WO2017146284A1 - Procédé de fabrication d'une structure d'impression 3d par renfort et composite - Google Patents

Procédé de fabrication d'une structure d'impression 3d par renfort et composite Download PDF

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Publication number
WO2017146284A1
WO2017146284A1 PCT/KR2016/001886 KR2016001886W WO2017146284A1 WO 2017146284 A1 WO2017146284 A1 WO 2017146284A1 KR 2016001886 W KR2016001886 W KR 2016001886W WO 2017146284 A1 WO2017146284 A1 WO 2017146284A1
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WO
WIPO (PCT)
Prior art keywords
reinforcing
printing
reinforcement
truss
target
Prior art date
Application number
PCT/KR2016/001886
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English (en)
Korean (ko)
Inventor
김도현
Original Assignee
기술융합협동조합
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Publication date
Application filed by 기술융합협동조합 filed Critical 기술융합협동조합
Publication of WO2017146284A1 publication Critical patent/WO2017146284A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y40/00—Auxiliary operations or equipment, e.g. for material handling
    • B33Y40/20—Post-treatment, e.g. curing, coating or polishing
    • 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
    • B29C37/00—Component parts, details, accessories or auxiliary operations, not covered by group B29C33/00 or B29C35/00
    • 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
    • B29C67/00—Shaping techniques not covered by groups B29C39/00 - B29C65/00, B29C70/00 or B29C73/00
    • 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
    • B29C70/02—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements, e.g. non-specified reinforcements, fibrous reinforcing inserts and fillers, e.g. particulate fillers, incorporated in matrix material, forming one or more layers and with or without non-reinforced or non-filled layers

Definitions

  • the present invention relates to a 3D printing structure manufacturing method using a reinforcing material and a composite material, and more particularly, to a 3D printing structure manufacturing method for reinforcing a core output through 3D printing using a reinforcing material and a composite material.
  • the 3D printer is a printer that produces three-dimensional sculptures using plastic powder, metal components, and polymer composite materials based on a three-dimensional design, and was originally developed to produce prototypes before manufacturing products.
  • the 3D printers are becoming more diverse, and the use of the 3D printer is expanding endlessly.
  • products printed with 3D printers are still lacking in terms of strength, and are supplemented by adding other materials.
  • Composite materials are made of macroscopic mixtures of two or more materials with different properties (reinforcement materials and matrix materials). They can form composite materials of various physical properties according to their combination and ratio. In addition, it has the advantage of reducing the number of parts by integrating a complicated shape and various parts while solving the fatigue damage problem of metal structures due to its flexibility and resistance to vibration. Developing composite materials is one of the future industries as a way to reduce carbon dioxide emissions, a global issue through fuel economy, by reducing the weight of composite materials in aircraft and automobiles.
  • the present invention provides a method for manufacturing a structure reinforced with a 3D printing structure by printing the core of the structure through a 3D printer and composite molding and ceramic coating on the outer surface, thereby increasing the lightness and strength.
  • the present invention provides a method for manufacturing a structure that reinforces a 3D printed structure by reinforcing an additional structure in a skeleton based on a truss structure so as to reinforce the inside of the 3D printed core, thereby improving bearing capacity in the core.
  • the present invention reinforces the interior of the 3D printed core using a reinforcing structure, and after forming a composite material to remove all or part of the reinforcing structure, thereby improving the support structure inside the core 3D printing structure that can reduce the weight of the target structure It provides a structure manufacturing method reinforced with.
  • 3D printing structure manufacturing method the step of 3D printing the core frame of the target structure, the step of reinforcing the interior of the core frame with a predetermined reinforcement structure, of the target structure reinforced with the reinforcement structure Molding a surface using a composite material, removing a predetermined reinforcing structure from among the reinforcing structures inside the target structure in which the composite is molded, and using a predetermined coating material on the surface of the target structure from which the predetermined reinforcing structure is removed. And coating.
  • the reinforcing may include reinforcing the inside of the target structure with a plurality of triangular wave structures having a predetermined displacement difference.
  • the intersection of the plurality of triangular wave structure can be fastened using fastening means.
  • the reinforcing step may include the first step of reinforcing the interior of the target structure with a truss structure and the second step of reinforcing the triangular inside of the truss structure with a circular structure. have.
  • the reinforcing step may include the step of reinforcing the inside of the lower triangular shape of the structure to the polygonal structure.
  • the structure reinforcing the 3D printing structure that can improve the bearing capacity inside the core A manufacturing method is provided.
  • the reinforcement structure by reinforcing the interior of the 3D printed core using the reinforcement structure, and after forming the composite material to remove all or part of the reinforcement structure, to reduce the weight of the target structure while improving the bearing capacity inside the core.
  • FIG. 1 is a flowchart illustrating a method of manufacturing a 3D printing structure according to an embodiment of the present invention.
  • FIG. 2 is a view showing an aircraft wing and its cross-sectional shape for explaining an embodiment of the present invention.
  • Figure 3 is a view showing an embodiment of the reinforcement inside and the cross section of the aircraft wing according to the prior art.
  • FIG. 4 is a view showing an embodiment of the cross section and the inner truss structure of the aircraft wing according to the prior art.
  • FIG. 5 is a view for explaining the process of reinforcing the cylindrical structure to the triangular structure inside the aircraft wing according to an embodiment of the present invention.
  • FIG. 6 is a view of applying a reinforcing structure reinforcing the truss structure inside the aircraft wing according to an embodiment of the present invention.
  • FIG. 7 is a view illustrating a reinforcing structure in which a truss structure is reinforced by using cylindrical and polygonal structures in an aircraft wing according to an embodiment of the present invention.
  • FIG. 8 is a view showing a reinforcing structure in which a double truss structure is reinforced inside an aircraft wing according to an exemplary embodiment of the present invention.
  • FIG. 1 is a flowchart illustrating a method of manufacturing a 3D printing structure according to an embodiment of the present invention.
  • a core frame of a target structure may be output to a 3D printer.
  • a target structure to manufacture a target structure, by outputting the core frame of the target structure through a 3D printer, easily and easily manufacture difficult shapes by machining, the design change is relatively free, customer opinion It can actively reflect, and can increase the supply rate of structures with increasing demand can occur.
  • the inside of the core frame may be reinforced with a predetermined reinforcement structure.
  • the process of reinforcing the reinforcing structure may be made at the same time as the output of the core frame to the 3D printer, or may be made through a separate process.
  • the material of the reinforcing structure may also be selectively applied to the same material as the core frame or a separate material.
  • the predetermined reinforcing structure may be utilized in various forms of reinforcing structures ranging from the reinforcing structure using the reinforcing material of the truss structure to various structures modified therefrom, and these embodiments will be described in more detail below.
  • the surface of the 3D printed target structure can be molded using a composite material.
  • the target structure is the wing structure of the aircraft, if you want to produce it through the manufacturing method of the present invention, after outputting the aircraft wing structure through a 3D printer, the outer surface to reinforce the strength, such as glass fiber, carbon fiber, etc. It can be molded into a composite material.
  • a predetermined reinforcement structure may be removed from the reinforcement structures inside the target structure in which the composite material is molded. That is, after the composite molding is made, since the strength of the target structure is substantially supplemented, it is possible to remove the predetermined reinforcing structure of the reinforcing structure reinforced in the step 120 to reduce unnecessary weight increase of the target structure.
  • the predetermined reinforcement structure may be all or part of the reinforcement structure reinforced in step 120, it may vary depending on the manufacturing environment.
  • the surface of the target structure from which the reinforcement structure is set in step 140 may be coated using a predetermined coating material.
  • a predetermined coating material may be one of ceramic and paint, and various materials may be used depending on the manufacturing environment.
  • FIG. 2 is a view showing an aircraft wing and its cross-sectional shape for explaining an embodiment of the present invention
  • Figure 3 is a view showing an embodiment of the cross section and the internal reinforcement of the aircraft wing according to the prior art
  • Figure 4 is a view showing an embodiment of the cross section and the inner truss structure of the aircraft wing according to the prior art.
  • Figure 2 shows a portion of the aircraft wing, the shape 220 of each part in the process of manufacturing and combining the aircraft wing by part is formed with a gentle curve.
  • the surface of the aircraft wing 210 is laminated in multiple layers, and as shown in the cross-section 220, the inside is using the reinforcement material from the outside Reinforcement was used to withstand pressure.
  • the reinforcing structures are arranged in a line, and as shown in FIG. 4, the reinforcing structures have been widely used as truss structures in which the reinforcing structures are continuously arranged in an oblique shape.
  • FIG. 5 is a view for explaining the process of reinforcing the cylindrical structure to the triangular structure inside the aircraft wing according to an embodiment of the present invention.
  • the reinforcing structure of the column shape 240 is inserted into the triangular column shape to compensate for this. It is possible to implement a more reinforced form of reinforcement structure.
  • FIG. 6 is a view of applying a reinforcing structure reinforcing the truss structure inside the aircraft wing according to an embodiment of the present invention.
  • the reinforcing structure As shown in FIG. 6, it is most effective to use the reinforcing structure when the upper and lower surfaces of the structure are close to a straight line, and when the shape of some or all of the surface of the structure is curved, another type of reinforcing structure may be used. .
  • Reinforcing step 140 of the present invention for this purpose, including the first step of reinforcing the interior of the structure to the truss structure and the second step of reinforcing the triangular inside of the truss structure as a circular structure, the reinforcement The structure can be implemented.
  • FIG. 7 is a view illustrating a reinforcing structure in which a truss structure is reinforced by using cylindrical and polygonal structures in an aircraft wing according to an embodiment of the present invention.
  • reinforcing step 140 the first step of reinforcing the inside of the structure with a truss structure, the second step of reinforcing the inside of the upper triangular shape of the truss structure with a circular structure and
  • the shape of the reinforcing structure may be implemented by including reinforcing the inside of the lower triangular shape of the truss structure with a polygonal structure.
  • FIG. 8 is a view showing a reinforcing structure in which a double truss structure is reinforced inside an aircraft wing according to an exemplary embodiment of the present invention.
  • the existing truss structure has a triangular wave shape, and when an additional triangular wave shape structure is applied so that the triangular wave does not overlap, an internal reinforcement structure having a double truss structure may be implemented. Therefore, the internal supporting force can be further strengthened through such a shape, and the double truss structure has been described in FIG.
  • the reinforcing step 140 may reinforce the inside of the structure with a plurality of triangular wave structures having a predetermined displacement difference.
  • the intersection of the plurality of triangular wave structures may be fastened by using fastening means, so that the bearing force between the structures may be further strengthened.
  • the structure manufacturing method reinforcing the 3D printing structure to enhance the light and strength This may be provided.
  • the method of manufacturing a 3D printing structure according to an embodiment of the present invention may be recorded in a computer readable medium including program instructions for performing various computer-implemented operations.
  • the computer readable medium may include program instructions, data files, data structures, etc. alone or in combination.
  • the medium or program instructions may be those specially designed and constructed for the purposes of the present invention, or they may be of the kind well-known and available to those having skill in the computer software arts.
  • Examples of computer-readable recording media include magnetic media such as hard disks, floppy disks, and magnetic tape, optical media such as CD-ROMs, DVDs, and magnetic disks, such as floppy disks.
  • Magneto-optical media and hardware devices specifically configured to store and execute program instructions, such as ROM, RAM, flash memory, and the like.
  • program instructions include not only machine code generated by a compiler, but also high-level language code that can be executed by a computer using an interpreter or the like.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Composite Materials (AREA)

Abstract

L'invention concerne un procédé de fabrication d'une structure d'impression 3D par renfort et un composite. Un procédé de fabrication d'une structure d'impression 3D comprend les étapes suivantes : l'impression en 3D d'un cadre central d'une structure; le moulage d'une surface de la structure au moyen d'un composite; le revêtement de la surface moulée au moyen du composite en utilisant de la céramique; et le renfort de l'intérieur de la structure par une structure de renfort prédéfinie.
PCT/KR2016/001886 2016-02-25 2016-02-25 Procédé de fabrication d'une structure d'impression 3d par renfort et composite WO2017146284A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR20160022403 2016-02-25
KR10-2016-0022403 2016-02-25

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WO2017146284A1 true WO2017146284A1 (fr) 2017-08-31

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019074916A3 (fr) * 2017-10-11 2019-05-23 Divergent Technologies, Inc. Incrustation de matériau composite dans des structures fabriquées de manière additive
US10836120B2 (en) 2018-08-27 2020-11-17 Divergent Technologies, Inc . Hybrid composite structures with integrated 3-D printed elements

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH08164488A (ja) * 1994-12-09 1996-06-25 Ship & Ocean Zaidan 超塑性成形用多層クラッド板とその製造方法、およびそれを用いた中空剛性ボードとその製造方法
US6630093B1 (en) * 1999-08-21 2003-10-07 Ronald D. Jones Method for making freeform-fabricated core composite articles
WO2008118649A1 (fr) * 2007-03-27 2008-10-02 Dynastrosi Laboratories, Inc. Procédé pour lier une pellicule opposée à un noyau de composite de forme libre
US8383028B2 (en) * 2008-11-13 2013-02-26 The Boeing Company Method of manufacturing co-molded inserts
US8522416B2 (en) * 2008-02-29 2013-09-03 Airbus Operations Gmbh Method for tolerance compensation between two fibre composite components
KR20150120643A (ko) * 2014-04-18 2015-10-28 쓰리디토시스 주식회사 블록 적층 방식과 수지압출 기술을 결합한 3d 프린팅 시스템 및 하이브리드 3d 프린팅을 위한 설계 데이터 생성 방법

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH08164488A (ja) * 1994-12-09 1996-06-25 Ship & Ocean Zaidan 超塑性成形用多層クラッド板とその製造方法、およびそれを用いた中空剛性ボードとその製造方法
US6630093B1 (en) * 1999-08-21 2003-10-07 Ronald D. Jones Method for making freeform-fabricated core composite articles
WO2008118649A1 (fr) * 2007-03-27 2008-10-02 Dynastrosi Laboratories, Inc. Procédé pour lier une pellicule opposée à un noyau de composite de forme libre
US8522416B2 (en) * 2008-02-29 2013-09-03 Airbus Operations Gmbh Method for tolerance compensation between two fibre composite components
US8383028B2 (en) * 2008-11-13 2013-02-26 The Boeing Company Method of manufacturing co-molded inserts
KR20150120643A (ko) * 2014-04-18 2015-10-28 쓰리디토시스 주식회사 블록 적층 방식과 수지압출 기술을 결합한 3d 프린팅 시스템 및 하이브리드 3d 프린팅을 위한 설계 데이터 생성 방법

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019074916A3 (fr) * 2017-10-11 2019-05-23 Divergent Technologies, Inc. Incrustation de matériau composite dans des structures fabriquées de manière additive
KR20200055794A (ko) * 2017-10-11 2020-05-21 디버전트 테크놀로지스, 인크. 적층 제조된 구조물 내의 복합 재료 인레이
US10814564B2 (en) 2017-10-11 2020-10-27 Divergent Technologies, Inc. Composite material inlay in additively manufactured structures
JP2020536769A (ja) * 2017-10-11 2020-12-17 ダイバージェント テクノロジーズ， インコーポレイテッドＤｉｖｅｒｇｅｎｔ Ｔｅｃｈｎｏｌｏｇｉｅｓ， Ｉｎｃ． 付加製造された構造における複合材料インレイ
JP7100122B2 (ja) 2017-10-11 2022-07-12 ダイバージェント テクノロジーズ， インコーポレイテッド 付加製造された構造における複合材料インレイ
US11584094B2 (en) 2017-10-11 2023-02-21 Divergent Technologies, Inc. Composite material inlay in additively manufactured structures
KR102522931B1 (ko) 2017-10-11 2023-04-17 디버전트 테크놀로지스, 인크. 적층 제조된 구조물 내의 복합 재료 인레이
US10836120B2 (en) 2018-08-27 2020-11-17 Divergent Technologies, Inc . Hybrid composite structures with integrated 3-D printed elements

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