WO2014038837A1 - Appareil pour fabriquer une structure stratifiée composite renforcée par l'insertion de broches le long d'une direction inclinée - Google Patents

Appareil pour fabriquer une structure stratifiée composite renforcée par l'insertion de broches le long d'une direction inclinée Download PDF

Info

Publication number
WO2014038837A1
WO2014038837A1 PCT/KR2013/007948 KR2013007948W WO2014038837A1 WO 2014038837 A1 WO2014038837 A1 WO 2014038837A1 KR 2013007948 W KR2013007948 W KR 2013007948W WO 2014038837 A1 WO2014038837 A1 WO 2014038837A1
Authority
WO
WIPO (PCT)
Prior art keywords
pins
composite laminate
laminate structure
composite
pin
Prior art date
Application number
PCT/KR2013/007948
Other languages
English (en)
Korean (ko)
Inventor
최익현
임철호
심은섭
Original Assignee
한국항공우주연구원
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 한국항공우주연구원 filed Critical 한국항공우주연구원
Publication of WO2014038837A1 publication Critical patent/WO2014038837A1/fr

Links

Images

Classifications

    • 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
    • B32B3/02—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 features of form at particular places, e.g. in edge regions
    • B32B3/06—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 features of form at particular places, e.g. in edge regions for securing layers together; for attaching the product to another member, e.g. to a support, or to another product, e.g. groove/tongue, interlocking
    • 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
    • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
    • 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
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • 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
    • 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
    • B32B37/1018—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 only vacuum

Definitions

  • the present invention is to produce a composite laminated structure in which the pins are reinforced to be inclined with respect to the thickness direction of the composite laminated structure to reinforce the interlayer performance of the composite laminated structure or to connect the plurality of laminated members, thereby reinforcing the performance or connecting the multiple members. Relates to a device.
  • Fiber-reinforced composites which are widely used in lightweight structures such as aerospace and transportation structural members, are manufactured by laminating unidirectional or woven prepregs and applying heat and pressure. Since the laminated structure of the composite structure does not have a separate reinforcing material in the thickness direction, an interlayer separation phenomenon in which layers are easily separated from each other due to external impact or the like occurs. Since this delamination lowers the strength of the structure, methods for preventing this have been studied by researchers in the related field. In other words, many studies have been conducted on methods such as stitching, z-pinning, textile, and toughened matrix to reinforce the weak delamination properties of the composite laminate structure.
  • the initial concept of the z-pinning method can be found in US Patent No. 4,808,461 (February 28, 1989, Prior Art 1).
  • the core concept of the prior art 1 is to put a pin in a polyvinyl foam in the thickness direction, to attach a thin stainless plate on the top and a release material film on the bottom is a so-called 'reinforced structure' for laminating during molding Positioning and forming the upper portion of the composite material is to collapse the preform by the high temperature and high pressure during the molding process is to be pinned into the laminate (see Figure 1).
  • U.S. Patent No. 5,186,776 (February 16, 1993, hereinafter 'Previous Technology 2') is a series of molding the pins directly from the bundle of composite reinforcing fibers and adding ultrasonic vibration to the molded pins and inserting them into the composite structure.
  • An apparatus and a method for operating the same are disclosed, and US Patent No. 5,589,015 (Dec. 31, 1996, hereinafter 'prior art 3') has ultrasonic vibrations in a compressible 'foam structure' in which pins are embedded in advance.
  • a method and system are disclosed for embedding a pin into a composite structure in a pre- or post-molded state by compressing while applying vibration using an apparatus.
  • FIG. 1 is an exemplary view showing a general composite molding method. Apply the release material 112 on the mold 111 for composite molding, put the composite prepreg stack 121, and lay the bleeder 113 to absorb the release material 112 and the resin again, After covering the whole with the film bag 115 to which the adapter 116 which applies a vacuum is attached, it seals with the sealant 117 at the edge.
  • the cork dam 114 may not be used depending on the characteristics of the molding method for molding the composite laminate structure 121.
  • Figure 2 is an exemplary view of a conventional z-pinning method, showing the concept of the prior art 1.
  • FIG. 3 is another exemplary diagram of a conventional z-pinning method, which is a case of forming a composite structure having a constant thickness using the conventional z-pinning method.
  • a composite laminated structure having a constant thickness by the conventional z-pinning method it is difficult because the stainless plate on the 'reinforced structure 330' interferes with deformation.
  • a 'foam structure' without a stainless plate is used, a 'foam structure (similar to 330 and 230') having a constant length of the pin 331 is used. It is difficult to satisfy all of the molding conditions in the part 323.
  • the length of the pin 331 is matched to the thick portion 322, in the case of the thin portion 323, the length of the pin 331 is long so that the molding pressure does not act on the composite laminate structure 323.
  • the basic requirements 7-8 atm or 20 atm of pressure depending on the material need to be applied to the composite laminate to remove bubbles and release excess resin in the molding stage). You will not be satisfied.
  • the length of the pin 331 is matched to the thin portion 323, in the case of the thick portion 322, the length of the pin 331 is short, so that only a part of the pin is stuck in the thickness direction of the laminated structure. The effect of the pinning method is not sufficiently exerted.
  • the thickness of the 'foam structure 330' should be manufactured to be changed to match the thickness of the laminated structure, which is a compressible foam 332 structure. Due to the nature of the process may not be easy.
  • the above prior arts have a characteristic that the pins are pre-embedded in the foam in order to pin the composite laminated structure in common, and the pins are driven into the composite laminated structure while the foam is compressed and collapsed by external vibration load or molding pressure.
  • the so-called 'form structure' ('reinforcement structure' can also be seen as a form of 'form structure') is used as a medium, and this 'form structure' is a feature of the technology.
  • the compression collapsed foam must be artificially removed after pinning, and the protruding portion of the pin must be forcibly broken to remove material waste. And process inefficiency is inevitable.
  • some scratches may occur at the location where the pin is broken, and the pin has a problem of adversely affecting the strength of the pin and the surrounding structure during the breaking of the pin.
  • the method of pinning the composite laminate structure using the foam structure or the reinforcement structure in this way because the depth of pin pins vary depending on the height when the height of the composite laminate structure is not constant, according to the prior art
  • the uneven height of the laminated composite structure has a big problem that the interlayer stiffness is uneven depending on the location.
  • the conventional method of z-pinning a composite laminate having a non-uniform height has a problem in that the configuration of the equipment is complicated and the process is very difficult to apply.
  • Patent Registration No. 0932302, 2009.12.08, hereinafter 'prior art 4' The prior art 4 is devised to solve the problems of the prior art as described above, the object of the invention is to be able to pin the pin while repeatedly reuse the associated jig without using the disposable 'foam structure'
  • the present invention provides a composite laminate structure in which pins are reinforced to reinforce performance, a method, a device for manufacturing the composite laminate structure, and a device manufacturing method.
  • the prior art 4 has an effect of greatly improving the bonding force between the laminated members by effectively inserting the pin into the plurality of laminated members.
  • the present invention is a follow-up study of the applicant's registered patents mentioned above, and the object of the present invention is to pin the staggered pins in an inclined direction, in particular in two or more inclined directions, so that the pins are interlayered surfaces of the laminate structure.
  • the present invention provides an apparatus for manufacturing a composite laminate structure in which pins are inclined with respect to a thickness direction of the composite laminate structure to reinforce the contact connection between two or more members so as to further enhance the clamping force. .
  • Apparatus for manufacturing a composite laminate structure of the present invention for achieving the object as described above, in the manufacturing apparatus of the composite laminate structure pinned for reinforcing interlayer separation performance or contact connection between a plurality of laminated members When the plane direction is referred to as the horizontal direction and the direction perpendicular to the horizontal direction is referred to as the vertical direction, the vertical portion S1 and the vertical portion S1 which are mounted on the composite laminate structure 21 before or after molding and extend in the vertical direction. Pins 51 and 51 to be inserted into the composite laminate structure 21 in a plurality of holes 53 and 53 ', respectively, which are connected to the portion S1 and incline portions S2 extending in a direction inclined with respect to the vertical direction.
  • An upper guide 40 having a plurality of elastic guide pins 41 and 41 ′ formed thereon; Characterized in that comprises a.
  • the plurality of holes 53 and 53 ' are characterized in that each of the inclined portions S2 and S2' is formed to be inclined in at least two different directions. In this case, it is more preferable that the plurality of holes 53 and 53 'are formed such that the inclined portions S2 and S2' inclined in different directions are alternately disposed.
  • the apparatus for manufacturing a composite laminate structure is mounted on the upper guide 40, the elastic guide pins 41, 41 'is inserted into the holes 53, 53' and the pins 51, 51 '.
  • the load adding means 60 is a pressure load by the molding pressure to add a load using at least one or more of the physical force selected from the vibration load portion by ultrasonic or vibration, or the gravity load portion by heavy material. It is preferable.
  • the lower guide 50 is attached to the lower surface of the film 12 which prevents the pin 51 from being separated before the insertion process into the composite laminate structure 21 in the pre-molding or post-molding state. .
  • the pins (51, 51 ') is characterized in that the lower end portion 55 is formed in a pointed shape.
  • the pins 51 and 51 ' are preferably formed with irregularities on the surface 57 of the pins so as to better prevent the pins from being separated after molding.
  • the present invention has a reinforcing effect of the delamination performance by applying a z-pinning method that pins in the thickness direction of the composite laminate structure basically in the manufacture of a composite laminate structure having a weak delamination performance, and also laminated two composites There is an effect of improving the adhesion between the structural members.
  • the pin in the conventional z-pinning method (disclosed in Prior Art 4, the applicant's registered patent), the pin may be pushed only in the vertical direction, so that the connection part may be easily separated by the external force and the pin may be separated.
  • the pins are staggered in two or more inclined directions, thereby further improving the interlayer separation inhibiting ability of the composite laminated structure and further improving the fastening force between the two or more laminated structures.
  • 1 is a view illustrating a general composite molding method
  • Figure 2 illustrates a conventional z-pinning method
  • Figure 3 is another illustration of a conventional z-pinning method
  • Figure 4 is an illustration of the initial state of the z-pinning method of the conventional invention by the present inventors
  • FIG. 5 is a detailed view of portion S of FIG. 4; FIG.
  • Figure 6 is an exemplary view of the termination state of the z-pinning method of the conventional invention by the present inventors
  • Figure 7 is a connection state between the two composite members of the present invention by the inventor
  • FIG. 8 is an exemplary view of an initial state of a z-pinning method of the present invention.
  • FIG. 9 is a detailed view of portion S of FIG. 9
  • FIG. 10 is an exemplary view of a z-pinning method termination state of the present invention.
  • FIG. 11 is a view illustrating a connection state between two composite members of the present invention.
  • Figure 12 is an exemplary view of the pin shape of the present invention
  • Mold 12 (release material) film
  • FIG. 8 is an exemplary view showing an initial state of the present invention for a composite laminate structure 21 in a state before molding among z-pinning methods of the present invention
  • FIG. 9 is a detailed view showing the S portion of FIG. 8 in detail.
  • the state before molding refers to a state in which prepregs are laminated
  • the state after molding refers to a state in which molding is completed by applying molding pressure to the laminated prepregs.
  • the pin may be inserted at the same time as the prepreg is laminated, and the pin may be pinned to the laminated prepreg first, followed by a general composite molding process to complete the composite laminate structure.
  • Pins may be inserted into the composite laminate structure in which the molding is completed, or pins may be inserted to join a plurality of composite laminate structures in a pre-molded or post-molded state.
  • a planar direction (generally in the xy plane direction) of the laminated member is referred to as a horizontal direction and a direction perpendicular to the horizontal direction (generally referred to as the z axis direction) is referred to as a vertical direction. It will be called.
  • the holes 53 and 53' are formed to extend in a vertical direction at an entrance portion and to be inclinedly extending as shown in FIG. have. More specifically, the holes 53 and 53 'are connected to the vertical portion S1 extending in the vertical direction and the inclined portion S2 connected to the vertical portion S1 and extending in an inclined direction with respect to the vertical direction. It consists of.
  • the holes 53 and 53 'formed as described above are provided with pins 51 and 51', respectively.
  • the upper guide 40 is mounted on the lower guide 50, and the hole 53 (of the lower guide 50) on a surface facing the lower guide 50 of the upper guide 40.
  • the elastic guide pins 41 and 41 ' are formed in the holes. And the elastic guide pins 41 and 41 'push out the pins 51 and 51' and ultimately the pins 51 and 51 'are laminated in the composite structure. It is obliquely lodged at (21).
  • the elastic guide pins 41 and 41 ' are made of an elastic material, the elastic guide pins 41 and 41' are inserted into the vertical portion S1 and guided to the inclined portions S2 and S2 'so that they can be moved downward. That is, the inclined direction of the pins 51 and 51 'in the holes 53 and 53' is inserted along the holes 53 and 53 'where the elastic guide pins 41 and 41' are bent (i.e., the inclination).
  • the pins 51 and 51 ' may be inclined to the inside of the composite laminate 21 in a natural manner.
  • the apparatus for manufacturing a composite laminate structure of the present invention enables the pins to be pushed into the composite laminate structure in an inclined direction, thereby more firmly tightening the contact connection between the interlayer surfaces of the laminate structure or two or more members thereof.
  • the prior art 4 (applicant's registered patent) had the effect of improving the fastening force by driving the pin, but the pin was stuck only in the vertical direction, there was a limit that the possibility of the deviation of the pin may occur, in the present invention is only vertical Not only in the direction, but also because the pin is driven in an inclined direction, the possibility of the pin falling off is much lower, resulting in a much higher tightening force.
  • the plurality of holes 53 and 53 ' are preferably formed such that each of the inclined portions S2 and S2' is inclined in at least two different directions.
  • 9 illustrates an example in which holes formed obliquely in two different directions are alternately arranged with holes inclined in different directions in the depth direction of the screen with reference to FIG. 9.
  • one inclined elastic guide pin / pin / hole / inclined portion with reference numeral 41/51/53 / S2 the inclined elastic guide pin in a different inclination direction based on Figure 9 / Pins / holes / inclined parts are indicated by the reference numeral 41 '/ 51' / 53 '/ S2'.
  • the plurality of holes (53, 53 ') are inclined in different directions
  • the inclined portions S2 and S2 ' may be formed to be alternately disposed.
  • this is only one example, and thus the present invention is not limited at all, and it is obvious that various changes may be made as necessary.
  • the holes may be formed to have only one inclined direction.
  • the pin may be inclined in two, three or more directions to maximize the tightening force. That is, it can be formed in any inclined direction so as to be staggered at various angles within a range where no interference between the holes occurs.
  • the pins 51, 51 ′ that are embedded into the composite laminate structure 21 before or after the molding are processed to have a length suitable for the thickness of the composite laminate structure 21 (thickness in consideration of an inclined direction) after molding. do.
  • the upper portion 54 of the holes 53, 53 ' can be easily guided to the holes 53, 53' by processing the guide pins 41, 41 'in the form of a dish head or the like.
  • the edge 52 of the lower guide 50 is configured to guide the movement of the upper guide 40. It is preferably formed.
  • the film bag 15 is covered thereon and the molding is performed in the same manner as in the general composite molding method.
  • the laminated prepregs are formed into the composite laminate structure, and at the same time, the pins are inserted in the inclined direction, and as a result, the composite laminate structure in which the pins are inclined is formed.
  • the apparatus for manufacturing a composite laminate structure is mounted on the upper guide 40, the elastic guide pins 41, 41 'is inserted into the holes 53, 53' and the pins 51, 51 '.
  • the load adding means 60 includes a plurality of means for adding a physical force such as molding pressure, that is, pressure loading by vacuum and high pressure applied during molding, vibration loading by ultrasonic or vibration, and gravity loading by heavy material. It is possible. In the case of covering with the film bag 15 and adding vacuum or molding pressure in and out of the film bag 15 as shown in FIG. 4, a separate hardware device for the load adding means 60 may not be required.
  • the lower guide 50 is preferably attached to the film 12 on the bottom surface.
  • the film 12 is attached before the insertion process into the composite laminate structure 21 in the pre- or post-molding state, and the film 12 prevents the pins 51 and 51 'from being separated.
  • the pins 51, 51 ' are provided in the holes 53, 53' (without a separate sealing means at the bottom), so that the holes 53, 53 '
  • the film 12 is attached to the bottom of the lower guide 50, but the film 12 acts as a sealing means, so that the pins 51 and 51 ' It can prevent departure.
  • FIG. 10 is an exemplary view illustrating a termination state of a z-pinning method of inserting a pin through a molding process for a composite laminate structure of a state before molding among various concepts of the present invention.
  • the composite pinned structure is first contacted with the elongated pins 51 and 51 'from the elongated pins 51 and 51' as shown in the middle portion of FIG. 21) It gets stuck inside.
  • the upper guide 40 and the lower guide 50 gradually approach each other, and later all the pins 51 and 51 'are brought into contact with the elastic guide pins 41 and 41' to be embedded into the composite laminate structure 21.
  • the pins 51, 51 ′ are completely embedded into the composite stack 21 until the upper guide 40 and the lower guide 50 come into contact with each other.
  • the load by the load-adding means 60 is transmitted to the entire composite laminate structure 21, and the composite laminate in the state before molding as shown in the present example In the case of targeting the structure and inserting the pin through the molding process, it may be possible to release the excess resin.
  • the load by the load-adding means 60 is transmitted to the entire composite laminate structure 21, the composite laminate structure 21 is also partially compressed, the pin 51 embedded in the inclined direction in the final compressed state It is preferable that the lower end 55 of the 51 ') touches the mold 11, and for this purpose, the lengths of the pins 51 and 51' should be accurately determined and utilized in advance by using a test or experience.
  • FIG. 11 is an exemplary view of a connection state between two composite laminate structural members, and is to illustrate that the method of the present invention may also be applied to a connection between two composite laminated structural members before or after forming.
  • the clamping force between the two members can be improved by staggering the pins 51 and 51 ′.
  • the use of this concept for the connection between the lower composite laminated structural member 24 and the upper composite laminated structural members 25, 26 avoids the use of metal rivets or bolts, which is advantageous in terms of weight reduction of the structure.
  • the present invention in the fabrication of a composite laminate structure having a weak delamination performance, by applying a z-pinning method pinned in the thickness direction of the composite laminate structure, the reinforcing effect of the delamination performance, improve the adhesion between the two composite laminate structure members It is effective to let.
  • the pins are staggered in two or more inclined directions, thereby further improving the interlayer separation inhibiting ability of the composite laminated structure and further improving the fastening force between the two or more laminated structures.
  • the surface of a pin is processed and inserted in an uneven

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Textile Engineering (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)

Abstract

La présente invention porte sur une structure stratifiée composite ou sur un appareil pour fabriquer la structure stratifiée composite renforcée par l'insertion de broches ou la liaison de multiples éléments, laquelle structure stratifiée composite est renforcée vis-à-vis des performances entre couches de la structure stratifiée composite ou relie de multiples éléments de stratification par l'insertion de broches selon une inclinaison dans la direction de l'épaisseur d'une partie de liaison de la structure stratifiée. L'appareil pour fabriquer la structure stratifiée composite selon la présente invention est disposé sur la structure stratifiée composite avant ou après la mise en forme, et est caractérisé en ce qu'il comprend : un guide inférieur comportant des broches insérées selon une inclinaison non verticale dans la structure stratifiée composite dans de multiples trous formés ; et un guide supérieur comportant des broches de guidage élastomères qui sont disposées de façon mobile dans une région correspondant à une région supérieure de trous contenant les broches inclinées de façon non verticale.
PCT/KR2013/007948 2012-09-04 2013-09-03 Appareil pour fabriquer une structure stratifiée composite renforcée par l'insertion de broches le long d'une direction inclinée WO2014038837A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR10-2012-0097557 2012-09-04
KR1020120097557A KR101345743B1 (ko) 2012-09-04 2012-09-04 경사진 방향들로 핀을 박아 성능을 보강하는 복합재 적층 구조물의 제조 장치

Publications (1)

Publication Number Publication Date
WO2014038837A1 true WO2014038837A1 (fr) 2014-03-13

Family

ID=49989279

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/KR2013/007948 WO2014038837A1 (fr) 2012-09-04 2013-09-03 Appareil pour fabriquer une structure stratifiée composite renforcée par l'insertion de broches le long d'une direction inclinée

Country Status (2)

Country Link
KR (1) KR101345743B1 (fr)
WO (1) WO2014038837A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016144571A1 (fr) * 2015-03-12 2016-09-15 Northrop Frumman Systems Corporation Broche en z à verrouillage mécanique et à forme configurable activée par la chaleur

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20190066340A (ko) 2017-12-05 2019-06-13 경상대학교산학협력단 보강망과 마이크로 체결재를 이용한 복합재 층간분리 수리기법

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4808461A (en) * 1987-12-14 1989-02-28 Foster-Miller, Inc. Composite structure reinforcement
US5868886A (en) * 1995-12-22 1999-02-09 Alston; Mark S. Z-pin reinforced bonded composite repairs
WO2001034381A1 (fr) * 1999-11-11 2001-05-17 Bae Systems Plc Renfort pour element stratifie d'un aeronef
KR100533481B1 (ko) * 1998-12-31 2006-01-27 주식회사 데크 복합재 적층판의 보울트홀 보강 성형방법
KR20090028861A (ko) * 2007-09-17 2009-03-20 한국항공우주연구원 핀을 박아 성능을 보강한 복합재 적층 구조물, 상기 복합재적층 구조물 제조 방법, 장치 및 상기 장치 제작 방법

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5832594A (en) * 1996-05-31 1998-11-10 The Boeing Company Tooling for inserting Z-pins

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4808461A (en) * 1987-12-14 1989-02-28 Foster-Miller, Inc. Composite structure reinforcement
US5868886A (en) * 1995-12-22 1999-02-09 Alston; Mark S. Z-pin reinforced bonded composite repairs
KR100533481B1 (ko) * 1998-12-31 2006-01-27 주식회사 데크 복합재 적층판의 보울트홀 보강 성형방법
WO2001034381A1 (fr) * 1999-11-11 2001-05-17 Bae Systems Plc Renfort pour element stratifie d'un aeronef
KR20090028861A (ko) * 2007-09-17 2009-03-20 한국항공우주연구원 핀을 박아 성능을 보강한 복합재 적층 구조물, 상기 복합재적층 구조물 제조 방법, 장치 및 상기 장치 제작 방법

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016144571A1 (fr) * 2015-03-12 2016-09-15 Northrop Frumman Systems Corporation Broche en z à verrouillage mécanique et à forme configurable activée par la chaleur
US9657762B2 (en) 2015-03-12 2017-05-23 Northrop Grumman Systems Corporation Thermally activated, shape configurable mechanical locking Z-pin

Also Published As

Publication number Publication date
KR101345743B1 (ko) 2013-12-30

Similar Documents

Publication Publication Date Title
KR100932302B1 (ko) 핀을 박아 성능을 보강한 복합재 적층 구조물, 상기 복합재적층 구조물 제조 방법, 장치 및 상기 장치 제작 방법
KR101394408B1 (ko) Ｚ-피닝 패치 및 이를 이용한 복합재 적층 구조물의 제조 또는 결합 방법
WO2014038837A1 (fr) Appareil pour fabriquer une structure stratifiée composite renforcée par l'insertion de broches le long d'une direction inclinée
WO2010079865A1 (fr) Appareil de mise à plat et de formage de pré-imprégnés et procédé de formage des pré-imprégnés
WO2016182173A1 (fr) Procédé de moulage par injection d'un insert à l'aide d'un matériau composite renforcé par une fibre et produit moulé par injection en utilisant ledit procédé
CN202471481U (zh) 一种胶黏剂拉伸测试标准试样制样模具
CA2935530C (fr) Jig de formage de frp et procede de formage de structure en frp
WO2013051809A2 (fr) Pièce de broche en z et procédé de fabrication ou de couplage d'une structure stratifiée composite qui utilise cette dernière
US11198262B2 (en) Integrated pick, place, and forming apparatus and method for composite charges over complex geometries
WO2017099379A1 (fr) Pièce de retouche à embrochement en z et procédé pour combinaisons de reliure intégrale utilisant celle-ci
WO2016093661A1 (fr) Dispositif de fixation pour empêcher la séparation de parties de moulage par injection
CN210401173U (zh) 一种3d打印混凝土层间粘结强度试验模具组件
WO2018043970A1 (fr) Renfort de poutre hybride de type angulaire, procédé de fabrication d'un renfort de poutre hybride de type angulaire, et procédé de construction d'un renfort de poutre hybride de type angulaire
WO2017146362A1 (fr) Appareil de fabrication d'un composite renforcé par des fibres
WO2017104879A1 (fr) Procédé d'assemblage et structure de tuyaux composites en plastique renforcé par des fibres de verre et procédé d'assemblage de structures composites en plastique renforcé par des fibres de verre
CN212156066U (zh) 一种塑胶卡扣
KR101348277B1 (ko) 펜더제조방법
WO2023158018A1 (fr) Coupleur de barres d'armature antidérapant
WO2019031933A1 (fr) Boîtier de coussin de sécurité gonflable pour véhicules et procédé de fabrication associé
WO2014163227A1 (fr) Procédé de fabrication d'un panneau composite doté d'un matériau central renforcé à trois surfaces et panneau composite utilisant celui-ci
CN219100802U (zh) 一种建筑用密目式安全立网
CN219114028U (zh) 一种便于抽拉的叠放架
CN217169721U (zh) 一种用于浴缸加工的表皮吸塑装置
CN215688004U (zh) 一种透镜帽迭合夹具
WO2023085518A1 (fr) Structure modulaire de semelle de longeron, son procédé de fabrication, pale d'éolienne comprenant une structure modulaire de semelle de longeron, et son procédé de fabrication

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: 13834478

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 13834478

Country of ref document: EP

Kind code of ref document: A1