US20150182824A1 - Shaft made of fiber-reinforced composite material - Google Patents

Shaft made of fiber-reinforced composite material Download PDF

Info

Publication number
US20150182824A1
US20150182824A1 US14/574,656 US201414574656A US2015182824A1 US 20150182824 A1 US20150182824 A1 US 20150182824A1 US 201414574656 A US201414574656 A US 201414574656A US 2015182824 A1 US2015182824 A1 US 2015182824A1
Authority
US
United States
Prior art keywords
prepreg
layer
fiber
carbon fiber
reinforcing layer
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US14/574,656
Other languages
English (en)
Inventor
Shinichi Takemura
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Eneos Corp
Original Assignee
JX Nippon Oil and Energy Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by JX Nippon Oil and Energy Corp filed Critical JX Nippon Oil and Energy Corp
Assigned to JX NIPPON OIL & ENERGY CORPORATION reassignment JX NIPPON OIL & ENERGY CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: TAKEMURA, SHINICHI
Publication of US20150182824A1 publication Critical patent/US20150182824A1/en
Abandoned legal-status Critical Current

Links

Images

Classifications

    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63B—APPARATUS FOR PHYSICAL TRAINING, GYMNASTICS, SWIMMING, CLIMBING, OR FENCING; BALL GAMES; TRAINING EQUIPMENT
    • A63B60/00—Details or accessories of golf clubs, bats, rackets or the like
    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63B—APPARATUS FOR PHYSICAL TRAINING, GYMNASTICS, SWIMMING, CLIMBING, OR FENCING; BALL GAMES; TRAINING EQUIPMENT
    • A63B53/00—Golf clubs
    • A63B53/10—Non-metallic shafts
    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63B—APPARATUS FOR PHYSICAL TRAINING, GYMNASTICS, SWIMMING, CLIMBING, OR FENCING; BALL GAMES; TRAINING EQUIPMENT
    • A63B2209/00—Characteristics of used materials
    • A63B2209/02—Characteristics of used materials with reinforcing fibres, e.g. carbon, polyamide fibres
    • A63B2209/023—Long, oriented fibres, e.g. wound filaments, woven fabrics, mats
    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63B—APPARATUS FOR PHYSICAL TRAINING, GYMNASTICS, SWIMMING, CLIMBING, OR FENCING; BALL GAMES; TRAINING EQUIPMENT
    • A63B2225/00—Miscellaneous features of sport apparatus, devices or equipment
    • A63B2225/02—Testing, calibrating or measuring of equipment
    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63B—APPARATUS FOR PHYSICAL TRAINING, GYMNASTICS, SWIMMING, CLIMBING, OR FENCING; BALL GAMES; TRAINING EQUIPMENT
    • A63B60/00—Details or accessories of golf clubs, bats, rackets or the like
    • A63B60/06—Handles
    • A63B60/08—Handles characterised by the material

Definitions

  • the present invention relates to a shaft made of a fiber-reinforced composite material.
  • a shaft made of a fiber-reinforced composite material used in a golf club shaft or the like.
  • a shaft is reduced in weight and maintains bending strength.
  • a reinforcing layer is provided on a straight layer to compensate for the lack of bending strength due to the weight reduction.
  • An aspect of the invention is to provide a shaft made of a fiber-reinforced composite material having a structure in which the bending rigidity can be adjusted.
  • a shaft made of a fiber-reinforced composite material includes: a straight layer having a reinforcement fiber oriented in an axial direction; a first reinforcing layer provided outside the straight layer and having a first carbon fiber; and a second reinforcing layer provided outside the first reinforcing layer and having a second carbon fiber.
  • a tensile elastic modulus of the first carbon fiber and a tensile elastic modulus of the second carbon fiber are different from each other and are smaller than that of the reinforcing fiber in the straight layer.
  • the tensile elastic modulus of the first carbon fiber in the first reinforcing layer and the tensile elastic modulus of the second carbon fiber in the second reinforcing layer are different from each other. Therefore, it is possible to adjust the bending rigidity of the shaft made of the fiber-reinforced composite material by changing a ratio of the lamination number of the first reinforcing layers to the lamination number of the second reinforcing layers.
  • the tensile elastic modulus of the second carbon fiber may be smaller than that of the first carbon fiber.
  • the layer containing the carbon fiber having a lower elastic modulus is located at the outside.
  • a bending fracture of the shaft is caused from the compression side.
  • the tensile elastic modulus of the carbon fiber contained in the layer is lower, a compression fracture does not easily occur. Therefore, when the tensile elastic modulus of the second carbon fiber is smaller than that of the first carbon fiber, the compression fracture is suppressed and thus bending strength can be further improved.
  • the tensile elastic modulus of the first carbon fiber and the tensile elastic modulus of the second carbon fiber may be 10 to 200 GPa. Even when the tensile elastic modulus of the first carbon fiber and the tensile elastic modulus of the second carbon fiber are in the range of 10 to 200 GPa, the bending rigidity can be adjusted as well as the bending strength can be improved.
  • FIG. 1 is a cross-sectional view schematically illustrating a shaft made of a fiber-reinforced composite material according to an embodiment
  • FIG. 2 is a diagram illustrating a planar shape of a mandrel and a cut shape of prepreg used in each layer of the shaft made of the fiber-reinforced composite material illustrated in FIG. 1 ;
  • FIG. 3 is a cross-sectional view schematically illustrating a shaft made of a fiber-reinforced composite material according to a modified example
  • FIG. 4 is a diagram illustrating a planar shape of a mandrel and a cut shape of prepreg used in each layer of the shaft made of the fiber-reinforced composite material illustrated in FIG. 3 ;
  • FIG. 5 is a cross-sectional view schematically illustrating a shaft made of a fiber-reinforced composite material according to another modified example
  • FIG. 6 is a diagram illustrating a planar shape of a mandrel and a cut shape of prepreg used in each layer of the shaft made of the fiber-reinforced composite material illustrated in FIG. 5 ;
  • FIG. 7 is a schematic block diagram of a test apparatus of shafts made of a fiber-reinforced composite material according to Examples 1 to 5 and Comparative Examples 1 and 2.
  • FIG. 1 is a cross-sectional view schematically illustrating a shaft made of a fiber-reinforced composite material according to an embodiment.
  • a shaft 1 made of a fiber-reinforced composite material is a long tubular body extending in an axial direction AX and is used for a golf club shaft, for example.
  • a width of the shaft 1 made of the fiber-reinforced composite material gradually decreases toward a tip end 1 b from a butt end 1 a .
  • the butt end 1 a corresponds to an end portion of a grip side
  • the tip end 1 b corresponds to an end portion of a head side.
  • the shaft 1 made of the fiber-reinforced composite material includes a bias layer 3 , a straight layer 4 , a first reinforcing layer 5 , and a second reinforcing layer 6 .
  • the bias layer 3 is the innermost layer of the shaft 1 made of the fiber-reinforced composite material and is provided over a full length in the axial direction AX of the shaft 1 made of the fiber-reinforced composite material.
  • the bias layer 3 includes a first bias layer 31 and a second bias layer 32 .
  • the first bias layer 31 and the second bias layer 32 are alternatively laminated for each of one layer or plural layers.
  • a set of bias layers 3 may have a lamination number of, for example, one to ten layers or two to eight layers.
  • the lamination number represents how many specific layers such as the bias layer 3 are laminated on average, that is, how many times the layers are wound around an axis of the shaft 1 made of the fiber-reinforced composite material, and the lamination number may be the decimal number.
  • the first bias layer 31 is a positive bias layer.
  • the first bias layer 31 is constituted by prepreg having a reinforcement fiber oriented so as to be inclined with respect to the axial direction AX.
  • the first bias layers 31 are laminated such that the orientation direction of the reinforcement fiber inclines at an angle of, for example, 15° to 75°, 20° to 60°, or 30° to 50° with respect to the axial direction AX.
  • the second bias layer 32 is a negative bias layer.
  • the second bias layer 32 is constituted by prepreg having a reinforcement fiber oriented so as to be inclined with respect to the axial direction AX and intersect with the orientation direction of the reinforcement fiber of the first bias layer 31 .
  • the second bias layers 32 are laminated such that the orientation direction of the reinforcement fiber inclines at an angle of, for example, 45° to ⁇ 75°, ⁇ 20° to ⁇ 60°, or ⁇ 30° to ⁇ 50° with respect to the axial direction AX.
  • the positive bias layer is the prepreg which is wound counterclockwise from a large-diameter side to a small-diameter side of the shaft 1 made of the fiber-reinforced composite material, that is, laminated in a left-hand screw direction
  • the negative bias layer is the prepreg which is wound clockwise from the large-diameter side to the small-diameter side of the shaft 1 made of the fiber-reinforced composite material, that is, laminated in a right-hand screw direction.
  • the reinforcement fiber of the first bias layer 31 and the second bias layer 32 may have a tensile elastic modulus of, for example, about 200 to 1000 GPa or about 400 to 800 GPa.
  • a carbon fiber is used by reason of a light weight and a high tensile elastic modulus.
  • any of a polyacrylonitrile (PAN)-based carbon fiber and a pitch-based carbon fiber may be used.
  • PAN polyacrylonitrile
  • a metal fiber, a silicon carbide fiber, an alumina fiber, a boron fiber, a potassium titanate fiber or the like may be used.
  • the straight layer 4 is provided outside the bias layer 3 .
  • the straight layer 4 is provided over the full length in the axial direction AX of the shaft 1 made of the fiber-reinforced composite material along an outer peripheral surface of the bias layer 3 .
  • the straight layer 4 is constituted by prepreg having a reinforcement fiber oriented in the axial direction AX. That is, the straight layers 4 are laminated such that the orientation direction of the reinforcement fiber inclines at an angle of, for example, 0° to ⁇ 5° with respect to the axial direction AX.
  • the lamination number of the straight layers 4 may be, for example, from one layer to ten layers or from two layers to eight layers.
  • the straight layer 4 may different in a laminated thickness between the butt end 1 a side and the tip end 1 b side, but may have the same laminated thickness.
  • the reinforcement fiber of the straight layer 4 may have a tensile elastic modulus of, for example, about 200 to 600 GPa or about 230 to 300 GPa.
  • a carbon fiber is used by reason of a light weight.
  • any of a PAN-based carbon fiber and a pitch-based carbon fiber may be used.
  • a metal fiber, a silicon carbide fiber, an alumina fiber, a boron fiber, a potassium titanate fiber or the like may be used.
  • the first reinforcing layer 5 is provided outside the straight layer 4 .
  • the first reinforcing layer 5 is provided at the tip end 1 b side of the shaft 1 made of the fiber-reinforced composite material along an outer peripheral surface of the straight layer 4 .
  • the first reinforcing layer 5 is constituted by prepreg having a first carbon fiber of a low tensile elastic modulus.
  • the first carbon fiber is oriented in substantially parallel (for example, about 0° to ⁇ 5°) with the axial direction AX.
  • the lamination number of the first reinforcing layers 5 is determined according to the purpose and is, for example, from one layer to ten layers.
  • the lamination number of the first reinforcing layers 5 is one to ten layers at the small-diameter side and is zero to one layer at the large-diameter side, and thus the lamination number thereof may be reduced at the large-diameter side.
  • the prepreg constituting the first reinforcing layer 5 unidirectional prepreg or fabric prepreg is used.
  • the prepreg constituting the first reinforcing layer 5 may be formed by laminating about one to five sheets having the identical or non-identical cut shape.
  • the carbon fiber of the first reinforcing layer 5 has a smaller tensile elastic modulus than the reinforcement fiber of the straight layer 4 and has the tensile elastic modulus of, for example, about 10 to 200 GPa.
  • the carbon fiber of the first reinforcing layer 5 may have the tensile strength of, for example, 0.5 to 10 GPa, 0.8 to 10 GPa or 1 to 10 GPa to improve bending strength.
  • the carbon fiber As an example of the carbon fiber, a pitch-based carbon fiber is used. Please note that the tensile elastic modulus and tensile strength of carbon fiber is measured in accordance with the JIS R 7608 ‘Carbon fibre—Determination of tensile properties of resin-impregnated yarn’.
  • the second reinforcing layer 6 is provided outside the first reinforcing layer 5 .
  • the second reinforcing layer 6 is provided at the tip end 1 b of the shaft 1 made of the fiber-reinforced composite material along an outer peripheral surface of the first reinforcing layer 5 .
  • the second reinforcing layer 6 is constituted by prepreg having a second carbon fiber of a low tensile elastic modulus.
  • the second carbon fiber is oriented in substantially parallel (for example, about 0° to ⁇ 5°) with the axial direction AX.
  • the lamination number of the second reinforcing layers 6 is determined according to the purpose and is, for example, from one layer to ten layers.
  • the lamination number of the second reinforcing layers 6 is one to ten layers at the small-diameter side and is zero to one layer at the large-diameter side, and thus the lamination number thereof may be reduced at the large-diameter side.
  • the prepreg constituting the second reinforcing layer 6 unidirectional prepreg or fabric prepreg is used.
  • the prepreg constituting the second reinforcing layer 6 may be formed by laminating about one to five sheets having the identical or non-identical cut shape.
  • the carbon fiber of the second reinforcing layer 6 has a smaller tensile elastic modulus than the reinforcement fiber of the straight layer 4 and may have the tensile elastic modulus of, for example, 10 to 200 GPa or about 30 to 200 GPa.
  • the carbon fiber of the second reinforcing layer 6 may have the tensile strength of, for example, 0.5 to 10 GPa, 0.8 to 5 GPa or 1 to 3 GPa to improve the bending strength.
  • the tensile elastic modulus of the second reinforcing layer 6 differs from the tensile elastic modulus of the first reinforcing layer 5 .
  • the tensile elastic modulus of the second reinforcing layer 6 may be smaller than that of the first reinforcing layer 5 to further improve the bending strength.
  • a pitch-based carbon fiber is used as an example of the carbon fiber.
  • the first reinforcing layer 5 and the second reinforcing layer 6 are located at the small-diameter side (tip end 1 b side) of the shaft 1 made of the fiber-reinforced composite material.
  • a lower limit of a range occupied by the first reinforcing layer 5 and the second reinforcing layer 6 may be, for example, not less than 1/20 or not less than 1/10 of the full length of the shaft 1 made of the fiber-reinforced composite material from the tip end 1 b .
  • An upper limit of the range occupied by the first reinforcing layer 5 and the second reinforcing layer 6 may be, for example, not more than 2 ⁇ 3 or not more than 1 ⁇ 2 of the full length of the shaft 1 made of the fiber-reinforced composite material from the tip end 1 b .
  • the length of the first reinforcing layer 5 and the second reinforcing layer 6 may be, for example, about 1 ⁇ 5 to 1 ⁇ 3 of the full length of the shaft 1 made of the fiber-reinforced composite material from the tip end 1 b.
  • FIG. 2 is a diagram illustrating a planar shape of a mandrel and a cut shape of prepreg used in each layer of the shaft 1 made of the fiber-reinforced composite material.
  • the reinforcement fiber used in each layer is formed as prepreg.
  • Each prepreg is formed in the form of sheet where each reinforcement fiber is impregnated with a matrix resin.
  • thermosetting resin such as epoxy resin, unsaturated polyester resin, phenolic resin, silicone resin, polyurethane resin, urea resin, melamine resin, or the like is used.
  • a mass per unit area of the reinforcement fiber of the prepreg is not particularly limited, but may be, for example, in the range of 30 to 180 g/m 2 or 50 to 150 g/m 2 .
  • flexibility is limited in the cut shape and weight design of the shaft and winding properties of the prepreg around a mandrel M may be inferior at the time of manufacturing the shaft 1 made of the fiber-reinforced composite material.
  • each prepreg is cut according to the lamination number and the laminated range (occupied range) of each layer.
  • prepreg P 31 of the first bias layer 31 , prepreg P 32 of the second bias layer 32 , and prepreg P 4 of the straight layer 4 each have a trapezoidal cut shape having the same height as the full length of the shaft 1 made of the fiber-reinforced composite material.
  • prepreg P 5 of the first reinforcing layer 5 and prepreg P 6 of the second reinforcing layer 6 each have a triangular cut shape.
  • the prepreg P 31 of the first bias layer 31 and the prepreg P 32 of the second bias layer 32 are attached by being shifted from each other in a half length of the circumference of the mandrel M (core bar) made of metal and are wound around the mandrel M as the prepreg of the bias layer 3 .
  • the prepreg P 4 of the straight layer 4 is wound around the outside of the prepreg of the bias layer 3 which is previously wound.
  • the prepreg P 5 of the first reinforcing layer 5 is wound around the outside of the prepreg P 4 of the straight layer 4 which is previously wound, and the prepreg P 6 of the second reinforcing layer 6 is wound around the outside of the prepreg P 5 of the first reinforcing layer 5 which is previously wound.
  • a heat shrinkage tape is wound around the outside of the prepreg P 6 of the second reinforcing layer 6 , the prepreg P 5 of the first reinforcing layer 5 , and the prepreg P 4 of the straight layer 4 to fix each layer.
  • the whole is put into a heating furnace to heat, and thus the matrix resin contained in each layer is cured.
  • the heat shrinkage tape is removed and the mandrel M is pulled out, and thus shaft 1 made of the fiber-reinforced composite material is produced.
  • the tensile elastic modulus of the carbon fiber in the first reinforcing layer 5 is different from that of the carbon fiber in the second reinforcing layer 6 .
  • the tensile elastic modulus of the carbon fiber becomes larger, the bending rigidity increases.
  • the tensile elastic modulus of the carbon fiber in the first reinforcing layer 5 and the tensile elastic modulus of the carbon fiber in the second reinforcing layer 6 are smaller than that of the reinforcement fiber in the straight layer 4 . Further, the tensile elastic modulus of the second carbon fiber may be lower than that of the first carbon fiber.
  • the tensile elastic modulus becomes smaller, each numerical value of them becomes larger.
  • the carbon fiber has characteristics that the compression fracture hardly occurs (here, when comparing the compression fracture strain of the carbon fiber, the value is as follows: Nippon Graphite Fiber XN-05: 2.9%, XN-10: 2.1%, XN-15: 1.75%, Mitsubishi Rayon TR50S: 1.2%, and Nippon Graphite Fiber XN-60: 0.15%).
  • a bending load is applied to the shaft made of the fiber-reinforced composite material, compression stress concentration occurs at just below an indenter and compression fracture easily occurs from this portion. In other words, bending strength of the shaft made of the fiber-reinforced composite material is influenced by the compression fracture strain.
  • the carbon fiber having a lower elastic modulus that is, the carbon fiber having a higher compression fracture strain is disposed at the outermost portion, it is possible to achieve an effect that the bending strength of the shaft made of the fiber-reinforced composite material is improved.
  • the carbon fiber having the lower tensile elastic modulus is used in the reinforcing layer to obtain the higher bending strength, the bending strength is improved, but the bending rigidity is also reduced and thus the adjustment range of the bending rigidity also becomes narrower.
  • the bending fracture of the shaft is caused from the compression side.
  • the tensile elastic modulus of the carbon fiber contained in the layer is lower, the compression fracture does not easily occur. Therefore, when the tensile elastic modulus of the carbon fiber in the second reinforcing layer 6 is smaller than that of the carbon fiber in the first reinforcing layer 5 , since the layer containing the carbon fiber having the lower elastic modulus is located at the outside, the compression fracture is suppressed and thus the bending strength can be further improved.
  • the shaft 1 made of the fiber-reinforced composite material is used as various shafts as well as the golf club shaft.
  • the shaft 1 made of the fiber-reinforced composite material may be further provided with other layers in addition to the bias layer 3 , the straight layer 4 , the first reinforcing layer 5 , and the second reinforcing layer 6 .
  • Other layers may be located inside the bias layer 3 or between the layer and the layer. Examples of other layers include a hoop layer having a carbon fiber oriented at an angle of approximately 90° with respect to the axial direction AX, or the like.
  • the shaft 1 made of the fiber-reinforced composite material may be further provided with at least one reinforcing layer at the outside of the second reinforcing layer 6 .
  • the at least one reinforcing layer is constituted by prepreg having a carbon fiber, and the tensile elastic modulus of the carbon fiber is smaller than that of the reinforcement fiber in the straight layer 4 .
  • the length of the first reinforcing layer 5 in the axial direction AX is substantially equal to that of the second reinforcing layer 6 in the axial direction AX, but is not limited thereto.
  • FIG. 3 is a cross-sectional view schematically illustrating a shaft made of a fiber-reinforced composite material according to a modified example.
  • FIG. 4 is a diagram illustrating a planar shape of a mandrel and a cut shape of prepreg used in each layer of the shaft made of the fiber-reinforced composite material illustrated in FIG. 3 .
  • a relation between the length of the first reinforcing layer 5 and the length of the second reinforcing layer 6 in the axial direction AX is different as compared to the above embodiment.
  • the length of the first reinforcing layer 5 in the axial direction AX from the tip end 1 b is longer than that of the second reinforcing layer 6 in the axial direction AX from the tip end 1 b . Even in this modified example, the same effect as the above embodiment can be achieved.
  • FIG. 5 is a cross-sectional view schematically illustrating a shaft made of a fiber-reinforced composite material according to another modified example.
  • FIG. 6 is a diagram illustrating a planar shape of a mandrel and a cut shape of prepreg used in each layer of the shaft made of the fiber-reinforced composite material illustrated in FIG. 5 .
  • a relation between the length of the first reinforcing layer 5 and the length of the second reinforcing layer 6 in the axial direction AX is different as compared to the above embodiment.
  • the length of the first reinforcing layer 5 in the axial direction AX from the tip end 1 b is shorter than that of the second reinforcing layer 6 in the axial direction AX from the tip end 1 b . Even in this modified example, the same effect as the above embodiment can be achieved.
  • Table 1 indicates the materials used in the shafts made of the fiber-reinforced composite material according to Examples and Comparative Examples.
  • Prepreg A carbon fiber prepreg E052AA-10N (made by Nippon Graphite Fiber Corporation, mass per unit area of carbon fiber: 100 g/m 2 , resin content: 37 weight %, thickness of prepreg: 0.109 mm)
  • Prepreg B carbon fiber prepreg E1026A-09N (made by Nippon Graphite Fiber Corporation, mass per unit area of carbon fiber: 95 g/m 2 , resin content: 37 weight %, thickness of prepreg: 0.102 mm)
  • Prepreg C carbon fiber prepreg E1526C-10N (made by Nippon Graphite Fiber Corporation, mass per unit area of carbon fiber: 100 g/m 2 , resin content: 33 weight %, thickness of prepreg: 0.094 mm)
  • Prepreg D carbon fiber prepreg NT61250-525S (made by Nippon Graphite Fiber Corporation, mass per unit area of carbon fiber: 125 g/m 2 , resin content: 25 weight %, thickness of prepreg: 0.093 mm)
  • Prepreg E carbon fiber prepreg F24N125 (made by JX Nippon Oil & Energy Corporation, mass per unit area of carbon fiber: 125 g/m 2 , resin content: 25 weight %, thickness of prepreg: 0.103 mm)
  • the prepreg A is a carbon fiber prepreg obtained by impregnating the carbon fiber of XN-05 (made by Nippon Graphite Fiber Corporation, tensile elastic modulus of 54 GPa, tensile strength of 1.1 GPa) with an epoxy resin (made by JX Nippon Oil & Energy Corporation, curing temperature of 130° C.) as a matrix resin.
  • XN-05 made by Nippon Graphite Fiber Corporation, tensile elastic modulus of 54 GPa, tensile strength of 1.1 GPa
  • an epoxy resin made by JX Nippon Oil & Energy Corporation, curing temperature of 130° C.
  • the prepreg B is a carbon fiber prepreg obtained by impregnating the carbon fiber of XN-10 (made by Nippon Graphite Fiber Corporation, tensile elastic modulus of 110 GPa, tensile strength of 1.7 GPa) with an epoxy resin (made by JX Nippon Oil & Energy Corporation, curing temperature of 130° C.) as a matrix resin.
  • XN-10 made by Nippon Graphite Fiber Corporation, tensile elastic modulus of 110 GPa, tensile strength of 1.7 GPa
  • an epoxy resin made by JX Nippon Oil & Energy Corporation, curing temperature of 130° C.
  • the prepreg C is a carbon fiber prepreg obtained by impregnating the carbon fiber of XN-15 (made by Nippon Graphite Fiber Corporation, tensile elastic modulus of 155 GPa, tensile strength of 2A GPa) with an epoxy resin (made by JX Nippon Oil & Energy Corporation, curing temperature of 130° C.) as a matrix resin.
  • XN-15 made by Nippon Graphite Fiber Corporation, tensile elastic modulus of 155 GPa, tensile strength of 2A GPa
  • an epoxy resin made by JX Nippon Oil & Energy Corporation, curing temperature of 130° C.
  • the prepreg D is a carbon fiber prepreg obtained by impregnating the carbon fiber of XN-60 (made by Nippon Graphite Fiber Corporation, tensile elastic modulus of 620 GPa, tensile strength of 3.4 GPa) with an epoxy resin (made by JX Nippon Oil & Energy Corporation, curing temperature of 130° C.) as a matrix resin.
  • XN-60 made by Nippon Graphite Fiber Corporation, tensile elastic modulus of 620 GPa, tensile strength of 3.4 GPa
  • an epoxy resin made by JX Nippon Oil & Energy Corporation, curing temperature of 130° C.
  • the prepreg E is a carbon fiber prepreg obtained by impregnating the carbon fiber of TR50S (made by Mitsubishi Rayon Co., Ltd., tensile elastic modulus of 240 GPa, tensile strength of 4.9 GPa) with an epoxy resin (made by JX Nippon Oil & Energy Corporation, curing temperature of 130° C.) as a matrix resin.
  • Hollow CFRP test pipes (Examples 1 to 5 and Comparative Examples 1 and 2) were produced using the above prepreg to simulate the tip end side of the shaft made of the fiber-reinforced composite material.
  • the prepreg was wound around a mandrel made of SUS304 having a diameter of 5.5 mm and a length of 1050 mm in the following order.
  • Prepreg of +45° and pregreg of ⁇ 45° were attached by being shifted from each other in a half length (8.6 mm) of the circumference of the mandrel and were wound around the mandrel as prepreg of the bias layer.
  • prepreg of the straight layer was wound around the outside of the prepreg of the bias layer which was previously wound.
  • prepreg of the first reinforcing layer was wound around the outside of the prepreg of the straight layer which was previously wound.
  • prepreg of the second reinforcing layer was wound around the outside of the prepreg of the first reinforcing layer which was previously wound.
  • a heat shrinkage tape made of polypropylene and PET (polyethylene terephthalate) was wound around the prepreg of each layer to fix the prepreg.
  • the whole was put into a heating furnace to heat at 130° C. for one hour, and thus the epoxy resin as a matrix resin was cured.
  • the heat shrinkage tape was removed and the mandrel was pulled out, thereby producing a CFRP pipe having the length of 1050 mm.
  • the CFRP pipe was cut into three equal parts by 350 mm length, thereby obtaining a test pipe having the length of 350 mm.
  • Example 1 had the following lamination structure.
  • the prepreg of +45° was laminated to have two layers and the prepreg of ⁇ 45° was laminated to have two layers using the prepreg D as the prepreg of the bias layer.
  • the lamination was performed to have three layers using the prepreg E as the prepreg of the straight layer.
  • the lamination was performed to have two layers using the prepreg C as the prepreg of the first reinforcing layer.
  • the lamination was performed to have two layers using the prepreg A as the prepreg of the second reinforcing layer.
  • the thickness of the bias layer was 0.37 ram
  • the thickness of the straight layer was 0.31 mm
  • the thickness of the first reinforcing layer was 0.19 mm
  • the thickness of the second reinforcing layer was 0.22 mm.
  • the inner diameter of the pipe was 5.5 mm and the outer diameter of the pipe was 7.7 mm.
  • Example 2 had the following lamination structure.
  • the prepreg of +45° was laminated to have two layers and the prepreg of ⁇ 45° was laminated to have two layers using the prepreg D as the prepreg of the bias layer.
  • the lamination was performed to have three layers using the prepreg E as the prepreg of the straight layer.
  • the lamination was performed to have two layers using the prepreg B as the prepreg of the first reinforcing layer.
  • the lamination was performed to have two layers using the prepreg A as the prepreg of the second reinforcing layer.
  • the thickness of the bias layer was 0.37 mm
  • the thickness of the straight layer was 0.31 mm
  • the thickness of the first reinforcing layer was 0.20 mm
  • the thickness of the second reinforcing layer was 0.22 mm.
  • the inner diameter of the pipe was 5.5 mm and the outer diameter of the pipe was 7.7 mm.
  • Example 3 had the following lamination structure.
  • the prepreg of +45° was laminated to have two layers and the prepreg of ⁇ 45° was laminated to have two layers using the prepreg D as the prepreg of the bias layer.
  • the lamination was performed to have three layers using the prepreg E as the prepreg of the straight layer.
  • the lamination was performed to have two layers using the prepreg C as the prepreg of the first reinforcing layer.
  • the lamination was performed to have two layers using the prepreg B as the prepreg of the second reinforcing layer.
  • the thickness of the bias layer was 0.37 mm
  • the thickness of the straight layer was 0.31 mm
  • the thickness of the first reinforcing layer was 0.19 mm
  • the thickness of the second reinforcing layer was 0.20 mm.
  • the inner diameter of the pipe was 5.5 mm and the outer diameter of the pipe was 7.6 mm.
  • Example 4 had the following lamination structure.
  • the prepreg of +45° was laminated to have two layers and the prepreg of ⁇ 45° was laminated to have two layers using the prepreg D as the prepreg of the bias layer.
  • the lamination was performed to have three layers using the prepreg E as the prepreg of the straight layer.
  • the lamination was performed to have three layers using the prepreg C as the prepreg of the first reinforcing layer.
  • the lamination was performed to have a single layer using the prepreg A as the prepreg of the second reinforcing layer.
  • the thickness of the bias layer was 0.37 mm
  • the thickness of the straight layer was 0.31 mm
  • the thickness of the first reinforcing layer was 0.28 mm
  • the thickness of the second reinforcing layer was 0.11 mm.
  • the inner diameter of the pipe was 5.5 mm and the outer diameter of the pipe was 7.6 mm.
  • Example 5 had the following lamination structure.
  • the prepreg of +45° was laminated to have two layers and the prepreg of ⁇ 45° was laminated to have two layers using the prepreg D as the prepreg of the bias layer.
  • the lamination was performed to have three layers using the prepreg E as the prepreg of the straight layer.
  • the lamination was performed to have a single layer using the prepreg C as the prepreg of the first reinforcing layer.
  • the lamination was performed to have three layers using the prepreg A as the prepreg of the second reinforcing layer.
  • the thickness of the bias layer was 0.37 mm
  • the thickness of the straight layer was 0.31 mm
  • the thickness of the first reinforcing layer was 0.09 mm
  • the thickness of the second reinforcing layer was 0.33 mm.
  • the inner diameter of the pipe was 5.5 mm and the outer diameter of the pipe was 7.7 mm.
  • Comparative Example 1 had the following lamination structure.
  • the prepreg of +45° was laminated to have two layers and the prepreg of ⁇ 45° was laminated to have two layers using the prepreg D as the prepreg of the bias layer.
  • the lamination was performed to have three layers using the prepreg E as the prepreg of the straight layer.
  • the lamination was performed to have four layers using the prepreg B as the prepreg of the first reinforcing layer.
  • the thickness of the bias layer was 0.37 mm
  • the thickness of the straight layer was 0.31 mm
  • the thickness of the first reinforcing layer was 0.41 mm.
  • the inner diameter of the pipe was 5.5 mm and the outer diameter of the pipe was 7.7 mm.
  • Comparative Example 2 had the following lamination structure.
  • the prepreg of +45° was laminated to have two layers and the prepreg of ⁇ 45° was laminated to have two layers using the prepreg D as the prepreg of the bias layer.
  • the lamination was performed to have three layers using the prepreg E as the prepreg of the straight layer.
  • the lamination was performed to have four layers using the prepreg E as the prepreg of the first reinforcing layer.
  • the thickness of the bias layer was 0.37 mm
  • the thickness of the straight layer was 0.31 mm
  • the thickness of the first reinforcing layer was 0.41 mm.
  • the inner diameter of the pipe was 5.5 mm and the outer diameter of the pipe was 7.7 mm.
  • FIG. 7 is a schematic block diagram of a test apparatus of the shafts made of the fiber-reinforced composite material according to Examples 1 to 5 and Comparative Examples 1 and 2.
  • a test apparatus 50 is an apparatus configured to perform a static three-point bending test and includes a pair of supporting members 51 and an indenter 52 .
  • the pair of supporting members 51 is a member configured to support a test pipe 10 of the shaft made of the fiber-reinforced composite material.
  • An upper end of the supporting member 51 forms a curved surface having a radius of 5 mm.
  • a distance between the pair of supporting members 51 that is, a distance between support points is 300 mm.
  • the indenter 52 is a member configured to apply a load to the test pipe 10 of the shaft made of the fiber-reinforced composite material from the top.
  • a lower end of the indenter 52 forms a curved surface having a radius of 75 mm.
  • a distance between each supporting member 51 and the indenter 52 that is, a distance between the support point and a load point is 150 mm. The indenter 52 moves downward to apply the load to the test pipe 10 .
  • the static three-point bending test was performed using the test apparatus 50 . Specifically, the test pipe 10 was placed on the pair of supporting members 51 , and the load was applied to the test pipe 10 by the indenter 52 . The moving speed of the indenter 52 was set to be 1 mm/min. In Examples 1 to 5 and Comparative Examples 1 and 2, a bending fracture load, fracture deflection, bending rigidity, and absorption energy were measured. Table 2 indicates measurement results of the shafts made of the fiber-reinforced composite material according to Examples 1 to 5 and Comparative Examples 1 and 2.
  • Example 2 Lami- Bias layer Inner Prepreg D (CF: XN-60) nation layer +45°: two layers struc- ⁇ 45°: two layers ture Four layers in total, full thickness of bias layer 0.37 mm
  • Straight layer Prepreg E (CF: TR50S) 0°: Three layers, full thickness of straight layer 0.31 mm First Prepreg C Prepreg B Prepreg C Prepreg C Prepreg C Prepreg B Prepreg E reinforcing (CF: XN-15) (CF: XN-10) (CF: XN-15) (CF: XN-15) (CF: XN-15) (CF: XN-15) (CF: XN-10) (CF: TR50S) layer 0°: two layers 0°: two layers 0°: two layers 0°: three layers 0°: single layer 0°: four layers 0°: four layers Layer thickness Layer thickness Layer thickness Layer thickness Layer thickness Layer thickness Layer thickness Layer thickness Layer thickness Layer thickness 0.19 mm 0.
  • the reinforcing layer was laminated to have four layers.
  • the reinforcing layer (first reinforcing layer and second reinforcing layer) contained two kinds of carbon fibers having a different tensile elastic modulus in Examples 1 to 5, whereas the reinforcing layer contained only one kind of carbon fiber in Comparative Examples 1 and 2.
  • the bending fracture loads in Examples 1 to 5 were greater than either of the bending fracture loads in Comparative Examples 1 and 2
  • the fracture deflections in Examples 1 to 5 were greater than either of the fracture deflections in Comparative Examples 1 and 2.
  • all kinds of absorption energy in Examples 1 to 5 were greater than any kinds of absorption energy in Comparative Examples 1 and 2.
  • the bending strength bending fracture load, fracture deflection, and absorption energy
  • Example 1 the first reinforcing layer and the second reinforcing layer were formed using the same prepreg, but the ratio of the lamination number was different from each other. Therefore, the bending rigidity in Example 1, the bending rigidity in Example 4, and the bending rigidity in Example 5 were different from each other. Thus, it was confirmed that the bending rigidity can be controlled in a wide range by changing the ratio of the lamination number of the first reinforcing layers to the lamination number of the second reinforcing layers.

Landscapes

  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Physical Education & Sports Medicine (AREA)
  • Golf Clubs (AREA)
  • Laminated Bodies (AREA)
  • Moulding By Coating Moulds (AREA)
US14/574,656 2013-12-27 2014-12-18 Shaft made of fiber-reinforced composite material Abandoned US20150182824A1 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
JP2013273099 2013-12-27
JP2013-273099 2013-12-27
JP2014245230A JP6490413B2 (ja) 2013-12-27 2014-12-03 繊維強化複合材料製シャフト
JP2014-245230 2014-12-03

Publications (1)

Publication Number Publication Date
US20150182824A1 true US20150182824A1 (en) 2015-07-02

Family

ID=53480648

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/574,656 Abandoned US20150182824A1 (en) 2013-12-27 2014-12-18 Shaft made of fiber-reinforced composite material

Country Status (2)

Country Link
US (1) US20150182824A1 (ja)
JP (1) JP6490413B2 (ja)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017013856A1 (en) 2015-07-17 2017-01-26 Nihon Kohden Corporation Lifesaving assisting apparatus
JP6164711B1 (ja) * 2016-07-06 2017-07-19 創造技術株式会社 補強用テープおよび補強用テープを用いた補強方法

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6273830B1 (en) * 1996-04-19 2001-08-14 Nippon Mitsubishi Oil Corporation Tapered hollow shaft
US6926617B2 (en) * 2002-03-15 2005-08-09 Sri Sports Limited Golf club shaft
US7048645B2 (en) * 2002-11-20 2006-05-23 Sri Sports Limited Golf club shaft
US8465612B2 (en) * 2009-09-25 2013-06-18 Sri Sports Limited Tubular body
US20130260911A1 (en) * 2012-03-29 2013-10-03 Bridgestone Sports Co., Ltd. Golf club shaft and golf club
US8876628B2 (en) * 2011-10-12 2014-11-04 Dunlop Sports Co. Ltd. Golf club shaft and golf club using the same
US8915796B2 (en) * 2011-12-29 2014-12-23 Dunlop Sports Co. Ltd Golf club shaft and golf club
US20150224375A1 (en) * 2012-10-10 2015-08-13 Dunlop Sports Co. Ltd. Golf club shaft

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5968621A (en) * 1996-01-16 1999-10-19 Shimano, Inc. Tubular member
JP3457872B2 (ja) * 1996-12-20 2003-10-20 三菱レイヨン株式会社 オーバーホーゼルタイプのゴルフクラブシャフト及びゴルフクラブ
JPH1199229A (ja) * 1997-09-29 1999-04-13 Mizuno Corp ゴルフクラブ用のシャフト
JP3540195B2 (ja) * 1998-05-01 2004-07-07 美津濃株式会社 繊維強化樹脂製ゴルフクラブ用シャフト
JP2000263653A (ja) * 1999-03-19 2000-09-26 Nippon Mitsubishi Oil Corp 繊維強化複合材料製管状体
JP2003024489A (ja) * 2001-07-11 2003-01-28 Sumitomo Rubber Ind Ltd ゴルフクラブシャフト
JP2004081230A (ja) * 2002-08-22 2004-03-18 Sumitomo Rubber Ind Ltd ゴルフクラブシャフト
JP2007000528A (ja) * 2005-06-27 2007-01-11 Nippon Oil Corp 繊維強化複合材料製ゴルフクラブ用シャフト
JP2013202250A (ja) * 2012-03-29 2013-10-07 Bridgestone Sports Co Ltd ゴルフクラブシャフト及びゴルフクラブ
JP6303161B2 (ja) * 2013-08-05 2018-04-04 住友ゴム工業株式会社 ゴルフクラブ用シャフト

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6273830B1 (en) * 1996-04-19 2001-08-14 Nippon Mitsubishi Oil Corporation Tapered hollow shaft
US6926617B2 (en) * 2002-03-15 2005-08-09 Sri Sports Limited Golf club shaft
US7048645B2 (en) * 2002-11-20 2006-05-23 Sri Sports Limited Golf club shaft
US8465612B2 (en) * 2009-09-25 2013-06-18 Sri Sports Limited Tubular body
US8876628B2 (en) * 2011-10-12 2014-11-04 Dunlop Sports Co. Ltd. Golf club shaft and golf club using the same
US8915796B2 (en) * 2011-12-29 2014-12-23 Dunlop Sports Co. Ltd Golf club shaft and golf club
US20130260911A1 (en) * 2012-03-29 2013-10-03 Bridgestone Sports Co., Ltd. Golf club shaft and golf club
US20150224375A1 (en) * 2012-10-10 2015-08-13 Dunlop Sports Co. Ltd. Golf club shaft

Also Published As

Publication number Publication date
JP6490413B2 (ja) 2019-03-27
JP2015143008A (ja) 2015-08-06

Similar Documents

Publication Publication Date Title
JPWO2010084809A1 (ja) Ｆｒｐ円筒の製造方法及びｆｒｐ円筒
KR960000558B1 (ko) 일방향 프리프렉 및 탄소섬유 강화 복합재료
JP2888664B2 (ja) Ｃｆｒｐ製光学用筒
JP5548516B2 (ja) 繊維強化プラスチック製ばね
JP5336225B2 (ja) 多軸ステッチ基材とそれを用いたプリフォーム
US20150182824A1 (en) Shaft made of fiber-reinforced composite material
US20170225383A1 (en) Method of manufacturing shaft-shape composite member
JP3771360B2 (ja) 繊維強化複合材料製管状体
US5753324A (en) Fiber-reinforced composite cylindrical form
US20180222167A1 (en) Shaft-like composite member
CN113646556B (zh) 具有碳纤维和玻璃纤维层的复合线圈弹簧
EP3279510B1 (en) Screw shaft, manufacturing method thereof, and ball screw device
JP2007216554A (ja) 繊維強化合成樹脂パイプ
JP2019171676A (ja) 繊維強化樹脂管状体、及びその製造方法
JP2007000528A (ja) 繊維強化複合材料製ゴルフクラブ用シャフト
KR20180008421A (ko) 골프 클럽 샤프트
JP2021094739A (ja) 筒状体
JP2007216558A (ja) 繊維強化合成樹脂ボビン
KR20140138032A (ko) 파이프 성형체
JPH09277389A (ja) テーパ付き中空シャフト
KR100760168B1 (ko) 반송용 부재
JP2007152938A (ja) Ｆｒｐ製部材
JP2566705B2 (ja) 一方向プリプレグと炭素繊維強化樹脂複合材料及びそれらの製造方法
JP6482841B2 (ja) ゴルフクラブ用シャフト及びゴルフクラブ用シャフトの製造方法
JP4877153B2 (ja) 繊維強化複合材料成形方法

Legal Events

Date Code Title Description
AS Assignment

Owner name: JX NIPPON OIL & ENERGY CORPORATION, JAPAN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:TAKEMURA, SHINICHI;REEL/FRAME:034545/0358

Effective date: 20141211

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION