WO2019131893A1 - Matériau composite, structure en couches, aile d'aéronef et procédé de fabrication de matériau composite - Google Patents

Matériau composite, structure en couches, aile d'aéronef et procédé de fabrication de matériau composite Download PDF

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Publication number
WO2019131893A1
WO2019131893A1 PCT/JP2018/048189 JP2018048189W WO2019131893A1 WO 2019131893 A1 WO2019131893 A1 WO 2019131893A1 JP 2018048189 W JP2018048189 W JP 2018048189W WO 2019131893 A1 WO2019131893 A1 WO 2019131893A1
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Prior art keywords
composite material
fiber
fibers
ply
oriented
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PCT/JP2018/048189
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English (en)
Japanese (ja)
Inventor
周 水口
展雄 武田
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国立大学法人東京大学
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Priority to JP2019562175A priority Critical patent/JPWO2019131893A1/ja
Publication of WO2019131893A1 publication Critical patent/WO2019131893A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • 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
    • B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
    • 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
    • B32B5/22—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
    • B32B5/28—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 impregnated with or embedded in a plastic substance
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the present invention relates to composite materials, laminated structures, aircraft wings and methods of making composite materials.
  • Composite materials are widely used in structures such as aircrafts and satellites because they are lightweight, have high strength, and can be freely designed to have strength and rigidity depending on applications.
  • the load or external force acting on such a structure is not uniform depending on the position on the structure. For this reason, according to the position on a structure, the weight reduction can be achieved, securing rigidity required for the position by changing the number of sheets of the composite material to laminate
  • U.S. Pat. No. 5,956,015 describes a composite laminate that reduces the weight of the wing skin without sacrificing flexural strength, flexural rigidity and damage tolerance.
  • first plurality of plies comprising longitudinally oriented reinforcing fibers with respect to the main loading direction, and reinforcing fibers oriented at an angle of between 15 degrees and 35 degrees to the main loading direction.
  • a laminate of the second plurality of plies is described.
  • the thickness is changed so as to form a gentle taper, the waste of material increases and the weight of the structure increases.
  • providing a gradual taper of 1:50 to 1: 100 may result in a weight gain of 30% or more as compared to a steep taper of 1: 5.
  • An object of the present invention is to provide a composite material, a laminated structure, a wing of an aircraft, and a method of manufacturing the composite material, which can achieve both suppression of delamination and weight reduction.
  • the composite material according to one aspect of the present invention is integrally connected to the main body in which the first fibers are oriented in the first direction and the end of the main body in the first direction in the matrix. It is equipped with a stress relieving portion provided.
  • the second fibers of the stress relieving portion continuous with the first fibers of the main body portion are oriented along a second direction which forms an acute angle with the first direction.
  • the main body portion in which the first fiber is oriented in the first direction is provided, while maintaining the elastic modulus in the first direction, the second direction having an acute angle with the first direction
  • the elastic modulus in the first direction at the end becomes small. For this reason, when laminating such a composite material, for example, stress concentration occurring at the end can be alleviated and peeling can be suppressed due to the high elastic modulus of the end. .
  • the first and second fibers are continuous, stress concentration at this boundary is also avoided.
  • the composite material according to another aspect of the present invention is connected to the first main body portion in which the first fibers are oriented in the first direction, and the one end portion of the first main body portion in the first direction. And a stress relaxation portion in which a second fiber continuous to the first fiber is oriented along a curve including a straight line directed in a third direction perpendicular to the first direction as a tangent. .
  • the stress relaxation portion in which the second fiber continuous to the first fiber is oriented is provided along the curve including, as a tangent, a straight line directed in the third direction perpendicular to the first direction, while maintaining the elastic modulus with respect to the first direction in one direction, the elastic modulus in multiple directions including the first direction in the stress relaxation portion decreases. For this reason, when laminating such a composite material, for example, the stress concentration generated in the portion corresponding to the stress relaxation portion is alleviated due to the high elastic modulus, and the peeling is suppressed. It becomes possible.
  • a third fiber continuous to the second fiber is oriented along a fourth direction toward the other end in the first direction of the first main body portion, integrally connected to the stress relieving portion, You may further provide the 2nd main-body part laminated
  • the third fibers continuous with the second fibers may be oriented in the fourth direction.
  • the fourth direction may form an acute angle with the first direction, or may be parallel to the first direction.
  • the curve indicating the orientation of the second fiber in the stress relieving portion may be a circular arc, an ellipse, or any other curve, but it is possible to continuously and smoothly connect the first fiber and the third fiber preferable.
  • a partially linear portion for example, a curve having a large radius of curvature may be included.
  • a laminated structure according to another aspect of the present invention includes a second composite material that is longer than the composite material in the first direction, and the composite material stacked on the second composite material.
  • the composite material provided with the above-described stress relaxation portion can be used as the composite material laminated on the second composite material, it is possible to reduce the stress concentration generated at the end. As a result, it is possible to suppress exfoliation between the second composite material.
  • the fibers included in the second composite material may not necessarily be oriented in the first direction, and may be oriented in different directions (for example, 90 degrees or ⁇ 45 degrees).
  • a composite material comprising fibers oriented in different directions may be further laminated in the gap with the composite material or above and below.
  • another composite material comprising fibers oriented at +45 degrees
  • yet another composite material comprising fibers oriented at -45 degrees
  • the composite materials of the above may be laminated in order.
  • the fibers may be made of the same material among the composite materials.
  • glass fibers or carbon reinforced fibers can be used as the fibers.
  • the resin the same material may be used among the composite materials, and for example, an epoxy resin or a carbon resin can be used as the resin.
  • an aircraft wing according to another aspect of the present invention includes the above-described laminated structure.
  • Another aspect of the present invention is a method of producing a composite material. Then, preparing a composite material in which fibers are oriented in a first direction into the matrix, and shearing the end of the composite material in a direction perpendicular to the first direction, And a body portion in which the first fibers are oriented along the direction, and an end portion of the body portion in the first direction, integrally provided, along a second direction forming an acute angle with the first direction Providing a stress relieving portion in which the second fibers continuous with the first fibers are oriented.
  • a step of preparing a composite material in which fibers are oriented in a first direction in a base material, and bending an intermediate portion in the first direction of the base material A first main body portion in which the first fibers are oriented in the first direction, and one end of the first main body portion in the first direction are integrally provided in the base material, in the first direction;
  • Providing including.
  • a stress relaxation portion in which the second fiber continuous to the first fiber is oriented along a curve including, as a tangent, a straight line directed in the third direction perpendicular to the first direction.
  • the elastic modulus in the first direction in the stress relaxation portion decreases. For this reason, when laminating such a composite material, for example, the stress concentration generated in the portion corresponding to the stress relaxation portion is alleviated due to the high elastic modulus, and the peeling is suppressed. It is possible to produce composite materials.
  • a middle part means the part which is not an edge part, and it is not restricted to the part which bisects the both ends of a base material. Therefore, the length in the first direction of the first main body and the length in the first direction of the second main body may be different. Also, the portion to be bent may not necessarily be perpendicular to the first direction. It is also possible to adjust the fourth direction by bending the first direction at an acute angle. After that, if necessary, the composite material can be cut to obtain a composite material having a desired shape.
  • the third direction may be a stacking direction, but may be an in-plane direction perpendicular to the first direction.
  • the base material is preferably in the form of a layer, but is not limited thereto.
  • the present invention it is possible to provide a composite material, a laminated structure, a wing of an aircraft, and a method of manufacturing the composite material, which can achieve both suppression of delamination and weight reduction.
  • FIG. 1A is a plan view conceptually showing a laminated structure 10 according to the first embodiment of the present invention
  • FIG. 1B is a front view of the laminated structure 10.
  • FIG. 2A is a plan view conceptually showing the laminated structure 100 of the comparative example
  • FIG. 2B is a front view of the laminated structure 100. As shown in FIG.
  • the laminated structure 10 includes a base ply 12 (an example of a “second composite material”) and a ply 14 (“composite material”) laminated on the ply 12. And a ply 16 (an example of a “base material” made of a “composite material”) laminated on the ply 14.
  • Each ply 12, the ply 14 and the ply 16 have a sheet-like layer structure made of CFRP (Carbon Fiber Reinforced Plastic), and are provided with fibers oriented in a predetermined direction in a resin.
  • CFRP Carbon Fiber Reinforced Plastic
  • Each ply of the laminated structure 10 is integrally molded by being heated and pressurized in an autoclave.
  • the laminated structure 10 does not have to be a double layer of the ply 14 and the ply 16, and may be only the ply 14 or the ply 16. Furthermore, other plies may be laminated.
  • the material and content of the resin and fibers of the ply 12, the ply 14 and the ply 16 of the laminated structure 10 can be appropriately set without changing the gist of the present invention.
  • the resin may be thermoplastic or thermosetting, and the fibers may be carbon fibers or glass fibers and the like.
  • the thickness and shape of the layer structure of the ply 12, the ply 14 and the ply 16 can be appropriately set according to the purpose and the like. Further, the ply 12, the ply 14 and the ply 16 do not have to be made of the same material, and for example, the materials of the resins contained in the ply 12 and the ply 14 may be made different. Furthermore, as described in detail later, plies having the same or different fiber orientations may be further stacked between each ply 12, ply 14 and ply 16 or up and down. Furthermore, a cover ply may be provided.
  • the orientation direction of the fibers 16C of the ply 16 is shown in FIG. 1A.
  • first direction and is referred to as "longitudinal direction X" or "0 degree direction”
  • first direction and is referred to as "longitudinal direction X" or "0 degree direction”
  • main portion 16A an example of a “main portion”.
  • each fiber 16C of the ply 16 is bent in the vicinity of the end on the other end side in the longitudinal direction X, and in a direction X1 (an example of “second direction”) forming an acute angle with the longitudinal direction X in plan view. It is oriented in parallel. In the present embodiment, the angle of the direction X1 with respect to the longitudinal direction X is +45 degrees.
  • a region in which the fibers 16C are oriented along the direction X1 is referred to as a stress relaxation portion 16B (an example of a "stress relaxation portion").
  • the length of the stress relaxation portion 16B is, for example, 5 mm, and the length of the main body portion 16A has a length of 10 times or more.
  • the lower ply 14 of the ply 16 also has a similar structure. Specifically, the fibers of the ply 14 are oriented parallel to the longitudinal direction X from one end of the ply 14 to the vicinity of the other end, bent near the end, and oriented parallel to the direction X1. For this reason, the ply 14 also includes the main body portion 14A and the stress relief portion 14B at substantially the same position as the ply 16 in the longitudinal direction X.
  • the length of the ply 14 in the first direction may be longer than that of the ply 16 so that the thickness of the stacked structure 10 in the stacking direction Z may be different. Furthermore, a plurality of plies having different lengths in the first direction may be stacked on the ply 16 as well.
  • FRP Fiber Reinforced Plastic
  • CFRP Fiber Reinforced Plastic
  • the elastic modulus in the direction different from the orientation direction is greatly reduced.
  • the elastic modulus in the direction different by 20 degrees from the orientation direction drops to about half of the elastic modulus in the orientation direction.
  • the elastic modulus of the main body portion 16A and the main body portion 14A in the longitudinal direction X is about 200 GPa
  • the elastic modulus of the stress relaxation portion 16B and the stress relaxation portion 14B is 50 GPa or less.
  • a ply containing fibers oriented in the depth direction Y (or “90 degree direction”) perpendicular to the longitudinal direction X and the stacking direction Z on the ply 16, +45 degrees from the longitudinal direction X and the depth direction Y
  • a ply containing fibers oriented in a direction, and a ply containing fibers oriented in the direction of ⁇ 45 degrees from the longitudinal direction X and the depth direction Y can be laminated repeatedly in random order.
  • a plurality of plies in which fibers are oriented in the 0 degree direction, +45 degree direction, -45 degree direction, and 90 degree direction can be repeatedly laminated.
  • the fibers of the ply 12 disposed below the ply 14 may be oriented in the 0 degree direction from one end of the longitudinal direction X to the other end.
  • the ply 12 is formed to be longer than the plies 16 and 14 in the longitudinal direction X. Unlike the plies 16 and 14, the fibers of the ply 12 are not oriented parallel to the direction X1 at the ends. However, it is not limited to this. For example, when the ply 12 is further laminated on another ply, the end of the fiber of the ply 12 whose thickness in the laminating direction changes is bent and oriented parallel to the direction X1 forming an acute angle with the longitudinal direction X It may be configured as follows. In that case, the ply 12 also has a body portion and a stress relief portion.
  • the fibers of the ply 12, the ply 14 and the ply 16 are not oriented in the stacking direction Z of the ply 12, the ply 14 and the ply 16. However, it is not limited to this.
  • FIG. 2A is a plan view of the laminated structure 100 according to the comparative example
  • FIG. 2B is a front view of the laminated structure 100.
  • the laminated structure 100 includes a base ply 120, a ply 140 stacked on the ply 120, and a ply 160 stacked on the ply 140.
  • Each ply 120, the ply 140 and the ply 160 have a sheet-like layer structure made of CFRP.
  • the fibers 160C of the ply 160 of the laminate structure 100 and the fibers of the ply 140 are oriented parallel to the longitudinal direction X over the entire area from one end to the other in the longitudinal direction X. There is.
  • the elastic modulus in the longitudinal direction X of the ply 140 is uniformly high, a large stress is generated for a predetermined strain. As a result, stress is concentrated at the end portion of the ply 140 whose thickness is changed, and a large peel stress and shear stress which cause peeling from the lower ply 120 occur. Further, in the laminated structure 100, since the elastic modulus also changes in the laminating direction as the thickness changes, the neutral axis of the cross section shifts to the ply 140 side, and a secondary bending deformation also occurs due to the tensile load. Do. As a result, a large bending moment is generated in the vicinity of the end of the ply 140, which causes a crack to occur and progress.
  • the elastic modulus in the longitudinal direction X of the stress relaxation portion 14B of the ply 14 is not more than half the elastic modulus of the main body portion 14A, the stress generated for a predetermined strain is also relative As small as As a result, it is possible to suppress the stress concentration in the stress relieving portion 14B and the generation of a crack associated therewith.
  • the stress relaxation portion 14B is provided, the change in elastic modulus in the stacking direction is also smaller than that in the stacked structure 100. Therefore, the neutral axis of the cross section does not change significantly, and secondary bending deformation due to tensile load is suppressed. As a result, the bending moment in the vicinity of the end portion of the ply 14 is reduced, so that it is possible to suppress the occurrence and progress of the crack as compared with the laminated structure 100.
  • FIG. 3A is a front view of the laminated structure 200 according to the comparative example
  • FIG. 3B is a front view of the laminated structure 300 according to the comparative example
  • FIG. 3C is a front view of the laminated structure 20 according to the present invention
  • FIG. These show the front view of the laminated structure 30 which concerns on this invention.
  • FIG. 4A is an enlarged view of a portion where the thickness direction of the laminated structure 200 changes
  • FIG. 4B is an enlarged view of the laminated structure 300
  • FIG. 4C is an enlarged view of the laminated structure 20, FIG. These show the same enlarged view of the laminated structure 30.
  • FIG. 4A is an enlarged view of a portion where the thickness direction of the laminated structure 200 changes
  • FIG. 4B is an enlarged view of the laminated structure 300
  • FIG. 4C is an enlarged view of the laminated structure 20, FIG. These show the same enlarged view of the laminated structure 30.
  • Each of the laminated structures 200, 300, 20 and 30 is a structure in which a plurality of plies made of T700SC / 2592 are laminated, and the length in the longitudinal direction X is 180 mm, and the length in the depth direction Y is , 10 mm. Both ends in the longitudinal direction X form thick portions where the thickness in the stacking direction Z is large, and 16 plies each having a thickness of about 100 ⁇ m (for example, 125 ⁇ m) are stacked. The central portion forms a thin portion having a small thickness in the stacking direction Z, and eight plies are stacked.
  • the fibers of each ply of the laminated structure 200 are uniformly oriented in the 0 degree direction, that is, in the longitudinal direction X from one end to the other end.
  • the fibers of each ply of the laminated structure 300 are also uniformly oriented in the 0 degree direction, that is, in the longitudinal direction X from one end to the other end.
  • the variation in the stacking direction Z is gentler than that of the stacked structure 200 in the 10: 1 taper (ie, 1 mm variation in the stacking direction).
  • a lower ply portion 22 in which eight plies are laminated and a ply portion 24 in which eight plies are laminated and laminated on the ply portion 22 (an example of a “composite material”) Equipped with The fibers of each ply of the ply portion 22 are oriented in the 0 degree direction.
  • the ply portion 24 includes a main portion 24A in which the fibers of each ply are oriented in the 0 degree direction, and a stress relaxation portion 24B in which the fibers are bent and oriented in the +45 degree direction.
  • the length of the stress relaxation portion 24B in the longitudinal direction X is 5 mm. Since each ply of the ply portion 24 is laminated after providing the stress relieving portion 24B by in-plane shear deformation, the thickness in the laminating direction Z is larger than that of the main portion 24A.
  • a lower ply portion 32 in which eight plies are laminated and a ply portion 34 in which eight plies are laminated and laminated on the ply portion 32 (an example of a “composite material”) Equipped with The fibers of each ply of the ply portion 32 are oriented in the 0 degree direction.
  • the ply portion 34 is integrally provided by connecting the body portion in which the fibers are oriented in the 0 ° direction and the end portion of the body portion, and the fibers connected to the fibers in the body portion are oriented in the + 45 ° direction
  • the ply portion 34 has a main portion 34A in which the fibers of each ply are oriented in the 0 degree direction and a stress relaxation portion 34B in which the fibers are bent and alternately oriented in the +45 degree direction or -45 degree direction.
  • the length of the stress relaxation portion 34B in the longitudinal direction X is 5 mm.
  • a tensile fatigue test was performed on such a laminated structure 200, 300, 20, and 30 under the conditions of a maximum load of 4000 N, a load ratio of 0.1, and a test frequency of 8 Hz.
  • FIG. 5 shows the test results of the laminated structures 200, 300 and 20.
  • the horizontal axis represents the number of cycles at which the maximum load is applied at the test frequency, and the vertical axis represents the delamination length.
  • the laminated structure 200 is shown to have exfoliation occurring from 2000 to 3000 times. After the occurrence of peeling, peeling progressed in proportion to the number of times of load application, and when a load of about 10,000 times was applied, peeling of 40 mm or more was formed.
  • peeling occurs in the laminated structure 300 from 9000 times to 10000 times. And after 12000 times, peeling progressed in proportion to the number of times of load application, and when load of about 17000 times was applied, peeling of 50 mm or more was formed.
  • the laminated structure 20 was significantly superior to the other laminated structures 30, 200, and 300 in that peeling occurred at 28,000 times to 29,000 times. Thereafter, the progress of peeling is suppressed, and it is shown that the progress of peeling is within 5 mm, that is, in the stress relaxation portion 24B even when a load of 6000 times (34000 times in total) is applied after the peeling occurs. It was done. Peeling progressed to the same extent as laminated structure 300 after 35000 times after that.
  • the main body portions 16A, 24A and 34A are provided, it is possible to withstand the load in the longitudinal direction X, and the stress relieving portion 16B. , 24B and 34B, it is possible to suppress the occurrence and progress of peeling.
  • laminated structure 10, 20 and 30 can also be manufactured by a different method.
  • the resin may be impregnated and molded.
  • the composite according to the present invention using a known manufacturing technology (RTM (Resin Transfer Molding), RFI (Resin Film Infusion), CPM (Compression Press Molding), FW (Filament Winding), LFT (Long Fiber Thermoplastic), etc.) Materials and laminate structures can be manufactured.
  • RTM Resin Transfer Molding
  • RFI Resin Film Infusion
  • CPM Compression Press Molding
  • FW Filament Winding
  • LFT Long Fiber Thermoplastic
  • a sheet-like prepreg in which fibers are oriented in a predetermined direction is prepared.
  • a CFRP prepreg can be used as a base material.
  • the end portion of such a prepreg (for example, a region within 5 mm to 10 mm from the end surface of the prepreg) is sheared in an in-plane direction perpendicular to the fiber orientation to correspond to the main portion and the stress relaxation portion Provide an area.
  • a method for shear deformation for example, a region corresponding to the main body maintaining the orientation direction of the fiber constant is gripped and fixed, and an end portion to be a free end is gripped to be in a plane perpendicular to the fiber orientation direction.
  • the end of the prepreg can be sheared and deformed. By changing the amount of movement in the shearing direction, it is possible to adjust the orientation direction of the fibers.
  • the orientation direction can be changed in the 45 ° direction by moving approximately 10 mm in the in-plane direction perpendicular to the orientation direction of the fibers.
  • shear deformation it is possible to use a robot provided in the automatic stacking apparatus, or it may be deformed manually while being heated.
  • the elastic modulus rapidly decreases in the direction different from the orientation direction.
  • the elastic modulus is halved when it deviates 20 degrees from the orientation direction, and a nearly constant low elastic modulus is maintained when it deviates by 45 degrees or more.
  • it is not always necessary to bend the fibers in the correct orientation direction.
  • variation in orientation between fibers can be tolerated.
  • a portion corresponding to the main body portion in which the fiber orientation direction is constant and an end portion in the fiber orientation direction of the main body portion are integrally provided to be bent, As a result, for example, it is possible to provide a prepreg including a portion corresponding to the stress relaxation portion in which the fibers are oriented along the 45 ° direction.
  • such a prepreg is cut into a desired shape.
  • the end face of each fiber is not 45 degrees It can align so that it may turn to the 0 degree direction which is an orientation direction of textiles in a main part.
  • Each fiber itself has a high elastic modulus in the axial direction, for example, in the stress relaxation portion whose orientation direction is changed in the 45-degree direction, the axis of the fiber, not the 45-degree direction perpendicular to the axial direction of the fibers
  • the present invention is not limited to this, and shear deformation may be performed after the shape is adjusted by cutting or the like.
  • the fiber may be bent to change the orientation direction by means other than shear deformation.
  • the laminated structure including the main body portion and the stress relieving portion can be integrally formed.
  • Such a laminated structure can be applied to transportation devices such as aircraft fuselages and wings, artificial satellites, automobiles, ships and the like.
  • the bottom of the skin of an aircraft wing is provided with a plurality of inspection openings called access holes. Since a large load is applied to the peripheral portion of the access hole, it is necessary to increase the thickness of the composite material. On the other hand, it is necessary to reduce the thickness of the composite material and achieve weight reduction at a position away from the peripheral portion and not subjected to a large load. By applying the laminated structure according to the present embodiment to such a portion, it is possible to achieve both suppression of delamination and weight reduction.
  • the laminated structure according to the present embodiment By using the above, it is possible to suppress the easy peeling of the laminated structure attached.
  • the laminated structure which concerns on this embodiment is applicable also to the structure of other parts, such as a fuselage
  • the length in the longitudinal direction X of the composite material according to the above embodiment is, for example, several tens of mm or more, but each composite material and the fibers contained therein may be shorter.
  • CFRP can be cut by using a short pulse laser such as a femtosecond laser.
  • the laser is used to cut in a brick shape so that the length in the longitudinal direction is 5 to 10 mm or less, and each particle has a fixed fiber orientation direction while maintaining the aligned state of each particle
  • a composite material can be formed that includes a body portion and a stress relaxation portion in which the orientation direction of these fibers is bent. Under the present circumstances, it may be made a structure which can absorb energy by filling between each particle
  • Such a composite material has a problem that brittle fracture occurs from the end due to fatigue, a stress relaxation portion is provided at the end of each particle to reduce stress concentration by reducing the elastic modulus in the longitudinal direction. Since it is possible, it becomes possible to control the brittle fracture from the end.
  • the configuration is such that the height in the stacking direction Z gradually increases from the end face of the stress relaxation portion 16B toward the main body portion 16A by chamfering (in other words, the length in the longitudinal direction X It is good also as composition which becomes small. With such a configuration, it is possible to further reduce the elastic modulus in the longitudinal direction X of the stress relaxation portion 16B.
  • the laminated structures 10, 20, and 30 according to the above embodiments may include one or more cover plies. By providing such a cover ply and covering the upper surface facing in the stacking direction Z with the cover ply, it is possible to further suppress delamination.
  • the fiber orientation in the longitudinal direction X in the horizontal portion of the cover ply to be laminated on the main body portion 16A and the stress relaxation portion 16B is stress relaxation portion. From 16B, for the portion where the inclination varies toward the ply 12, the fiber orientation is in the direction X1, and then for the tapered portion toward the ply 12 while maintaining the inclination, the fiber orientation is again in the longitudinal direction X, The fiber orientation is in the direction X1 for the part reaching the ply 12 and the inclination is changed again in the horizontal direction, and for the horizontal part along the upper surface of the ply 12 in the longitudinal direction X. It can be structured as
  • the stress relaxation portion having a low elastic modulus in the portion where the stress is discontinuous, it becomes possible to suppress the occurrence of peeling due to the concentration of the stress in that portion.
  • the stress concentration at the tip of the CFRP disposed diagonally can be relaxed.
  • FIG. 6 is a perspective view of a laminated structure 60 according to a fifth modification.
  • the laminated structure described above has an object of alleviating stress concentration generated at an end in the longitudinal direction X, which is a direction in which a load is applied.
  • the stress relaxation portion 62B is provided at the free end of the depth direction Y end of the ply 62 including the fibers oriented in the 90 ° direction.
  • the ply 62 is integrally connected to the end of the main portion 62A in which the first fibers 62C are oriented in the depth direction Y and the end of the main portion 62A in the depth direction Y in the base material.
  • a stress relaxation portion 62B in which the first fibers 62C are oriented along a direction (for example, the X1 direction) forming an acute angle with the depth direction Y.
  • Another layer of the laminated structure 60 may be provided with a stress relaxation portion which relieves stress concentration generated at the end in the longitudinal direction X.
  • a stress relaxation portion which relieves stress concentration generated at the end in the longitudinal direction X.
  • a body portion in which fibers are oriented along the longitudinal direction X, and a tip portion continuous to the fibers along a direction (for example, X1 direction) forming an acute angle with the longitudinal direction X The stress relieving portion may be provided.
  • FIG. 7A is a plan view of the laminated structure 70 according to the second embodiment
  • FIG. 7B is a front view of the laminated structure 70.
  • the laminated structure 70 comprises at least a ply 12 and a ply 74 laminated on the ply 12.
  • the ply 74 has a structure in which the central portion is folded and laminated. Specifically, it is connected to a first main portion 74A1 in which fibers 74C1 (an example of "first fibers”) are oriented along the longitudinal direction X, and one end in the longitudinal direction X of the first main portion 74A1.
  • the stress relieving portion 74B (one example of “second fibers”) integrally provided and continuous to the fiber 74C1 is curvilinearly oriented, and the stress relieving part 74B (one example of “intermediate part”)
  • An example of a fiber 74C3 (“third fiber") continuous with the fiber 74C2 along the longitudinal direction X (an example of the "fourth direction") which is integrally provided and connected to the other end of the first main body 74A1 ) Is provided, and the second main body 74A2 is provided.
  • FIG. 7A also shows the orientation direction of the fibers 74C3 in the second main portion 74A2 that is the lower layer of the first main portion 74A1 in order to easily show the orientation direction of the fibers 74C.
  • the fibers 74C1 and the fibers 74C3 are oriented along the longitudinal direction X in parallel with each other, slightly separated in the depth direction Y.
  • the fibers 74C1 and the fibers 74C3 connected to the fibers 74C3 are smoothly bent so as to form an arc-shaped curve having a diameter larger than the distance between the fibers 74C1 and the fibers 74C3 in a plan view.
  • two tangents (L11 and L21 in FIG. 8) at both ends in the depth direction Y are directed in the longitudinal direction X and a tangent at one end in the longitudinal direction X (L31 in FIG.
  • An example of “a straight line facing in the direction” faces in the depth direction Y.
  • the fibers 74C1 and the fibers 74C3 are slightly separated in the stacking direction Z and oriented parallel to one another along the longitudinal direction X. Further, the fibers 74C2 are connected to the fibers 74C1 and the fibers 74C3 by drawing a gentle curve. For this reason, a tangent at one end of the longitudinal direction X of the fiber 74C2 (an example of “a straight line facing the third direction”) faces the stacking direction Z.
  • the fibers 74C2 in the stress relieving portion 74B are spirally bent so as to advance in the stacking direction Z while drawing a loop.
  • the elastic modulus of the stress relieving portion 74B is not only in the longitudinal direction X but also in any direction, the longitudinal direction X of the main body portion 74A1.
  • FIG. 8 shows a modification of the shape of the fibers 74C as viewed in the stacking direction Z.
  • FIG. 8A shows the shape of the fibers 74C1 '.
  • the fibers 74C1 ' have the same shape as the fibers 74C. That is, the fibers 74C11 'and the fibers 74C31' are oriented parallel to each other and in the longitudinal direction X while being slightly separated from each other in the depth direction Y, and the fibers 74C21 'are more than the distance between the fibers 74C11' and 74C31 '. It is smoothly curved to form an arc-shaped curve having a wide diameter.
  • the two tangents L11 and L21 at both ends in the depth direction Y are in the longitudinal direction X, and the tangent L31 at one end in the longitudinal direction X (a straight line facing the third direction) ) Is facing in the depth direction Y.
  • the fiber 74C shown in FIG. 7 is provided over the laminated structure of the main body 74A1 and the main body 74A2 by bending the ply 74
  • the fiber 74C1 ′ shown in FIG. 8A consists of a single layer It is provided in the ply.
  • a single main body including fibers 74C11 'oriented along the longitudinal direction X and fibers 74C31' oriented along the longitudinal direction X, and one end in the longitudinal direction of the main body
  • the stress relieving portion is integrally provided, and a fiber 74C21 'continuous to the fiber 74C11' and the fiber 74C31 'is oriented along a curve.
  • the elastic modulus of the stress relaxation portion is relatively small not only in the longitudinal direction X but also in any direction (for example, not more than half the elastic modulus in the longitudinal direction X of the main body 74A1) Have. Therefore, for example, even when a load in the direction X1 is received, it is possible to relieve the stress concentration.
  • the fibers 74C21 'of the stress relaxation portion of two adjacent fibers 74C1' may be arranged to overlap.
  • FIG. 8B also shows the shape of the fibers 74C2 '.
  • the fibers 74C22 ' may have an elliptical curve whose minor axis is the distance between the fibers 74C12' and the fibers 74C32 '.
  • a tangent L32 (an example of a "straight line pointing in the third direction") at one end in the longitudinal direction X is directed in the depth direction Y.
  • the curve of the fiber 74C12 'connecting the fiber 74C12' and the fiber 74C32 ' may be an ellipse, an arc, another higher order curve, or a combination of two or more thereof, and the curvature is partially small. It may include a portion that looks straight. Further, the fibers 74C12 'and the fibers 74C32' may be provided in the same main body, or may be provided in different main bodies by being bent.
  • FIG. 8C also shows the shape of the fiber 74C3 '.
  • the fibers 74C13 'and the fibers 74C33' are bent at the stress relieving portion provided with the fibers 74C23 'so as to substantially overlap when viewed in the stacking direction Z. Even in such a shape, the tangent L33 at one end of the longitudinal direction X of the fiber 74C23 'is directed in the depth direction Y.
  • FIG. 8D also shows the shape of the fibers 74C4 '.
  • the fibers 74C14 ' are oriented in the longitudinal direction X, and the fibers 74C34' are in the direction X2 ("fourth direction") forming an acute angle (eg 45 degrees) with the longitudinal direction X (Example) oriented.
  • the fibers 74C24 ' are bent at the stress relieving portion provided. Even in such a shape, the tangent L34 at one end of the longitudinal direction X of the fiber 74C24 'is directed in the depth direction Y. Further, tangents L14 and L24 at both ends in the depth direction Y are in the longitudinal direction X.
  • the elastic modulus of each of the stress relaxation portions provided with the fibers 74C21 'to 74C24' is smaller than the elastic modulus in the longitudinal direction X of the main body portion 74A1 in any direction (for example, , Half or less). Therefore, for example, even when a load in the direction X1 is received, it is possible to relieve the stress concentration.
  • the composite material shown in FIG. 8D has a high elastic modulus not only in the longitudinal direction X but also in the direction X2. For this reason, it is possible to suitably use a composite material in which a fiber 74C4 'as shown in FIG. 8D is provided at a place where it is known that a strong load is applied in two directions (longitudinal direction X and direction X2). Become.
  • the position at which the base material is bent does not necessarily have to be the central portion in the longitudinal direction X.
  • the base material may be bent at a position deviated from the central portion in the longitudinal direction X so that the length in the longitudinal direction X of the first body portion and the length in the longitudinal direction X of the second body portion are different. .
  • FIG. 9 is a view for explaining an example of a process of bending a base material performed by the automatic laminating apparatus M in order to produce the composite material as described above.
  • the composite material and the laminated structure according to the present invention can be manufactured by various methods. For example, a dry fiber is bent to form a desired laminated structure, and then the resin is impregnated. You may do so.
  • the automatic laminating apparatus M includes two adjacent cylindrical rollers R1 and R2 and a stage S.
  • a layered prepreg sheet P in which fibers are oriented in a predetermined direction in a base material is prepared.
  • the prepreg sheet P is passed using the roller R1 while passing the prepreg sheet P through the gap between the roller R1 and the roller R2 so that the orientation direction of the fibers of the prepreg sheet P and the moving direction by rotation of the roller R1 coincide. It is pressed against the stage S. As a result, a prepreg sheet P in which the fibers are oriented in the same direction as the moving direction of the roller R1 is disposed on the stage S.
  • FIG. 9B shows a state in which the prepreg sheet P is disposed on the stage S while the roller R1 and the roller R2 move in the right direction in the drawing by rotating.
  • the roller R1 and the roller R2 are rotated in the opposite direction, and the prepreg sheet P is pressed against the prepreg sheet P disposed on the stage S using the roller R1 using the roller R2, so that the base material is intermediate A process of folding the part and laminating the base material is performed.
  • FIG. 9C shows a state in which the prepreg sheet P is laminated while the roller R1 and the roller R2 move to the left in the drawing respectively by rotating in the opposite direction.
  • FIG. 10 shows the manufactured laminated structure 70 '.
  • the laminated structure 70 ′ comprises a ply 12 and four plies 74 ′ laminated on the ply 12.
  • each ply 74 ′ has the same configuration as the ply 74.
  • the first main body portion in the upper layer, the second main body portion in the lower layer, and a stress relaxation portion (an example of an “intermediate portion”) connecting these are provided.
  • the four plies 74 ' are provided such that the length in the longitudinal direction X becomes smaller as the upper layer becomes. Therefore, as a result of the position in the longitudinal direction X of the stress relieving portions 74B 'of each ply 74' being different, the laminated structure 70 'has a tapered shape as shown in FIG. Furthermore, a cover ply CP is provided above the stacking direction Z of the four plies 74 'so as to cover the stress relieving portion 74B'.
  • Each of the laminated structure 70 ′ and the standard test piece was subjected to a tensile test, and the number of cycles when broken was measured.
  • the standard test piece is provided with the cover ply CP after laminating 8 plies so as to have a taper of 5: 1 equivalent to the ply 74'. It has a structure.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Textile Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

L'invention concerne un matériau composite qui permet une réduction de poids et une prévention de séparation. Le matériau composite comprend : une section corps (16A) dans laquelle des fibres (16C) sont alignées dans une matrice dans une première direction X ; et une section relâchement de contrainte (16B) qui est reliée d'un seul tenant à une extrémité de la section corps (16A) dans la première direction X et dans laquelle les fibres (16C) sont alignées dans une seconde direction X1 qui forme un angle aigu avec la première direction X, de telles fibres étant continues avec les fibres de la section corps (16A).
PCT/JP2018/048189 2017-12-28 2018-12-27 Matériau composite, structure en couches, aile d'aéronef et procédé de fabrication de matériau composite WO2019131893A1 (fr)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021161717A1 (fr) * 2020-02-12 2021-08-19 三菱重工業株式会社 Structure de matériau composite

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6115710B2 (fr) * 1979-02-22 1986-04-25 Hasegawa Kagaku Kogyo Kk
JPH0496331U (fr) * 1991-01-29 1992-08-20
JPH0569491A (ja) * 1991-01-15 1993-03-23 United Technol Corp <Utc> 折れ曲がり形状の複合材層の製造方法及びその装置
JP2006218720A (ja) * 2005-02-10 2006-08-24 Murata Mach Ltd プリプレグシートの自動積層装置
US20080187441A1 (en) * 2006-10-18 2008-08-07 Karl Schreiber Fan blade made of a textile composite material

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6115710B2 (fr) * 1979-02-22 1986-04-25 Hasegawa Kagaku Kogyo Kk
JPH0569491A (ja) * 1991-01-15 1993-03-23 United Technol Corp <Utc> 折れ曲がり形状の複合材層の製造方法及びその装置
JPH0496331U (fr) * 1991-01-29 1992-08-20
JP2006218720A (ja) * 2005-02-10 2006-08-24 Murata Mach Ltd プリプレグシートの自動積層装置
US20080187441A1 (en) * 2006-10-18 2008-08-07 Karl Schreiber Fan blade made of a textile composite material

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021161717A1 (fr) * 2020-02-12 2021-08-19 三菱重工業株式会社 Structure de matériau composite
GB2607494A (en) * 2020-02-12 2022-12-07 Mitsubishi Heavy Ind Ltd Composite material structure

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