WO2018154846A1 - 複合材料及び複合材料の製造方法 - Google Patents
複合材料及び複合材料の製造方法 Download PDFInfo
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- WO2018154846A1 WO2018154846A1 PCT/JP2017/038049 JP2017038049W WO2018154846A1 WO 2018154846 A1 WO2018154846 A1 WO 2018154846A1 JP 2017038049 W JP2017038049 W JP 2017038049W WO 2018154846 A1 WO2018154846 A1 WO 2018154846A1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0003—Producing profiled members, e.g. beams
- B29D99/0005—Producing noodles, i.e. composite gap fillers, characterised by their construction
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C64/00—Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
- B29C64/10—Processes of additive manufacturing
- B29C64/141—Processes of additive manufacturing using only solid materials
- B29C64/147—Processes of additive manufacturing using only solid materials using sheet material, e.g. laminated object manufacturing [LOM] or laminating sheet material precut to local cross sections of the 3D object
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
- B29C70/228—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being stacked in parallel layers with fibres of adjacent layers crossing at substantial angles
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- B32B3/06—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions for securing layers together; for attaching the product to another member, e.g. to a support, or to another product, e.g. groove/tongue, interlocking
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- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
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- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/28—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer comprising a deformed thin sheet, i.e. the layer having its entire thickness deformed out of the plane, e.g. corrugated, crumpled
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- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/737—Articles provided with holes, e.g. grids, sieves
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- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
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- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
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- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
Definitions
- the present invention relates to a composite material and a method for manufacturing the composite material.
- CFRP Carbon Reinforced Plastics are lighter than metal materials and have higher specific strength and specific rigidity, and are therefore used in aircraft structures.
- This composite material is molded by laminating a sheet (prepreg) in which a reinforcing fiber is impregnated with a thermosetting resin, and then curing by heating and pressing.
- Patent Document 1 describes that a composite material is formed by laminating two types of sheets having different thicknesses.
- Such a composite material is lightweight and highly rigid, but has a characteristic that rigidity is low with respect to a force in the stacking direction. Therefore, when such a composite material is used, the rigidity is improved by increasing the thickness in a portion where stress is concentrated, for example, around the opening, compared to other portions.
- This invention solves the subject mentioned above, and it aims at providing the manufacturing method of the composite material which suppresses the increase in weight, suppressing the fall of intensity
- a composite material includes a first layer in which a plurality of first sheets that are composite materials including reinforcing fibers and a resin are stacked, and the first layer.
- a second layer in which a plurality of second sheets having a thickness smaller than that of the first sheet are stacked, the second layer being a composite material provided on a partial region of the surface of the first sheet and including a reinforcing fiber and a resin.
- a third layer that covers a surface of the first layer and a surface of the first layer and includes a third sheet that is a composite material including a reinforcing fiber and a resin, and the second sheet of the second layer includes the third sheet. It occupies a wider area on the surface of the first layer than the second sheet laminated on the three-layer side.
- this composite material an inclined portion is formed by a second layer in which a second sheet having a small thickness is laminated. Therefore, this composite material can improve the strength of the inclined portion, and can suppress an increase in weight while suppressing a decrease in strength.
- the thickness of the second layer is preferably 10% to 200% of the thickness of the first layer. This composite material can suppress an increase in weight while appropriately suppressing a decrease in strength by setting the second layer to such a thickness.
- the thickness of the second sheet is preferably 2% to 50% of the thickness of the first sheet. This composite material can suppress an increase in weight while suppressing a decrease in strength more appropriately by setting the second sheet to such a thickness.
- the second layer includes the second sheet positioned closest to the first layer as the bottom second sheet, and the second sheet positioned closest to the third layer.
- the length in the stacking direction extends from the end in the direction parallel to the surface of the bottom-side second sheet to the end in the direction parallel to the surface of the surface-side second sheet. It is preferable that it is 5% or more and 20% or less with respect to the length along the direction parallel to the surface to a part.
- the third sheet has the same thickness as the first sheet.
- This composite material can produce the general part except a thickened part for a short time by setting the 3rd sheet
- the composite material it is preferable that an opening is formed in the composite material, and the second layer is provided around the opening.
- the composite material can appropriately suppress a decrease in strength by providing the second layer around the opening where stress is likely to concentrate and increasing the thickness.
- a method for manufacturing a composite material according to the present disclosure forms a first layer by laminating a plurality of first sheets that are composite materials including reinforcing fibers and a resin.
- a second layer forming step for forming the second layer, and a third sheet, which is a composite material including a reinforcing fiber and a resin, are provided so as to cover the surface of the second layer and the surface of the first layer.
- a third layer forming step of forming a layer wherein in the second layer forming step, the second sheet is more than the second layer laminated on the third layer side.
- the second sheet is laminated so as to occupy a wide area on the surface area. According to this manufacturing method, it is possible to manufacture a composite material that suppresses an increase in weight while suppressing a decrease in strength.
- the second layer forming step includes a second sheet laminate forming step in which the second sheet is laminated to form a second sheet laminate, and the second sheet laminate is the first sheet laminate. It is preferable to have the 2nd sheet laminated body arrangement
- an increase in weight can be suppressed while suppressing a decrease in strength.
- FIG. 1 is a schematic diagram of a composite material according to the present embodiment.
- FIG. 2 is a schematic view of the composite material according to the present embodiment.
- FIG. 3 is a schematic cross-sectional view of the composite material according to the present embodiment.
- FIG. 4 is a diagram for explaining a method for manufacturing a composite material according to the present embodiment.
- FIG. 5 is a schematic diagram of a model of a composite material according to an example.
- FIG. 6 is a schematic diagram of a composite material according to a comparative example.
- FIG. 7 is a table of the analysis results of the comparative example and the example.
- composition of composite material 1 and 2 are schematic views of a composite material according to the present embodiment.
- the composite material 10 according to the present embodiment is a member used for products such as aircraft.
- FIG. 1 is a cross-sectional view of the composite material 10
- FIG. 2 is a top view of the composite material 10.
- the composite material 10 includes a first layer 20, a second layer 30, and a third layer 40, and an opening 50 is formed.
- the composite material 10 is circular in the example of FIG. 2, but the shape is not limited to this and is arbitrary.
- the first layer 20 is a stacked body in which a plurality of first sheets 22 are stacked (superimposed) along the Z direction.
- the first sheet 22 is a composite material including a reinforcing fiber and a resin, and more specifically, a composite material obtained by impregnating a reinforcing fiber with a resin.
- the first sheet 22 has a plate shape, that is, a sheet shape.
- the first sheet 22 has a flat plate shape in the example of FIG. 1, but may have an arbitrary shape such as a curved shape.
- the first sheet 22 is carbon fiber reinforced plastics (CFRP: Carbon Fiber Reinforced Plastic) in which carbon fibers are used as reinforcing fibers.
- CFRP Carbon Fiber Reinforced Plastic
- the reinforcing fibers are not limited to carbon fibers, and may be other plastic fibers, glass fibers, or metal fibers.
- the resin is, for example, a thermosetting resin or a thermoplastic resin.
- An example of the thermosetting resin is an epoxy resin.
- Examples of the thermoplastic resin include polyether ether ketone (PEEK), polyether ketone ketone (PEKK), and polyphenylene sulfide (PPS).
- PEEK polyether ether ketone
- PEKK polyether ketone ketone
- PPS polyphenylene sulfide
- resin is not limited to these, You may use other resin.
- the first layer 20 forms the surface 20A by laminating the first sheet 22.
- the surface 20A is the surface of the first sheet 22 laminated on the upper side of the first layer 20 in the Z direction, that is, the uppermost stage.
- the Z direction is the direction in which the first sheets 22 are laminated, that is, the lamination direction.
- the X direction is a direction orthogonal to the Z direction, and is a direction parallel to the surface 20A. Furthermore, the X direction is a radial direction with respect to the central axis Ax of the opening 50, and the Z direction is an axial direction along the central axis Ax.
- the second layer 30 is provided in the region 20 ⁇ / b> A ⁇ b> 1 of the first layer 20.
- the region 20A1 is a partial region of the surface 20A.
- the second layer 30 is a stacked body in which a plurality of second sheets 32 are stacked (superimposed) in the Z direction on the region 20A1.
- the second sheet 32 is a composite material including a reinforcing fiber and a resin.
- the second sheet 32 is a composite material in which a reinforcing fiber is impregnated with a resin.
- the thickness of the second sheet 32 that is, the length along the Z direction, is smaller than the thickness of the first sheet 22 (length along the Z direction).
- seat 32 is the same as the 1st sheet
- six second sheets 32 are laminated on the second layer 30, but this number is an example, and the number of the second sheets 32 to be laminated is arbitrarily set according to the product. Is set.
- the second sheet 32 closest to the first layer 20 occupies the entire region 20A1 of the first layer 20, and is closer to the third layer 40 side than that.
- the second sheet 32 occupies only a part of the region 20A1.
- the second sheet 32 occupies a wider area on the area 20A1 than the second sheet 32 laminated on the third layer 40 side. That is, as the second sheet 32 is laminated on the first layer 20 side, the area occupied on the area 20A1 is larger, and the second sheet 32 laminated on the third layer 40 side is on the area 20A1. Occupied area is getting smaller. Further, the entire surface of the second sheet 32 overlaps the second sheet 32 laminated on the first layer 30 side.
- the second sheet 32 on the first layer 20 side is referred to as a stacked second sheet 32A.
- the second sheet 32 opposite to the first layer 20 (the third layer 40 side) is referred to as a laminated second sheet 32B.
- the laminated second sheet 32A is a laminated second sheet 32B laminated on the surface, and the laminated second sheet 32B is laminated on the laminated second sheet 32A. In this case, as shown in FIGS.
- the second sheet 32A to be laminated is a part of the surface on the end 32A1 side when viewed from above, that is, when viewed from the third layer 40 side along the Z direction. However, it is exposed from the laminated second sheet 32B.
- the end portion 32A1 is an end portion along the X direction (direction parallel to the surface) of the stacked second sheet 32A. In other words, the end portion 32A1 of the stacked second sheet 32A is located on the X direction side, that is, the radially outer side, than the end portion 32B1 of the stacked second sheet 32B.
- the end portion 32B1 of the laminated second sheet 32B is located within the region of the surface of the laminated second sheet 32A and is not exposed outside the region of the surface of the laminated second sheet 32A.
- the end portion 32B1 is an end portion along the X direction (direction parallel to the surface) of the laminated second sheet 32B.
- the end portion 32A2 and the end portion 32B2 are at the same position along the X direction.
- the surface on the end 32A2 side of the second stacked sheet 32A is not exposed from the stacked second sheet 32B in a top view and overlaps the stacked second sheet 32B.
- the end portion 32A2 is an end surface on the opening 50 side of the second laminated sheet 32A, that is, an inner peripheral surface.
- the end portion 32B2 is an end surface on the opening 50 side of the laminated second sheet 32B, that is, an inner peripheral surface.
- the second sheet 32A to be laminated and the laminated second sheet 32B are laminated in this way, so that it can be said that the second sheet 32 is laminated stepwise. That is, in the second layer 30, the end portion 30B on the X direction side is formed by laminating the end portion 32A1 and the end portion 32B1 while shifting the position in the X direction. Accordingly, the end 30B has a slope shape inclined with respect to the Z direction. On the other hand, in the second layer 30, the end portion 30C on the opening 50 side, that is, the inner peripheral surface side, is formed with the end portion 32A2 and the end portion 32B2 kept in the same position along the X direction. Therefore, the end 30C has a shape along the Z direction and a circumferential shape.
- the second sheet 32 closest to the first layer 20 is the second stacked sheet 32A, and the second sheet 32 stacked thereon is the stacked second sheet 32B.
- the distance along the X direction between the end portion 32A1 and the end portion 32B1 is uniform in all the second sheets 32. That is, the second sheet 32 is stacked while shifting the position of the end portion in the X direction, and the length of the shift is uniform.
- the distance along the X direction between the end portion 32A1 and the end portion 32B1 is not uniform for each second sheet 32 but may be different for each second sheet 32.
- the third layer 40 is provided so as to cover the surfaces of the first layer 20 and the second layer 30.
- the third layer 40 is provided from the surface of the second layer 30 to the region 20A2 of the first layer 20, and covers the surface of the second layer 30 and the region 20A2 of the surface 20A of the first layer 20.
- the region 20A2 is a partial region of the surface 20A of the first layer 20, and is a region other than the region 20A1.
- the surface of the second layer 30 is an area exposed to the outside in the second layer 30, and in addition to the surface of the second sheet 32 closest to the third layer 40, each of the second layers 30 exposed to the outside.
- region namely, area
- seat 32 is included.
- a resin rich layer 34 is formed (filled) between the third layer 40 and the region on the end 30B side of the second sheet 32.
- the resin rich layer 34 is a layer formed of a resin included in the second sheet 32 and the like, and does not include reinforcing fibers.
- the third layer 40 has a third sheet 42. Similar to the first sheet 22, the third sheet 42 is a composite material including a reinforcing fiber and a resin. In other words, the third sheet 42 is a composite material in which a reinforcing fiber is impregnated with a resin.
- the third sheet 42 is preferably thicker (length along the Z direction) than the second sheet 32 and has the same thickness as the first sheet 22. Furthermore, the third sheet 42 is preferably made of the same material as the first sheet 22. In other words, it can be said that the third layer 40 includes the first sheet 22. In the present embodiment, the third layer 40 includes only one third sheet 42, but a plurality of third sheets 42 may be stacked (superimposed) along the Z direction.
- the opening 50 is formed so as to penetrate the first layer 20, the second layer 30, and the third layer 40 along the Z direction. That is, it can be said that the second layer 30 is provided around the opening 50.
- the opening part 50 is circular, the shape is arbitrary.
- the opening 50 is, for example, a rivet hole or an opening for providing an aircraft window.
- the opening 50 opens so that the center of the second layer 30 is the central axis Ax, but the opening position is not limited to this and is arbitrary.
- the composite material 10 is configured as described above, but a more detailed shape will be described below.
- FIG. 3 is a schematic cross-sectional view of the composite material according to the present embodiment.
- FIG. 3 is a partial cross-sectional view of the composite material 10.
- the thickness of the first layer 20, that is, the length along the Z direction is defined as a thickness A1.
- the thickness of the second layer 30 is set to a thickness A2.
- the thickness of the third layer 40 is set to a thickness A3.
- the thickness A2 is preferably 10% or more and 200% or less of the thickness A1.
- thickness A3 is 0.4 mm or less, for example, it is not restricted to it.
- the thickness of the first sheet 22 in the first layer 20, that is, the length along the Z direction is defined as a thickness B1.
- the thickness of the second sheet 32 in the second layer 30 is defined as thickness B2.
- seat 42 in the 3rd layer 40 is set to thickness B3.
- the thickness B2 is preferably 2% or more and 50% or less of the thickness B1.
- the thickness B2 is preferably 2% or more and 50% or less of the thickness B3.
- thickness B1 and thickness B3 are 0.12 mm or more and 0.8 mm or less.
- thickness B2 is 0.02 mm or more and 0.06 mm or less.
- seats 32 of the 2nd layer 30 is set to the bottom 2nd sheet
- seat 32S is made into edge part 32S1.
- seats 32 of the 2nd layer 30 be the surface side 2nd sheet
- seat 32T is made into edge part 32T1.
- the radius of the opening 50 be the length C0.
- the length along the X direction from the end 30C to the end 32T1 of the second layer 30 is defined as a length C1.
- a length along the X direction from the end portion 32T1 to the end portion 32S1 is set as a length C2.
- the length along the X direction from the central axis Ax of the opening 50 to the end 32T1 is defined as a length C3.
- the ratio of the lengths C1, C2, and C3 can be arbitrarily set.
- FIG. 4 is a diagram for explaining a method for manufacturing a composite material according to the present embodiment.
- a plurality of first sheets 22 are stacked in the Z direction to form the first layer 20 (step S ⁇ b>10; first layer forming step). ).
- the first sheet 22 is in an uncured state of the resin, that is, a prepreg.
- a plurality of second sheets 32 are laminated along the Z direction to form the second sheet laminate 31 (step S12; second sheet laminate formation step).
- the second sheet laminate forming step the second sheet 32 is not directly laminated on the first layer 20, but is laminated at a location different from that on the first layer 20. That is, the second sheet laminate 31 is laminated at a location different from that on the first layer 20. It can be said that the second sheet laminate 31 is the second layer 30 before being disposed on the first layer 20. Therefore, in the second sheet laminate forming step, the second sheet 32 occupies a wider area on the area 20A1 of the surface 20A of the first layer 20 than the second sheet 32 laminated on the third layer 40 side.
- seat 32 is laminated
- the second sheet laminate forming step when a part of the surface of the laminated second sheet 32A on the end 32A1 side is viewed from above, that is, when viewed from the third layer 40 side along the Z direction.
- the second sheet laminate 31 is formed so as to be exposed from the laminated second sheet 32B.
- the second sheet 32 is in an uncured state of the resin, that is, a prepreg. Note that the order of the steps S10 and S12 is not limited to this and is arbitrary.
- Step S14 Second sheet laminate arrangement step.
- Step S12 and Step S14 are second layer forming steps in which a plurality of second sheets 32 are stacked to form the second layer 30 on the region 20A1 of the first layer 20.
- the second sheet laminate 31 is disposed on the first layer 20 after the second sheet laminate 31 is formed in another place in this way.
- the method for forming the second layer 30 is not limited to this, and the second sheet 32 may be stacked in order on the first layer 20 to form the second layer 30. .
- the second layer forming step may be any method in which a plurality of second sheets 32 are stacked to form the second layer 30 on the region 20A1 of the first layer 20.
- the second layer 30 is formed such that a part of the surface on the end 32A1 side of the stacked second sheet 32A is exposed from the stacked second sheet 32B in a top view. If it is.
- the third sheet 42 is provided so as to cover the surface 30A of the second layer 30 and the surface of the first layer 20, thereby forming the third layer 40 (step S16; third).
- the third layer 40 is formed by one third sheet 42, but the plurality of third sheets 42 are covered with the surface 30 ⁇ / b> A of the second layer 30 and the surface of the first layer 20.
- the third layer 40 may be formed by stacking.
- the third sheet 42 is in an uncured state of the resin, that is, a prepreg.
- the laminate of the first layer 20, the second layer 30, and the third layer 40 is heated while being pressurized to form the composite material 10 (step S18).
- cures, and the composite material 10 of a predetermined shape is formed.
- the resin between the third layer 40 and the region on the end 30B side of the second sheet 32 is cured, and the resin rich layer 34 is also formed.
- the opening 50 is formed (step S20). Specifically, the opening 50 is formed so as to penetrate the first layer 20, the second layer 30, and the third layer 40 with respect to the composite material 10 formed by pressurization and heating. Thereby, the manufacturing process of the composite material 10 is completed. As described above, in the present embodiment, the first layer 20, the second layer 30, and the third layer 40 are laminated by laminating the sheets having no opening, and the opening 50 is formed after the lamination. However, the opening 50 is formed in each sheet in advance, and the composite material 10 may be manufactured by laminating the sheets formed with the opening 50.
- the composite material 10 includes the first layer 20, the second layer 30, and the third layer 40.
- the first layer 20 is a laminate in which a plurality of first sheets 22 that are composite materials including reinforcing fibers and a resin are laminated.
- the second layer 30 is a stacked body provided on the region 20A1 of the first layer 20.
- the second layer 30 is a composite material including reinforcing fibers and a resin, and a plurality of second sheets 32 having a thickness smaller than that of the first sheet 22 are laminated.
- the region 20A1 is a partial region of the surface 20A of the first layer 20.
- the third layer 40 includes a third sheet 42 that is a composite material that covers the surface of the second layer 30 and the surface of the first layer 20 and includes reinforcing fibers and a resin.
- the second sheet 32 occupies a wider area on the area 20A1 of the surface 20A of the first layer 20 than the second sheet 32 laminated on the third layer 40 side.
- a composite material formed of a composite material including a reinforcing fiber and a resin may have a large thickness in order to improve the strength at a location where stress is concentrated.
- the composite material is provided with a thickened portion which is a portion where the thickness is increased and a normal thick portion which is a portion where the thickness is not increased.
- an inclined portion that is inclined to change the thickness from the thickened portion to the normal thick portion is provided between the thickened portion and the normal thick portion.
- stress concentration tends to occur, and the strength may be reduced.
- the composite material 10 according to this embodiment forms an inclined portion by the second layer 30.
- the second layer 30 is configured by laminating a second sheet 32 having a thickness smaller than that of the first sheet 22.
- the area occupied on the area 20A1 of the second sheet 32 in the twentieth layer 30 is larger than the area occupied on the area 20A1 of the second sheet 32 laminated on the third layer 40 side. Therefore, the composite material 10 has a smaller space filled with the resin-rich layer 34 having a lower strength than the case where the first sheet 22 is laminated to form the inclined portion, for example, and the second sheet 32, that is, the reinforcing fiber.
- the space having can be increased. Therefore, the composite material 10 according to the present embodiment can improve the strength of the inclined portion.
- the composite material 10 according to the present embodiment can maintain the strength against stress concentration even if the inclination of the inclined portion is steep, because the strength of the inclined portion is improved. Can be suppressed. Thus, the composite material 10 according to the present embodiment can suppress an increase in weight while suppressing a decrease in strength.
- the thickness A2 of the second layer 30 is preferably 10% or more and 200% or less of the thickness A1 of the first layer 20.
- the composite material 10 which concerns on this embodiment can suppress the increase in a weight, suppressing the fall of intensity
- the thickness B2 of the second sheet 32 is preferably 2% or more and 50% or less of the thickness B1 of the first sheet 22.
- the composite material 10 which concerns on this embodiment can suppress the increase in a weight, suppressing the fall of intensity
- the second sheet 32 positioned closest to the first layer 20 is referred to as a bottom second sheet 32S
- the second sheet 32 positioned closest to the third layer 40 is referred to as a surface side second sheet 32T.
- the thickness A2 which is the length along the Z direction is 5% or more and 20% or less with respect to the length C2.
- the length C2 is along the direction parallel to the surface from the end 32S1 in the direction parallel to the surface of the bottom-side second sheet 32S to the end 32T1 in the direction parallel to the surface of the top-side second sheet 32T. Length.
- the ratio of the length of the thickness A2 to the length C2, that is, the taper ratio is set in this manner, thereby suppressing an increase in weight more appropriately while suppressing a decrease in strength. be able to.
- the third sheet 42 preferably has the same thickness as the first sheet 22.
- the third sheet 42 that covers the second sheet 32 has such a thickness, so that the general part (excluding the thickened part (the place where the second sheet 32 is laminated)) is removed ( The portion where the second sheet 32 is not laminated) can be manufactured in a short time.
- the composite material 10 has an opening 50 that is an opening, and the second layer 30 is provided around the opening 50. Stress concentration is likely to occur around the opening.
- the composite material 10 can appropriately suppress a decrease in strength by providing the second layer 30 around the opening 50 where stress is likely to concentrate and increasing the thickness.
- the composite material 10 does not necessarily have the opening 50, and the second layer 30 is not limited to being provided around the opening 50.
- the second layer 30 is preferably provided at a location where stress concentrates other than the periphery of the opening 50.
- the method for manufacturing the composite material 10 includes a first layer forming step, a second layer forming step, and a third layer forming step.
- the first layer 20 is formed by laminating a plurality of first sheets 22 which are composite materials including reinforcing fibers and a resin.
- the second layer forming step a plurality of second sheets 32 having a thickness smaller than that of the first sheet 22 are stacked, and the second layer 30 is formed on the region 20 ⁇ / b> A ⁇ b> 1 of the first layer 20.
- the third sheet 42 is provided so as to cover the surface of the second layer 30 and the surface of the first layer 20 to form the third layer 40.
- the second sheet 32 occupies a wider area on the area 20A1 of the surface 20A of the first layer 20 than the second sheet 32 laminated on the third layer 40 side.
- the second sheet 32 is laminated. According to this manufacturing method, it becomes possible to manufacture the composite material 10 that suppresses an increase in weight while suppressing a decrease in strength.
- the second layer forming step includes a second sheet laminate forming step of forming the second sheet laminate 31 by laminating the second sheets 32, and the second sheet laminate 31 on the region 20A1 of the first layer 20. And a second sheet laminate arrangement step of forming the second layer 30 by arranging the second layer 30. According to this manufacturing method, since the second sheet laminate 31 in which the second sheets 32 having different thicknesses are laminated is disposed on the first layer 20, the composite material 10 can be more easily manufactured.
- FIG. 5 is a schematic diagram of a model of a composite material according to an example.
- FIG. 6 is a schematic diagram of a composite material according to a comparative example.
- the composite material model 10 ⁇ / b> A according to the example includes the first layer 20, the second layer 30, and the third layer 40 as in the above-described embodiment.
- the third layer 40 of the model 10 ⁇ / b> A has a sheet having the same thickness as the first layer 20, that is, the first sheet 22 as the third sheet 42.
- the length along the X direction from the end 32S1 to the end 10A1 is defined as a length C4.
- the end portion 10A1 is an end portion on the X direction side of the model 10A.
- Example 1 and Example 2 in which the dimensions of the model 10A were changed were performed.
- the length C1 is 40 mm
- the length C2 is 32 mm
- the length C4 is 20 mm
- the thickness A2 is 1.6 mm.
- Example 2 has the same dimensions as Example 1 except that the length C2 is 8 mm. That is, in Example 1, the ratio of thickness A2 to length C2 is 1:20, and in Example 2, the ratio is 1: 5.
- the composite material model 10 ⁇ / b> X includes a first layer 20, a second layer 30 ⁇ / b> X, and a third layer 40.
- the second layer 30X of the model 10X is a stack of the first sheets 22. That is, in the model 10X, the thickness of each sheet of the second layer is larger than the model 10A.
- Comparative Example 1 and Comparative Example 2 in which the dimensions of the model 10X were changed were also performed.
- the length C1 is 40 mm
- the length C2 is 32 mm
- the length C4 is 20 mm
- the thickness A2 is 1.6 mm.
- Comparative Example 2 has the same dimensions as Comparative Example 1 except that the length C2 is 8 mm. That is, Comparative Examples 1 and 2 have the same dimensions as Examples 1 and 2 except for the thickness of the sheet of the second layer 30X.
- FIG. 7 is a table of the analysis results of the comparative example and the example.
- the generated maximum stress von Mises stress
- Comparative Example 2 (taper ratio 1: 5)
- the maximum stress was 44.5 MPa.
- Example 1 (taper ratio is 1:20)
- the maximum stress was 17.5 MPa.
- Example 2 (taper ratio is 1: 5), the maximum stress was 25.5 MPa.
Abstract
Description
図1及び図2は、本実施形態に係る複合材料の模式図である。本実施形態に係る複合材料10は、例えば航空機などの製品に用いられる部材である。図1は、複合材料10の断面図であり、図2は、複合材料10の上面図である。図1及び図2に示すように、複合材料10は、第1層20と、第2層30と、第3層40とを有し、さらに開口部50が形成されている。複合材料10は、図2の例では円形であるが、形状はこれに限られず任意である。
次に、複合材料10の製造方法について説明する。図4は、本実施形態に係る複合材料の製造方法を説明する図である。図4に示すように、複合材料10を製造する際は、最初に、第1シート22をZ方向に沿って複数積層して、第1層20を形成する(ステップS10;第1層形成ステップ)。この第1層形成ステップにおいて、第1シート22は、樹脂が未硬化の状態、すなわちプリプレグである。
次に、本発明の実施例について説明する。本実施例においては、比較例に係る複合材料10Xと、本実施形態に係る複合材料10とのモデルに対し、FEM(Finite Element Method)解析を行った。
20 第1層
22 第1シート
30 第2層
32 第2シート
32A 被積層第2シート
32B 積層第2シート
32A1 端部
40 第3層
42 第3シート
50 開口部
Claims (8)
- 強化繊維と樹脂とを含む複合材である第1シートが複数積層された第1層と、
前記第1層の表面の一部の領域上に設けられ、強化繊維と樹脂とを含む複合材であり、前記第1シートよりも厚みが小さい第2シートが複数積層された第2層と、
前記第2層の表面及び前記第1層の表面を覆い、強化繊維と樹脂とを含む複合材である第3シートを備える第3層と、を有し、
前記第2層の前記第2シートは、前記第3層側に積層されている前記第2シートよりも、前記第1層の表面の領域上の広い領域を占めている、
複合材料。 - 前記第2層の厚みは、前記第1層の厚みの10%以上200%以下である、請求項1に記載の複合材料。
- 前記第2シートの厚みは、前記第1シートの厚みの2%以上50%以下である、請求項1又は請求項2に記載の複合材料。
- 前記第2層は、
最も前記第1層側に位置している前記第2シートを底側第2シートとし、最も前記第3層側に位置している前記第2シートを表面側第2シートとした場合、
前記積層方向に沿った長さが、前記底側第2シートの表面に平行な方向における端部から、前記表面側第2シートの表面に平行な方向における端部までの、表面に平行な方向に沿った長さに対し、5%以上20%以下である、請求項1から請求項3のいずれか1項に記載の複合材料。 - 前記第3シートは、前記第1シートと同じ厚みである、請求項1から請求項4のいずれか1項に記載の複合材料。
- 前記複合材料には、開口が形成されており、前記第2層は、前記開口の周囲に設けられている、請求項1から請求項5のいずれか1項に記載の複合材料。
- 強化繊維と樹脂とを含む複合材である第1シートを複数積層して第1層を形成する第1層形成ステップと、
強化繊維と樹脂とを含む複合材であって前記第1シートよりも厚みが小さい第2シートを複数積層して、前記第1層の表面の一部の領域上に第2層を形成する第2層形成ステップと、
強化繊維と樹脂とを含む複合材である第3シートを、前記第2層の表面及び前記第1層の表面を覆うように設けて第3層を形成する第3層形成ステップと、を有し、
前記第2層形成ステップでは、前記第2シートが、前記第3層側に積層されている前記第2シートよりも、前記第1層の表面の領域上の広い領域を占めるように、前記第2シートを積層する、
複合材料の製造方法。 - 前記第2層形成ステップは、
前記第2シートを積層して第2シート積層体を形成する第2シート積層体形成ステップと、
前記第2シート積層体を前記第1層の表面の一部の領域上に配置することで、前記第2層を形成する第2シート積層体配置ステップと、を有する、請求項7に記載の複合材料の製造方法。
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EP17897405.1A EP3569402B1 (en) | 2017-02-22 | 2017-10-20 | Composite material and method for manufacturing composite material |
US16/485,176 US20190389096A1 (en) | 2017-02-22 | 2017-10-20 | Composite material and method for manufacturing composite material |
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2017
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- 2017-10-20 US US16/485,176 patent/US20190389096A1/en not_active Abandoned
- 2017-10-20 CN CN201780086356.3A patent/CN110290919A/zh active Pending
- 2017-10-20 EP EP17897405.1A patent/EP3569402B1/en active Active
- 2017-10-20 CA CA3053099A patent/CA3053099C/en not_active Expired - Fee Related
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Cited By (4)
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JP6484378B1 (ja) * | 2018-09-21 | 2019-03-13 | 太平洋工業株式会社 | 樹脂成形品及び樹脂成形品の製造方法 |
WO2020059195A1 (ja) * | 2018-09-21 | 2020-03-26 | 太平洋工業株式会社 | 樹脂成形品及び樹脂成形品の製造方法 |
JP2020049664A (ja) * | 2018-09-21 | 2020-04-02 | 太平洋工業株式会社 | 樹脂成形品及び樹脂成形品の製造方法 |
US11667371B2 (en) * | 2020-04-03 | 2023-06-06 | The Boeing Company | Composite materials having reinforced access openings |
Also Published As
Publication number | Publication date |
---|---|
US20190389096A1 (en) | 2019-12-26 |
EP3569402B1 (en) | 2021-12-08 |
CA3053099A1 (en) | 2018-08-30 |
EP3569402A1 (en) | 2019-11-20 |
CA3053099C (en) | 2021-06-15 |
EP3569402A4 (en) | 2020-01-22 |
JP6804626B2 (ja) | 2020-12-23 |
CN110290919A (zh) | 2019-09-27 |
JPWO2018154846A1 (ja) | 2019-06-27 |
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