KR102322411B1 - Aircraft Wing End Composite Structure Manufacturing Equipment - Google Patents

Aircraft Wing End Composite Structure Manufacturing Equipment Download PDF

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Publication number
KR102322411B1
KR102322411B1 KR1020200144081A KR20200144081A KR102322411B1 KR 102322411 B1 KR102322411 B1 KR 102322411B1 KR 1020200144081 A KR1020200144081 A KR 1020200144081A KR 20200144081 A KR20200144081 A KR 20200144081A KR 102322411 B1 KR102322411 B1 KR 102322411B1
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South Korea
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mold plate
laminate
carbon fiber
unit
central mold
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KR1020200144081A
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Korean (ko)
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강정석
기웅
권기철
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재단법인 한국탄소산업진흥원
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Priority to KR1020200144081A priority Critical patent/KR102322411B1/en
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    • 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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • 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
    • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
    • B29C43/32—Component parts, details or accessories; Auxiliary operations
    • B29C43/34—Feeding the material to the mould or the compression means
    • 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
    • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
    • B29C43/32—Component parts, details or accessories; Auxiliary operations
    • B29C43/56—Compression moulding under special conditions, e.g. 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
    • 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
    • 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
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • 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
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
    • 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
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • B29C70/386—Automated tape laying [ATL]
    • 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
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • B29C70/386—Automated tape laying [ATL]
    • B29C70/388—Tape placement heads, e.g. component parts, details or accessories
    • 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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/681—Component parts, details or accessories; Auxiliary operations
    • B29C70/683—Pretreatment of the preformed part, e.g. insert
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • 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
    • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
    • B29C43/32—Component parts, details or accessories; Auxiliary operations
    • B29C43/34—Feeding the material to the mould or the compression means
    • B29C2043/3433—Feeding the material to the mould or the compression means using dispensing heads, e.g. extruders, placed over or apart from the moulds

Abstract

The present invention comprises: a mold composed of a central mold plate, a peripheral mold plate to which the central mold plate is movably coupled in the vertical direction, a lifting drive part for moving the central mold plate in the vertical direction, and a film adsorbed in a vacuum on the upper surface of the lifting drive part, the central mold plate, and the peripheral mold plate; and an automatic fiber laminating machine composed of a supply unit for supplying carbon fiber tape, a head unit for laminating, cutting, heating, and pressing the supplied carbon fiber tape, and a robot unit for moving the head unit to a set position and forming a laminate by laminating the carbon fiber tape on the upper surface of the film. Even if the thickness of the laminate is gradually increased, the height of the upper part of the laminate with respect to the upper part of the peripheral mold plate is kept constant. Therefore, when a pressing part moves up along the edge of the laminate, damage to the edge of the laminate by collision with the pressing part is prevented.

Description

항공기 날개 끝단 복합재 구조물 제조장치{Aircraft Wing End Composite Structure Manufacturing Equipment}Aircraft Wing End Composite Structure Manufacturing Equipment

본 발명은 항공기 날개 끝단 복합재 구조물 제조장치에 관한 것이다.The present invention relates to an apparatus for manufacturing an aircraft wing tip composite structure.

도 1에 도시된 바와 같이, 일반적인 항공기 날개 끝단 복합재 구조물 제조장치는, 몰드판(21)과 자동섬유적층기로 구성된다. 자동섬유적층기는 헤드부(13)가 컷팅부(13a), 레이저부(13b), 가압롤러(13c)로 구성된다. As shown in FIG. 1, a typical aircraft wing tip composite structure manufacturing apparatus consists of a mold plate 21 and an automatic fiber laminator. In the automatic fiber laminating machine, the head part 13 is composed of a cutting part 13a, a laser part 13b, and a pressure roller 13c.

필름(22)은 실링재(ST)에 의해 몰드판(21)의 상면에 부착된다. 튜브(24)는 실링재(ST)를 한쪽을 통과하여, 필름(22)의 하면과 몰드판(21)의 상면 사이 공간 내 공기를 흡입하여 필름(22)을 몰드판(21)에 진공흡착시킨다. The film 22 is attached to the upper surface of the mold plate 21 by the sealing material ST. The tube 24 passes through one side of the sealing material ST and sucks air in the space between the lower surface of the film 22 and the upper surface of the mold plate 21 to vacuum the film 22 to the mold plate 21 . .

컷팅부(13a)는 필름(22) 위에 탄소섬유테이프(T)를 컷팅하여 올려놓는다. 레이저부(13b)는 탄소섬유테이프(T)에 레이저 빔(E1)을 조사하여 탄소섬유테이프(T)를 가열한다. 탄소섬유테이프(T) 내 수지 또는 바인더가 녹는다. 가열된 탄소섬유테이프를 가압롤러(13c)로 가압하여 적층물(TE)을 형성한다. 이를 반복하여, 몰드판(21) 위에 설정된 형상과 두께를 가진 항공기 날개 끝단 복합재 구조물을 만들어낸다. The cutting part 13a cuts and puts the carbon fiber tape T on the film 22 . The laser unit 13b heats the carbon fiber tape T by irradiating the laser beam E1 to the carbon fiber tape T. The resin or binder in the carbon fiber tape (T) is melted. A laminate TE is formed by pressing the heated carbon fiber tape with a pressure roller 13c. By repeating this, an aircraft wing tip composite structure having a shape and thickness set on the mold plate 21 is produced.

한편, 도 2에 도시된 바와 같이, 항공기 날개 끝단 복합재 구조물은 상당히 두꺼운 두께를 가진다.On the other hand, as shown in Figure 2, the aircraft wing tip composite structure has a fairly large thickness.

이렇게 두꺼운 항공기 날개 끝단 복합재 구조물을 만들기 위해, 점차 두꺼워지는 적층물(TE)을 가압롤러(13c)가 반복적으로 가압할 때, 가압롤러(13c)가 적층물(TE)의 모서리(edge)를 타고 적층물(TE)의 상면으로 올라간다.In order to make such a thick aircraft wing tip composite structure, when the pressure roller 13c repeatedly presses the gradually thickening laminate TE, the pressing roller 13c rides on the edge of the laminate TE. It rises to the upper surface of the laminate TE.

그러나, 적층물(TE)이 너무 두꺼워지면 가압롤러(13c)가 적층물의 모서리에 심하게 부딪친 후에 적층물(TE)의 상면으로 올라가게 된다. 이 경우, 적층물(TE)의 모서리가 심하게 손상된다.However, when the laminate TE becomes too thick, the pressure roller 13c comes up to the upper surface of the laminate TE after the pressing roller 13c hits the edge of the laminate. In this case, the edge of the laminate TE is severely damaged.

따라서, 항공기 날개 끝단 복합재 구조물 제조과정에서, 적층물의 모서리 부위가 손상되는 것을 방지할 수 있는 제조장치 개발이 필요하다.Therefore, it is necessary to develop a manufacturing device capable of preventing damage to the edge portion of the laminate during the manufacturing process of the aircraft wing tip composite structure.

한국공개특허(10-2019-0052414)Korean Patent Publication (10-2019-0052414)

본 발명의 목적은, 상술한 문제점을 해결할 수 있는 항공기 날개 끝단 복합재 구조물 제조장치를 제공하는 데 있다.It is an object of the present invention to provide an apparatus for manufacturing an aircraft wing tip composite structure capable of solving the above-described problems.

상기 목적을 달성하기 위한 항공기 날개 끝단 복합재 구조물 제조장치는, Aircraft wing tip composite structure manufacturing apparatus for achieving the above object,

중앙몰드판과, 상기 중앙몰드판이 상하방향으로 이동 가능하게 결합되는 주변몰드판과, 상기 중앙몰드판을 상하방향으로 이동시키는 승강구동부와, 상기 중앙몰드판과 상기 주변몰드판의 상면에 진공흡착된 필름으로 구성된 몰드; 및A central mold plate, a peripheral mold plate to which the central mold plate is movably coupled in the vertical direction, an elevating driving unit for moving the central mold plate in the vertical direction, and vacuum suction on the upper surfaces of the central mold plate and the peripheral mold plate a mold consisting of an old film; and

탄소섬유테이프를 공급하는 공급유닛과, 공급된 상기 탄소섬유테이프를 적층, 절단, 가열, 가압하는 헤드유닛과, 상기 헤드유닛을 설정된 위치로 이동시키는 로봇유닛으로 구성되어, 상기 필름의 상면에 상기 탄소섬유테이프를 적층하여 적층물을 형성하는 자동섬유적층기를 포함하는 것을 특징으로 한다.It consists of a supply unit for supplying a carbon fiber tape, a head unit for laminating, cutting, heating, and pressing the supplied carbon fiber tape, and a robot unit for moving the head unit to a set position, It is characterized in that it includes an automatic fiber laminator for forming a laminate by laminating carbon fiber tapes.

본 발명은, 항공기 날개 끝단 복합재 구조물을 만드는 동안, 중앙몰드판을 내려 점차 두꺼워지는 적층물을 하강시켜, 가압부가 적층물의 모서리를 타고 적층물의 상면으로 올라가는 높이를 일정하게 유지시킨다. 이로 인해, 적층물이 두꺼워져도 가압부와의 충돌에 의해 적층물의 모서리가 손상되지 않아, 항공기 날개 끝단 복합재 구조물의 품질을 향상시킬 수 있다.The present invention, while making the aircraft wing tip composite structure, by lowering the central mold plate to lower the gradually thickening laminate, the pressing part rides the edge of the laminate to maintain a constant height to the upper surface of the laminate. Due to this, even if the laminate is thickened, the edge of the laminate is not damaged by the collision with the pressing part, thereby improving the quality of the aircraft wing tip composite structure.

여기에 더하여, 본 발명은 헤드유닛의 레이저부가 복수 개의 단위 레이저로 구성된다. 한 개의 단위 레이저는 한 개의 탄소섬유테이프를 담당하여 가열한다. 이와 같은 레이저부를 구비함으로써, 일렬로 배치되어 절단된 탄소섬유테이프의 폭과 동일한 폭으로, 레이저 빔의 폭을 조절할 수 있어, 한 번 레이저 빔을 조사받은 탄소섬유테이프가 다시 레이저 빔을 받아 녹는 것이 방지된다. 따라서, 상술한 레이저부를 사용하여, 항공기 날개 끝단 복합재 구조물의 품질을 향상시킬 수 있다.In addition to this, in the present invention, the laser unit of the head unit is composed of a plurality of unit lasers. One unit laser is responsible for heating one carbon fiber tape. By having such a laser unit, it is possible to adjust the width of the laser beam to the same width as the width of the carbon fiber tapes arranged in a line and cut, so that the carbon fiber tape irradiated with the laser beam once is melted by receiving the laser beam again. is prevented Therefore, using the above-described laser unit, it is possible to improve the quality of the aircraft wing tip composite structure.

도 1은 일반적인 항공기 날개 끝단 복합재 구조물 제조장치를 나타낸 도면이다.
도 2는 도 1에 도시된 가압롤러가 항공기 날개 끝단 복합재 구조물 모서리에 부딪친 상태를 나타낸 도면이다.
도 3은 본 발명의 일 실시예에 따른 항공기 날개 끝단 복합재 구조물 제조장치를 나타낸 도면이다.
도 4는 도 3에 도시된 자동섬유적층기의 작동을 설명하기 위한 도면이다.
도 5는 도 4에 도시된 몰드의 동작상태도이다.
도 6은 도 4에 도시된 레이저부의 작동을 설명하기 위한 도면이다.1 is a view showing a typical aircraft wing tip composite structure manufacturing apparatus.
Figure 2 is a view showing a state in which the pressure roller shown in Figure 1 collided with the edge of the aircraft wing tip composite structure.
Figure 3 is a view showing an aircraft wing tip composite structure manufacturing apparatus according to an embodiment of the present invention.
4 is a view for explaining the operation of the automatic fiber laminating machine shown in FIG.
FIG. 5 is an operation state diagram of the mold shown in FIG. 4 .
6 is a view for explaining the operation of the laser unit shown in FIG.

이하, 본 발명의 일 실시예에 따른 항공기 날개 끝단 복합재 구조물 제조장치를 자세히 설명한다.Hereinafter, an apparatus for manufacturing an aircraft wing tip composite structure according to an embodiment of the present invention will be described in detail.

도 3에 도시된 바와 같이, 본 발명의 제1실시예에 따른 항공기 날개 끝단 복합재 구조물 제조장치는, 몰드(100), 자동섬유적층기(200)로 구성된다.As shown in FIG. 3 , the aircraft wing tip composite structure manufacturing apparatus according to the first embodiment of the present invention includes a mold 100 and an automatic fiber laminator 200 .

[몰드][Mold]

몰드(100)는 중앙몰드판(110), 주변몰드판(120), 승강구동부(미도시), 필름(140)으로 구성된다.The mold 100 is composed of a central mold plate 110 , a peripheral mold plate 120 , a lift driving unit (not shown), and a film 140 .

<중앙몰드판><Central mold plate>

중앙몰드판(110)은 세라믹이나 금속 재질로 만들어져 사각의 판 형상으로 형성된다. 중앙몰드판(110)은 주변몰드판(120)에 상하방향으로 이동 가능하게 결합된다. The central mold plate 110 is made of a ceramic or metal material and is formed in a rectangular plate shape. The central mold plate 110 is movably coupled to the peripheral mold plate 120 in the vertical direction.

중앙몰드판(110)의 주변몰드판(120)에 대한 상대위치는 탄소섬유테이프(T)가 적층되어 형성되는 적층물(TE)의 두께에 의해 조절된다.The relative position of the central mold plate 110 with respect to the peripheral mold plate 120 is controlled by the thickness of the laminate TE formed by laminating the carbon fiber tape T.

도 5에 도시된 바와 같이 중앙몰드판(110)은, 적층물(TE)의 두께가 두꺼워지더라도, 주변몰드판(120)의 상단부로부터 적층물(TE)의 상단부까지의 높이가 미리 결정된 기준높이와 항상 동일한 높이를 가지게 하강된다.As shown in FIG. 5 , the central mold plate 110 has a predetermined height from the upper end of the peripheral mold plate 120 to the upper end of the laminate TE, even if the thickness of the laminate TE is increased. It descends to always have the same height as its height.

여기서, 기준높이는 가압부(223)가 적층물(TE)의 모서리에 만났을 때 적층물(TE)의 모서리에 손상이 발생되지 않는 주변몰드판(120)의 상단부로부터 적층물(TE)의 상단부까지의 높이로써, 이러한 기준높이는 반복적인 실험에 의해 구해진다.Here, the reference height is from the upper end of the peripheral mold plate 120 that does not cause damage to the corner of the laminate TE to the upper end of the laminate TE when the pressing part 223 meets the edge of the laminate TE. As the height of , this reference height is obtained by repeated experiments.

중앙몰드판(110)의 내부에는 열선(미도시)이 내장된다. 열선(미도시)은 전기를 공급받아 열을 발생시켜, 중앙몰드판(110)을 가열한다. 이로 인해, 중앙몰드판(110) 위에 탄소섬유테이프(T)를 적층하기 전에, 중앙몰드판(110)을 미리 가열하여, 중앙몰드판(110)과 레이저부(222)에 의해 가열된 탄소섬유테이프(T)의 온도차를 줄인다. 따라서, 중앙몰드판(110)과 탄소섬유테이프(T)의 온도차로 인해, 항공기 날개 끝단 복합재 구조물 제조과정에서 구조물이 뒤틀리는 것이 방지된다.A heating wire (not shown) is built in the inside of the central mold plate 110 . The heating wire (not shown) receives electricity and generates heat to heat the central mold plate 110 . For this reason, before laminating the carbon fiber tape T on the central mold plate 110 , the central mold plate 110 is heated in advance, and the carbon fibers heated by the central mold plate 110 and the laser unit 222 . Reduce the temperature difference of the tape (T). Therefore, due to the temperature difference between the central mold plate 110 and the carbon fiber tape (T), it is prevented that the structure is distorted during the manufacturing process of the aircraft wing tip composite structure.

<주변몰드판><Around mold plate>

주변몰드판(120)은 세라믹이나 금속 재질로 만들어진다. 주변몰드판(120)의 중앙영역에는 중앙몰드판(110)이 삽입되는 절개공(111)이 형성된다. 중앙 영역에 형성된 절개공(111)에 의해 주변몰드판(120)은 위쪽에서 바라볼 경우 사각의 링 형상의 구조를 갖는다. The peripheral mold plate 120 is made of a ceramic or metal material. A cut-out hole 111 into which the central mold plate 110 is inserted is formed in the central region of the peripheral mold plate 120 . When viewed from above, the peripheral mold plate 120 has a rectangular ring-shaped structure due to the cut-out hole 111 formed in the central region.

<승강구동부><Elevation gate eastern part>

승강구동부(미도시)는 중앙몰드판(110)에 연결되어 중앙몰드판(110)을 상하방향으로 이동시킨다. 승강구동부는 중앙몰드판(110)에 결합되는 이동블록과, 이동블록에 연결되어 이동블록의 승강을 안내하는 승강가이드와, 이동블록에 연결되어 이동블록을 이동시키는 액츄에이터 등, 공지된 기술을 사용하여 다양하게 구성될 수 있다. The lifting driving unit (not shown) is connected to the central mold plate 110 to move the central mold plate 110 in the vertical direction. The elevating drive unit uses a known technology, such as a moving block coupled to the central mold plate 110, an elevating guide connected to the moving block to guide the elevating of the moving block, and an actuator connected to the moving block to move the moving block. Thus, it can be configured in various ways.

작업자는 승강구동부를 조작하여 중앙몰드판(110)을 상하방향으로 이동시킬 수 있다. 한편, 승강구동부의 조작은 자동으로 이루어질 수도 있다. 이 경우, 적층물(TE)을 찍는 카메라와, 카메라에서 전송된 영상에 보면서 적층물(TE)의 두께에 따라 중앙몰드판(110)을 하강시키는 제어부가 더 포함된다.The operator may move the central mold plate 110 in the vertical direction by manipulating the lift driving unit. On the other hand, the operation of the lift driving unit may be made automatically. In this case, a control unit for lowering the central mold plate 110 according to the thickness of the laminate TE while viewing the image transmitted from the camera and the image transmitted from the camera is further included.

<필름><Film>

필름(140)은 중앙몰드판(110)과 주변몰드판(120)의 상면을 덮는다. 필름(140)은 수지가 녹는 온도 350℃ 이상에서 견딜 수 있는, 폴리이미드, 테프론 등으로 만들어진다. 필름(140)은 실링재(ST)에 의해 주변몰드판(120)의 상면에 부착된다. 실링재(ST)는 필름(140)의 테두리를 따라 위치된다. The film 140 covers the upper surfaces of the central mold plate 110 and the peripheral mold plate 120 . The film 140 is made of polyimide, Teflon, etc., which can withstand a temperature of 350° C. or higher at which the resin melts. The film 140 is attached to the upper surface of the peripheral mold plate 120 by the sealing material ST. The sealing material ST is positioned along the edge of the film 140 .

[자동섬유적층기][Automatic Fiber Laminator]

도 3에 도시된 바와 같이, 자동섬유적층기(200)는 공급유닛(210), 헤드유닛(220), 로봇유닛(230)으로 구성된다.As shown in FIG. 3 , the automatic fiber laminator 200 includes a supply unit 210 , a head unit 220 , and a robot unit 230 .

<공급유닛><Supply unit>

공급유닛(210)은 탄소섬유테이프(T)를 적재하고 헤드유닛(220)으로 공급한다. 공급유닛(210)은 프레임, 커버, 보빈, 모터, 전원, 전선 등으로 구성되며, 이 밖에도 공급유닛(210)은 공지된 기술을 사용하여 다양한 구성이 가능하다.The supply unit 210 loads the carbon fiber tape (T) and supplies it to the head unit 220 . The supply unit 210 is composed of a frame, a cover, a bobbin, a motor, a power source, a wire, and the like. In addition, the supply unit 210 can be configured in various ways using known techniques.

탄소섬유테이프(T)의 종류로, 열가소성 탄소섬유테이프, 드라이(dry) 탄소섬유테이프, 열경화성 탄소섬유테이프가 있다.As a kind of carbon fiber tape (T), there are a thermoplastic carbon fiber tape, a dry carbon fiber tape, and a thermosetting carbon fiber tape.

열가소성 탄소섬유테이프는 탄소섬유와 일방향 열가소성수지로 구성된다. 열가소성수지는 탄소섬유 사이로 함침된다. 열가소성수지로 PPS, PEI, PEEK, PEKK 등이 사용된다.Thermoplastic carbon fiber tape is composed of carbon fiber and unidirectional thermoplastic resin. The thermoplastic resin is impregnated between the carbon fibers. PPS, PEI, PEEK, PEKK, etc. are used as thermoplastic resins.

드라이 탄소섬유 테이프는 바인더가 3% 이내 함유된 일방향 탄소섬유로 구성된다. Dry carbon fiber tape is composed of unidirectional carbon fiber containing less than 3% binder.

열경화성 탄소섬유테이프는 일방향 탄소섬유와 열경화성수지로 구성된다. 열경화성 수지는 탄소섬유 사이로 함침된다. 열경화성 수지로 페놀수지, 에폭시 수지 등이 사용된다.Thermosetting carbon fiber tape is composed of unidirectional carbon fiber and thermosetting resin. The thermosetting resin is impregnated between the carbon fibers. Phenolic resins, epoxy resins, etc. are used as thermosetting resins.

탄소섬유테이프(T)는 폭이 작은 탄소섬유테이프(T)가 사용되며, 복수 개가 나란히 공급되어 절단된다. 본 실시예에서는 폭이 6.35mm인 탄소섬유테이프(T)가 사용되며, 최대 16개가 나란히 공급될 수 있다. 몰드(100) 위에 절단되어 놓이는 탄소섬유테이프(T)의 개수는 만들고자 하는 항공기 날개 끝단 복합재 구조물의 형상과 두께에 따라 달라진다. A carbon fiber tape (T) having a small width is used as the carbon fiber tape (T), and a plurality of them are supplied side by side and cut. In this embodiment, a carbon fiber tape (T) having a width of 6.35 mm is used, and a maximum of 16 pieces can be supplied side by side. The number of carbon fiber tapes (T) cut and placed on the mold 100 varies depending on the shape and thickness of the aircraft wing tip composite structure to be made.

<헤드유닛><Head unit>

헤드유닛(220)은 몰드(100) 위에서 탄소섬유테이프(T)를 절단하고 가열하고 가압하여 적층하는 것을 반복한다. 그러면 몰드(100) 위에 설정된 형상과 두께의 항공기 날개 끝단 복합재 구조물이 만들어진다. 도 4에 도시된 바와 같이, 헤드유닛(220)은 절단부(221), 레이저부(222), 가압부(223)로 구성된다.The head unit 220 cuts the carbon fiber tape T on the mold 100 and repeats the lamination by heating and pressing. Then, the aircraft wing tip composite structure of the shape and thickness set on the mold 100 is made. As shown in FIG. 4 , the head unit 220 includes a cutting unit 221 , a laser unit 222 , and a pressing unit 223 .

절단부cut

절단부(221)는 공급유닛(210)으로부터 공급받은 탄소섬유테이프(T)를 절단하여 몰드(100) 위에 올려놓는다. 절단부(221)는 프레임, 커버, 칼날, 모터, 링크, 전원, 전선 등으로 구성되며, 이 밖에도 절단부(221)는 공지된 기술을 사용하여 다양한 구성이 가능하다.The cutting part 221 cuts the carbon fiber tape T supplied from the supply unit 210 and puts it on the mold 100 . The cutting unit 221 is composed of a frame, a cover, a blade, a motor, a link, a power source, an electric wire, and the like. In addition, the cutting unit 221 can be configured in various ways using known techniques.

레이저부laser part

도 6에 도시된 바와 같이, 레이저부(222)는 복수 개로 단위 레이저(222a)로 구성된다. 복수 개의 단위 레이저(222a)는 일렬로 배치되어 절단된 탄소섬유테이프(T)에, 레이저 빔(E1)을 조사한다. 그러면, 절단된 탄소섬유테이프(T)가 가열되어, 탄소섬유테이프(T) 내 수지가 녹는다. 본 실시예에서는 6.35mm 폭의 탄소섬유테이프(T)가 최대 16개 공급 가능하므로, 레이저부는 16개의 단위 레이저(222a)가 일렬로 배치된다.As shown in FIG. 6 , the laser unit 222 is composed of a plurality of unit lasers 222a. A plurality of unit lasers 222a are arranged in a line and irradiate a laser beam E1 to the cut carbon fiber tape T. Then, the cut carbon fiber tape (T) is heated, and the resin in the carbon fiber tape (T) is melted. In this embodiment, since a maximum of 16 carbon fiber tapes T of 6.35 mm width can be supplied, 16 laser unit lasers 222a are arranged in a line in the laser unit.

한 개의 단위 레이저(222a)는 한 개의 탄소섬유테이프(T)에 레이저 빔(E1)을 조사한다. 한 개의 단위 레이저(222a)가 방출하는 레이저 빔(E1)의 폭은 한 개의 탄소섬유테이프(T)의 폭에 대응하도록 형성된다. 따라서, 한 개의 단위 레이저(222a)는 한 개의 탄소섬유테이프(T)를 담당하여 가열하게 된다. One unit laser 222a irradiates a laser beam E1 on one carbon fiber tape T. The width of the laser beam E1 emitted by one unit laser 222a is formed to correspond to the width of one carbon fiber tape T. Accordingly, one unit laser 222a is responsible for heating one carbon fiber tape T.

복수 개의 단위 레이저(222a)는 전체가 일률적으로 작동되는 것이 아니고 각각 개별적으로 제어된다. 따라서, 레이저 빔(E1)을 조사하는 단위 레이저(222a)의 개수를 조절하여 조사되는 레이저 빔(E1)의 폭을 조절할 수 있다. 도 6에 도시된 바와 같이, 공급되는 탄소섬유테이프(T)의 전체 폭이 복수 개의 단위 레이저(222a)의 전체 폭보다 작은 경우, 탄소섬유테이프(T)의 폭 위치에 대응하는 단위 레이저(222a)만을 작동시켜 레이저 빔(E1)을 조사할 수 있다. The plurality of unit lasers 222a are not all operated uniformly, but are individually controlled. Accordingly, the width of the irradiated laser beam E1 may be adjusted by adjusting the number of unit lasers 222a irradiating the laser beam E1. 6, when the total width of the supplied carbon fiber tape (T) is smaller than the total width of the plurality of unit lasers (222a), the unit laser (222a) corresponding to the width position of the carbon fiber tape (T). ) can be operated to irradiate the laser beam E1.

레이저부(222)는 프레임, 커버, 레이저발생장치, 전원, 전선, 케이블베어 등으로 구성되며, 이 밖에도 레이저부(222)는 공지된 기술을 사용하여 다양한 구성이 가능하다. 이와 같은 레이저부(222)를 구비함으로써, 일렬로 배치되어 절단된 탄소섬유테이프의 폭과 동일한 폭으로, 레이저 빔의 폭을 조절할 수 있어, 한 번 레이저 빔을 조사받은 탄소섬유테이프가 다시 레이저 빔을 받아 녹는 것이 방지된다. 이로 인해, 탄소섬유 강화 열가소성 복합재의 품질이 향상된다.The laser unit 222 is composed of a frame, a cover, a laser generator, a power source, a wire, a cable bear, and the like. In addition, the laser unit 222 can be configured in various ways using known techniques. By having such a laser unit 222, it is possible to adjust the width of the laser beam to the same width as the width of the carbon fiber tape that is arranged and cut in a line, so that the carbon fiber tape irradiated with the laser beam once becomes a laser beam again. to prevent melting. Due to this, the quality of the carbon fiber reinforced thermoplastic composite is improved.

가압부pressurized part

가압부(223)는 가열된 탄소섬유테이프(T)를 가압한다. 가압부(223)는 프레임, 커버, 롤러, 모터, 전원, 전선 등으로 구성되며, 이 밖에도 가압부(223)는 공지된 기술을 사용하여 다양한 구성이 가능하다.The pressing unit 223 presses the heated carbon fiber tape (T). The pressing unit 223 is composed of a frame, a cover, a roller, a motor, a power source, an electric wire, and the like. In addition, the pressing unit 223 can be configured in various ways using known techniques.

탄소섬유테이프(T)에 대한 절단부(221)의 절단과 레이저부(222)의 가열 및 가압부(223)의 가압이 반복적으로 이루어져 도 5에 도시된 바와 같은 소정 두께를 가지는 적층물(TE)이 형성된다.A laminate (TE) having a predetermined thickness as shown in FIG. 5 by repeatedly cutting the cutting part 221 for the carbon fiber tape (T), heating the laser part 222, and pressing the pressing part 223 this is formed

<로봇유닛><Robot Unit>

로봇유닛(230)은 헤드유닛(220)을 몰드(100) 위의 설정된 위치로 이동시킨다. 로봇유닛(230) 프레임, 커버, 모터, 링크, 전원, 전선, 케이블베어 등으로 구성되며, 이 밖에도 로봇유닛(230)은 공지된 기술을 사용하여 다양한 구성이 가능하다.The robot unit 230 moves the head unit 220 to a set position on the mold 100 . The robot unit 230 is composed of a frame, a cover, a motor, a link, a power supply, an electric wire, a cable bear, and the like.

100: 몰드 110: 중앙몰드판
120: 주변몰드판 140: 필름
200: 자동섬유적층기 210: 공급유닛
220: 헤드유닛 221: 절단부
222: 레이저부 223: 가압부
230: 로봇유닛 E1: 레이저 빔
T: 탄소섬유테이프 TE: 적층물100: mold 110: central mold plate
120: surrounding mold plate 140: film
200: automatic fiber laminating machine 210: supply unit
220: head unit 221: cut
222: laser unit 223: pressurized unit
230: robot unit E1: laser beam
T: Carbon fiber tape TE: Laminate

Claims (3)

중앙몰드판과, 상기 중앙몰드판이 상하방향으로 이동 가능하게 결합되는 주변몰드판과, 상기 중앙몰드판을 상하방향으로 이동시키는 승강구동부와, 상기 중앙몰드판과 상기 주변몰드판의 상면에 진공흡착된 필름으로 구성된 몰드; 및
탄소섬유테이프를 공급하는 공급유닛과, 공급된 상기 탄소섬유테이프를 적층, 절단, 가열, 가압하는 헤드유닛과, 상기 헤드유닛을 설정된 위치로 이동시키는 로봇유닛으로 구성되어, 상기 필름의 상면에 상기 탄소섬유테이프를 적층하여 적층물을 형성하는 자동섬유적층기를 포함하며,
상기 헤드유닛은,
상기 주변몰드판에 먼저 접촉하고 일정 거리 활주한 후, 상기 중앙몰드판 위에 적층된 상기 적층물의 모서리를 타고 올라가, 상기 적층물을 가압하는 롤러를 포함하며,
상기 승강구동부는,
상기 주변몰드판의 상단부로부터 상기 적층물의 상단부까지의 높이가,
상기 롤러가 상기 중앙몰드판 위에 적층된 상기 적층물의 모서리를 만났을 때, 상기 롤러가 상기 적층물의 모서리를 손상시키지 않고, 상기 적층물의 상단부로 타고 올라갈 수 있는 높이인 기준높이에 도달하면,
상기 중앙몰드판에 적층된 적층물의 두께가 점점 두꺼워지더라도, 상기 주변몰드판의 상단부로부터 상기 적층물의 상단부까지의 높이를 상기 기준높이로, 상기 중앙몰드판을 하강시켜 맞추는 것을 특징으로 하는 자동섬유적층기를 포함하는 것을 특징으로 하는 항공기 날개 끝단 복합재 구조물 제조장치.A central mold plate, a peripheral mold plate to which the central mold plate is movably coupled in the vertical direction, an elevating driving unit for moving the central mold plate in the vertical direction, and vacuum suction on the upper surfaces of the central mold plate and the peripheral mold plate a mold consisting of an old film; and
It consists of a supply unit for supplying a carbon fiber tape, a head unit for laminating, cutting, heating, and pressing the supplied carbon fiber tape, and a robot unit for moving the head unit to a set position, It includes an automatic fiber laminator that laminates carbon fiber tapes to form a laminate,
The head unit is
After first contacting the peripheral mold plate and sliding for a certain distance, it climbs up the edge of the laminate laminated on the central mold plate, and includes a roller for pressing the laminate,
The elevating drive unit,
The height from the upper end of the peripheral mold plate to the upper end of the laminate is,
When the roller meets the edge of the laminate stacked on the central mold plate, the roller reaches the reference height, which is a height that can ride up to the upper end of the stack without damaging the edge of the stack,
Automatic fiber, characterized in that even if the thickness of the laminate laminated on the central mold plate becomes thicker, the height from the upper end of the peripheral mold plate to the upper end of the laminate is the reference height, and the central mold plate is lowered to fit Aircraft wing tip composite structure manufacturing apparatus comprising a laminator. 삭제delete 삭제delete
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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH05162155A (en) * 1991-12-11 1993-06-29 Ikeda Bussan Co Ltd Molding method and mold of inner trimming material
JP2014172287A (en) * 2013-03-08 2014-09-22 Apic Yamada Corp Resin molding mold, resin molding apparatus, resin molding method and method of evaluating resin molding mold
KR20190052414A (en) 2017-11-08 2019-05-16 재단법인 한국탄소융합기술원 Method for manufacturing light aircraft integrated horizontal stabilizer
KR20200050479A (en) * 2018-10-30 2020-05-12 재단법인 한국탄소융합기술원 Apparatus and method for manufacturing thermoplastic reinforced panel of aircraft
KR102144682B1 (en) * 2019-11-27 2020-08-18 재단법인 한국탄소융합기술원 Automated fiber placement machine and thermoplastic reinforced panel of aircraft made by the same

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH05162155A (en) * 1991-12-11 1993-06-29 Ikeda Bussan Co Ltd Molding method and mold of inner trimming material
JP2014172287A (en) * 2013-03-08 2014-09-22 Apic Yamada Corp Resin molding mold, resin molding apparatus, resin molding method and method of evaluating resin molding mold
KR20190052414A (en) 2017-11-08 2019-05-16 재단법인 한국탄소융합기술원 Method for manufacturing light aircraft integrated horizontal stabilizer
KR20200050479A (en) * 2018-10-30 2020-05-12 재단법인 한국탄소융합기술원 Apparatus and method for manufacturing thermoplastic reinforced panel of aircraft
KR102144682B1 (en) * 2019-11-27 2020-08-18 재단법인 한국탄소융합기술원 Automated fiber placement machine and thermoplastic reinforced panel of aircraft made by the same

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