WO2019077860A1 - 修理パッチ、修理パッチの成形方法、複合材の修理方法及び成形治具 - Google Patents

修理パッチ、修理パッチの成形方法、複合材の修理方法及び成形治具 Download PDF

Info

Publication number
WO2019077860A1
WO2019077860A1 PCT/JP2018/030651 JP2018030651W WO2019077860A1 WO 2019077860 A1 WO2019077860 A1 WO 2019077860A1 JP 2018030651 W JP2018030651 W JP 2018030651W WO 2019077860 A1 WO2019077860 A1 WO 2019077860A1
Authority
WO
WIPO (PCT)
Prior art keywords
repair patch
repaired
curvature
radius
repair
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/JP2018/030651
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
耕大 下野
長谷川　剛一
琢磨 平井
駿佑 吉野
譲 西室
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 US16/756,035 priority Critical patent/US11338529B2/en
Priority to EP18867557.3A priority patent/EP3698957A4/en
Publication of WO2019077860A1 publication Critical patent/WO2019077860A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Images

Classifications

    • 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
    • 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
    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/04—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements
    • B29C73/10—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements using patches sealing on the surface of the article
    • 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
    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/04—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements
    • B29C73/06—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements using plugs sealing in the hole
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
    • B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
    • B29C65/4835—Heat curing adhesives
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/486—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by their physical form being non-liquid, e.g. in the form of granules or powders
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/001—Joining in special atmospheres
    • B29C66/0012—Joining in special atmospheres characterised by the type of environment
    • B29C66/0014—Gaseous environments
    • B29C66/00145—Vacuum, e.g. partial vacuum
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/301—Three-dimensional joints, i.e. the joined area being substantially non-flat
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/80—General aspects of machine operations or constructions and parts thereof
    • B29C66/82—Pressure application arrangements, e.g. transmission or actuating mechanisms for joining tools or clamps
    • B29C66/826—Pressure application arrangements, e.g. transmission or actuating mechanisms for joining tools or clamps without using a separate pressure application tool, e.g. the own weight of the parts to be joined
    • B29C66/8266—Pressure application arrangements, e.g. transmission or actuating mechanisms for joining tools or clamps without using a separate pressure application tool, e.g. the own weight of the parts to be joined using fluid pressure directly acting on the parts to be joined
    • B29C66/82661—Pressure application arrangements, e.g. transmission or actuating mechanisms for joining tools or clamps without using a separate pressure application tool, e.g. the own weight of the parts to be joined using fluid pressure directly acting on the parts to be joined by means of vacuum
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/90—Measuring or controlling the joining process
    • B29C66/91—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux
    • B29C66/914—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux
    • B29C66/9141—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature
    • B29C66/91441—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature the temperature being non-constant over time
    • B29C66/91443—Measuring or controlling the joining process by measuring or controlling the temperature, the heat or the thermal flux by controlling or regulating the temperature, the heat or the thermal flux by controlling or regulating the temperature the temperature being non-constant over time following a temperature-time profile
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2030/00—Pneumatic or solid tyres or parts thereof
    • 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
    • B32B2556/00—Patches, e.g. medical patches, repair patches
    • 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
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • B32B37/1009—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure using vacuum and fluid pressure
    • 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
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • B32B37/1207—Heat-activated adhesive

Definitions

  • the present invention relates to a repair patch for a composite material for repairing a portion to be repaired of a composite material, a method for forming the repair patch, a method for repairing a composite material, and a forming jig.
  • the portion to be repaired for example, there is a cylindrical outer peripheral surface (also referred to as a single contour surface) extending in the axial direction.
  • a counterbore as a recess is formed on the single contour surface, and the counterbore is filled with the repair material.
  • a repair material used for such a portion to be repaired for example, there is a repair patch described in Patent Document 1.
  • the repair patch is frusto-conical in shape and has a bottom, a top and a bevel.
  • the wing outer plate 101 of an aircraft when the portion to be repaired is, for example, the wing outer plate 101 of an aircraft, the wing outer plate is viewed in a cross section cut by a plane orthogonal to its wing length direction.
  • the radius of curvature of the single contour surface of the outer surface of the main wing skin 101 is continuously different in the span direction.
  • the radii of curvature Ra and Ra ′ of the single contour surface on the outer surface and the inner surface on the upper side of the main wing outer plate 101 are the BB cross sections on the tip side of the main wing.
  • the radius of curvature Rc, Rc 'of the single contour surface of the outer surface on the upper side of the main wing outer plate is larger.
  • the radii of curvature Rb and Rb 'of the single contour surface on the lower outer surface and the inner surface of the main wing outer plate 101 are the lower outer surface of the main wing outer plate and the BB cross section on the tip side of the main wing and
  • the radius of curvature Rd, Rb ′ of the single contour surface on the inner surface is larger.
  • the present invention provides a repair patch, a method of forming a repair patch, a method of repairing a composite material, and a forming jig, which can properly repair a portion to be repaired even if the portion to be repaired is a curved surface. It will be an issue.
  • the repair target portion serving as a surface opposite to a bonding surface formed on the repair target portion A bonding surface to be bonded and a surface which is a surface opposite to the bonding surface in a thickness direction, and the surface is formed in a predetermined cross section cut by a surface intersecting a predetermined direction in the surface. It is characterized in that it has a curved surface which is a radius of curvature on the surface side.
  • the curved surface of the surface of the repair patch has a smaller radius of curvature than the curved surface of the outer peripheral surface of the portion to be repaired, or the larger radius of curvature than the curved surface of the inner peripheral surface of the portion to be repaired.
  • repair patch can be a repair patch that is easy to conform to the portion to be repaired, even if a plurality of types of repair patches are prepared in advance, a number of types of repair patches that can be handled with a small number of types are available. can do.
  • the outer peripheral edge of the thin repair patch is easily deformed. For this reason, when the portion to be repaired is the outer peripheral surface, the radius of curvature of the first surface side outer than the central portion is made smaller, and when the portion to be repaired is the inner peripheral surface, Then, by enlarging the outer first surface side curvature radius, the peripheral portion of the repair patch becomes easy to conform to the portion to be repaired.
  • the adhesive surface can be activated by peeling off the peel ply, the adhesiveness to the portion to be repaired can be enhanced.
  • the portion to be repaired in the forming jig for forming a repair patch of a composite material for repairing a portion to be repaired of the composite material, the portion to be repaired extends along an axial direction. It is a cylindrical inner peripheral surface, and the surface which becomes the surface on the opposite side of the bonding surface bonded to the portion to be repaired in the thickness direction intersects the predetermined direction in the surface. And a curved surface of a first surface-side radius of curvature that is concave toward the adhesive surface side from the surface side, and the inner circumferential surface of the portion to be repaired is the predetermined surface within the surface.
  • a patch for repairing the composite material for repairing the portion to be repaired is prepared in advance.
  • the repair portion is a cylindrical outer peripheral surface extending along an axial direction, and the repair patch has a surface opposite to an adhesive surface to be bonded to the repair portion in a thickness direction.
  • the composite material of the repair patch is obtained by impregnating a reinforcing fiber with a thermosetting resin and temporarily curing the thermosetting resin, the adhesive is the thermosetting resin, and the bonding step is performed.
  • the repair patch is covered with a vacuum bag, and the interior of the vacuum bag is vacuumed to bring the repair patch into a vacuum state by pressing the repair patch, and the thermosetting resin is heated in the vacuum state.
  • the repair patch is adhered to the portion to be repaired, and in the adhesion step, heating is performed at a predetermined temperature rising rate so as to be equal to or higher than the glass transition temperature of the thermosetting resin.
  • the repair patch in the pre-cured state can be disposed in the portion to be repaired. Therefore, when the repair patch is fully cured, the repair patch can be softened, whereby the repair patch can be suitably adapted to the portion to be repaired, that is, the shape of the repair patch conforms to the portion to be repaired Can be For this reason, generation
  • FIG. 1 is a three-sided view schematically showing a repair patch used in the method of repairing a composite material according to the present embodiment.
  • FIG. 2 is sectional drawing which shows typically the to-be-repaired part used as the object of the repair method of the composite material which concerns on this embodiment.
  • FIG. 3 is explanatory drawing which compared the shape of the counterbore of a to-be-repaired part, and a repair patch.
  • FIG. 4 is a three-sided view schematically showing a forming jig for forming the repair patch according to the present embodiment.
  • FIG. 5 is an explanatory view of an example regarding a method of forming a repair patch according to the present embodiment.
  • FIG. 6 is an explanatory view of an example regarding a method of repairing a composite material using the repair patch according to the present embodiment.
  • the surface 12 is composed of a bottom surface 10a, and in the BB cross section, the bottom surface 10a is a curved surface which is convex from the bonding surface 11 side to the surface 12 side.
  • the bottom surface 10a is a flat surface in a straight line.
  • the surface 12 which is a curved surface has a first surface-side radius of curvature R1 smaller than a second surface-side radius of curvature of the surface (outer peripheral surface) of the portion 5 to be repaired It has become.
  • the surface 12 is provided with an index 13 capable of discriminating the axial direction of the repair patch 10 by visual observation.
  • the indicator 13 is an arrow as an example, it is not limited to the arrow, and is not particularly limited as long as the indicator 13 can determine the axial direction of the repair patch 10.
  • the composite material 1 has a repair target portion 5 to be repaired formed on the surface side (the upper side in FIG. 2), and the repair patch 10 is adhered to the repair target portion 5 and cured. Is formed.
  • the composite material 1 has a cylindrical shape extending along the axial direction, and the portion to be repaired 5 is the outer peripheral surface 7 of the composite material 1.
  • the outer peripheral surface 7 of the portion to be repaired 5 has a radius of curvature R2 on the second surface side larger than the radius of curvature R1 on the first surface side of the surface 12 of the repair patch 10 in a cross section perpendicular to the axial direction. It has become.
  • the adherend surface 15 has a bottom surface 6a and a side surface 6b.
  • the bottom surface 6a of the adherend surface 15 faces the top surface 10b of the adhesion surface 11, and the side surface 6b of the adherend surface 15 is an adhesion surface 11.
  • the side surface 6b of the counterbore 6 is a curved surface which is convex on the side surface 6b side of the bonding surface 11 which faces in the cross section shown in FIG. 2 cut by the surface orthogonal to the axial direction.
  • the curvature radius of the side surface 6b which is a curved surface is the second curvature radius r2.
  • step S14 forming step.
  • the heater mat 28 is installed on the surface of the plurality of laminated reinforcing fiber base, and the vacuum suction port 25 is installed.
  • the heater mat 28 melts the resin of the prepreg as the reinforcing fiber base and heats the prepreg to a predetermined temperature at which the resin is partially thermally cured.
  • the bag film (vacuum bag) 29 is disposed via the sealing material 30 so as to cover the heater mat 28.
  • the bag film 29 is formed one size larger than the repair patch 10, and the sealing material 30 is airtightly disposed between the bag film 29 and the forming jig 20.
  • the resin sheet 35 is a sheet of resin, and is made of a material that can be adhered to the resin used for the repair patch 10.
  • the resin sheet 35 may be the same as or different from the resin used for the repair patch 10, and is not particularly limited.
  • a plurality of types of repair patches 10 having different diameters are prepared, and the repair patch 10 is appropriately selected and used according to the shape (size) of the counterbore 6 to be formed.
  • the counterbore formation step S21 the resin sheet placement step (adhesive placement step) S22, the repair patch placement step S24, the positioning step S25, and the forming step (adhesion step) S26 I'm going in order.
  • Defective portions are formed on the surface of the composite material 1 before the repair target portion forming step S21.
  • the defect portion formed on the surface of the composite material 1 is processed by cutting or the like to form the counterbore 6 having the shape shown in FIGS.
  • the counterbore formation step S21 by forming the counterbore 6 having the shape shown in FIG. 2 and FIG. 6, the shape suitable for repair can be obtained.
  • the counterbore 6 is processed such that the number of laminations of the reinforcing fiber base to be removed by processing is the same as the number of laminations of the repair patches 10 in the portion to be repaired 5 of the composite material 1 .
  • the radius of the counterbore 6 is a constant ratio from the bottom surface 6a toward the opening portion, in the same way that the radius of the repair patch 10 increases at a constant rate (a1).
  • the positioning step S25 in a vacuum state, it is checked whether or not the gap between the counterbore 6 and the repair patch 10 is smaller than the thickness of the resin sheet 35. That is, the difference between the second surface side radius of curvature R2 and the first surface side radius of curvature R1, in other words, the difference between the second radius of curvature r2 and the first radius of curvature r1 There is a difference such that the clearance between the repair patch 10 is smaller than the thickness of the resin sheet 35.
  • the vacuum state is released and the bag film 37 is removed.
  • the heater mat 39 is installed on the positioned repair patch 10, and the vacuum suction port 36 is installed.
  • the heater mat 39 heats the repair patch 10 and the resin sheet 35 so that the temperature of the glass transition temperature at which the resin of the repair patch 10 and the resin sheet 35 is melted and completely cured is equal to or higher.
  • the bag film 37 is disposed via the seal material 38 so as to cover the heater mat 39.
  • the inside of the bag film 37 is vacuumed by vacuum suctioning the inside of the bag film 37 through the vacuum suction port 36.
  • the resin is melted by the heater mat 39 in a vacuum state to completely cure the resin, whereby the repair patch 10 and the resin sheet 35 are integrally cured in the portion to be repaired 5 , And the repair unit 8 is formed (step S27).
  • the heating temperature is raised so that the temperature rising rate is 5 degrees or more per minute. This is because the repair patch 10 and the resin sheet 35 can be heated rapidly, so that the resin can be suitably softened before the repair patch 10 and the resin sheet 35 are completely cured.
  • the surface 12 having the curved surface of the first surface-side radius of curvature R1 can be obtained, even when the outer peripheral surface 7 of the portion to be repaired 5 is a curved surface,
  • the repair patch 10 can be adhered according to the shape of the outer peripheral surface 7. Thereby, the residual stress to the side away from the portion to be repaired 5 generated at the peripheral portion of the repair patch 10 can be reduced, and the peeling of the repair patch 10 from the portion to be repaired 5 can be suppressed.
  • the curved surface of the surface 12 in the repair patch 10 has a smaller radius of curvature than the curved surface of the outer peripheral surface 7 of the portion 5 to be repaired.
  • the repair patch 10 can be made easy to conform to the counterbore 6, so even when preparing a plurality of types of repair patches 10 in advance, it is possible to cope with a small number of types. Repair patch 10 can be made.
  • the repair patch 10 in a pre-cured state can be disposed in the counterbore 6.
  • the repair patch 10 when the repair patch 10 is completely cured, the repair patch 10 can be softened, whereby the repair patch 10 is suitably adapted to the counterbore 6, ie, the shape of the repair patch 10 is counterbalanced. It can be shaped according to the hole 6. For this reason, generation
  • the repair patch 10 can be suitably bonded to the portion to be repaired 5 having a cylindrical outer peripheral surface, so-called single contour surface.
  • the posture of the repair patch 10 with respect to the counterbore 6 can be arranged appropriately.
  • the gap between the counterbore 6 and the repair patch 10 can be made smaller than the thickness of the resin sheet 35 in a vacuum state, the countersunk hole 6 and the repair patch 10 can be made of resin The sheet 35 can be properly adhered. For this reason, the mixing of air bubbles between the counterbore 6 and the repair patch 10 can be suppressed.
  • the repair patch 10 and the resin sheet 35 can be positioned in the positioning step S25, the repair patch 10 can be suitably bonded to the counterbore 6 it can.
  • the repair patch 10 in a pre-cured state can be disposed in the counterbore 6. Therefore, when the repair patch is completely cured, the repair patch 10 can be softened, whereby the repair patch 10 can be favorably fitted to the counterbore 6. For this reason, generation
  • the repair patch 10 and the resin sheet 35 can be rapidly heated to the glass transition temperature or more. It can be suitably softened before the repair patch 10 and the resin sheet 35 are completely cured.
  • the first surface-side radius of curvature R1 of the surface 12 of the repair patch 10 does not have to be a constant radius of curvature, and in the circumferential direction of the portion 5 to be repaired The first surface side radius of curvature R1 may be reduced. According to this configuration, the outer peripheral edge of the thin repair patch 10 is easily deformed. For this reason, the peripheral edge portion of the repair patch 10 becomes easy to conform to the counterbore 6 by making the outside first surface side curvature radius R1 smaller than the central portion.
  • FIG. 7 is a cross-sectional view schematically showing another example of the forming jig for forming the repair patch according to the present embodiment.
  • the forming jig 40 shown in FIG. 7 has a forming surface 41 for forming the repair patch 10, and the forming surface 41 is a surface for forming the surface 12 of the repair patch 10. That is, the molding surface 41 has a shape complementary to the surface 12 of the repair patch 10. Specifically, on the forming jig 40, a forming surface 41 having a first surface side curvature radius R1 is formed. The first surface side radius of curvature R1 of the molding surface 41 is smaller than the second surface side radius of curvature R2 of the outer peripheral surface 7 of the portion 5 to be repaired.
  • the upper side of the molding surface 41 is an opening, and the opening is formed in a circular shape, and is a curved surface that is convex downward in a cross section cut by a plane orthogonal to the axial direction. That is, when the forming jig 40 shown in FIG. 7 is compared with the forming jig 20 shown in FIG. 4, the first surface side curvature radius of the forming surface 41 of the forming jig 40 and the surface of the forming jig 20 are the same.
  • the side surface 10c of the repair patch 10 formed by the forming jig 40 and the side surface 21b of the forming jig 20 have the same first curvature radius r1.
  • the shape of the surface 12 can be formed with high accuracy.
  • the forming jig shown in FIG. 8 in which the first surface side curvature radius R1 on the surface 12 of the repair patch 10 becomes smaller from the central portion toward the outside. 40a may be used.
  • the forming jig 40a shown in FIG. 8 changes the diameter of the first surface-side radius of curvature R1 of the forming surface 41 smaller as it goes outward from the central portion, whereby the first curvature radius of the repair patch 10 is obtained. r1 is also changed.
  • FIG. 10 a bottomed counterbore 6 having a bottom surface 6 a and a side surface 6 b is formed in the portion to be repaired 5, and has a configuration substantially similar to the above-described counterbore 6.
  • the repair patch 10 also has a bottom surface 10a, a top surface 10b and a side surface 10c, and has substantially the same configuration as the repair patch 10 described above.
  • the second surface-side radius of curvature R2 of the inner peripheral surface 9 of the portion to be repaired 5 is smaller than the first surface-side radius of curvature R1 of the surface 12 (10a) of the repair patch 10.
  • the first surface curvature radius R1 of the surface 12 (10a) of the repair patch 10 is larger than the second surface curvature radius R2 of the inner circumferential surface 9 of the portion 5 to be repaired.
  • the second curvature radius r2 of the side surface 6b of the counterbore 6 is larger than the first curvature radius r1 of the side surface 10c of the repair patch 10.
  • the first curvature radius r1 of the side surface 10c of the repair patch 10 is smaller than the second curvature radius r2 of the side surface 6b of the counterbore 6 of the portion 5 to be repaired.
  • the first surface side radius of curvature R1 of the surface 12 of the repair patch 10 is set to the second surface of the inner circumferential surface 9.
  • the seat is set to be larger than the side curvature radius R2 and to have the first curvature radius r1 of the side surface 10c of the repair patch 10 smaller than the second curvature radius r2 of the side surface 6b of the counterbore 6
  • a forming jig 60 shown in FIG. 11 is used as a forming jig for forming the repair patch 10 shown in FIG. 10.
  • the forming jig 60 shown in FIG. 11 has a forming surface 61 for forming the repair patch 10, and the forming surface 61 is a surface for forming the surface 12 (10a) of the repair patch 10. That is, the molding surface 61 has a shape complementary to the surface 12 of the repair patch 10. Specifically, on the forming jig 60, a forming surface 61 having a first surface side curvature radius R1 is formed. The first surface-side radius of curvature R1 of the molding surface 61 is larger than the second surface-side radius of curvature R2 of the inner peripheral surface 9 of the portion 5 to be repaired.
  • the shape of the surface 12 of the repair patch 10 can be formed with high precision.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
PCT/JP2018/030651 2017-10-17 2018-08-20 修理パッチ、修理パッチの成形方法、複合材の修理方法及び成形治具 Ceased WO2019077860A1 (ja)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US16/756,035 US11338529B2 (en) 2017-10-17 2018-08-20 Repair patch, method for molding repair patch, method for repairing composite material, and molding jig
EP18867557.3A EP3698957A4 (en) 2017-10-17 2018-08-20 REPAIR PLASTER, METHOD OF MOLDING A REPAIR PLASTER, METHOD OF REPAIR OF COMPOSITE MATERIAL AND MOLDING DEVICE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2017201302A JP6946143B2 (ja) 2017-10-17 2017-10-17 修理パッチ、修理パッチの成形方法、複合材の修理方法及び成形治具
JP2017-201302 2017-10-17

Publications (1)

Publication Number Publication Date
WO2019077860A1 true WO2019077860A1 (ja) 2019-04-25

Family

ID=66174028

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2018/030651 Ceased WO2019077860A1 (ja) 2017-10-17 2018-08-20 修理パッチ、修理パッチの成形方法、複合材の修理方法及び成形治具

Country Status (4)

Country Link
US (1) US11338529B2 (enExample)
EP (1) EP3698957A4 (enExample)
JP (1) JP6946143B2 (enExample)
WO (1) WO2019077860A1 (enExample)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11692585B2 (en) * 2019-01-15 2023-07-04 Goodrich Corporation Composite shaft with outer periphery ring
CN115157725B (zh) * 2022-05-30 2024-11-26 浙江天能电池江苏新能源有限公司 一种蓄电池外壳沙孔修复方法
US20250162268A1 (en) * 2023-11-17 2025-05-22 Goodrich Corporation Repair of high value thermoplastic structures using automated fiber placement

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6124561B2 (enExample) 1978-08-17 1986-06-11 Daikin Kogyo Co Ltd
JPH11348141A (ja) * 1998-06-12 1999-12-21 Taiei Shoko Kk 架設成形体の補修方法、シート並びにその製法
US20120080135A1 (en) * 2010-09-30 2012-04-05 The Boeing Company Systems and Methods for On-Aircraft Composite Repair Using Double Vacuum Debulking
JP2013545638A (ja) * 2010-11-04 2013-12-26 ザ・ボーイング・カンパニー 複合材応急補修テンプレートツール及び方法
JP2014100847A (ja) * 2012-11-20 2014-06-05 Mitsubishi Aircraft Corp 複合材の修理方法および複合材
JP2014188995A (ja) * 2013-03-28 2014-10-06 Mitsubishi Aircraft Corp 被修理部の修理方法および修理により得られた修理結果物
US20160159057A1 (en) * 2014-12-05 2016-06-09 The Boeing Company Forming of staged thermoset composite materials
JP2018114721A (ja) * 2017-01-20 2018-07-26 三菱重工業株式会社 複合材の修理方法

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9622780D0 (en) * 1996-11-01 1997-01-08 British Aerospace Repair of composite laminates
US9770871B2 (en) * 2007-05-22 2017-09-26 The Boeing Company Method and apparatus for layup placement
US8936695B2 (en) * 2007-07-28 2015-01-20 The Boeing Company Method for forming and applying composite layups having complex geometries
BRPI0822774B1 (pt) * 2008-06-27 2020-08-25 Compagnie Generale Des Etablissements Michelin método para preparar uma porção de um pneumático para reparo.
JP5657017B2 (ja) * 2010-10-22 2015-01-21 株式会社ブリヂストン ラジアルタイヤの修理方法、修理済みラジアルタイヤおよびパッチラバー
DE102011006032A1 (de) * 2011-03-24 2012-09-27 Airbus Operations Gmbh Verfahren zur Herstellung eines Strukturbauteils sowie Strukturbauteil
US9539798B2 (en) * 2014-02-17 2017-01-10 The Boeing Company Verifiable quick patch repair for composite structures
US10322552B2 (en) * 2015-01-20 2019-06-18 Sikorsky Aircraft Corporation Composite repair armature

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6124561B2 (enExample) 1978-08-17 1986-06-11 Daikin Kogyo Co Ltd
JPH11348141A (ja) * 1998-06-12 1999-12-21 Taiei Shoko Kk 架設成形体の補修方法、シート並びにその製法
US20120080135A1 (en) * 2010-09-30 2012-04-05 The Boeing Company Systems and Methods for On-Aircraft Composite Repair Using Double Vacuum Debulking
JP2013545638A (ja) * 2010-11-04 2013-12-26 ザ・ボーイング・カンパニー 複合材応急補修テンプレートツール及び方法
JP2014100847A (ja) * 2012-11-20 2014-06-05 Mitsubishi Aircraft Corp 複合材の修理方法および複合材
JP2014188995A (ja) * 2013-03-28 2014-10-06 Mitsubishi Aircraft Corp 被修理部の修理方法および修理により得られた修理結果物
US20160159057A1 (en) * 2014-12-05 2016-06-09 The Boeing Company Forming of staged thermoset composite materials
JP2018114721A (ja) * 2017-01-20 2018-07-26 三菱重工業株式会社 複合材の修理方法

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP3698957A4

Also Published As

Publication number Publication date
US20200254699A1 (en) 2020-08-13
EP3698957A1 (en) 2020-08-26
JP6946143B2 (ja) 2021-10-06
JP2019072947A (ja) 2019-05-16
US11338529B2 (en) 2022-05-24
EP3698957A4 (en) 2021-07-07

Similar Documents

Publication Publication Date Title
US9365282B2 (en) Method of repairing composite material and composite material
CN101903162A (zh) 一种用于修理纤维复合物固体构件的方法
CN101489769B (zh) 复合件制造方法
US5683646A (en) Fabrication of large hollow composite structure with precisely defined outer surface
US11396141B2 (en) Repair patch, method for molding repair patch, and method for repairing composite material
EP3750698B1 (en) Repair patch, repair patch molding method, and repair method for composite material
JP2018203229A5 (enExample)
WO2019077860A1 (ja) 修理パッチ、修理パッチの成形方法、複合材の修理方法及び成形治具
CN108495739B (zh) 用于制造风轮机叶片本体的方法与设备
US20170282446A1 (en) Pre-polymerized thermosetting composite part and methods for making such a part
US11396173B2 (en) Tool and associated method for manufacturing the same
EP4074499A1 (en) Methods for repairing composite material using pre-cured plugs
JP2019072947A5 (enExample)
JP7783717B2 (ja) 一体化された犠牲表面を備えた複合スパー
EP4467328B1 (en) Method for manufacturing spars or ribs for aircrafts
US20240239061A1 (en) Method of Manufacturing a Component from a Composite Material with Locally Different Thicknesses
JP6820753B2 (ja) 修理パッチの成形方法
US20210114318A1 (en) Method for manufacturing a part made of composite material comprising a first, then a second polymerization
KR20150111003A (ko) 스트링거가 일체화된 항공기 동체 제작방법
JP2021041701A (ja) 修理パッチ、被修理部の修理方法及び補修部

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18867557

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

ENP Entry into the national phase

Ref document number: 2018867557

Country of ref document: EP

Effective date: 20200518