIG. 13 (a). FIG. 14 is an enlarged perspective view showing a portion B of FIG. 13 (a). It is a side view which shows the state which mounted the prepreg laminated body in the upper mold | type (lower mold). It is a side view which shows a mode that the surplus part of the prepreg laminated body mounted in the upper mold | type (lower mold) is excised. It is a perspective view which shows the state in which the prepreg laminated body which cut off the surplus thickness was accommodated in the cavity of the upper mold | type and the lower mold | type. It is a side view which shows the state which match | combined the upper mold | type and the lower mold | type which accommodated the prepreg laminated body which trimmed the surplus meat. It is sectional drawing which shows a mode that a strip | belt-shaped prepreg is laminated | stacked on the flange part of a prepreg laminated body after combining an upper mold | type and a lower mold | type. It is a side view which shows the state which attached the side type | mold to the combined upper type | mold and lower type | mold. It is sectional drawing which shows a mode that a prepreg assembly is coat | covered with a bag film with a bag film, and deaerates. It is sectional drawing which shows the state which hold | maintained the prepreg assembly under the vacuum. It is a fragmentary sectional view which shows a mode that a volt | bolt is screwed in the hole of an upper mold | type in order to isolate | separate an upper mold | type and a lower mold | type. It is a fragmentary perspective view which shows a mode that a flat tool is inserted in the groove | channel provided in the flange part of the lower mold | type in order to isolate | separate a fiber reinforced composite material part from a lower mold | type. It is sectional drawing which shows the dimension in the curing temperature of a lower mold | type and a fiber reinforced composite. It is a graph which shows the dimensional change by the temperature change of a fiber reinforced composite material component and a shaping | molding die.

Explanation of symbols

1. Fiber reinforced composite material parts
10 ... flat plate
11, 11 '・ ・ ・ Flange part
12,13 ... Protrusions
1a, 1b ... Prepreg laminate
10a, 10b ... flat plate
11a, 11a ', 11b, 11b' ... Flange
1c ・ ・ ・ Strip prepreg
1d ・ ・ ・ Filler
1 '... Prepreg assembly 2, 3, 4 ... Other parts
20, 30 ... Flat plate
21, 21 ', 31, 31' ・ ・ ・ Flange part
22, 32 ... projection
23, 33, 43 ... Junction
23a, 33a ... Step
23b ・ ・ ・ Recess
24 ... mark 5 ... surface plate
50 ... Fastener (rivet)
6 ... Upper mold
60 ... cavity
60a ・ ・ ・ Horizontal part
60b ・ ・ ・ Vertical part
60c ・ ・ ・ Inclined part
60d ・ ・ ・ End face
61 ... Groove
62 ・ ・ ・ Flange
63, 64 ... recess
65 ・ ・ ・ Groove
66 ... Hole 7 ... Lower mold
70 ・ ・ ・ Cavity
70a ・ ・ ・ Horizontal part
70b ・ ・ ・ Vertical part
70c ・ ・ ・ Inclined part
70d ・ ・ ・ End face
71 ... Groove
72 ・ ・ ・ Flange
73, 74 ... recess
75 ・ ・ ・ Groove
76 ... Hole 8 ... Side type
90 ... pin
90a ・ ・ ・ Head
91 ・ ・ ・ Seal for preventing resin leakage
92 ・ ・ ・ Trimming tool
93 ・ ・ ・ Base
94 ・ ・ ・ Bag film
95 ... Suction tube
96 ・ ・ ・ Adhesive seal
97 ... Bolt
98 ・ ・ ・ Flat tool

Claims (12)

A fiber reinforced composite material part comprising a fiber reinforced composite material and provided with protrusions having identification information and joint position information of other parts to be joined. The fiber reinforced composite part according to claim 1, wherein the information is represented by at least one selected from the group consisting of the shape, size, number and arrangement of the protrusions, and marks provided on the protrusions. Fiber reinforced composite parts characterized by 3. The fiber-reinforced composite part according to claim 2, wherein the other part has a joint part having a stepped part or a recessed part with which a protrusion of the fiber-reinforced composite part is engaged. . 4. The fiber-reinforced composite material part according to claim 2, wherein marks corresponding to the protrusions and the other parts are provided. 5. The fiber-reinforced composite part according to claim 1, wherein the protrusions of the fiber-reinforced composite part are a pair of I-shaped protrusions, and the other parts engage with the I-shaped protrusions. A rectangular plate-like joint that engages with the I-shaped protrusion, thereby aligning the other part with a preset joint position with respect to the fiber-reinforced composite part. Fiber reinforced composite parts characterized in that they can be used. 5. The fiber-reinforced composite part according to claim 1, wherein the protrusions of the fiber-reinforced composite part are a pair or more of L-shaped protrusions, and the other parts engage with the L-shaped protrusions. A rectangular plate-like joint that engages with the L-shaped protrusion, thereby aligning the other part with a preset joint position with respect to the fiber-reinforced composite material part. Fiber reinforced composite parts characterized by that. In a method of manufacturing a fiber reinforced composite material structure by joining a fiber reinforced composite material part and another part, at least one fiber reinforced composite material part has a protrusion having identification information and joining position information of the other part to be joined And aligning the other part with the fiber reinforced composite part using the protrusion. 8. The method of manufacturing a fiber-reinforced composite structure according to claim 7, wherein the information is at least one selected from the group consisting of the shape, size, number and arrangement of the protrusions, and marks provided on the protrusions. A method characterized by: 9. The method of manufacturing a fiber-reinforced composite structure according to claim 8, wherein a joint portion having a stepped portion or a recessed portion that engages with the protrusion is provided on the other component, and the protrusion is engaged with the stepped portion or recessed portion. Thereby adjusting the other part to a preset joining position with respect to the fiber-reinforced composite part. 10. The method for manufacturing a fiber-reinforced composite structure according to claim 7, wherein a mark corresponding to each of the protrusion and the other part is provided. In the manufacturing method of the fiber reinforced composite material structure according to any one of claims 7 to 10, a pair of I-shaped protrusions are provided on the fiber-reinforced composite material part, and the I-shaped protrusions are provided on the other parts. By providing a rectangular plate-like joint portion to be engaged, and by engaging the rectangular plate-like joint portion with the I-shaped protrusion, the other component is placed at a joint position set in advance with respect to the fiber-reinforced composite material component. A method characterized by combining. In the manufacturing method of the fiber reinforced composite material structure in any one of Claims 7-10, a pair or more L-shaped protrusion is provided in the said fiber reinforced composite material component, The said L-shaped protrusion is provided in the said other component. By providing a rectangular plate-like joint portion to be engaged, and by engaging the rectangular plate-like joint portion with the L-shaped protrusion, the other component is placed at a preset joint position with respect to the fiber-reinforced composite material component. A method characterized by combining.

Images