JP2004017370A - Manufacturing method for composite panel for airplane, and apparatus therefor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a method for efficiently manufacturing a composite panel for an airplane by laminating a wide prepreg, a narrow prepreg or the like in individual areas and also cutting them in separate areas in order to realize the high speed lamination of the prepregs and performing the feed of the prepregs by hanging-up aerial feed, and an apparatus therefor. <P>SOLUTION: A release film is closely brought into contact with a planar table 4 and a planar laminate having a large area is formed by the four-axial control of the wide prepreg 5 of an unidirectional material and/or a cross material on the film. The narrow prepreg 13 is laminated on the film in the same way on another table 12 and the formation of a lattice-like laminate is performed parallelly and, next, the large area laminate and the lattice like laminate are floated along with the release film by blowing off air from the areas under the respective tables. Thereafter, the laminates are aerially fed to be placed on one cutting table 9 and cut into a required shape to form a skin part and a doubler part laminate successively. Both of them are hung up from the cutting table in a curtain state and aerially fed to be placed and laminated on the lamination fixture 22 of a single contour surface to form the composite panel. <P>COPYRIGHT: (C)2004,JPO

Description

[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to a method and an apparatus for manufacturing a composite material panel made of CFRP or the like used as a panel for an aircraft fuselage or wing, or a rocket fuselage or fairing.
[0002]
[Prior art]
BACKGROUND ART Conventionally, composite panels made of CFRP or the like have been used instead of metal panels on outer wall surfaces of various parts such as a fuselage and wings in order to reduce the weight of aircraft. In order to manufacture this composite material panel, a prepreg automatic laminating machine (commonly known as ATL) for directly laminating a prepreg directly on a lamination type having an upper surface as a contour surface has been developed and used.
This automatic prepreg laminator has the function of laminating unidirectional prepregs of 3 or 6 inches in width under NC control. However, since lamination can always be performed only in units of narrow widths, lamination of large areas and lamination of thick plates takes time. And it was inefficient.
[0003]
In addition, the recently developed fiber placement device (commonly known as FPM) is capable of laminating prepregs on a laminated type having a complicated contour surface, and is capable of simultaneously laminating dozens of narrow prepregs having a width of 3 to 10 mm. Although the feature is that the prepreg width is too small for many minutes, the lamination time per unit area is much longer than that of the automatic prepreg laminating machine, and the efficiency is very low.
[0004]
And in any of the above, the method of directly laminating the prepreg on the lamination mold is because the lamination mold is constrained by the automatic lamination of the prepreg, so other work cannot be performed on the mold during the automatic lamination of the prepreg, and the production rate of the panel is high. Did not go to production.
[0005]
In addition, in order to enable prepreg lamination to a lamination type having a three-dimensional contour surface in any of the above, since the lamination head has a 10-axis control function having all functions and a function of cutting the prepreg, The lamination head was very heavy, and the entire apparatus was large.
[0006]
Furthermore, the cutting function of the prepreg can only cut linearly, so that it cannot cope with fine shape cutting.
[0007]
Furthermore, in order to perform prepreg lamination on a lamination type having a complicated contour surface, very high computing power is required to control the lamination head, and the control takes a long time. Thus, efficient prepreg lamination could not be performed.
[0008]
[Problems to be solved by the invention]
Therefore, the present invention disassembles the functions of the conventional all-in-one type prepreg automatic laminating machine and operates them as individual functions to realize high-speed lamination of prepregs. Lamination, and furthermore, scattered planar lamination of narrow prepregs is performed in individual areas, and the shape of the prepreg laminate obtained by performing these is sequentially performed in another area. In a separate area, and the transfer of the prepreg laminate from each planar stacking area to the cutting area and the transfer of the prepreg laminate from the cutting area to the stacking jig are lifted and transported in the air, thereby being efficient. To provide a method and an apparatus capable of producing an aircraft composite panel by a simple prepreg lamination. It is.
[0009]
[Means for Solving the Problems]
One of the manufacturing methods of the aircraft composite panel of the present invention for solving the above-mentioned problem is that a release film is brought into close contact with a flat laminated table by vacuum suction, and then a one-way material or And / or laminating a wide prepreg of the cloth material by four-axis control to form a large-area prepreg laminated body, and releasing the release film after closely adhering the release film to another planar lamination table by vacuum suction. A unidirectional material and / or a cross material of narrow width prepreg slit to various widths on the film are plane-laminated at required intervals in the vertical and horizontal directions by four-axis control to form a grid-like prepreg laminate. The formation was performed in parallel, and then a large-area prepreg laminate and a grid-like prepreg laminate were blown out from under each of the planar lamination tables, and were floated together with the release film. , Sequentially slide-mounted in the air, placed on one cutting table, fixed by vacuum suction, cut into the required size and shape, and successively laminated skin part prepreg laminate, doubler prepreg laminate Then, the skin prepreg laminate and the doubler prepreg laminate are sequentially lifted in the form of a curtain from a cutting table, conveyed in the air, placed on a laminating jig having a single contour surface, laminated, and laminated. It is characterized by the following.
[0010]
In this method of manufacturing a composite panel for an aircraft, the prepreg laminate of the skin portion placed on the laminating jig having a single contour surface is lifted from the cutting table, and the release film is vacuum-sucked to the cutting table. The doubler prepreg laminate to be laminated on the skin prepreg laminate placed on the laminating jig of the single contour surface is lifted from the cutting table, transported in the air and laminated, when releasing the release film It is necessary to take a method of lifting the entire product, transporting it in the air, laminating the release film on the skin prepreg laminate, and then removing the release film.
[0011]
Another one of the manufacturing methods of the aircraft composite panel of the present invention is that, after a release film is closely adhered to a flat laminated table by vacuum evacuation, a one-way material and / or a cloth material is formed on the release film. A wide prepreg is laminated on a plane by four-axis control with a gap to form a prepreg laminate having an intermittent large area, and a release film is adhered to another planar lamination table by evacuation and then released. A unidirectional material and / or a cross material of narrow width prepreg slit to various widths on the film are plane-laminated at required intervals in the vertical and horizontal directions by four-axis control to form a grid-like prepreg laminate. After the forming is performed in parallel, and then the intermittent large-area prepreg laminate and the lattice-like prepreg laminate are blown out from under each of the planar lamination tables and floated together with the release film. Sequentially transported in the air in a sliding manner, placed on one cutting table, fixed by vacuum suction, cut into the required size and shape, and successively interrupted skin prepreg laminate, doubler prepreg laminate Was formed, and then the intermittent skin portion prepreg laminate was lifted in a curtain form from the cutting table, transported in the air, placed on a double-contour surface laminating jig, and the intermittent skin portion prepreg laminate was spread on the double contour surface. A wide prepreg is additionally laminated in the gap of the intermittent skin prepreg laminate, and then the doubler prepreg laminate is lifted in the form of a curtain from a cutting table on the skin prepreg laminate having no gap, and is transported in the air and placed. And laminated to form a composite panel.
[0012]
In this method for manufacturing a composite panel for an aircraft, the intermittent skin portion prepreg laminate placed on the laminating jig having the double contour surface, and a wide prepreg added to the gap of the intermittent skin portion prepreg laminate, and after the lamination, there is no gap When the doubler prepreg laminated body to be laminated on the skin prepreg laminated body is lifted from one cutting table and transported in the air, and placed and laminated on the laminating jig, it is lifted together with the release film and transported in the air. It is necessary to take a method of placing and laminating each with the mold film facing up, and then removing the release film.
[0013]
Another one of the manufacturing methods of the aircraft composite panel of the present invention is that a release film is adhered to a flat laminated table by vacuum suction, and then a one-way material and / or a cloth material is placed on the release film. A wide prepreg is planarly laminated by four-axis control to form a large-area prepreg laminate, and a release film is adhered to another planar lamination table by vacuum suction. Forming a lattice-shaped prepreg laminate by laminating narrow prepregs of unidirectional material or / and cloth material slit to dimensions at required intervals in the vertical and horizontal directions by four-axis control; After the release film is brought into close contact with another planar lamination table by vacuum suction, the unidirectional material and the cross material narrow prepreg are manually loaded at a plurality of required positions or four-axis control on the release film. More planar lamination, forming a scattered prepreg laminate in parallel, and then a large area prepreg laminate, a grid-like prepreg laminate and a scattered prepreg laminate under each planar laminate table After the air is blown out of the mold and the release film is floated together, the film is successively transported in the air in a sliding manner, placed on one cutting table, fixed by vacuum suction, and cut into required dimensions and shapes. A prepreg laminated body, a doubler prepreg laminated body and a locally reinforced prepreg laminated body are sequentially formed, and then these are sequentially lifted in a curtain form from a cutting table, transported in the air, and placed on a laminating jig having a single contour surface. And laminated to form a composite panel.
[0014]
In this method of manufacturing a composite panel for an aircraft, the prepreg laminate of the skin portion placed on the laminating jig having a single contour surface is lifted from the cutting table, and the release film is vacuum-sucked to the cutting table. A doubler prepreg laminate to be laminated on the skin prepreg laminate on the laminating jig and a local reinforcing prepreg laminate to be laminated on the doubler laminate are lifted from the cutting table and transported in the air. At the time of lamination, the release film is lifted together with the release film, transported in the air, and the release film is removed, and the release film is removed each time the laminate is laminated on the skin prepreg laminate and the doubler prepreg laminate. is necessary.
[0015]
Still another one of the manufacturing methods of the aircraft composite panel of the present invention is that a release film is brought into close contact with a flat laminated table by vacuum suction, and then a one-way material and / or a cloth material is placed on the release film. The wide prepregs are planarly laminated with a gap by four-axis control to form an intermittent large-area prepreg laminate, and the release film is closely adhered to another planar lamination table by evacuation, and then separated. Laminate prepregs are made by laminating unidirectional materials and / or cloth materials of narrow width prepreg slitted to various widths on a mold film at required intervals in the vertical and horizontal directions by 4-axis control. And, after adhering the release film to another flat laminated table by vacuum suction, a plurality of narrow prepregs of one-way material and / or cloth material are formed on the release film. The lamination is performed in parallel at a required position by manual loading or four-axis control to form a dotted prepreg laminate, and then an intermittent large-area prepreg laminate, a grid-like prepreg laminate, and a dotted prepreg. After air is blown out from under each of the planar laminating tables and the release film is lifted together with the release film, the laminated bodies are sequentially conveyed in the air, placed on one cutting table, fixed by vacuum suction, and fixed to the required dimensions, It is cut into a shape to form an intermittent skin prepreg laminate, a doubler prepreg laminate, and a locally reinforced prepreg laminate, and then the intermittent skin prepreg laminate is lifted from a cutting table and transported in the air to form a double contour. On the double-sided surface of the intermittent skin prepreg laminate, and A wide prepreg is additionally laminated between layers, and then a doubler prepreg laminate and a locally reinforced prepreg laminate are successively lifted in a curtain form from a cutting table on the skin prepreg laminate having no gap, and then transported in the air and placed. Thus, a composite panel is formed.
[0016]
In this method of manufacturing a composite panel for an aircraft, the intermittent skin portion prepreg laminate to be placed on the laminating jig having the double contour surface, and a wide prepreg added to the gap between the intermittent skin portion prepreg laminate, and after the lamination, there is no gap. The doubler prepreg laminate laminated on the skin prepreg laminate and the locally reinforced prepreg laminate laminated on the doubler prepreg laminate are each lifted from one cutting table, transported in the air, and placed on the laminating jig. When placing and laminating, it is necessary to take a method in which the release film is lifted and transported in the air, placed and laminated with the release film facing upward, and then the release film is removed.
[0017]
The aircraft composite panel manufacturing apparatus of the present invention for carrying out each of the above-described manufacturing methods is provided with a unidirectional member and / or a cross over a planar laminating table provided with a large number of small holes for vacuum suction and air blowing on the upper surface. A wide prepreg laminating apparatus equipped with an automatic laminating machine having a four-axis control laminating head for planarly laminating a wide prepreg of materials, and another flat laminating table also having a number of small holes for vacuum suction and air blowing on the upper surface. Prepreg laminating device equipped with an automatic laminating machine having a 4-axis control laminating head for laminating narrow prepregs of one-way material and / or cloth material in a grid pattern, and vacuum suction and air blowing on the upper surface as well. Either a narrow width prepreg is provided with a template for detecting a hand-laden position above another flat lamination table provided with a number of small holes, or a narrow prepreg is planarly laminated. A prepreg interspersed laminating apparatus provided with an automatic laminating machine having an axis-controlled laminating head, and the wide prepreg laminating apparatus, the narrow prepreg laminating apparatus, and the prepreg interspersed laminating apparatus are provided at positions surrounded by three sides and vacuum is provided on the upper surface. A prepreg laminate cutting device provided with an automatic cutting machine above a cutting table provided with a number of small holes for suction and air blowing, and a single prepreg provided at a position facing the prepreg dotted laminating device so as to sandwich the prepreg laminate cutting device. A prepreg laminate having a contour surface or a double contour surface, a prepreg laminate, a wide prepreg laminating apparatus, a narrow prepreg laminating apparatus, a prepreg interspersed laminating apparatus, and a prepreg laminated body cutting apparatus. Transport device for aerial transport to the prepreg, the prepreg laminate cutting device and the prepreg And traffic the laminate stacking jig those comprising more hanger with crane for air conveying lifting the prepreg laminate like a curtain.
[0018]
In this aircraft composite panel manufacturing apparatus, the narrow prepreg laminating apparatus includes a plurality of prepreg cassettes accommodating the narrow prepregs of various widths to be attached to and detached from the laminating head of the automatic laminating machine. Is preferred.
[0019]
BEST MODE FOR CARRYING OUT THE INVENTION
An embodiment of a method and apparatus for manufacturing a composite panel for aircraft according to the present invention will be described with reference to the drawings. First, an apparatus for performing a method for manufacturing a composite panel for an aircraft will be described with reference to FIGS. 1 to 3. 1 is a wide prepreg laminating apparatus, and the wide prepreg laminating apparatus 1 has a small hole for vacuum suction and air blowing on the upper surface. 2, a 10 m wide, 15 m long flat laminated table 4 provided with an air supply / discharge space 3 at the bottom and a wide prepreg of unidirectional material and / or cloth material provided above the table, having a width dimension exceeding 1 m. And an automatic laminating machine 7 having a four-axis control laminating head 6 for laminating 5 in a plane. Reference numeral 8 denotes a prepreg laminate cutting device provided adjacent to the wide prepreg laminating device 1. The prepreg laminate cutting device 8 has a large number of small holes 2 for vacuum suction and air blowing on an upper surface, and an air supply / discharge space 3 at a lower portion. And a cutting table 9 having a width of 10 m and a length of 15 m, and an automatic cutting machine 10 provided thereabove. Reference numeral 11 denotes a narrow prepreg laminating device provided adjacent to the prepreg laminate cutting device 8. The narrow prepreg laminating device 11 has a plurality of small holes 2 for vacuum suction and air blowing on the upper surface and air supply / discharge at the lower portion. A flat laminating table 12 having a width of 10 m and a length of 15 m provided with the space 3 and a narrow prepreg tape 13 of one material and / or a cloth material having a width of 1 to 20 cm provided above the flat laminating table 13 are laminated in a grid pattern. An automatic laminating machine 15 having a laminating head 14 of four-axis control. The thin prepreg laminating apparatus 11 is equipped with a plurality of prepreg cassettes 16 each containing a narrow prepreg tape 13 of one material or cloth material slit to various widths. It can be replaced. Reference numeral 17 denotes a prepreg interspersed laminating device provided adjacent to the prepreg laminate cutting device 8 in a direction perpendicular to the direction of the wide prepreg laminating device 1 and the narrow prepreg laminating device 11. One example is a plane laminating table 18 having a width of 10 m and a length of 15 m provided with a large number of small holes 2 for vacuum suction and air blowing on the upper surface and an air supply / discharge space 3 at the lower part, and a narrow width prepreg manual loading position provided thereabove. It comprises a detection template 19. Another example of the prepreg interspersed laminating apparatus 17 is a 4-axis system in which narrow prepregs of 10 to 20 mm unidirectional material or cloth material are interspersed and plane-stacked on a plane stacking table 18 as shown in FIG. An automatic laminating machine 21 having a controlled laminating head 20 is provided. 1 to 3, reference numeral 22 denotes a prepreg laminate stacking jig provided at a position facing the prepreg interspersed stacking device 17 with the prepreg laminate cut device 8 interposed therebetween. The top surface has a single contour surface 23 as shown in FIG. 3 and the double contour surface 24 as shown in FIG. In FIG. 1 to FIG. 3, reference numeral 25 denotes the prepreg laminate cutting device 8 and the prepreg laminate laminate jig 22, and the prepreg laminate cut by the prepreg laminate cutting device 8 is lifted in a curtain shape to form a prepreg laminate. This is a crane with a hanger 26 that conveys to the body stacking jig 22 in the air. Reference numerals 27 and 27 'denote slide-type transfer devices for transferring the prepreg laminate from the wide prepreg lamination device 1 and the narrow prepreg lamination device 11 to the prepreg laminate cutting device 8. As shown in FIGS. 6 and 7, the slide-type transfer devices 27 and 27 'are moved from the rails 28 and 28' at both ends of the flat stacking tables 4 and 12 of the stacking devices 1 and 11 to both sides of the cutting table of the cutting device 8. Traveling devices 30, 30 'traveling on end rails 29 are provided with openable and closable chucks 31 for gripping both side ends of the release film F arranged on the flat laminated tables 4, 12.
[0020]
The plurality of prepreg cassettes 16 provided in the narrow prepreg laminating apparatus 11 in the aircraft composite panel manufacturing apparatus having the above-described configuration are provided with a feeding roll 33 and a winding roll 34 in a case 32 as shown in FIG. 8, for example. For example, as shown in FIG. 9, as shown in FIG. 9, a narrow prepreg tape 13 having a width of 1 to 20 cm and a narrow prepreg tape 35 having a 45 ° direction and a narrow prepreg 36 having a 0 ° direction are wound around a feeding roll 33. The prepreg cassette 16 is wound around together with one end of a roll-up paper 37 and fixed to a winding roll 34. The prepreg cassette 16 is appropriately replaced with the lamination head 14 shown in FIGS. At the time of shifting by 14-axis control, the feeding roll 33 is rotated and the narrow prepreg tape 13 is fed. It is to be laminated.
[0021]
Next, various embodiments of a method for manufacturing an aircraft composite panel by the manufacturing apparatus of the embodiment configured as described above will be described. In the embodiment of the method for manufacturing a single-contour composite panel used for a body panel in which an opening such as a window is not formed, the prepreg interspersing device 17 of the manufacturing apparatus is not used, and the prepreg laminate stacking jig 22 has an upper surface. However, as shown in FIG. 3, a single contour surface 23 is used. Hereinafter, the steps of the present manufacturing method will be described. As shown in FIG. 2, a release film F is placed on a plane laminating table 4 of the wide prepreg laminating apparatus 1 and vacuum-suctioned from a small hole 2 opened on the upper surface through a lower air supply / discharge space 3 so that the release film F is flat. After being brought into close contact with the laminating table 4, on the release film F, as shown in FIG. , And a large area prepreg laminate P ₁ To form In parallel with this, the release film F is placed on the planar laminating table 12 of the narrow prepreg laminating apparatus 11 as shown in FIG. 2, and vacuum suction is performed from the small hole 2 opened on the upper surface through the lower air supply / discharge space 3, After the release film F is brought into close contact with the planar laminating table 12, on the release film F, for example, as shown in FIG. Is fed from a prepreg cassette 16 mounted on a lamination head 14 of an automatic laminator 15 of a 4-axis control, and is planarly laminated at required intervals in the vertical and horizontal directions to form a lattice-shaped prepreg laminate P. ₂ To form Next, the large-area prepreg laminate P ₁ Air is blown out from the small holes 2 of the planar laminating table 4 to float the release film F together, and then the release film F is attached to the chuck 31 provided in the traveling device 30 of the slide-type transfer device 27 shown in FIGS. Of the prepreg laminate P on the cutting table 9 of the cutting device 8 by sliding the traveling device 30 along the rails 28 and 29 and slidingly transporting the traveling device 30 to the adjacent prepreg laminate cutting device 8. ₁ After the chuck 31 is separated from the release film F, the vacuum is sucked through the small air hole 2 opened on the upper surface of the cutting table 9 through the lower air supply / discharge space 3, and the release film F and the large area are removed. Prepreg laminate P ₁ On the cutting table 9. Thereafter, the laminate is cut by the automatic cutting machine 10 into the required size and shape as shown in FIG. 10 to form the skin prepreg laminate S. Next, while the release film F on the cutting table 9 is vacuum-sucked, one end of the skin portion prepreg laminate S is gripped by the hanger 26 of the crane 25 and peeled off from the release film F as shown in FIG. Hang it in a curtain. Then, the crane 25 is moved in the perpendicular direction to transport the skin prepreg laminate S in the air to the prepreg laminate stacking jig 22 having the upper surface of the single contour surface 23, and the prepreg stack S is transferred onto the single contour surface 23 of the stacking jig 22 in FIG. Hang and place as shown. Next, the lattice-shaped prepreg laminate P ₂ Is blown out from the small holes 2 of the plane laminating table 12 to float the release film F together, and then released to the chuck 31 provided in the traveling device 30 'of the slide-type transfer device 27' shown in FIGS. The film F is gripped on both side edges, and the traveling device 30 'is run on rails 28' and 29 to be conveyed in the air to the adjacent prepreg laminate cutting device 8 in a sliding manner, and the prepreg is placed on the cutting table 9 of the cutting device 8. Laminate P ₂ After the chuck 31 is separated from the release film F, vacuum suction is performed from the small hole 2 opened on the upper surface of the cutting table 9 through the lower air supply / discharge space 3, and the release film F and the release film F are arranged in a grid. Prepreg laminate P ₂ On the cutting table 9. Thereafter, the laminate is cut by the automatic cutting machine 10 into a required size and shape to form a doubler portion prepreg laminate D which reinforces a mounting portion such as a stringer in the fuselage panel as shown in FIG. Next, the doubler prepreg laminate D is blown out from the small holes 2 of the cutting table 9 to float the whole of the release film F. Then, as shown in FIG. And lift it up in a curtain shape as in FIG. Then, the crane 25 is caused to travel in the perpendicular direction to transport the doubler prepreg laminate D to the prepreg laminate stacking jig 22 in the air, and the skin prepreg stack previously placed on the single contour surface 23 of the stacking jig 22. The doubler prepreg laminate D is suspended and placed on the body S with the release film F facing upward, laminated, and then the release film F is peeled off and removed, as shown in FIG. A composite panel P1 having a single contour shape for a panel is produced.
[0022]
In the embodiment of the manufacturing method of the double contour-shaped composite material panel used for the wing panel and the fuselage panel, the prepreg interspersing device 17 of the manufacturing apparatus is not used, and the prepreg laminate jig 22 has an upper surface shown in FIG. As described above, the double contour surface 24 is used. Hereinafter, the steps of the present manufacturing method will be described. As shown in FIG. 2, the release film F was placed on the flat laminating table 4 of the wide prepreg laminating apparatus 1, and the release film F was brought into close contact with the flat laminating table 4 by vacuum suction from the small hole 2 opened on the upper surface. Thereafter, as shown in FIG. 15, a wide prepreg 5 having a width of 1 m of the one-way material and the cloth material is planarly laminated on the release film F by a laminating head 6 of an automatic laminating machine 7 of four-axis control. , Intermittent large area prepreg laminate P ₁ '. In parallel with this, in the narrow prepreg laminating apparatus 11, as in the previous embodiment, as shown in FIGS. ₂ To form Next, the intermittent large-area prepreg laminate P ₁ ′ Is blown out from the small holes 2 of the planar laminating table 4 to float the release film F together with the release film F. Then, the release film is attached to the chuck 31 provided in the traveling device 30 of the slide-type transfer device 27 shown in FIGS. F is gripped at both ends, and the traveling device 30 is run on the rails 28 and 29 to be conveyed in the air to the adjacent prepreg laminate cutting device 8 in a sliding manner, and the prepreg having an intermittent large area is placed on the cutting table 9 of the cutting device 8. Laminate P ₁ ′ Is lowered, the chuck 31 is separated from the release film F, and vacuum suction is performed through the small hole 2 opened on the upper surface of the cutting table 9. ₁ 'On the cutting table 9. Thereafter, the sheet is cut by the automatic cutting machine 10 into the required size and shape as shown in FIG. 16 to form the intermittent skin portion prepreg laminate S '. Next, air is blown out from the small holes 2 of the cutting table 9 to float the intermittent skin portion prepreg laminate S 'together with the release film F, and then the hanger 26 of the crane 25 grips one end of the release film F. It is hung in the shape of a curtain in the same manner as 11. Then, the crane 25 is run in the perpendicular direction to transport the intermittent skin portion prepreg laminate S ′ in the air to the prepreg laminate stacking jig 22 having the double contour surface 24 on the upper surface, and onto the double contour surface 24 of the stacking jig 22. As shown in FIG. 17, it is hung down and placed with the release film F facing upward. Next, the release film F is peeled off as shown in FIG. 18 and the intermittent skin portion prepreg laminate S 'is shifted to fit the double contour surface 24, and the gap between the intermittent skin portion prepreg laminate S' is drawn. As shown in FIG. 19, the wide prepreg 5 is additionally laminated by hand to form a skin prepreg laminate S having no gap as shown in FIG. During this time, the lattice-shaped prepreg laminate P ₂ Is slidably transported in the air to the adjacent prepreg laminate cutting device 8 in the same procedure as in the above-described embodiment, and is placed on the cutting table 9 so that it has the required dimensions and shape. The automatic cutting machine 10 cuts and forms a doubler prepreg laminate D serving as a reinforcing structure of a mounting portion such as a stringer in a wing panel or a fuselage panel as in FIG. Next, the doubler portion prepreg laminate D is transported in the air to the prepreg laminate laminate jig 22 in the same procedure as in the above-described embodiment, and is first placed on the double contour surface 24 of the laminate jig 22. On the formed skin portion prepreg laminate S, the doubler portion prepreg laminate D was suspended and placed with the release film F facing upward, laminated, and then the release film F was peeled off and removed as shown in FIG. As shown in (1), a double contour composite panel P2 used for the wing panel and the fuselage panel is produced.
[0023]
In the embodiment of the method of manufacturing a single contour composite panel used for a body panel for forming an opening such as a window, the prepreg dotted apparatus 17 of the manufacturing apparatus uses the one provided with the automatic laminating machine 21 shown in FIG. The prepreg laminate jig 22 has an upper surface having a single contour surface 23. Hereinafter, the steps of the present manufacturing method will be described. In the wide prepreg laminating apparatus 1 and the narrow prepreg laminating apparatus 11, the prepreg laminate P having a large area is formed in the same manner as in the above-described method of manufacturing a single contour composite panel. ₁ And lattice-shaped prepreg laminate P ₂ Are formed in parallel. At the same time, the prepreg dotted device 17 ₃ To form 22. That is, the release film F is placed on the planar laminating table 18 of the prepreg dotted device 17 as shown in FIG. Is brought into close contact with the planar laminating table 18, and on the release film F, a narrow prepreg 13 ′ of a unidirectional material or a cloth material having a width of 10 to 20 mm is moved by the laminating head 20 of an automatic controller 21 of four-axis control. The prepreg laminated body P which is scattered at a required position, ₃ To form Next, a large-area prepreg laminate P ₁ And lattice-shaped prepreg laminate P ₂ Were sequentially cut into required dimensions and shapes by a prepreg laminate cutting device 8 in the same manner as in the above-described method for producing a single contour composite panel, thereby forming a skin prepreg laminate S and a doubler prepreg laminate D. Thereafter, these are sequentially placed and laminated on the single contour surface 23 of the prepreg laminated body laminating jig 22. Thereafter, the dotted prepreg laminate P ₃ Is blown out from the small holes 2 of the planar laminating table 18 to float the release film F together, and is manually conveyed to the prepreg laminate cutting device 8 in the air, and the dotted prepreg laminate P is placed on the cutting table 9 of the cutting device 8. ₃ And put it down. Then, vacuum suction is performed through the small holes 2 of the cutting table 9, and the prepreg laminate P interspersed with the release film F ₃ Is closely adhered to a cutting table 9 and is cut by an automatic cutting machine 10 so as to have a required size and shape, and as shown in FIG. 23, a locally reinforced prepreg laminate for reinforcing openings such as windows in a fuselage panel. Form body G. Next, the local reinforcing prepreg laminate G is blown out from the small holes 2 of the cutting table 9 to float the release film F together, and then the hanger 26 of the crane 25 grips one end of the release film F to form a curtain. Hang up. Then, the crane 25 is caused to travel on the prepreg laminate stacking jig 22 to transport the locally reinforced prepreg laminate G in the air, and the skin prepreg laminates S, which are previously placed and stacked on the single contour surface 23 of the stacking jig 22, On the doubler portion prepreg laminate D, the locally reinforcing prepreg laminate G is suspended and placed with the release film F facing upward, laminated, and then the release film F is peeled off and removed, as shown in FIG. As shown, a single contour-shaped composite panel P3 for a fuselage panel for forming an opening such as a window is produced.
[0024]
In the embodiment of the manufacturing method of the double contour composite panel used for the wing panel having the reinforcing portion for mounting the equipment, the prepreg dotted device 17 of the manufacturing apparatus includes the template 19 for detecting the narrow-width prepreg stacking position. A prepreg laminate jig 22 having an upper surface with a double contour surface is used. Hereinafter, the steps of the present manufacturing method will be described. In the wide prepreg laminating apparatus 1 and the narrow prepreg laminating apparatus 11, the prepreg laminate P having the intermittent large area is formed in the same manner as the method of manufacturing the double contour-shaped composite panel described above. ₁ 'And lattice-like prepreg laminate P ₂ Are formed in parallel. At the same time, the prepreg dotted device 17 ₃ '. That is, the release film F is placed on the planar laminating table 18 of the prepreg spotting device 17 in the same manner as in FIG. 20, and vacuum suction is performed through the small holes 2 opened on the upper surface to bring the releasing film F into close contact with the planar laminating table 18. After that, the narrow-width prepreg 13 ′ of a unidirectional material or a cloth material having a width of 10 to 20 mm is detected on the release film F by a manual-loading position detecting template 19 shown in FIGS. Then, the prepreg laminated body P shown in FIG. ₃ '. Next, an intermittent large-area prepreg laminate P ₁ ′, Lattice-like prepreg laminate P ₂ Are sequentially cut into required dimensions and shapes by the prepreg laminate cutting device 8 in the same manner as in the above-described method of manufacturing the double contour composite panel, and the intermittent skin prepreg laminate S ′ and the doubler prepreg laminate D are cut. To form Then, the intermittent skin portion prepreg laminate S ′ is transported in the air to the prepreg laminate stacking jig 22 in the same manner as in the above-described manufacturing method, and is suspended on the double contour surface 24 of the stacking jig 22 as in FIG. After being placed and peeling off the release film F, the intermittent skin portion prepreg laminate S ′ was adjusted to the double contour surface 24 while being shifted in the same manner as in FIG. The wide prepreg 5 is additionally stacked in the gap by hand as in FIG. 19 to form the skin prepreg laminate S without gap as in FIG. Next, the doubler portion prepreg laminate D is transported in the air to the prepreg laminate laminate jig 22 in the same manner as in the above-described manufacturing method, and the skin portion formed by being first placed on the double contour surface 24 of the laminate jig 22. The doubler prepreg laminate D is suspended and placed on the prepreg laminate S with the release film F facing upward, laminated, and then the release film F is peeled off and removed. Next, the dotted prepreg laminate P ₃ ′ Is transported in the air to the prepreg laminate cutting device 8, and the prepreg laminate P is scattered with the release film F on the cutting table 9 of the cutting device 8. ₃ ′ And hang it down. Then, vacuum suction is performed through the small holes 9 of the cutting table 9, and the prepreg laminate P interspersed with the release film F is provided. ₃ ′ Is brought into close contact with a cutting table 9 and then cut by an automatic cutting machine 10 into a required size and shape, and as shown in FIG. 26, a locally reinforced prepreg laminate which serves as reinforcement for mounting equipment on a wing panel. G ′ is formed. Next, the locally reinforced prepreg laminate G 'is transported in the air in the same manner as in the above-described manufacturing method, and the skin prepreg laminate S and the doubler portion previously placed and laminated on the double contour 24 surface of the prepreg laminate lamination jig 22. On the prepreg laminate D, the locally reinforced prepreg laminate G 'is suspended and placed with the release film F facing upward, laminated, and then the release film F is peeled off and removed, as shown in FIG. Then, a composite panel P4 having a double contour shape for a wing panel having a reinforcing portion for mounting equipment is manufactured.
[0025]
【The invention's effect】
As can be seen from the above description, the method of manufacturing an aircraft composite panel of the present invention separately performs large-area skin prepreg lamination, doubler prepreg lamination, and local reinforcement prepreg lamination, thereby simplifying the lamination of each part. Can be fast. In addition, since each prepreg laminate obtained thereby is cut into required shapes and dimensions individually, each prepreg laminate can be precisely cut precisely. Furthermore, since the required composite panel is produced by collectively laminating the cut and formed prepreg laminates, it is possible to efficiently and easily obtain a highly accurate composite panel. In addition, since the transport of each prepreg laminate to the cutting area and the transport from the cutting area to the collective lamination area are performed by air, each prepreg laminate can be transported safely and quickly without deformation or damage, The connection of each process is performed smoothly, and the production of a composite panel by high-speed lamination can be realized.
[0026]
Further, according to the aircraft composite panel manufacturing apparatus of the present invention, the above-described excellent composite panel manufacturing method can be performed easily, reliably, and efficiently. In addition, the present manufacturing apparatus is a simple, lightweight and inexpensive apparatus for individually configuring a laminating apparatus, a cutting apparatus, a laminating jig, and a transporting apparatus for each prepreg laminated body. It is possible to operate at a higher speed than a large-scale apparatus such as the above, and each apparatus can be used continuously without being idle, so that the production rate of the composite panel can be increased.
[Brief description of the drawings]
FIG. 1 is a schematic plan view of an aircraft composite panel manufacturing apparatus of the present invention.
FIG. 2 is a sectional view taken along line AA of FIG.
FIG. 3 is a perspective view of FIG. 1;
FIG. 4 is a plan view showing another example of the prepreg interspersed laminating apparatus in the manufacturing apparatus of FIG. 1;
FIG. 5 is a perspective view showing another example of a prepreg laminate stacking jig in the manufacturing apparatus of FIG.
FIG. 6 is a schematic perspective view showing a slide-type transfer device for moving the prepreg stack in the air in a sliding manner by moving between the wide prepreg stacking device, the narrow prepreg stacking device, and the prepreg stack cutting device in the manufacturing apparatus of FIG. It is.
FIG. 7 is an enlarged perspective view of a portion B in FIG. 6;
FIG. 8 is a vertical sectional side view showing a prepreg cassette provided in the narrow prepreg laminating apparatus in the manufacturing apparatus of FIG. 1;
FIG. 9 is a perspective view showing a prepreg tape and roll-up paper housed in a prepreg cassette of FIG. 8;
FIG. 10 is a perspective view showing a skin prepreg laminate obtained by cutting a large-area prepreg laminate with a prepreg laminate cutting device.
FIG. 11 is a side view showing a state where the skin portion prepreg laminate is lifted and transported in the air.
FIG. 12 is a perspective view showing a state where a skin portion prepreg laminate is placed on a prepreg laminate laminate jig having a single contour surface in the manufacturing apparatus of FIG. 1;
FIG. 13 is a perspective view showing a doubler prepreg laminate obtained by laminating a lattice-like prepreg laminate obtained by laminating with a narrow width prepreg laminating apparatus, placing the prepreg laminate in a prepreg laminate cutting apparatus in the air, and cutting it. It is.
14 is a perspective view showing a state where a double contour prepreg laminate of FIG. 13 is laminated on the skin prepreg laminate of FIG. 12 to form a single contour composite panel.
FIG. 15 is a perspective view showing a state in which a prepreg laminate having an intermittent large area is formed by a wide prepreg laminating apparatus in the manufacturing apparatus of FIG. 1;
16 is a perspective view showing an intermittent skin portion prepreg laminate obtained by cutting the intermittent large-area prepreg laminate of FIG. 15 with a prepreg laminate cutting device.
17 is a perspective view showing a state where the intermittent skin portion prepreg laminate of FIG. 16 is placed on a prepreg laminate laminate jig having a double contour surface.
FIG. 18 is a perspective view showing a state in which the intermittent skin portion prepreg laminate of FIG. 17 is adapted to a double contour surface.
19 is a perspective view showing a state in which a wide prepreg is additionally laminated in a gap of the intermittent skin portion prepreg laminate of FIG. 18;
FIG. 20 is a perspective view showing a skin prepreg laminate having no gap obtained by additionally laminating the wide prepreg of FIG. 19;
21 is a perspective view showing a state in which a double contour-shaped composite material panel is formed by laminating a doubler prepreg laminate on the skin prepreg laminate having no gap shown in FIG. 20;
FIG. 22 is a perspective view showing a state where a dotted prepreg laminate is formed by the prepreg dotted laminated device of FIG. 4;
23 is a perspective view showing a locally reinforced prepreg laminate obtained by cutting the dotted prepreg laminate of FIG. 22 with a prepreg laminate cutting device.
24 is a diagram showing a single contour shape obtained by laminating the local reinforcing prepreg laminate of FIG. 23 on a skin prepreg laminate and a doubler prepreg laminate which are placed and laminated on a prepreg laminate laminate jig having a single contour surface. It is a perspective view which shows the state which made the composite material panel of FIG.
FIG. 25 is a perspective view showing a state in which a dotted prepreg laminate is formed by the prepreg dotted laminated device in the manufacturing apparatus of FIG. 1;
26 is a perspective view showing a locally reinforced prepreg laminate obtained by cutting the dotted prepreg laminate of FIG. 25 with a prepreg laminate cutting device.
FIG. 27 is a diagram showing a double-contour prepreg laminate obtained by laminating the local reinforcement prepreg laminate of FIG. 26 on a skin prepreg laminate and a doubler prepreg laminate placed on a prepreg laminate laminate jig having a double contour surface. It is a perspective view showing the state where a composite material panel was made.
[Explanation of symbols]
1 Wide prepreg laminating equipment
2 small holes
3 Air supply and exhaust space
4 plane lamination table
5 Wide prepreg
6 Laminated head
7 Automatic laminating machine
8 Pre-preg laminate cutting machine
9 Cutting table
10 Automatic cutting machine
11 Narrow width prepreg laminating device
12 plane lamination table
13 Narrow width prepreg tape
14 Laminated head
15 Automatic laminating machine
16 prepreg cassette
17 Pre-preg dotted laminating equipment
18 plane lamination table
19 Narrow prepreg hand-loading position detection template
20 Laminated head
21 Automatic laminating machine
22 Pre-preg laminate jig
23 Single contour surface
24 Double contour surface
25 crane
26 Hanger
27, 27 'Sliding transfer device
28, 28 ', 29 rails
30,30 'traveling device
31 chuck
32 Case of prepreg cassette
33 Feeding roll
34 Entrainment roll
35 45 ° narrow width prepreg
360 ° Width Pre-preg
37 rolled paper
F Release film
P ₁ Large area prepreg laminate
P ₁ ′ Intermittent large area prepreg laminate
P ₂ Lattice prepreg laminate
P ₃ Dotted prepreg laminate
P ₃ ′ Dotted prepreg laminate
S Skin prepreg laminate
S 'Intermittent skin prepreg laminate
D Doubler prepreg laminate
G, G 'Locally reinforced prepreg laminate
P1 Single contour composite panel for fuselage panel
P2 Double contour composite panel used for wing panel and fuselage panel
P3 Single contour composite panel for fuselage panel making opening
P4 Double contour composite material for wing panel with reinforcement for equipment installation
Flannel

Claims (10)

After the release film is brought into close contact with the flat lamination table by vacuum suction, wide prepregs of a unidirectional material and / or a cross material are planarly laminated on the release film by four-axis control to form a large-area prepreg laminate. After forming and releasing the release film into close contact with another planar laminated table by vacuum suction, a narrow prepreg of one-way material or / and cloth material slit to various width dimensions on the release film is formed. By laminating planes at required intervals in the vertical and horizontal directions by four-axis control, forming a lattice-shaped prepreg laminate in parallel, then a large-area prepreg laminate and a lattice-shaped prepreg laminate After air is blown out from the bottom of each flat laminated table to float the release film together with the release film, it is sequentially transported in the air in a sliding manner and placed on one cutting table, and vacuum suction is performed. After being cut and fixed to the required size and shape, a skin prepreg laminate and a doubler prepreg laminate are sequentially formed, and then the skin prepreg laminate and the doubler prepreg laminate are successively cut. A composite panel for an aircraft, wherein the composite panel is lifted in the form of a curtain from above, transported in the air, placed on a laminating jig having a single contour surface, and laminated to form a composite panel. In the method for manufacturing an aircraft composite material panel according to claim 1, the release film is vacuum-sucked to the cutting table when the skin prepreg laminate placed on the single-contour surface laminating jig is lifted from the cutting table. Take the method of peeling from the release film as it is, and doubler prepreg laminate to be laminated on skin prepreg laminate placed on laminating jig with single contour surface, lifted from cutting table and transported in the air and laminated Manufacturing a composite panel for an aircraft, wherein a method of lifting the release film together with the release film, transporting the release film upward, stacking the release film on the skin prepreg laminate, and then removing the release film is adopted. Method. After the release film is brought into close contact with the flat lamination table by vacuum evacuation, wide prepregs of one-way material and / or cloth material are planarly laminated on the release film by 4-axis control with a gap, and the intermittent large area After forming a prepreg laminate of above, a release film is brought into close contact with another planar lamination table by evacuation, and then a one-way material and / or a cross material slit into various width dimensions on the release film Are laminated in parallel in the vertical and horizontal directions at required intervals by four-axis control to form a grid-like prepreg laminate, and then a prepreg laminate having an intermittent large area. After air is blown out from under each of the planar laminating tables and the release film is lifted together with the release film, the lattice-shaped prepreg laminated body is sequentially conveyed in the air in a sliding manner onto one cutting table. After being fixed by vacuum suction, it is cut into the required size and shape to form an intermittent skin prepreg laminate and a doubler prepreg laminate, and then the intermittent skin prepreg laminate is cut from the cutting table. It is lifted in the shape of a curtain, transported in the air, placed on a double-contour surface lamination jig, and the intermittent skin prepreg laminate is applied to the double contour surface, and a wide prepreg is added to the gap between the intermittent skin prepreg laminates The double prepreg laminate is then lifted in a curtain form from a cutting table, transported in the air, placed on the skin prepreg laminate without gaps, and then laminated to form a composite panel. Of manufacturing composite aircraft panels. The method for manufacturing a composite panel for an aircraft according to claim 3, wherein an intermittent skin portion prepreg laminate placed on a laminating jig having a double contour surface, and a wide prepreg additionally laminated in a gap between the intermittent skin portion prepreg laminate. After that, the doubler prepreg laminate to be laminated on the skin prepreg laminate having no gap is lifted from one cutting table, transported in the air, and then placed and laminated on the lamination jig. A method for manufacturing a composite panel for an aircraft, comprising a method of transporting, placing and laminating each with a release film on top, and then removing the release film. After the release film is brought into close contact with the flat lamination table by vacuum suction, wide prepregs of a unidirectional material and / or a cross material are planarly laminated on the release film by four-axis control to form a large-area prepreg laminate. After forming and releasing the release film into close contact with another planar laminated table by vacuum suction, a narrow prepreg of one-way material or / and cloth material slit to various width dimensions on the release film is formed. By laminating planes at required intervals in the vertical and horizontal directions by four-axis control to form a lattice-like prepreg laminate, and further releasing the release film on another planar lamination table by vacuum suction. Thereafter, on the release film, narrow prepregs of one-way material and / or cloth material are manually stacked at a plurality of required positions or planarly laminated by four-axis control to form a dotted prepreg laminate. Was performed in parallel, and then a large-area prepreg laminate, a grid-like prepreg laminate, and a scattered prepreg laminate were blown with air from under each of the planar lamination tables to float together with the release film. After that, they are successively transported in the air in a sliding manner, placed on one cutting table, fixed by vacuum suction, cut into required dimensions and shapes, and sequentially laminated with a skin portion prepreg laminate and a doubler prepreg laminate. And a locally reinforced prepreg laminate, which are then sequentially lifted in a curtain form from a cutting table, transported in the air, placed on a single-contour surface laminating jig, and laminated to form a composite panel. A method for manufacturing a composite panel for an aircraft. In the method for manufacturing an aircraft composite panel according to claim 5, when the skin prepreg laminate placed on the single-contour surface lamination jig is lifted from the cutting table, the release film is vacuum-sucked to the cutting table. Take a method of peeling from the release film as it is, the doubler prepreg laminate to be laminated on the skin prepreg laminate on the lamination jig and the local reinforcing prepreg laminate to be laminated on the doubler laminate, the cutting table A method of lifting the release film together with the release film, lifting the release film upward, and removing the release film each time the layers are laminated on the skin prepreg laminate and the doubler prepreg laminate, respectively. A method for manufacturing a composite panel for an aircraft, comprising: After the release film is brought into close contact with the flat lamination table by vacuum suction, wide prepregs of one-way material and / or cloth material are planarly laminated on the release film with 4-axis control with a gap, and intermittent large area After forming a prepreg laminate of above, and after adhering a release film to another planar lamination table by vacuum evacuation, a one-way material and / or a cross material slit into various width dimensions on the release film Are laminated in a vertical and horizontal direction at required intervals by four-axis control to form a lattice-shaped prepreg laminate, and the release film is vacuum-evacuated on another planar laminate table. After being brought into close contact with each other by suction, narrow prepregs of one-way material and / or cloth material are manually stacked or planar-stacked at a plurality of required positions on the release film by scattered prepregs. The formation of the layered body is performed in parallel, and then the intermittent large-area prepreg laminated body, the lattice-shaped prepreg laminated body, and the dotted prepreg laminated body are blown out from under each of the plane laminated tables and separated. After being floated together with the mold film, it is sequentially conveyed in the air, placed on one cutting table, fixed by vacuum suction, cut into a required size and shape, and successively, the intermittent skin portion prepreg laminate, A doubler prepreg laminate and a locally reinforced prepreg laminate are formed, and then the intermittent skin prepreg laminate is lifted in a curtain form from a cutting table, transported in the air, and placed on a double-contour laminating jig. After the prepreg laminate is applied to the double contour surface, a wide prepreg is additionally laminated in the gap of the intermittent skin prepreg laminate, and then there is no gap Aircraft characterized in that a doubler prepreg laminate and a locally reinforced prepreg laminate are successively lifted in a curtain form from a cutting table, transported in the air, placed on the skin prepreg laminate, and laminated to form a composite panel. Method of manufacturing composite panels. The method for manufacturing a composite panel for an aircraft according to claim 7, wherein the intermittent skin portion prepreg laminate to be placed on the laminating jig having the double contour surface, and a wide prepreg additionally laminated in a gap between the intermittent skin portion prepreg laminate. Thereafter, the doubler prepreg laminate laminated on the skin prepreg laminate having no gap and the locally reinforced prepreg laminate laminated on the doubler prepreg laminate are lifted from one cutting table and transported in the air, respectively, to be stacked and cured. A method of lifting and laminating the release film together with the release film, transporting it in the air, placing and releasing the release film upward, and then removing the release film. A method of manufacturing a composite panel. An automatic laminating machine having a 4-axis control laminating head for planarly laminating a wide prepreg of a unidirectional material and / or a cloth material above a planar laminating table provided with a number of small holes for vacuum suction and air blowing on an upper surface. Four-axis control for laminating a narrow prepreg of one-way material and / or cloth material in a grid pattern above a prepreg laminating apparatus and another planar laminating table also provided with a number of small holes for vacuum suction and air blowing on the upper surface. Narrow prepreg laminating apparatus equipped with an automatic laminating machine having a laminating head and a template for detecting a narrow prepreg hand-loading position above another flat laminating table also provided with a number of small holes for vacuum suction and air blowing on the upper surface. Or a prepreg interspersed laminating apparatus having an automatic laminating machine having a 4-axis control laminating head for laminating a narrow prepreg in a plane. An automatic cutting machine is provided above a cutting table provided at a position surrounded by three sides by a wide prepreg laminating apparatus, a narrow prepreg laminating apparatus and a prepreg dotted laminating apparatus and provided with a large number of small holes for vacuum suction and air blowing on the upper surface. A prepreg laminate cutting device, a prepreg laminate laminate jig having a single contour surface or a double contour surface provided at a position facing the prepreg interspersed lamination device so as to sandwich the prepreg laminate cutting device, and the wide prepreg lamination device. , A narrow-width prepreg laminating apparatus, a slide-type transport apparatus for transporting a prepreg laminated body in the air in a sliding manner between a prepreg-scattered laminating apparatus and a prepreg-laminated-sheet cutting apparatus, The prepreg laminate is lifted in the shape of a curtain by going back and forth with the jig and transported in the air. More comprising manufacturing apparatus for aircraft composite panel hanger with crane for. The apparatus for manufacturing an aircraft composite panel according to claim 9, wherein the narrow-width prepreg laminating apparatus includes a plurality of prepreg cassettes accommodating thin-width prepregs of various widths detachably attached to a laminating head of the automatic laminating machine. An aircraft composite panel manufacturing apparatus, comprising:

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