WO2015119023A1 - 複合材構造 - Google Patents

複合材構造 Download PDF

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Publication number
WO2015119023A1
WO2015119023A1 PCT/JP2015/052407 JP2015052407W WO2015119023A1 WO 2015119023 A1 WO2015119023 A1 WO 2015119023A1 JP 2015052407 W JP2015052407 W JP 2015052407W WO 2015119023 A1 WO2015119023 A1 WO 2015119023A1
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WO
WIPO (PCT)
Prior art keywords
corrugated core
base
face plate
composite structure
opening
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.)
Ceased
Application number
PCT/JP2015/052407
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
阿部　俊夫
清嘉 ▲高▼木
小山　貴之
雄哉 吉野
和昭 岸本
斎藤　浩一
隆司 石田
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to RU2016127706A priority Critical patent/RU2641733C1/ru
Priority to CN201580004813.0A priority patent/CN105916673B/zh
Priority to US15/112,903 priority patent/US20160339668A1/en
Priority to CA2938645A priority patent/CA2938645C/en
Priority to EP15745972.8A priority patent/EP3081373B1/en
Publication of WO2015119023A1 publication Critical patent/WO2015119023A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/28—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer comprising a deformed thin sheet, i.e. the layer having its entire thickness deformed out of the plane, e.g. corrugated, crumpled
    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B27/08—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/38—Layered products comprising a layer of synthetic resin comprising epoxy resins
    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/42—Layered products comprising a layer of synthetic resin comprising condensation resins of aldehydes, e.g. with phenols, ureas or melamines
    • 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
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
    • B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
    • B65D5/00—Rigid or semi-rigid containers of polygonal cross-section, e.g. boxes, cartons or trays, formed by folding or erecting one or more blanks made of paper
    • B65D5/40—Rigid or semi-rigid containers of polygonal cross-section, e.g. boxes, cartons or trays, formed by folding or erecting one or more blanks made of paper specially constructed to contain liquids
    • 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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass 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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite 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
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/544—Torsion strength; Torsion stiffness
    • 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
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/546—Flexural strength; Flexion stiffness
    • 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
    • B32B2439/00—Containers; Receptacles
    • B32B2439/40—Closed containers
    • 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
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/34—Tanks constructed integrally with wings, e.g. for fuel or water
    • 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 a composite material structure.
  • Composite structures which are structures formed from composite materials made by combining fibers (for example, carbon fibers and glass fibers) and resins (for example, epoxy resins and phenol resins), are used in various industrial products including aircraft. Has been applied.
  • the composite material structure is lightweight and highly rigid, and further has the advantage that the number of parts and the number of assembly steps can be reduced by integral molding. In recent years, the range of application has been expanded.
  • Patent Document 1 US Pat. No. 6,702,911.
  • the inventors have studied that the structure disclosed in Patent Document 1 does not sufficiently take advantage of the composite material structure of reducing the number of parts and the number of assembly steps.
  • Patent Document 2 discloses a first layer, a plurality of tubular members arranged side by side on the first layer, and the plurality of the plurality of tubular members.
  • a composite structural truss element is disclosed, comprising a second layer disposed on a tubular member, which are integrally formed as a unitary structure.
  • Patent Document 3 discloses a composite structure having two skin layers and a plurality of tubular members (hat ⁇ sections) having a substantially rectangular cross section sandwiched between the skin layers. The body is disclosed.
  • Patent Document 4 discloses a composite material frame having a plurality of truss elements and a cap.
  • the truss elements are flexibly coupled to each other and to the cap.
  • the frame bends along the desired surface to be bonded and provides the necessary rigidity once bonded to the surface.
  • an object of the present invention is to provide a composite material structure having a sufficient rigidity and a reduced number of parts.
  • the composite structure includes a first face plate and a corrugated core joined to the first face plate.
  • the corrugated core has at least one opening.
  • the composite structure further includes a second face plate facing the first face plate, and the corrugated core is joined between the first face plate and the second face plate.
  • a truss structure is formed in the corrugated core by forming a plurality of openings in the corrugated core.
  • the corrugated core is bonded to the first face plate and extends in the first direction along the first face plate
  • the second bond is bonded to the second face plate and extends in the first direction.
  • a connecting portion that is connected between the first joint portion and the second joint portion and extends in the first direction.
  • the first space surrounded by the second joint portion, the connecting portion, and the first face plate extends in the first direction
  • the second space surrounded by the first joint portion, the connecting portion, and the second face plate extends in the first direction
  • the space extends in the first direction
  • the first space and the second space have shapes that are alternately arranged in a second direction along a first face plate different from the first direction. May be.
  • the at least one opening may be provided in the connecting portion.
  • the 1st joined part, the 2nd joined part, and the connecting part may be repeatedly arranged side by side so that a periodic structure may be formed in the corrugated core in the 2nd direction.
  • the shape of the corrugated core that is, the shape of the first joint portion, the second joint portion, and the connecting portion is not necessarily limited to the shape in which the periodic structure is formed in the second direction. The structure may vary depending on the position of the composite structure.
  • a plurality of openings are formed in the corrugated core, whereby the corrugated core is connected to the first joint portion, and is connected to the first base portion extending in the first direction and the second joint portion, in the first direction.
  • a first base portion extending obliquely with respect to the first direction
  • a first oblique column portion extending obliquely with respect to the first direction and connecting the first base portion and the second base portion, and extending obliquely with respect to the first direction.
  • a second oblique column part connecting the second base part.
  • the opening may be circular or oval.
  • the composite material structure when the composite material structure includes a first face plate and a second face plate, the composite material structure may be used as a liquid tank that holds liquid between the first face plate and the second face plate.
  • a corrugated structure including a face plate and a corrugated core is employed as the composite material structure.
  • a high-strength structure can be realized with a small number of parts, and the advantages of the composite structure can be effectively utilized.
  • the rigidity is excessively high, so that the shapeability in the manufacturing process is lowered.
  • the reduction in formability can be a problem when applying a composite structure to a complex curved surface, such as the outer surface of an aircraft.
  • a corrugated core having at least one opening is used in the embodiment described below.
  • the rigidity can be adjusted moderately, and the problem of reduced formability can be addressed.
  • FIG. 1 is a perspective view showing the configuration of the composite structure 10 according to the first embodiment of the present invention
  • FIG. 2 is a side view showing the configuration of the composite structure 10.
  • an XYZ orthogonal coordinate system may be used. That is, in the following description, the X-axis direction, the Y-axis direction, and the Z-axis direction are directions perpendicular to each other.
  • the composite structure 10 includes face plates 1 and 2 and a corrugated core 3.
  • Both the face plates 1 and 2 and the corrugated core 3 are made of a composite material (that is, a material in which fibers (for example, carbon fibers and glass fibers) and a resin (for example, epoxy resin or phenol resin) are combined). ing.
  • the face plates 1 and 2 are provided so as to face each other, and the corrugated core 3 is joined between the face plates 1 and 2. That is, the face plate 1 is joined to one main surface of the corrugated core 3, and the face plate 2 is joined to the other main surface opposite to the one main surface.
  • the term “joining” as used in the present embodiment refers to both joining of separately formed members by bonding and other methods, and joining by integrally forming a single structure. Note that this is a concept that includes.
  • the corrugated core 3 includes a joint 11 that is joined to the face plate 1, a joint 12 that is joined to the face plate 2, and a joint that connects the joints 11 and 12.
  • Part 13 is provided.
  • the connecting portion 13 is connected to the joint portions 11 and 12 so as to be inclined with respect to the inner surfaces 1 a and 2 a of the face plates 1 and 2.
  • the connecting portion 13 may be joined to the joining portions 11 and 12 so as to be perpendicular to the inner surfaces 1a and 2a of the face plates 1 and 2.
  • the joining parts 11 and 12 and the connecting part 13 are all provided so as to extend in the Y-axis direction (first direction along the face plates 1 and 2).
  • the joint portions 11 and 12 and the connecting portion 13 are repeatedly arranged in the X-axis direction (a direction along the face plates 1 and 2 and a second direction different from the first direction).
  • the corrugated core 3 has a structure in which the spaces 14 and 15 extend in the Y-axis direction and are alternately arranged in the X-axis direction. .
  • Such a structure makes it possible to realize a high-strength structure with a small number of parts and to effectively use the advantages of the composite structure.
  • the joint portions 11 and 12 and the connecting portion 13 are repeatedly arranged side by side so that a periodic structure is formed in the corrugated core 3 in the X-axis direction.
  • the shape of the corrugated core 3, that is, the shapes of the joint portions 11 and 12 and the connecting portion 13 is not necessarily limited to the formation of a periodic structure in the X-axis direction. It may vary depending on the position of the composite structure 10.
  • the corrugated core 3 is provided with a plurality of openings 4.
  • the plurality of openings 4 are arranged in the Y-axis direction in each of the connecting portions 13.
  • the rigidity of the composite material structure 10 is appropriately adjusted by providing the corrugated core 3 with the opening 4. This is useful for improving the formability in the manufacturing process.
  • the composite structure 10 of the present embodiment in which the opening 4 is provided in the corrugated core 3 has various other advantages.
  • the composite material structure 10 of this embodiment is designed by appropriately designing the shape of the opening 4 together with the thicknesses of the composite materials constituting the face plates 1 and 2 and the corrugated core 3 and the fiber lamination method (lamination angle).
  • the advantage is that the strength and rigidity of the composite structure 10 can be freely set.
  • providing the opening 4 in the corrugated core 3 leads to a reduction in the mass of the composite structure 10.
  • the composite material structure 10 of the present embodiment can access each position of the composite material structure 10 through the opening 4 and can improve the ease of inspection of each part of the composite material structure 10. .
  • the composite structure 10 of the present embodiment may be used as a liquid tank that holds a liquid (for example, fuel) in the space between the face plates 1 and 2, for example, a fuel tank.
  • a liquid for example, fuel
  • the opening 4 is formed in such a shape that a truss structure is formed in the corrugated core 3. Such a structure is effective for efficiently transmitting a shear load inside the composite structure 10 and countering the shear load.
  • the shape of the opening 4 can be variously changed according to the purpose. The preferred shape of the opening 4 will be discussed in detail later.
  • the composite structure 10 has a structure having flat face plates 1 and 2, that is, a structure in which the outer surfaces 1 b and 2 b of the face plates 1 and 2 are flat.
  • the outer surfaces 1b and 2b of the face plates 1 and 2 may be curved surfaces as shown in FIGS.
  • the outer surfaces 1b and 2b of the face plates 1 and 2 are complicated curved surfaces. It is particularly suitable for such cases.
  • FIG 1 and 2 illustrate a structure in which the opening 4 is provided only in the connecting portion 13 of the corrugated core 3 (that is, a structure in which the opening 4 is provided only in a portion away from the face plate 1 of the corrugated core 3).
  • the opening 4 can be provided at any position of the corrugated core 3 (including the joints 11 and 12).
  • FIG. 5 and FIG. 6 are diagrams showing the composite material structure of the second embodiment.
  • FIG. 5 is a perspective view showing a configuration of a composite structure 10A according to another embodiment
  • FIG. 6 is a side view showing a configuration of the composite structure 10A.
  • the composite structure 10 ⁇ / b> A has a configuration in which the face plate 2 is removed from the composite structure 10 of FIGS. 1 and 2.
  • the joint portion 12 of the corrugated core 3 is not joined to the face plate 2 and functions as a portion that connects the adjacent connecting portions 13.
  • a space 14 is formed that is surrounded by the joint portion 12 and the connecting portion 13 of the corrugated core 3 and the inner surface 1a of the face plate 1, and the space 14 extends in the Y-axis direction. Yes.
  • the corrugated core 3 is provided with an opening 4.
  • the composite structure 10A shown in FIGS. 5 and 6 has a lower strength than the composite structure 10 shown in FIGS. 1 and 2, but a high-strength structure is realized with a small number of parts. It is the same in that the advantages of the composite structure can be effectively utilized.
  • 5 and 6 also show a structure in which the opening 4 is provided only in the connecting portion 13, the opening 4 is provided at an arbitrary position (including the joint portions 11 and 12) of the corrugated core 3. Note that this can be done.
  • FIGS. 7 and 8 show the structure when the outer surface 1b (surface opposite to the corrugated core 3) of the face plate 1 is a plane, but as shown in FIGS. 7 and 8,
  • the outer surface 1b of the face plate 1 may be a curved surface.
  • FIGS. 9A to 9D show the structure of the corrugated core 3 (that is, the shape of the opening 4 provided in the corrugated core 3) suitable for efficiently transmitting the shear load inside the composite structure 10, 10A. It is a side view. 9A to 9D show structures when the connecting portion 13 of the corrugated core 3 is viewed in the direction of arrow A in FIG. 9A to 9D, not the Z-axis direction but the Z′-axis direction that is perpendicular to the Y-axis direction and is along the connecting portion 13 is illustrated, and the vertical direction in FIGS. 9A to 9D Note that is in the Z′-axis direction.
  • FIG. 9A shows an example of the structure of the connecting portion 13 in which the truss structure is formed.
  • the opening 4 is provided in the connecting portion 13 of the corrugated core 3 side by side in the Y-axis direction.
  • the openings 4 other than the openings 4 positioned at both ends are formed in a substantially isosceles triangle with rounded corners, and the openings 4 positioned at both ends are formed in a right triangle with rounded corners.
  • the openings 4 having the side surfaces 17 facing the joint portions 11 and the openings 4 having the side surfaces 18 facing the joint portions 12 are alternately arranged. ing.
  • the base portions 21 and 22, the oblique column portions 23 and 24, and the column portion 25 are formed in the connecting portion 13.
  • the base 21 is connected to the joint 11 and is provided so as to extend in the Y-axis direction along the joint 11.
  • the base portion 22 is connected to the joint portion 12 and is provided so as to extend in the Y-axis direction along the joint portion 12.
  • the joint portion 11 is a portion joined to the face plate 1
  • the joint portion 12 is a portion joined to the face plate 2 (when the face plate 2 is provided).
  • the oblique column portions 23 and 24 extend obliquely with respect to the base portions 21 and 22 (that is, obliquely with respect to the Y-axis direction) and connect the base portions 21 and 22.
  • the oblique column portion 23 is connected to the base portions 21 and 22 such that the position in the Y-axis direction of the end connected to the base portion 22 is shifted in the + Y direction from the end connected to the base portion 21.
  • the oblique column portion 24 is connected to the base portions 21 and 22 so that the position in the Y-axis direction of the end connected to the base portion 21 is shifted in the + Y direction from the end connected to the base portion 22.
  • the column part 25 extends perpendicularly to the base parts 21 and 22 from the ends of the base parts 21 and 22 to connect the base parts 21 and 22.
  • the oblique structures 23 and 24 that extend obliquely with respect to the base portions 21 and 22 and connect the base portions 21 and 22 are provided. It is possible to transmit the shear load efficiently inside.
  • Such a structure of the connecting portion 13 is effective for supporting a shear load acting on the composite material structures 10 and 10A while reducing the weight of the composite material structures 10 and 10A.
  • FIG. 9B is a side view showing another example of the structure of the connecting portion 13 of the corrugated core 3 for efficiently transmitting the shear load inside the composite structure 10, 10A.
  • the opening 4 is provided in the connecting portion 13 side by side in the Y-axis direction.
  • the openings 4 other than the openings 4 located at both ends are formed in a substantially right trapezoid shape with rounded corners, and the openings 4 located at both ends are formed in a right triangle with rounded corners. ing.
  • the length in the Y-axis direction of the side surface 17 facing the joint portion 11 is longer than the length in the Y-axis direction of the side surface 18 facing the joint portion 12.
  • the openings 4 and the openings 4 whose lengths in the Y-axis direction of the side surfaces 17 facing the joint portions 11 are shorter than the lengths in the Y-axis direction of the side surfaces 18 facing the joint portions 12 are alternately arranged. Yes.
  • base portions 21 and 22, oblique column portions 23 and 24, and column portions 25 and 26 are formed in the connecting portion 13.
  • the base 21 is connected to the joint 11 and is provided so as to extend in the Y-axis direction along the joint 11.
  • the base portion 22 is connected to the joint portion 12 and is provided so as to extend in the Y-axis direction along the joint portion 12.
  • the oblique column portions 23 and 24 extend obliquely with respect to the base portions 21 and 22 (that is, obliquely with respect to the Y-axis direction) and connect the base portions 21 and 22.
  • the oblique column portion 23 is connected to the base portions 21 and 22 such that the position in the Y-axis direction of the end connected to the base portion 22 is shifted in the + Y direction from the end connected to the base portion 21.
  • the oblique column portion 24 is connected to the base portions 21 and 22 so that the position in the Y-axis direction of the end connected to the base portion 21 is shifted in the + Y direction from the end connected to the base portion 22. .
  • the column portion 25 extends vertically from the ends of the base portions 21 and 22 to connect the base portions 21 and 22.
  • Each column portion 26 is provided at a position between adjacent oblique column portions 23 and 24, and extends perpendicularly to the base portions 21 and 22 to connect the base portions 21 and 22.
  • the oblique structures 23 and 24 that extend obliquely with respect to the base portions 21 and 22 and connect the base portions 21 and 22 are provided. It is possible to transmit the shear load efficiently inside.
  • Such a structure of the connecting portion 13 is effective for supporting a shear load acting on the composite material structures 10 and 10A while reducing the weight of the composite material structures 10 and 10A.
  • a thickness direction load (plate thickness direction (Z-axis direction)) is provided by providing a column portion 26 that extends perpendicularly to the base portions 21 and 22 and connects the base portions 21 and 22. The strength against the load acting on the surface is also improved.
  • FIG. 9C is a side view showing still another example of the structure of the connecting portion 13 of the corrugated core 3 for efficiently transmitting the shear load inside the composite material structures 10 and 10A.
  • the opening 4 is provided side by side in the Y-axis direction in the connecting portion 13, thereby forming a truss structure in the connecting portion 13.
  • each opening 4 is formed in a substantially right triangle with rounded corners.
  • base portions 21 and 22, oblique column portions 23 and 24, and column portions 25 and 26 are formed in the connecting portion 13.
  • the base 21 is connected to the joint 11 and is provided so as to extend in the Y-axis direction along the joint 11.
  • the base portion 22 is connected to the joint portion 12 and is provided so as to extend in the Y-axis direction along the joint portion 12.
  • the oblique column portions 23 and 24 extend obliquely with respect to the base portions 21 and 22 (that is, obliquely with respect to the Y-axis direction) and connect the base portions 21 and 22.
  • the oblique column portion 23 is connected to the base portions 21 and 22 such that the position in the Y-axis direction of the end connected to the base portion 22 is shifted in the + Y direction from the end connected to the base portion 21.
  • the oblique column portion 24 is connected to the base portions 21 and 22 so that the position in the Y-axis direction of the end connected to the base portion 21 is shifted in the + Y direction from the end connected to the base portion 22. .
  • FIG. 9C unlike the structure of FIG.
  • the column portion 25 extends vertically from the ends of the base portions 21 and 22 to connect the base portions 21 and 22.
  • Each column portion 26 is provided such that one end thereof is connected to a position where the oblique column portions 23 and 24 are in contact and the other end is connected to the base portion 21 or 22.
  • the column portion 26 extends perpendicularly to the base portions 21 and 22 to connect the base portions 21 and 22.
  • the oblique structures 23 and 24 that extend obliquely with respect to the base portions 21 and 22 and connect the base portions 21 and 22 are provided. It is possible to transmit the shear load efficiently inside.
  • Such a structure of the connecting portion 13 is effective for supporting a shear load acting on the composite material structures 10 and 10A while reducing the weight of the composite material structures 10 and 10A.
  • the thickness direction load (the thickness direction (Z-axis direction)) is provided by providing the column portion 26 that extends perpendicularly to the base portions 21 and 22 and connects the base portions 21 and 22. The strength against the load acting on the surface is also improved.
  • FIG. 9D is a side view showing still another example of the structure of the connecting portion 13 of the corrugated core 3 for efficiently transmitting the shear load inside the composite material structures 10 and 10A.
  • the opening 4 is provided in the connecting portion 13 side by side in the Y-axis direction.
  • the connection portion 13 is provided with four types of openings 4a to 4d, whereby a truss structure is formed in the connection portion 13.
  • the opening 4a has a substantially rhombus shape with rounded corners.
  • the opening 4 b has a substantially isosceles triangular shape with rounded corners, and has a side surface 17 that faces the joint portion 11.
  • the opening 4 c has a substantially isosceles triangular shape with rounded corners, and has a side surface 18 that faces the joint 12.
  • the pair of openings 4b and 4c are arranged side by side in a direction perpendicular to the Y-axis direction.
  • the openings 4 d have a substantially isosceles triangular shape with rounded corners, and are located at both ends of the row of openings 4.
  • the base portions 21 and 22, the oblique column portions 23 and 24, and the column portion 25 are formed in the connecting portion 13.
  • the base 21 is connected to the joint 11 and is provided so as to extend in the Y-axis direction along the joint 11.
  • the base portion 22 is connected to the joint portion 12 and is provided so as to extend in the Y-axis direction along the joint portion 12.
  • the oblique column portions 23 and 24 extend obliquely with respect to the base portions 21 and 22 (that is, obliquely with respect to the Y-axis direction) and connect the base portions 21 and 22.
  • the oblique column portion 23 is connected to the base portions 21 and 22 such that the position in the Y-axis direction of the end connected to the base portion 22 is shifted in the + Y direction from the end connected to the base portion 21.
  • the oblique column portion 24 is connected to the base portions 21 and 22 so that the position in the Y-axis direction of the end connected to the base portion 21 is shifted in the + Y direction from the end connected to the base portion 22. .
  • FIG. 1 In the structure of FIG.
  • the oblique column portions 23 and 24 are provided so as to intersect with each other, and the oblique column portions 23 and 24 are joined at the center thereof.
  • the column portion 25 extends vertically from the ends of the base portions 21 and 22 to connect the base portions 21 and 22.
  • the composite material is provided by providing oblique column portions 23 and 24 that extend obliquely with respect to the base portions 21 and 22 and connect the base portions 21 and 22.
  • the shear load can be efficiently transmitted inside the structures 10 and 10A.
  • Such a structure of the connecting portion 13 is effective for supporting a shear load acting on the composite material structures 10 and 10A while reducing the weight of the composite material structures 10 and 10A.
  • FIGS. 10A to 10C show the structure of the corrugated core 3 suitable for efficiently transmitting the thickness direction load (that is, the load acting in the thickness direction (Z-axis direction)) inside the composite structure 10, 10A. It is a side view which shows (namely, the shape of the opening 4 provided in the corrugated core 3).
  • 10A to 10C show structures when the connecting portion 13 of the corrugated core 3 is viewed in the direction of arrow A in FIG. 10A to 10C also show the Z′-axis direction (the direction perpendicular to the Y-axis direction and along the connecting portion 13), not the Z-axis direction. It should be noted that the vertical direction in FIGS. 10A to 10C is the Z′-axis direction.
  • FIG. 10A is a side view showing an example of the structure of the connecting portion 13 of the corrugated core 3 for efficiently transmitting the shear load inside the composite structure 10, 10A.
  • a substantially rectangular opening 4 is provided in the connecting portion 13 side by side in the Y-axis direction.
  • Base portions 21 and 22 and column portions 25 and 26 are formed in the connecting portion 13 by the opening 4 having such a shape.
  • the base 21 is connected to the joint 11 and is provided so as to extend in the Y-axis direction along the joint 11.
  • the base portion 22 is connected to the joint portion 12 and is provided so as to extend in the Y-axis direction along the joint portion 12.
  • the column portions 25 and 26 extend perpendicularly to the base portions 21 and 22 to connect the base portions 21 and 22.
  • the column portion 25 is connected to the ends of the base portions 21 and 22, and the column portion 26 is connected to the base portions 21 and 22 at an intermediate position between the base portions 21 and 22.
  • the thickness direction load is provided inside the composite material structure 10, 10 ⁇ / b> A by providing column portions 25, 26 extending perpendicularly to the base portions 21, 22 and connecting the base portions 21, 22. Can be transmitted efficiently.
  • Such a structure of the connecting portion 13 is effective for supporting a thickness direction load acting on the composite material structures 10 and 10A while reducing the weight of the composite material structures 10 and 10A.
  • FIG. 10B is a side view showing another example of the structure of the connecting portion 13 of the corrugated core 3 for efficiently transmitting the shear load inside the composite structure 10, 10A.
  • the circular opening 4 is provided in the connection part 13 along with the Y-axis direction.
  • the base portions 21 and 22 and the column portion 27 are formed in the connecting portion 13.
  • the base 21 is connected to the joint 11 and is provided so as to extend in the Y-axis direction along the joint 11.
  • the base portion 22 is connected to the joint portion 12 and is provided so as to extend in the Y-axis direction along the joint portion 12.
  • the column portion 27 extends perpendicularly to the base portions 21 and 22 to connect the base portions 21 and 22.
  • the load in the plate thickness direction is efficiently generated inside the composite material structures 10 and 10A. It is possible to communicate well.
  • Such a structure of the connecting portion 13 is effective for supporting a thickness direction load acting on the composite material structures 10 and 10A while reducing the weight of the composite material structures 10 and 10A.
  • the opening 4 is circular, stress is not easily concentrated in the vicinity of the opening 4, and the strength of the composite structure 10, 10A can be improved.
  • FIG. 10C is a side view showing another example of the structure of the connecting portion 13 of the corrugated core 3 for efficiently transmitting the shear load inside the composite structure 10, 10A.
  • an oval opening 4 that is long in the direction perpendicular to the Y-axis direction is provided in the connecting portion 13 side by side in the Y-axis direction.
  • the term “oval” is used to include both a figure formed by connecting two semicircles by two parallel line segments and an ellipse.
  • the base portions 21 and 22 and the column portion 27 are formed in the connecting portion 13.
  • the base 21 is connected to the joint 11 and is provided so as to extend in the Y-axis direction along the joint 11.
  • the base portion 22 is connected to the joint portion 12 and is provided so as to extend in the Y-axis direction along the joint portion 12.
  • the column portion 27 extends perpendicularly to the base portions 21 and 22 to connect the base portions 21 and 22.
  • the load in the thickness direction is efficiently generated inside the composite material structures 10 and 10 ⁇ / b> A. It is possible to communicate well.
  • Such a structure of the connecting portion 13 is effective for supporting a thickness direction load acting on the composite material structures 10 and 10A while reducing the weight of the composite material structures 10 and 10A.
  • the opening 4 is oval, stress is unlikely to concentrate in the vicinity of the opening 4, and the strength of the composite structure 10, 10A can be improved.
  • FIG. 11 shows the structure of the corrugated core 3 suitable for efficiently transmitting the axial load (that is, the load acting in the Y-axis direction) inside the composite structure 10, 10A. It is a side view which shows the shape of the opening 4 currently made.
  • FIG. 11 shows a structure when the connecting portion 13 of the corrugated core 3 is viewed in the direction of arrow A in FIG. Also in FIG. 11, not the Z-axis direction but the Z′-axis direction (direction perpendicular to the Y-axis direction and along the connecting portion 13) is illustrated. Note that the vertical direction in FIG. 11 is the Z′-axis direction.
  • substantially rectangular openings 4 are arranged in a matrix (that is, lined up in the Y-axis direction and the Z′-axis direction) in the connecting portion 13.
  • base portions 21 and 22, column portions 25 and 26, and a beam portion 28 are formed in the connecting portion 13.
  • the base 21 is connected to the joint 11 and is provided so as to extend in the Y-axis direction along the joint 11.
  • the base portion 22 is connected to the joint portion 12 and is provided so as to extend in the Y-axis direction along the joint portion 12.
  • the column portions 25 and 26 extend perpendicularly to the base portions 21 and 22 to connect the base portions 21 and 22.
  • the column portion 25 is connected to the ends of the base portions 21 and 22, and the column portion 26 is connected to the base portions 21 and 22 at an intermediate position between the base portions 21 and 22.
  • the beam portion 28 extends in the axial direction (that is, the Y-axis direction) of the composite material structures 10 and 10A and connects the adjacent column portions 25 and 26 to each other.
  • the structure shown in FIG. 11 is provided with a beam portion 28 that extends in the axial direction (that is, the Y-axis direction) of the composite material structures 10 and 10A and connects the adjacent column portions 25 and 26 to each other. It is possible to transmit the axial load efficiently within 10, 10A.
  • Such a structure of the connecting portion 13 is effective for supporting an axial load acting on the composite material structures 10 and 10A while reducing the weight of the composite material structures 10 and 10A.
  • the face plates 1, 2 and the corrugated core 3 can be manufactured in various ways.
  • the face plate 1 and the corrugated core 3 may be integrally formed, or may be joined after the face plate 1 and the corrugated core 3 are produced as separate members.
  • the face plate 2 and the corrugated core 3 may be integrally formed, or may be joined after the face plate 2 and the corrugated core 3 are produced as separate members.
  • all of the face plates 1 and 2 and the corrugated core 3 may be integrally molded.
  • intermediate products that finally become the face plates 1 and 2 and the corrugated core 3 are each made of a sheet-like or tape-like prepreg, and the produced intermediate product is a cocure ( It may be joined by co-cure, co-bond, or secondary adhesion.
  • FIG. 12 is a conceptual diagram showing an example of a manufacturing method for manufacturing the composite structure 10 using a sheet-like prepreg.
  • a sheet-like prepreg 32 is laminated on the flat mandrel 31 to form a laminated body 33 (FIG. 12A).
  • the stacked body 33 is an intermediate product formed in the corrugated core 3 in a later step.
  • the number of prepregs 32 to be laminated and the fiber direction of each prepreg 32 are determined so that the finally formed corrugated core 3 has appropriate strength and rigidity.
  • an opening 4 is formed in the laminate 33 by punching or cutting (FIG. 12B).
  • the laminate 33 is formed into the shape of the corrugated core 3 to be finally formed by pressing or draping (FIG. 12 (c)). At this point, the laminate 33 is uncured.
  • the step of joining the separately formed face plates 1 and 2 and the corrugated core 3 is performed to complete the manufacture of the composite material structure 10 (FIG. 12D).
  • the joining can be performed in various ways.
  • the face plates 1 and 2 and the corrugated core 3 may be joined by co-cure.
  • the uncured members 34 and 35 that finally become the face plates 1 and 2 are formed by laminating the prepreg, and the members 34 and 35 are cured together with the laminated body 33, whereby the face plates 1 and 2 and the corrugated core 3 are cured. Is completed.
  • the face plates 1 and 2 and the corrugated core 3 may be joined by a co-bond.
  • the laminated body 33 is cured to form the corrugated core 3, while uncured members 34 and 35 that finally become the face plates 1 and 2 are formed by laminating prepregs.
  • the cured corrugated core 3 is cured in a state where the corrugated core 3 is in contact with the uncured members 34 and 35 via an adhesive, whereby the composite material in which the face plates 1 and 2 and the corrugated core 3 are joined together.
  • the structure 10 is completed.
  • the face plates 1 and 2 and the corrugated core 3 may be joined by secondary adhesion.
  • the laminated body 33 is cured to form the corrugated core 3, while the cured face plates 1 and 2 are formed.
  • the adhesive is cured in a state where the cured corrugated core 3 is in contact with the cured face plates 1 and 2 through an adhesive, and thereby the face plates 1 and 2 and the corrugated core 3 are joined.
  • the finished composite structure 10 is completed.
  • FIG. 13 is a conceptual diagram showing an example of a manufacturing method for manufacturing the composite structure 10 using a tape-shaped prepreg (prepreg tape).
  • a prepreg tape 36 is laminated on the flat mandrel 31 to form a laminated body 33 in which the openings 4 are formed (FIG. 13A).
  • the prepreg tape 36 may be laminated by using an AFP (automated? Fiber? Placement) technique.
  • AFP automated? Fiber? Placement
  • the laminate 33 is formed into the shape of the corrugated core 3 to be finally formed by pressing or draping (FIG. 13B). Further, a step of joining the face plates 1 and 2 and the corrugated core 3 is performed (FIG. 13C). Similar to the manufacturing method of FIG. 12, in the step of joining the face plates 1 and 2 and the corrugated core 3, any of co-cure, co-bond, and secondary bonding may be used.
  • the composite structure 10 is completed through the above steps.
  • FIG. 14 is a conceptual diagram showing a manufacturing method for manufacturing the composite material structure 10 using an RTM (resin transfer molding) technique in which a dry preform is impregnated with resin.
  • RTM resin transfer molding
  • a dry preform 41 having an opening 4 is prepared (FIG. 14A).
  • the dry preform 41 having the opening 4 may be formed by forming the opening 4 in a flat dry preform by punching or cutting.
  • the corrugated core 3 is formed by impregnating the dry preform 41 with resin by RTM (FIG. 14B). Specifically, the resin is impregnated with the dry preform 41 sandwiched between the mandrels 42 and 43, and the resin is further cured at a desired temperature. Thereby, the hardened corrugated core 3 is completed.
  • a step of joining the separately formed face plates 1 and 2 and the corrugated core 3 is performed to complete the manufacture of the composite material structure 10 (FIG. 14C).
  • the joining can be performed in various ways.
  • the face plates 1 and 2 and the corrugated core 3 may be joined by a co-bond.
  • the uncured members 34 and 35 that finally become the face plates 1 and 2 are formed by laminating the prepreg, and further, the corrugated core 3 after curing is uncured members 34 and 35 via an adhesive. Curing is performed in a state of being in contact with the. Thereby, the composite material structure 10 in which the face plates 1 and 2 and the corrugated core 3 are joined is completed.
  • the face plates 1 and 2 and the corrugated core 3 may be joined by secondary adhesion.
  • the cured face plates 1 and 2 are prepared, and the adhesive is cured in a state where the cured corrugated core 3 is in contact with the cured face plates 1 and 2 through an adhesive. Is called.
  • the composite material structure 10 in which the face plates 1 and 2 and the corrugated core 3 are joined is completed.
  • the composite material structure 10A without the face plate 2 can be manufactured by not joining the face plate 2 to the corrugated core 3 in the above-described manufacturing method.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Laminated Bodies (AREA)
PCT/JP2015/052407 2014-02-04 2015-01-28 複合材構造 Ceased WO2015119023A1 (ja)

Priority Applications (5)

Application Number Priority Date Filing Date Title
RU2016127706A RU2641733C1 (ru) 2014-02-04 2015-01-28 Конструкция из композитного материала
CN201580004813.0A CN105916673B (zh) 2014-02-04 2015-01-28 复合材料构造
US15/112,903 US20160339668A1 (en) 2014-02-04 2015-01-28 Composite material structure
CA2938645A CA2938645C (en) 2014-02-04 2015-01-28 Composite material structure
EP15745972.8A EP3081373B1 (en) 2014-02-04 2015-01-28 Composite material structure

Applications Claiming Priority (2)

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JP2014019566A JP6238168B2 (ja) 2014-02-04 2014-02-04 複合材構造
JP2014-019566 2014-02-04

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WO2015119023A1 true WO2015119023A1 (ja) 2015-08-13

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EP (1) EP3081373B1 (enExample)
JP (1) JP6238168B2 (enExample)
CN (1) CN105916673B (enExample)
CA (1) CA2938645C (enExample)
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SE539953C2 (en) * 2016-02-08 2018-02-06 Nitiu Ab Disposable board container and uses of board having a core structure of close packed asymmetric tetrahedrons
EP3498591A1 (en) * 2017-12-13 2019-06-19 AIRBUS HELICOPTERS DEUTSCHLAND GmbH A composite truss beam with a sandwich web
CN108407400A (zh) * 2018-01-25 2018-08-17 大连理工大学 碳纤维增强复合材料波纹芯夹层结构汽车防撞梁
DE102018207763A1 (de) * 2018-05-17 2019-11-21 Airbus Operations Gmbh Rumpfstruktur für ein Luftfahrzeug
CN109501404B (zh) * 2018-11-20 2021-02-02 华侨大学 一种高效减振的层级多孔复合板
FR3091263A1 (fr) * 2018-12-28 2020-07-03 Daher Aerospace Bec de bord d’attaque à structure optimisée

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CA2938645A1 (en) 2015-08-13
JP2015145124A (ja) 2015-08-13
EP3081373A4 (en) 2016-12-07
RU2641733C1 (ru) 2018-01-22
EP3081373B1 (en) 2019-04-03
CN105916673A (zh) 2016-08-31
CA2938645C (en) 2017-10-10
US20160339668A1 (en) 2016-11-24
CN105916673B (zh) 2017-09-22
JP6238168B2 (ja) 2017-11-29
EP3081373A1 (en) 2016-10-19

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