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    • 专利摘要:
    summary patent of invention: "method and device to transport, place and compact composite reinforcers". the present invention relates to a device for compacting an elongated contoured composite tray that includes the first and second flexible sections of fiber-reinforced resin, flexible along their lengths. the first section is flexible within the foreground and the second section is flexible within the foreground as well as the background.
    公开号:BR112014002045B1
    申请号:R112014002045-0
    申请日:2012-07-06
    公开日:2020-03-31
    发明作者:Samuel R. Stewart；Paul J. Ballow
    申请人:The Boeing Company；
    IPC主号:
    专利说明:

    Descriptive Report of the Patent for Invention for COMPACTOR FOR USE IN THE MANUFACTURE OF A CONTROLLED ELONGED COMPOSITE STRUCTURE AND METHOD OF USING A COMPACTOR.
    INFORMATION FROM THE PREVIOUS TECHNIQUE
    Technical Field [001] The present invention generally relates to composite manufacturing structures and is more particularly a method and device for transporting, placing and compacting bypassed composite reinforcers.
    Background [002] During the manufacture of contoured composite reinforcers such as stringers, a compactor can be used to compact a stringer tray against the surfaces of the tool. In some cases, the surfaces of the tool can be contoured along one or more planes. Compactors have been developed in such a way that they are flexible along a simple plane of curvature, consequently in that the stringer is contoured in more than one plane, the tool surfaces have relatively complex geometries that require the compaction process to be carried out with the hand. When laying the contoured composite stringers by hand, grooves may form in the laminate layers that come together at various points on the tray and undesired fiber distortion may occur. Using the techniques of manually laying, the location of layer creases and layer assembly is difficult to control, thus introducing variations in the finished part, which can affect the performance of the part. Also, the human factor involved in manual laying can introduce variations in the process that lead to unwanted inconsistencies in the finished parts.
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    2/24 [003] Consequently, there is a need for a method and device for compacting contoured composite reinforcers such as stringers that can consistently and predictably distribute creases and layering in a way that improves part quality and / or performance. There is also a need for a compactor device that can be used to transport the stringers to a curing tool and that conforms to the curvatures of the stringer compound during stringer placement and compaction.
    SUMMARY [004] The reported embodiments provide a method and device for transporting, placing and compacting composite reinforcers, such as stringer, which are contoured in more than one plane. The compactor places and compresses the stringer trays in a curing tool in a way that regulates and standardizes the distribution of creases in the layer and / or layer assembly. The reported compaction device is flexible in multiplanes and conforms to the contours of the stringer despite the undulations in the geometry of the stringer. The predictable crease / layer assembly allows engineering changes to be made to the stringer design that compensate for crease / layer assembly, thereby improving part quality and / or performance.
    [005] According to a reported embodiment, a compactor is provided for use in the manufacture of an elongated, contoured composite structure. The compactor comprises at least one first flexible section along its length within a foreground and at least a second section coupled with the first section and flexible along its length within the foreground and within a second plane. The first and second planes are generally orthogonal to each other. Each of the first and second
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    3/24 tions includes a generally planar cover portion and a cover portion adapted to be received within a cavity in the composite structure. The lid portion includes a plurality of reinforcement strips extending transversely across the width of the lid portion and spaced along the length. The lid portion also includes a plurality of flexible rubber joints along its length that allows the second section to flex within the second plane. The cover portion includes a plurality of slits that extend transversely there substantially in line with the flexible rubber gaskets.
    [006] According to another embodiment, a device is provided for transporting and compacting a controlled composite cover reinforcement tray having a cavity there. The device comprises a cover portion adapted to be placed within the cavity and a generally planar cover portion coupled with the cover and flexible portion within a foreground generally parallel to the cover portion. The cover portion and the cover portion are each flexible in a background generally orthogonal to the foreground. The lid portion includes laminated layers of flexible material and substantially rigid reinforcement strips. The flexible material can comprise a rubber.
    [007] According to another embodiment, a method of using a compactor to manufacture a composite reinforcer is provided. The method comprises forming a composite reinforcement tray and bringing the compactor into contact with the tray. The reinforcement tray is attached to the compactor and the compactor is used to transport and place the reinforcement tray on a surface. The reinforcement tray is compacted against the surface by the compactor. The adhesion of the reinforcement tray to the compactor includes a generation of vacuum inside the compactor, and the use of vacuum for
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    4/24 suction of the reinforcement tray against the compactor. The suction of the reinforcement tray against the compactor includes the generation of a suction force by stretching the air through the sides of the compactor in contact with the tray. Using the compactor to place the reinforcement tray includes the conformation of the compactor in the geometry of the surface by allowing the compactor to flex within two generally orthogonal planes.
    [008] According to yet another embodiment, a method is provided to make a compactor flexible in the orthogonal planes to compact a contoured composite reinforcement tray. The method comprises laying at least a first portion of the compactor by placing a plurality of composite reinforcement strips generally parallel, in spaced relation to each other and forming flexible joints between the reinforcement strips by laminating a layer of flexible rubber with the strips of reinforcement. The lamination includes curing the rubber layer and reinforcement strips. The laying of the first portion of the compactor includes the provision of at least one flat layer of reinforced resin fiber, notching the opposite edges of the flat layer to form the flange strips on the flat layer and laying the reinforcement strips on the flange strips.
    [009] In summary, according to one aspect of the invention, a compactor is provided for use in the manufacture of an elongated contoured composite structure, including at least one first flexible section along its length within a foreground; and at least a second section coupled to the first flexible section along its length within a foreground and within a second plane.
    [0010] Advantageously, the compactor in which the first and second planes are generally orthogonal to each other.
    [0011] Advantageously, the compactor in which the second section
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    5/24 of the compactor includes a first generally planar portion and a portion adapted to be received within a cavity in the composite structure.
    [0012] Advantageously, the compactor in which the first portion includes a plurality of reinforcement strips that extend transversely across the width of the first portion and spaced along the extension of the first portion, tears between the reinforcement strips and a flexible material in the rips.
    [0013] Advantageously, the compactor in which the second portion includes a plurality of slits that extend transversely there and the slits are substantially aligned with the grooves in the first portion.
    [0014] Advantageously, the compactor in which the second section includes a plurality of flexible rubber joints along its length that allows the second section to flex within the second plane.
    [0015] Advantageously, the compactor in which the second section includes alternating strips of reinforcement and rubber along its length. [0016] Advantageously, the compactor still comprises a connection joint between the first and the second sections.
    [0017] According to another aspect of the invention, a device is provided for transporting and compacting a contoured composite cover reinforcement tray having cavity, including a cover portion adapted to be placed within the cavity; and a cover portion generally planar coupled with the cover portion and flexible within the foreground generally parallel to the cover portion.
    [0018] Advantageously, the device in which the cover portion and the cover portion are each flexible in a background generally orthogonal to the foreground.
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    [0019] Advantageously, the device in which the lid portion includes laminated layers of flexible material and substantially rigid reinforcement strips that extend transversely across the width of the lid portion.
    [0020] Advantageously, the device in which the flexible material is a rubber, the reinforcement strips are spaced apart along the length of the cover portion to define the transverse slits, and the slots are substantially filled with the rubber.
    [0021] Advantageously, the device in which the reinforcement strips include unidirectional fiber reinforced resin and the flexible material includes synthetic rubber.
    [0022] Advantageously, the device in which the cover portion includes a plurality of slits there along its length, in which the slits extend substantially perpendicular to the plane of the cover and are substantially aligned with the slits between the reinforcement strips .
    [0023] Advantageously, the device in which the cover portion includes a plurality of slits along its length that are adapted to be coupled with a vacuum source for suction of the tray against the cover portion.
    [0024] In accordance with another aspect of the present invention, there is provided a method of using a compactor to manufacture a composite reinforcer, including forming a composite reinforcement tray; bring the compactor into contact with the reinforcement tray; adhere the reinforcement tray to the compactor; using the compactor to transport and place the reinforcement tray on a surface; and use the compactor to compact the reinforcement tray against the surface.
    [0025] Advantageously, the method in which the adhesion of the reinforcement tray to the compactor includes the generation of a vacuum within the
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    7/24 compactor and the use of vacuum to suck the reinforcement tray against the compactor.
    [0026] Advantageously, the method in which the suction of the reinforcement tray against the compactor includes the generation of a suction force by stretching the through the sides in the compactor in contact with the reinforcer tray.
    [0027] Advantageously, the method in which I use the compactor to place the reinforcement tray includes the conformation of the compactor to the geometry of the surface, which allows the compactor to flex within the two generally orthogonal planes.
    [0028] According to yet another aspect of the present invention, there is provided a method of manufacturing a flexible compactor in the orthogonal planes to compact a contoured composite reinforcement tray including laying at least a first portion of compactor by placing a plurality of strips composite reinforcement generally parallel in relation to each other; and to form flexible joints between the reinforcement strips by laminating a layer of flexible rubber with the reinforcement strips.
    [0029] Advantageously, the method in which the lamination includes curing the rubber layer and reinforcement strips.
    [0030] Advantageously, the method in which the laying of the first portion of the compactor includes the provision of at least one flat layer of reinforced resin, notch of the opposite edges of the flat layer to form the flange strips in the flat layer and laying of the strips of reinforcement on the flange strips.
    [0031] Advantageously, the method further includes laying a second portion of the compactor by laying a plurality of layers of fiber-reinforced resin on a tool having a cavity therein; and placing a bladder inside the tool cavity on the resin-reinforced layers
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    8/24 seated fiber, where the first portion of the compactor is seated by placing the reinforcement strips on the fiber-reinforced resin layers seated on the tool.
    [0032] In accordance with another aspect of the present invention, a device is provided for transporting, placing and compacting a contoured composite cover stringer including a generally planar, elongated, substantially continuous cap portion, the cap portion including a first flexible section only within a foreground and including a plurality of laminated layers of fiber reinforced resin, a second flexible section within the foreground and flexible within a second plane orthogonal to the foreground, the second section including a plurality of stacked strips of unidirectional fiber reinforced resin, the stacked strips being spaced along the length of the lid portion to define the slits between the stacked strips, the second section still including flexible rubber filling the slots and extending across the entire width of the portion cover and a connection joint between the first and the second sections; a cover-shaped portion joined to the cover portion, the cover portion having a generally open interior and a plurality of slits at that point, its extension communicating with the open interior and dividing the covering portion into segments, the slits being, respectively , aligned with the slots in the second section of the lid portion, the shaped portion of the lid being adapted to be coupled with a vacuum source to draw a vacuum from the open interior that produces a vacuum suction force through the slits that stretch the stringer against the configured portion of cover.
    [0033] In accordance with another aspect of the present invention, another method of making a flexible compactor is provided for transporting, placing and compacting a composite stringer
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    9/24 ta having composite contours along its length, including the laying of at least a first portion of the compactor by placing a plurality of composite reinforcement strips generally in parallel, in the spaced relationship between them, providing at least one flat layer fiber-reinforced resin, carving the opposite edges of the flat layer to form flange strips on the flat layer and laying the reinforcement strips on the flange strips; forming flexible joints between the reinforcement strips by laminating a flexible rubber layer with the reinforcement strips, including co-curing the rubber layer and reinforcement strips; laying a second portion of the compactor laying a plurality of layers of fiber-reinforced resin on a tool having a cavity there; placing a bladder inside the tool cavity on top of the fiber-reinforced resin layers, where the first portion of the compactor is laid by placing the reinforcement strips on the fiber-reinforced resin layers on the tool; and knurled slits in the second portion of the compactor that are aligned with the flexible joints in the first portion of the compactor.
    BRIEF DESCRIPTION OF THE DRAWINGS [0034] The new aspects believed to be advantageous features are described in the attached claims. Advantageous embodiments, however, as well as a preferred mode of use, other objectives and their advantages, will be better understood with reference to the following detailed description of an advantageous embodiment of the present invention, when read in conjunction with the accompanying drawings, in which:
    [0035] Figure 1 is an illustration of a perspective view of a compactor according to a reported embodiment.
    [0036] Figure 2 is an illustration of a perspective view of
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    10/24 a stringer provided in an aircraft liner curved in two planes.
    [0037] Figure 3 is an illustration of a side view of the stringer shown in Figure 2.
    [0038] Figure 4 is an illustration of a sectional view taken along line 4-4 in Figure 3.
    [0039] Figure 5 is an illustration of a sectional view taken along line 5-5 in Figure 3.
    [0040] Figure 6 is an illustration of a cross-sectional, detailed view of a layer tray used to form a section of the compactor shown in Figure 1.
    [0041] Figure 7 is an illustration similar to Figure 6, but showing a layer tray used to form another section of a compactor shown in Figure 1.
    [0042] Figure 8 is an illustration of a plan view of a layer forming part of the trays shown in Figures 6 and 7.
    [0043] Figure 9 is an illustration similar to Figure 8, but showing the opposite edges of a portion of the layer having been carved.
    [0044] Figures 10 to 17 are illustrations of plan views of a laying tool and successive laying steps used to manufacture the compactor.
    [0045] Figure 18 is an illustration of a sectional view taken along line 18-18 in Figure 1.
    [0046] Figure 19 is an illustration of a flowchart of a method of manufacturing the compactor.
    [0047] Figure 20 is an illustration of a cross-sectional view of a cover stringer that is a vacuum bag formed over a male die.
    [0048] Figure 21 is an illustration of a sectional view of the long
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    11/24 cover rina formed between male and female stamping dies.
    [0049] Figure 22 is an illustration similar to Figure 21, but showing the compactor having been installed in the stringer tray.
    [0050] Figures 23 to 26 are illustrations of sectional views showing successive stages of transport, placement and compacting of the cover stringer in a curing tool using the compactor.
    [0051] Figure 27 is an illustration of a flow chart of a method for making a composite stringer.
    [0052] Figure 28 is an illustration of an aircraft production flowchart and service methodology.
    [0053] Figure 29 is a block diagram illustration of an aircraft.
    DETAILED DESCRIPTION OF THE INVENTION [0054] Referring first to figures 1-5, a compactor 30 (Figure 1) can be used for transporting, placing and compacting a curved composite laminate reinforcer such as, without limitation, the contoured roof stringer 50 shown in figures 2 to 5; Compactor 30 is generally semi-rigid, with a degree of flexibility that allows compactor 30 to flex and conform to complex tool surfaces (not shown in Figure 1) during the placement and compaction of a stringer tray on the tool. During transport and placement of the stringer 50, it is held in the compactor 30 by a vacuum suction force 31. The compactor 30 is elongated and largely comprises a first portion of segmented cover 38 and second portion of generally planar, continuous cover 36 The cover portion 38 includes angled side walls 38a and bottom wall 38b.
    [0055] The cover 36 includes flanges that extend laterally
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    12/24
    36a. The cover portion 36 together with the cover portion 38 and a pair of end walls 45 form an enclosed internal space 35 that extends substantially along the entire length "L" of the compactor 30. A pneumatic connection fitting 42 in one or more both of the end wall 45 is adapted to couple the inner space 35 of the compactor 30 with a suitable vacuum source (not shown) to draw a vacuum into the compactor 30. As will be discussed below, the cover portion 38 includes a plurality of generally parallel slots 40 that allow air to be drawn through the cover portion 38 into the internal space 35. The slits 40 extend substantially the entire height of the cover portion 38 and divide into individual segments 41 that allow the portion of cover 38 of the compactor 30 to be flexed when placing and compacting the tray in the tool. Slots 40 also allow air to be drawn into the internal space 35, creating a vacuum suction force 31 that retains the stringer 50 in the compactor 30 during the process of transport, placement and compaction. This vacuum adhesion of the stringer 50 to the compactor 30 may allow a more symmetrical distribution of the crease and assembly of the layer during stringer compaction.
    [0056] Compactor 30 includes at least one single flexible first section 32 and at least one second will be double flexible 34. Sections 32, 34 are coupled together by joints 48 which are suitable for application, such as, without limitation , connection joints, plug-in joints or butt joints. In the illustrated embodiment, compactor 30 includes only a section 34 coupled between two of sections 32 by two joints 48. However, compactor 30 may have more than one of sections 34 located in any area along the length of compactor 30, including- also at the end of compactor 30. In some embodiments, substan
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    13/24 the entire compactor 30 may comprise a double flexible section 34. The compactor 30 may have more or less than two single flexible sections 32. As will be discussed in more detail later, section 34 of the compactor 30 includes flexible joints 23 that allow section 34 to flex in every two planes 44, 46 that are substantially orthogonal to each other. The plane 44 extends substantially parallel to and through the lid 36, while the plane 46 extends substantially perpendicular to the lid 36. The flexible joint 23 can also allow the torsional deviation of the compactor 30 along its longitudinal axis 47.
    [0057] Both the cover portion 36 and the cover portion 38 can be formed from the laminated layers (not shown in figure FIG. 1) of fiber reinforced resin such as, without limitation, carbon epoxy fiber. The number and thickness of the layers used to form the lid portion 36 in section 32 are selected in such a way that the lid portion 36 is flexible within the plane 44 to the degree necessary to allow the compactor 30 to conform to the surfaces of the curved tools (not shown) when placing and compacting the stringer seat on the tool. Slots 41 in the cover portion 38 allow the cover portion 38 to flex together with the cover portion 38 within the plane 44. [0058] As will be described later, the area of the cover portion that lies within the double flexible section 34 of compactor 30 is formed of a combination of materials which are co-cured to form a plurality of flexible joints 23. These flexible joints 23 allow the lid portion 36 to flex within both planes 44, 46, as well as to twist around its longitudinal axis 47. Slots 40 in the cover portion 38 also allow the area of the cover portion 38 within section 34 to flex within plane 46. As a result of the compactor 30's ability to flex in
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    14/24 two planes 44, 46 and conform to the geometry of a contoured tool 158 (Figures 24-26) another surface during the process of placing and compacting the stringer, the location and / or the pattern of the layer assembly and / or crease in the layer (not shown) can become more consistent, regular and / or predictable from the part-to-part, allowing for appropriate compensation engineering changes to be made in the design of the stringer 50 which can improve the stringer performance 50.
    [0059] Referring next to Figures 2-5, the cover stringer 50 generally has a cover-shaped cross section comprising a top 56, angled side walls 55, a pair of laterally extending flanges 58. A stringer 50 may be provided on the inner surface 52a of a coating 52 having composite contours to which stringer 50 may be required to conform. Flanges 58 of stringer 50 can be secured to coating 52 by any appropriate means, such as fasteners (not shown), bonding adhesives or by curing composite stringer 50 with coating 52 in those applications where coating 52 is a composite . As shown in figures 2 and 3, the stringer 50 has a first curvature outside the plane 54 and as shown in Figure 5, it has a second curvature outside the plane 60 conforming to the contours of the compound of the facing surface 52a.
    [0060] Attention, below, is directed to Figure 6 which illustrates a typical layer tray 61 used to form section 34 of the compactor 30 shown in Figure 1. The tray 61 is formed layer-by-layer on a seating tool 65 having a cavity 66 to form the cover portion 38 of the stringer 50 and flange surfaces 65a to form the cover portion 36. Two full-width layers 64 of fiber-reinforced resin are laid over the pore
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    15/24 cavity 66 and covering the flange surfaces 65a. Three additional layers 68 of fiber-reinforced resin are seated within cavity portion 66. In one embodiment, layers 64 can be skewed layers, while layers 68 can comprise a combination of skewed layers and flat wavy layers. The number of layers and their fiber orientation may vary, depending on the application.
    [0061] A sixth layer 70 comprises a plurality of reinforcement strips 70a of unidirectional fiber reinforced resin that are spaced along the length of the tool 65 and each has fiber orientations extending transversely through the cavity portion 6. A sixth layer 70 may comprise one or more stacked reinforcement strips 70a of the unidirectional molding material tape. A seventh layer 72 comprises a flexible uncured synthetic rubber layer, such as, without limitation, Viton® fluoroelastomer, which is slightly smaller in width than the strips in the sixth layer 70. The seventh layer 72 can comprise other materials that remain flexible following the cure. An eighth layer 74 comprises a second set of resin strips reinforced with unidirectional fiber 74a that cover the cavity portion 66 of the tool 65 and are, respectively, aligned with the strips 70a forming the layer 70, as will be discussed in more detail below. A ninth final layer 76 comprises a second full-width, flexible, uncured synthetic layer, which may also be a fluroelastomer such as Viton®. The cover portion 38 of the tray 61 is formed by layers 64 and 68, while the cover portion 36 is formed by a combination of layers 64, 70, 72, 74 and 76.
    [0062] With reference to Figure 7, the forming section 32 of tray 63 of the compactor 30 comprises a pair of layers of
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    16/24 full width 78 extending through the cavity portion 66 and over the flange surfaces 65a of the tool 65. Three additional layers 80 are laid over the cavity portion 66. Then a full width layer 86 is laid , followed by three layers 88 covering only the portion of cavity 66. Finally, another layer of full width 90 is laid. Each of the tray 63 layers may comprise a unidirectional fiber molding material or fabric having fiber orientations selected for a particular application.
    [0063] Attention is now directed to Figures 8-17 which illustrate the sequential steps used to form tray 61 shown in Figure 6. Referring first to Figure 8, a substantially flat tray 62 of layers 64 shown in Figure 6 is provided , which has an extension substantially equivalent to that of all three sections 32, 34 of compactor 30. Next, as shown in Figure 9, the opposing edges 95 along the compactor section 34 of settlement 62 are notched using any technique of appropriate material removal, such as, without limitation, die cutter. This notch results in a series of flange strips 64a in each of the layers 64 which are spaced along the length of the section 34 and are separated by the slots 128.
    [0064] Figure 10 illustrates tool 65 ready to receive the layer 61 tray shown in Figure 5. As previously mentioned, tool 65 includes a cover-shaped cavity portion 66 to form the cover portion 38 of the compactor 30 and a pair of flange surfaces 65a to form the flange portions 36a of the cover portion 36 of the compactor 30.
    [0065] Figure 11 illustrates the notched layers 64 having settled on the tool 65, with the flange strips spaced 64a overlying the flange surfaces 65 a of the tool 65. Figure 12
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    17/24 reflects the end of the next step in the seating process, in which layers 68 are seated within cavity portion 66 of tool 65, overlapping layers 64. Then, as shown in figure 13, an inflatable bladder 142 is placed in the cavity portion 66 overlapping layers 68.
    [0066] With reference to Figure 14, the next step in the manufacturing process comprises the laying of reinforcement strips of the unidirectional molding material that extend transversely 70a, in alignment with and overlapping the flange strips 64 (Figure 13) of the whiting notched 62. Each of the reinforcement strips 70a may comprise one or more layers of unidirectional molding material tape, however, other types of reinforcement may be possible. Reinforcement strips 70a extend substantially over the entire width of the cover section 36 and spaced in a pitch that is appropriate for the particular application.
    [0067] Figure 15 shows the rubber layer 72 having been laid over the reinforcement strips 70a, followed by that, as shown in Figure 16, a second set of spaced, generally parallel reinforcement strips 74a is laid over the layer rubber 72, aligned with both the underlying reinforcement strips 70a and the flange strips 64a (see Figures 13 and 14). Reinforcement strips 74a reinforce the area of the cap section 36 that overlaps the cavity 66. Finally, as shown in Figure 17, a second layer 76 of uncured synthetic rubber or similar flexible material is laid over the reinforcement strips 74a. The second rubber layer 76 extends substantially over the entire width of the tray 61.
    [0068] Figure 18 is a sectional illustration showing one of the flexible joints 23 in the compactor section 34. The aligned stacking of the reinforcement strips 64a, 70a, 74a forms slots 128 that are filled with rubber from the rubber layers 72 76 du
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    18/24 during layer lamination of the lid portion 36. Following this lamination, the flexible rubber joints 23 extend across substantially the entire width of the lid portion 36. The reinforcement strips 64a, 70a, 74a provide compactor section 34 with the necessary stiffness to maintain its shape and prevent collapse when a vacuum is drawn into the compactor 30, while the rubber-filled grooves 128 forming joints 23 allow the lid portion 36 to flex within one of the orthogonal planes 44, 46 (Figure 1). The flexible rubber joints 23 are aligned to match the location of the slits 40 along the length of the compactor.
    [0069] Figure 19 is a flow chart illustrating the steps of a compactor manufacturing method 30. In one embodiment, which starts in step 92, a flat tray 62 of layer 64 is provided and in step 94 the edges of tray 62 are notched. In 96, the notched tray 62 is placed on and formed on a tool 65 and the additional layers 68 can be laid, as required, to reinforce the cover portion 38 of the compactor 30. Then, as shown in 106, an inflatable bladder 142 it is installed in a cavity 66 of the tool 65, overlapping the layers 64, 68. Alternatively, as shown in 100, the layers 64 can be seated on the forming tool 65 without notching, followed by the additional cover layers 68 being able to be 102, as required. In 104, the edges of the layers 64 are notched to form the reinforcement flange strips 64 in the double bending section 34 of the compactor 30. In 108, the composite reinforcement strips 70a are seated on the flange strips 64a and in 110 a first layer 72 of the uncured rubber is seated on the flange strips 64a. In 112, the second set of unidirectional composite reinforcement strips 74a are laid on the first layer of sludge
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    19/24 cha 72 in order to further reinforce the area of the cap portion 36 which overlaps the cavity 66. In 114, the second layer 76 of the uncured rubber is seated on the reinforcement strips 74.
    [0070] Each of the compactor sections 32 is laid first by laying the layers of the covering portion 38 in step 116 and then laying the layers in the covering portion 36 in step 118. As the cover layers of the compactor section 32 are being laid, at least three layers are interspersed with the cover layers of compactor section 34, as shown in step 120, in order to form the overlap connection joints 48 between compactor sections 32, 34. Joints 48 can reduce the localized stiffness and increase the total durability of the compactor 30. As previously mentioned, although the connection joints 48 have been shown in the exemplary embodiment, other types of joints may be possible.
    [0071] In 122, the compactor tray is vacuum bagged and the layers of rubber and composite resin are co-cured, with or without autoclave processing. Following co-curing, the slits 40 in the cover portion 38 of the compactor 30 are formed by cutting, knurling or other appropriate processes. As previously mentioned, the slits 40 are located and spaced from each other in such a way that they are substantially aligned with the deposited rubber slots 128.
    [0072] Attention is then directed to Figures 20-26 which illustrate the steps of a method of forming, transporting, placing and compacting a tray of a composite cover stringer 50 using flexible compactor 30. Referring first to Figure 20, a composite cover stringer 50 can be formed by placing a composite multilayer load on a male die 152 and using a vacuum bag 153 to compact and
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    20/24 form the charge on the matrix 152. Alternatively, as shown in Figure 21, the stringer 50 can be formed by the stamping that forms a composite charge between male and female matrices 152, 156, respectively, creating a cover cavity 154. Following the formation, the stringer 50 can be centered when necessary. With the stringer 50 supported on the female matrix 156, the compactor 30 is placed in the cover cavity 154 of the stringer 50 such that the cover portion 38 of the compactor 30 engages the side walls 55 and the top 56 of the stringer 50 and the portions rings 36a of compactor cover 36 overlap and engage flanges 58 of stringer 50. Stringer 50 and compactor 30 can remain on female die 156 which can be used as a retaining fastener to maintain the shape of stringer 50 up to they are ready to be removed and transported for placement. Optionally, the stringer 50 can be transferred to a holding device (not shown) until ready for placement. In order to remove the stringer 50 from the female die 156 (or an optional holding device), a vacuum is drawn from inside the compactor 30 which collects air through the slits 40 (Figure 1) to create a suction force 31 (Figure 22) that leads the stringer 50 to adhere to the compactor 30.
    [0073] As shown in Figure 23, with the stringer 50 attached to the compactor 30, the compactor 30 is raised along with the stringer 50 away from the female die 156 and is used to transport the stringer 50 to a structure such as tool 158, as shown in Figure 23, having female tool surfaces 159 which are curved in more than one plane and substantially conjugate with the external mold line (OML) surface (not shown) of the stringer 50. Compactor 30 is used for place the stringer 50 in a cavity 160 of tool 158, as shown in Figure
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    21/24
    25. With compactor 30 and stringer 50 installed in tool cavity 160, a set of vacuum bag 155 is installed over compactor 30 and stringer 50, and a vacuum is drawn into bag 155 (Figure 25) which, together with compactor 30, compacts tray 50 against tool surfaces 159. Following the compaction of stringer 50, as shown in Figure 26, compactor 30 is stretched away from stringer 50. Stringer 50 can then be further processed. For example, chargers (not shown) can be installed on stringer 50, one or more balloons (not shown) can be installed against stringer 50, stringer 50 can be provided on liner 52 (Figure 2) and cured in an autoclave ( not shown), etc.
    [0074] Figure 27 illustrates a flow chart of the stringer 50 manufacturing steps previously described in connection with figures 20 - 25. Starting at 162, the composite stringer load 50 is seated and optionally centered as needed. In 164, the stringer load is formed in a stringer shape, as by die stamping or other processes. The formed stringer 50 can be centered after being formed in step 164, if not previously centered in step 162. Optionally, the stringer 50 can be transferred to a holding device until it is ready to be transported and placed by the compactor 30. In 166 , the compactor 30 is installed in the stringer cavity 160. The compactor 30 can remain on the stringer 50 to maintain its shape until the stringer 50 is ready to be removed from the female die 156 or a holding device. In 168, the stringer 50 is adhered to the compactor 30 using its force generated by stretching a vacuum inside the compactor 30 which sucks the stringer 50 against the compactor 30. Then, in 170, the compactor 30 is used to lift and transport the stringer 50 up to a tool, device
    Petition 870190131393, of 11/12/2019, p. 25/36
    22/24 vo, part or other structure or surface. For example, and without limitation, compactor 30 can be used to transport stringer 50 to a tool 158, then place the stringer 50 in a desired location on tool 158 or another structure or surface. As the stringer 50 is being placed by the compactor 30, the compactor 30 can flex in one or both of the orthogonal planes 44, 46 or twist around a longitudinal axis 47 (Figure 1) to the extent necessary to conform the seat. stringer 50 to the curved surfaces of the frame such as tool surfaces 159.
    [0075] In 174, a vacuum bag 155 along with other usual fabric components (bagging) (not shown) is installed and sealed on tool 158, covering stringer 50 and compactor 30. In 176, a vacuum is removed in the bag 155 that compresses the stringer 50 through the compactor 30, while the vacuum is kept inside the compactor 30. The vacuum drawn from inside the compactor 30 can assist in the evacuation of the vacuum bag 155 during the compaction process, as a result of air leak to compactor 30 through slits 40 (Figure 1). In 178, the stringer tray 50 is removed from the bag, the vacuum inside the compactor 30 is released and the compactor 30 is removed from the tool 158. In 180, the compactor can be staggered for reuse in the compaction of another stringer tray 50 The stringer manufacturing process can be continued at 182, depending on the application, installing loaders on the stringer 50, applying balloons, providing liners on the stringer, etc.
    [0076] Embodiments of the invention can find use in a variety of potential applications, particularly in the transportation industry, including, for example, aerospace, marine, automotive applications and another application in which the equipment for maintenance 870190131393, 11/12/12 2019, p. 26/36
    Automated 23/24 tar can be used. Thus, with reference below to figures 28 and 29, the embodiments of the invention can be used in the context of aircraft manufacturing and service method 184 as shown in Figure 28 and an aircraft 186 as shown in Figure 29. Applications in aircraft the embodiments of the invention may include, for example, without limitation, reinforcement member tray such as, without limitation, reinforcements and side members. During pre-production, exemplary method 184 may include specification and design 188 of aircraft 186 and acquisition of material 190. During production, component manufacturing and sub-assembly 192 and system integration 194 of aircraft 186 occur. Next, aircraft 186 can proceed through certification and delivery 196 in order to be put into service 198. While in service by a customer, aircraft 186 is scheduled for routine maintenance and service 200, which may also include modification, reconfiguration , repolling, etc. [0077] Each of the method 184 processes can be performed by a system integrator, a third party and / or an operator (eg, a customer). For the purposes of this description, a system integrator may include, without limitation, any number of aircraft manufacturers and subcontractors to the main system; a third party may include, without limitation, any number of sellers, sub-contractors and suppliers; and an operator can be an airline, leasing company, military entity, service organization, etc.
    [0078] As shown in Figure 29, the aircraft 186 produced by the exemplary method 184 can include an airplane structure 202 with a plurality of systems 204 and an interior 206. The airplane structure 202 can be manufactured using a reported method and compactor. Examples of high-level 204 systems include one or more of a 208 propulsion system, an electrical system 210, an
    Petition 870190131393, of 11/12/2019, p. 27/36
    Hydraulic 24/24 212, and an environmental system 214. Any number of other systems can be included. Although an example of aerospace is shown, the principles of the invention can be applied to other industries such as the marine and automotive industries.
    [0079] The systems and methods realized here can be employed during any one or more of the production stages and service method 184. For example, the components or subassemblies corresponding to the 192 production process can be manufactured or manufactured in a similar way to those components or sub-assemblies produced while aircraft 186 is in service. Also, one or more embodiments of the apparatus, embodiments of the method or a combination thereof may be used during production stages 192 and 194, for example, by substantially speeding up the assembly of or reducing the cost of an aircraft 186. Similarly, one or further embodiments of the apparatus, embodiments of the method or a combination thereof may be used while aircraft 186 is in service, for example and, without limitation, maintenance and service 200.
    [0080] The description of the different advantageous embodiments has been presented for purposes of illustration and description and is not intended to be exhaustive or limited to the embodiments in the manner reported. Many changes and variations will be made evident to those of ordinary skill. In addition, different advantageous embodiments can provide different advantages when compared to other advantageous embodiments. The selected embodiment or embodiments are selected and described in order to better explain the principles of the embodiments, practical application and enable others skilled in the art to understand the invention for various embodiments with various modifications as are appropriate for the particular intended use.
    权利要求:
    Claims (10)
    [1]
    1. Compactor (30) for use in the manufacture of an elongated contoured composite structure (50), characterized by the fact that it comprises:
    at least one first flexible section (20) along its extension within a foreground (44); and at least a second section (34) coupled to the first section (32) and flexible along its extension within the first plane (44) and within a second plane (46), in which the second section (34) of the compactor (30) includes a first portion (36) generally flat and a second portion (38) adapted to be received within a cavity in the composite structure (50), wherein the first portion (36) includes:
    a plurality of reinforcement strips (70a) extending transversely across the width of the first portion (36) and spaced along the first portion (36), wherein the reinforcement strips (70a) include unidirectional fiber reinforced resin, slits (128) between the reinforcement strips (70a), and a flexible material in the slots (128), and in which the flexible material includes synthetic rubber.
    [2]
    2. Compactor (30), according to claim 1, characterized by the fact that the first and second planes (44, 46) are generally orthogonal to each other.
    [3]
    Compactor (30) according to claim 1 or 2, characterized in that the second portion (38) includes a plurality of slits (40) which extend transversely therein, and the slits (40) are substantially aligned with the slots (128) in the first portion (36).
    [4]
    4. Compactor (30), according to any of the king
    Petition 870190131393, of 11/12/2019, p. 29/36
    2/3 preceding vindications, characterized by the fact that the second section (47) includes a plurality of flexible rubber joints (23) along its length, allowing the second section (34) to flex within the second plane (46) .
    [5]
    Compactor (30) according to any one of the preceding claims, characterized by the fact that the second section (34) includes alternating strips of reinforcement and rubber along its length.
    [6]
    Compactor (30) according to any one of the preceding claims, characterized by the fact that it also comprises a connection joint between the first and the second sections (32, 34).
    [7]
    7. Method of using a compactor (30) as defined in any one of claims 1 to 6, characterized by the fact that it comprises:
    forming (164) a composite reinforcement tray;
    bring (166) the compactor (30) in contact with the reinforcement tray;
    adhering (168) the reinforcement tray to the compactor (30); use (170) the compactor (30) to transport and place the reinforcement tray on a surface; and use (172) the compactor (30) to compact the reinforcement tray against the surface.
    [8]
    8. Method according to claim 7, characterized by the fact that the adhesion of the reinforcement tray to the compactor (30) includes:
    generate a vacuum inside the compactor (30), and use the vacuum to suck the reinforcement tray against the compactor (30).
    [9]
    9. Method according to claim 7 or 8, featuring
    Petition 870190131393, of 11/12/2019, p. 30/36
    3/3 due to the fact that suction of the reinforcement tray against the compactor (30) includes the generation of a suction force by drawing air through the sides of the compactor (30) in contact with the reinforcer tray.
    [10]
    Method according to any one of claims 7 to 9, characterized in that the use of the compactor (30) to place the reinforcement tray includes the conformation of the compactor (30) to the geometry of the surface by allowing the compactor ( 30) to flex within the two generally orthogonal planes.
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2666951A|1951-08-30|1954-01-26|Us Rubber Co|Method and apparatus for drawing plastic sheets|
    US2810976A|1952-12-27|1957-10-29|American Brake Shoe Co|Method and apparatus for ornamenting ceramic ware|
    US2816593A|1956-06-21|1957-12-17|Cyril Bath Co|Method for stretch forming tapered blanks|
    US2995177A|1958-05-16|1961-08-08|Us Rubber Co|Apparatus for splicing tire treads|
    GB921135A|1959-08-21|1963-03-13|Bristol Siddeley Engines Ltd|Articles of reinforced resin and methods of making same|
    US2986194A|1959-12-03|1961-05-30|Cyril Bath Co|Rapid cycle stretch and wipe forming machine|
    US3285794A|1963-02-25|1966-11-15|Parsons Corp|Inflatable tool for applying bonding pressure to patterned areas|
    US3357379A|1965-10-22|1967-12-12|Westinghouse Electric Corp|Domestic incinerator appliance|
    US4086378A|1975-02-20|1978-04-25|Mcdonnell Douglas Corporation|Stiffened composite structural member and method of fabrication|
    JPS5224273A|1975-08-18|1977-02-23|Hiroshi Kodama|Device for forming hollow column consisted of frp|
    US4185069A|1976-02-08|1980-01-22|Smith George L|Production of plastics articles|
    DE2734025C3|1977-07-28|1982-01-07|Wagener Schwelm GmbH & Co, 5830 Schwelm|Device for repairing and making conveyor belts endless|
    DE3277865D1|1982-07-19|1988-02-04|Boeing Co|Method and apparatus for fiber lamination|
    US4550044A|1983-08-08|1985-10-29|Figgie International, Inc.|Ballistic resistant armor panel and method of constructing the same|
    DE3535458C1|1985-10-04|1987-01-08|Kleinewefers Textilmaschinen G|Method for regulating the moisture of a textile material web or the like by squeezing and device for carrying out this method|
    US5425973A|1985-12-27|1995-06-20|Mcdonnell Douglas Corporation|Integral overwrap shield|
    GB8629267D0|1986-12-08|1987-02-11|Westland Plc|Laying pre-impregnated fibre reinforced material on surface|
    US4861406A|1987-08-17|1989-08-29|The Boeing Company|Method and apparatus for handling plies of composite material|
    US4980008A|1989-07-17|1990-12-25|Ball Corporation|Method for decorating cylindrical, metallic containers|
    US5214951A|1992-05-06|1993-06-01|Waddell Thomas T|Method and apparatus for controlled bending of strip stock|
    FR2693146B1|1992-07-02|1994-08-19|Snecma|Installation for the draping of multilayer structures in composite materials.|
    US6045651A|1993-09-07|2000-04-04|The Boeing Company|Hand assisted lamination system|
    US5538589A|1994-08-31|1996-07-23|The Boeing Company|Composite stringer assembly machine|
    US5700347A|1996-01-11|1997-12-23|The Boeing Company|Thermoplastic multi-tape application head|
    US5676080A|1996-05-15|1997-10-14|Quintrex Australia Pty Ltd.|Watercraft|
    US7681835B2|1999-11-18|2010-03-23|Rocky Mountain Composites, Inc.|Single piece co-cure composite wing|
    AU1665702A|2000-11-15|2002-05-27|Toyota Motor Sales Usa Inc|One-piece closed-shape structure and method of forming same|
    WO2002081210A1|2001-04-06|2002-10-17|Marion Composites, A Division Of Advanced Technical Products, Inc.|Method of manufacturing a hollow section, grid stiffened panel|
    US7052572B2|2001-08-01|2006-05-30|Fuji Jukogyo Kabushiki Kaisha|Method for manufacturing a structure|
    US6649006B2|2001-10-09|2003-11-18|Lockheed Martin Corporation|Method of making a waffle stiffener|
    US6814916B2|2002-08-30|2004-11-09|The Boeing Company|Forming method for composites|
    US7137182B2|2002-11-22|2006-11-21|The Boeing Company|Parallel configuration composite material fabricator|
    US7249943B2|2003-08-01|2007-07-31|Alliant Techsystems Inc.|Apparatus for forming composite stiffeners and reinforcing structures|
    US7357166B2|2004-11-24|2008-04-15|The Boeing Company|Flexible mandrel for highly contoured composite stringer|
    US7527759B2|2005-04-13|2009-05-05|The Boeing Company|Method and apparatus for forming structural members|
    DE102005044823B3|2005-09-20|2007-05-16|Airbus Gmbh|Placing method of thin material layer onto relief mold for producing composite material involves arranging elastically-reversible deformable portion with attached material layer so that surface relief of material layer matches relief mold|
    JP2009542493A|2006-07-06|2009-12-03|エアバスドイチェランドゲゼルシャフトミットベシュレンクテルハフツング|Method of manufacturing composite fiber parts for use in aircraft or spacecraft, molded core material, and composite fiber parts obtained therefrom|
    DE102006031326B4|2006-07-06|2010-09-23|Airbus Deutschland Gmbh|Mold core and method for producing a fiber composite component for the aerospace industry|
    DE102006031335B4|2006-07-06|2011-01-27|Airbus Operations Gmbh|Method for producing a fiber composite component for aerospace applications|
    US7788784B2|2006-10-17|2010-09-07|The Boeing Company|Method of assembling composite structure|
    US7644491B2|2006-10-17|2010-01-12|The Boeing Company|Device for assembling composite structure incorporating flipper assemblies|
    US7814644B2|2006-10-17|2010-10-19|The Boeing Company|Positioning assembly for composite structure|
    US7871040B2|2006-11-10|2011-01-18|The Boeing Company|Composite aircraft structures with hat stiffeners|
    WO2008062818A1|2006-11-22|2008-05-29|Fukui Prefectural Government|Reinforced thermoplastic-resin multilayer sheet material, process for producing the same, and method of forming molded thermoplastic-resin composite material|
    EP2132302B1|2007-03-12|2016-01-27|Technion Research & Development Foundation Ltd.|Vascularized islets and methods of producing same|
    US7861969B2|2007-05-24|2011-01-04|The Boeing Company|Shaped composite stringers and methods of making|
    EP2159038A4|2007-05-28|2017-08-02|Airbus Operations S.L.|Method and tool for producing composite-material structures|
    JP2008307692A|2007-06-12|2008-12-25|Toray Ind Inc|Fiber-reinforced plastic and its manufacturing method|
    US8118959B2|2007-06-27|2012-02-21|The Boeing Company|Method and apparatus for contouring composite pre-preg articles|
    FR2928295B1|2008-03-07|2017-12-08|Duqueine Rhone Alpes|METHOD AND DEVICE FOR MOLDING A CURVED PIECE OF COMPOSITE MATERIAL AND CORRESPONDING PIECE|
    US9238335B2|2008-07-10|2016-01-19|The Boeing Company|Mandrel for autoclave curing applications|
    CN101462780B|2009-01-23|2011-10-12|国家海洋局天津海水淡化与综合利用研究所|Low temperature multiple-effect distillation seawater desalination system and process flow thereof|
    DE102009029575B4|2009-09-18|2011-06-22|Airbus Operations GmbH, 21129|Method for stiffening a fiber composite component and arrangement for producing a stiffened fiber composite component|
    JP5521175B2|2009-10-30|2014-06-11|国立大学法人金沢大学|Press molding apparatus and press molding method|
    US8795567B2|2010-09-23|2014-08-05|The Boeing Company|Method for fabricating highly contoured composite stiffeners with reduced wrinkling|
    US20120073738A1|2010-09-29|2012-03-29|The Boeing Company|Method and apparatus for laying up barrel-shaped composite structures|
    US8551380B2|2010-11-12|2013-10-08|The Boeing Company|Method of laying up prepreg plies on contoured tools using a deformable carrier film|
    US9931807B2|2011-08-08|2018-04-03|The Boeing Company|Flexible compactor with reinforcing spine|
    US8997642B2|2011-08-08|2015-04-07|The Boeing Company|Method for transporting, placing and compacting composite stiffeners|
    US9649809B2|2012-11-02|2017-05-16|The Boeing Company|Wrinkle diffuser system for composites|
    US9731457B2|2012-11-02|2017-08-15|The Boeing Company|System and method for minimizing wrinkles in composites|
    US9272767B2|2013-04-19|2016-03-01|The Boeing Company|Compacting uncured composite members on contoured mandrel surfaces|US9586699B1|1999-08-16|2017-03-07|Smart Drilling And Completion, Inc.|Methods and apparatus for monitoring and fixing holes in composite aircraft|
    US9625361B1|2001-08-19|2017-04-18|Smart Drilling And Completion, Inc.|Methods and apparatus to prevent failures of fiber-reinforced composite materials under compressive stresses caused by fluids and gases invading microfractures in the materials|
    US8997642B2|2011-08-08|2015-04-07|The Boeing Company|Method for transporting, placing and compacting composite stiffeners|
    US9931807B2|2011-08-08|2018-04-03|The Boeing Company|Flexible compactor with reinforcing spine|
    US8826957B2|2012-08-31|2014-09-09|General Electric Company|Methods and systems for automated ply layup for composites|
    US9199417B1|2013-01-02|2015-12-01|The Boeing Company|Systems and methods for assembling stiffened composite structures|
    US9221236B1|2013-01-02|2015-12-29|The Boeing Company|Systems and methods for assembling stiffened composite structures|
    US9221235B1|2013-01-02|2015-12-29|The Boeing Company|Systems and methods for assembling stiffened composite structures|
    WO2014122268A1|2013-02-08|2014-08-14|Lm Wp Patent Holding A/S|A system and method for the manufacture of an article|
    US9272767B2|2013-04-19|2016-03-01|The Boeing Company|Compacting uncured composite members on contoured mandrel surfaces|
    US9370922B1|2014-03-18|2016-06-21|The Boeing Company|Systems and methods for stretch-forming multi-thickness composite skins|
    US10401875B2|2014-07-31|2019-09-03|The Boeing Company|Electronic stopper in actuator control|
    DE102014216160A1|2014-08-14|2016-02-18|Airbus Operations Gmbh|Mold core, method and system for producing curved composite components|
    US9873500B2|2014-09-16|2018-01-23|The Boeing Company|Process and apparatus for handling, installing, compacting, splicing, and/or assembling composite stringers|
    US9993925B2|2015-08-25|2018-06-12|The Boeing Company|End effector apparatus and methods for handling composite structures|
    US10399283B2|2015-10-06|2019-09-03|The Boeing Company|Method and device for producing contoured composite laminate stiffeners with reduced wrinkling|
    US10836121B2|2016-02-08|2020-11-17|Bell Helicopter Textron Inc.|Methods of manufacture of a composite wing structure|
    GB2550403A|2016-05-19|2017-11-22|Airbus Operations Ltd|Aerofoil body with integral curved spar-cover|
    US10583617B2|2016-11-28|2020-03-10|General Electric Company|Automatic systems and methods for stacking composite plies|
    FI127614B|2017-04-07|2018-10-15|Patria Aerostructures Oy|Composite element and method of manufacturing the same|
    JP6715226B2|2017-10-25|2020-07-01|株式会社Ｓｕｂａｒｕ|Composite material forming jig and composite material forming method|
    US20190177007A1|2017-12-11|2019-06-13|The Boeing Company|Composite repair kit|
    EP3623143B1|2018-09-11|2021-05-05|Airbus Operations, S.L.|Methods for manufacturing curved omega stringers and z shaped stringers of composite material and for manufacturing a composite material stiffened panel with curvature|
    USD891963S1|2018-09-19|2020-08-04|Highway Care Ltd.|Combined T-barrier connector and barrier|
    US20210053299A1|2019-08-22|2021-02-25|The Boeing Company|Highly contoured composite structures and system and method for making the same|
    US11214021B2|2020-03-06|2022-01-04|The Boeing Company|Method and system for manufacturing a cured composite structure|
    法律状态:
    2018-04-03| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2019-09-17| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2020-01-28| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2020-03-31| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 06/07/2012, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/205,226|US8997642B2|2011-08-08|2011-08-08|Method for transporting, placing and compacting composite stiffeners|
    US13/205,226|2011-08-08|
    PCT/US2012/045674|WO2013022534A2|2011-08-08|2012-07-06|Method and device for transporting, placing and compacting composite stiffeners|
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