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    • 专利摘要:
    METHOD FOR MANUFACTURING A THICK THERMOPLASTIC COMPOUND PIECE AND A CONTINUOUS COMPRESSION MOLDING DEVICE FOR A THICK THERMOPLASTIC COMPOUND PIECE. A method and apparatus are used to pre-consolidate and compact a pile of thermoplastic composite layers (16) before total consolidation and formation in the form of the final piece. Pre-consolidation and compaction are achieved by heating the stack of layers (16) to a temperature below the melting point of the thermoplastic in order to soften the layers (18), and then compress the stack of layers (16).
    公开号:BR112015009406B1
    申请号:R112015009406-6
    申请日:2013-09-09
    公开日:2021-03-16
    发明作者:Randall D. Wilkerson；James R. Fox
    申请人:The Boeing Company；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION 1.Field:
    [001] The described modalities generally refer to the manufacture of composite laminates and, more particularly, they refer to a method and apparatus for forming thick thermoplastic composite structures. 2.Fundamentals:
    [002] Fiber-reinforced thermoplastic laminates can be manufactured by assembling a stack of pre-preg layers, and consolidating the stack of layers into a finished piece. Consolidation is achieved by heating the layers to their melting temperature and molding the layer stack into the shape of the desired part using conventional compression molding, continuous compression molding, or other techniques. During molding, sliding the layers in relation to each other allows the stack of layers to change shape and conform to the geometry of a mold tool. Thin thermoplastic laminates comprising relatively few pre-preg layers can be manufactured without difficulty using continuous compression molding, in part because the heat required to melt the thermoplastic is transferred relatively quickly through the thickness of the laminate.
    [003] Problems can arise, however, when manufacturing thermoplastic composite laminates that are relatively thick, especially those with complex geometries. When the thermoplastic resin melts during consolidation and formation, excessive movement of the material required for consolidation allows reinforcement fibers to move and distort both in and out of the plane.
    [004] Another problem during the formation of thick thermoplastic composite laminates is caused by the excessive volume of material resulting from the need for a large number of layers in the layer stack. Stacks of layers that are particularly thick can be difficult or impossible to consolidate and conform to the shape. Bulky material can be partly taken into account when making adjustments to the mold tooling, however, it can still be difficult nonetheless to fully consolidate the layer stack during forming. The inability to fully consolidate stacks of thick layers, due to excessive material volume, can lead to porosities and internal voids in the finished part.
    Consequently, there is a need for a method and apparatus for manufacturing thick thermoplastic composite laminates that unstack and partially consolidate a stack of thermoplastic layers prior to molding in order to reduce undulations, porosity and internal voids in the finished part. There is also a need for a method and apparatus as described herein that reduces or eliminates fiber distortion, as the layer stack is being formed in its final shape.
    [006] Document EP0317861 discloses a method in which two profile halves, or an open profile of fibrous structures impregnated with plastic, are fed to a device directly by the molding process. In the device, the profile halves are processed by joining and / or shaping with pairs of cylinders to form closed hollow profiles.
    [007] Document FR2929167 discloses a process for manufacturing a thermoplastic composite material. The process comprises applying a pressure and temperature cycle on top of a pile of continuous fiber fabrics pre-impregnated with a thermoplastic resin. The stack is wrapped in a film and heated, so as to reach at least the melting temperature of the resin. The gases present in the pile escape through at least one opening left in the surrounding film and at least one through channel formed in the compaction plate.
    [008] Document W02011 / 106117 discloses the manufacture of an elongated thermoplastic composite member by a continuous molding process. A pre-consolidated thermoplastic laminate is softened by heating to a temperature below its melting point, and is fed substantially continuously through multiple sets of tool dies. Tool dies incrementally shape portions of softened laminates through a mandrel to form the laminate in a shape that has a closed cross section. SUMMARY OF THE INVENTION
    [009] The described modalities provide a method and an apparatus for forming pieces of thermoplastic composite laminate that are relatively thick and / or have complex geometries. The volume of material in disassembled layers is substantially reduced, before consolidation and total formation, thereby reducing the need to take into account the volume of material in the tooling used to consolidate and form the part. The method employs a material compaction technique carried out at an elevated temperature sufficient to soften the thermoplastic resin, but below its melting point. This compaction results in partial consolidation of the layer pile in which the layers adhere to each other in contact face to face over substantially all their surface areas, before being heated to the melting temperature in preparation for total consolidation and formation. As a result of such compacting and partial consolidation of material, fiber distortion caused by material movement is substantially reduced, and undulation and internal porosities and voids are reduced or eliminated, all of which lead to better part quality. Furthermore, the method and apparatus may allow the manufacture of thicker thermoplastic composite laminates than has been possible to date. The apparatus includes a continuous compression molding machine (CCM) that incorporates a pre-consolidation zone for compaction and pre-consolidation of the layer pile before being consolidated and formed into the shape of the final piece.
    [0010] According to a described embodiment, a method is provided for producing a thick thermoplastic composite part. The method comprises assembling a layer stack including a plurality of thermoplastic composite layers, and pre-consolidating the layer stack, including softening the layers by heating the layers in the layer stack to a temperature below the melting point of the thermoplastic and compressing the stack of layers. The method further comprises consolidating the pre-consolidated layer stack, including heating the layer stack to at least the melting temperature of the thermoplastic. Compressing the stack of layers of softened layers includes applying enough layer pressure to compact the layer stack, and may also include placing the layer stack between two tools, and forcing the tools against each other. Compression of the layer pile of the softened layers is done in a continuous compression molding machine. Consolidation of the pre-consolidated layer stack is done by compacting the layer stack. The method may further comprise forming the layer stack in a desired shape as the layer stack is being consolidated. Formation of the layer pile in the desired shape can also be done in a continuous compression molding machine.
    [0011] According to another described embodiment, a method is provided for forming a thick thermoplastic composite part. The method comprises assembling a stack of layers by arranging a plurality of thermoplastic composite layers on top of each other, and pre-consolidating the stack of layers using a first set of parameters, the first set of parameters including a first pre-selected temperature, a first pre-selected pressure and a first pre-selected time duration. The method also includes consolidating the pre-consolidated layer stack using a second set of parameters, the second set of parameters including a second pre-selected temperature, a second pre-selected pressure and a second pre-selected time interval. The layer stack is assembled by continuously feeding multiple thermoplastic composite layers into a continuous compression molding machine. The first pre-selected temperature is a temperature sufficient to soften the layers, but it is below the melting point of the thermoplastic. The first preselected pressure is sufficient to compact the stack of layers. The first pre-selected time interval is sufficient to allow the layers in the layer stack to soften to the first pre-selected temperature, and to allow compaction of the layer stack at the first pre-selected pressure. The second preselected temperature is high enough to result in the fusion of the thermoplastic layers in the layer stack, and the second preselected pressure is high enough to completely consolidate the layer stack.
    [0012] According to another described embodiment, a method is provided for continuous compression molding of a thermoplastic composite part. The method comprises assembling a layer stack including a plurality of thermoplastic pre-preg layers, and compacting the layer stack by heating the layers to a temperature below their melting point and compressing the layer stack. The method further comprises molding the stack of compacted layers into a shape of the desired part, including heating the layers to at least their melting point and additionally compressing the stack of layers to fully consolidate the layers. Compression of the layer stack is done by placing the layer stack between a pair of tools, and using the tools to apply a compaction pressure to the layer stack. Compaction of the layer stack and molding of the layer stack can be done on a continuous compression molding machine.
    [0013] According to yet another described embodiment, an apparatus is provided for compression molding of a thick thermoplastic composite part. The apparatus comprises a pre-consolidation zone and a consolidation zone. The pre-consolidation zone receives a stack of layers of thermoplastic layers, and includes a heater to heat the stack of layers and pre-consolidation tools to compress the stack of layers. The consolidation zone includes consolidation tools to consolidate and form the stack of pre-consolidated layers in the shape of the part. The apparatus may additionally comprise a pre-forming zone for preforming the layer stack after the layer stack has been pre-consolidated. The apparatus may also include a pulsating drive mechanism for moving the stack of layers through the pre-consolidation zone and through the consolidation zone in continuous incremental steps. BRIEF DESCRIPTION OF THE DRAWINGS
    [0014] Unpublished resources considered characteristics of the illustrative modalities will be presented in the attached claims. The illustrative modalities, however, as well as a preferred mode of use, and their additional objectives and advantages, will be better understood by reference to the following detailed description of such an illustrative modality of the present description, when read in conjunction with the attached drawings, on what:
    [0015] Figure 1 is an illustration of a perspective view of a thick thermoplastic composite part manufactured according to the method and apparatus described.
    [0016] Figure 2 is an illustration of a flowchart showing in general the steps of a method to manufacture thick thermoplastic composite laminated parts.
    [0017] Figure 3 is an illustration of a cross-sectional view of a stack of composite thermoplastic layers that have been laid out on a tool.
    [0018] Figure 4 is an illustration similar to that of figure three, but showing a tool displaced in the stack of layers in preparation for a pre-consolidation cycle.
    [0019] Figure 5 is an illustration similar to figure 4, but showing the layer stack having been compressed in the tool to partially consolidate the layer stack while being heated to a temperature that softens the layers.
    [0020] Figure 6 is an illustration of a diagrammatic view of continuous compression molding apparatus used to perform the described method.
    [0021] Figure 7 is an illustration of a flowchart showing the steps of a continuous compression molding method using pre-consolidation and material compaction.
    [0022] Figure 8 is an illustration of a flowchart of aircraft production and service methodology.
    [0023] Figure 9 is an illustration of an aircraft block diagram. DETAILED DESCRIPTION
    [0024] Referring first to figure 1, the described modalities refer to a method for forming a relatively thick thermoplastic composite (TCP) piece 10. In the illustrated example, piece TCP 10 is a substantially straight elongated structural element, with a generally U-shaped cross section 12 with inwardly flanged flanges 14 forming a generally open interior 16. However, the described method can be employed to form TCP structural elements with a variety of other cross-sectional shapes, as well as curvatures or contours and / or varied thicknesses along their lengths. The TCP 10 piece may comprise a laminate formed from a stack of pre-preg layers (not shown) that include a suitable thermoplastic polymer resin matrix, such as, without limitation, polyether ether ketone ("PEEK"), polyether ketone ketone ("PEKK"), polyphenylsulfone ("PPS"), polyetherimide ("PEI"), which can be reinforced with a fibrous component such as glass (type s or type e) or carbon fiber (not shown). The reinforcement fibers within each layer can be oriented in a unidirectional or non-uniform arrangement, depending on the particular application. The types, thicknesses and quantities of relative fibers in the polymer matrix, as well as the type of polymer matrix used in each layer can vary widely, based on numerous factors, including cost and the desired final physical and mechanical properties of the part 10. The composite part 10 has a "T" thickness which requires the provision of a relatively large number of layers which can be difficult to form as a single layer stack.
    [0025] Referring now to figures 2 to 5, the TCP piece 10 shown in figure 1 can be manufactured by a method starting at step 17 shown in figures 2, in which a stack of layers TCP 16 shown in figure 3 is mounted on the other surface of a suitable tool 24. The stack of layers 16 comprises a plurality of pre-preg thermoplastic layers 18 which can be arranged on top of each other either by hand or using automatic material placement equipment (not shown). As shown in figure 3, layers 18 in the layer 16 stack may not be completely flat against each other, because of undulations or other irregularities in layers 18 in their pre-preg state, resulting in waviness and / or voids or gaps. 22 between at least some of the layers 18.
    [0026] The layer stack 16 having been disposed on tool 20, the next step 19 of the method shown in figure 2 is carried out, which comprises pre-consolidating the layer stack 16 by subjecting the layer stack 16 to heat and pressure for a pre-selected time, resulting in compaction of the layer pile 16. Referring to figure 4, in preparation for the pre-consolidation step 19, a second tool 24 can be placed on the layer pile 16 and forced 26 against the layer stack 16. The tools 20, 24 shown in figure 4 can comprise conventional pressure plate tools installed in a conventional compression press (not shown). The tools 20, 24 can be specially configured to pre-consolidate the stack of layers 16, but, alternatively, the tools 20, 24 can comprise the tools that are later used to form the stack of layers 16 in the final shape of the particular part 10 to be formed. For example, tools 20, 24 may comprise matrices conjugated to curvatures, contours and other surface features that are required to form the stack of layers 16 in the final shape of part 10.
    [0027] Figure 5 illustrates the upper tool 20 having been forced 26 against the lower tool 20 to compress the stack of layers 16 using a pre-selected amount of pressure or force 26. As pressure is applied to the stack of layers 16, the layer stack 16 is heated 30 to a pre-selected temperature. Heating can be carried out by contact heating using heated tools 20, 24, or by performing the pre-consolidation cycle inside an oven. Other processes can be used to apply the necessary pressure to the layer stack 16 during the pre-consolidation cycle, such as, without limitation, vacuum bag and / or autoclave processing. During the pre-consolidation cycle that results in compaction of the layer stack 16, the layer stack 16 is heated to a "pre-consolidation temperature" in which layers 18 soften and become quickly malleable, but which is below temperature into which the thermoplastic resin in layers 18 begins to melt and flow. Softening of layers 18 when the pre-consolidation temperature has been reached allows layers 18 to level under pressure 26, substantially eliminating any void gap 22 between layers 18 (Figure 3) and partially consolidating layers 18 so that they they are firmly packaged in face-to-face contact with each other substantially throughout their areas.
    [0028] Pressure 26, pre-consolidation temperature and dwell time (the length of time the stack of layers 16 is subjected to consolidation temperature) are pre-selected and will vary with the application, including thickness of the part, part geometry, the type of thermoplastic material that is used, as well as the type and size of the reinforcement fibers. In a typical application in which a stack of 16 layers is assembled comprising 60 layers of carbon fiber pre-preg thermoplastic with a melting temperature of 350 ° C, satisfactory pre-consolidation and material compaction were achieved using a pre-temperature - 330 ° C consolidation, a pressure of 5 bars and a residence time of approximately 80 seconds. Generally, the residence time has to be sufficient to allow heat to fully penetrate layers 18 in the layer 16 stack and bring layers 18 to the pre-consolidation temperature. The part in this example was formed at a temperature of 375 ° C. It should be noted here that the example presented is merely illustrative and should not be interpreted as limiting.
    [0029] Following the aforementioned pre-consolidation cycle, the stack of layers 16 remains pre-consolidated until it is subsequently formed and fully consolidated, as shown in step 21 in figure 2. The stack of layers 16 remains pre-consolidated in because the combination of heat and pressure applied during the pre-consolidation cycle causes the layers 18 to stick together and maintain their shape. In addition, the adhesion of the layers 18 to one another reduces excess material movement during consolidation and subsequent formation processes, thereby substantially eliminating fiber distortion in the plane and outside the plane caused by excess movement of the layer material.
    [0030] The method described above can be performed as part of a continuous compression molding (CCM) process using a CCM 32 machine shown in figure 6. The CCM 32 machine can generally include a pre-consolidation zone 42, a pre-forming zone 44, and a consolidation station 48. Multiple layers 34, 36 of composite materials are supplied both with continuous rolls (not shown) and in the form of stacks (not shown) of pre-cut TPC blanks , such as the stack of layers 16 previously described. Layers 34, 36 of TPC material are fed together with leaf element forming mandrels 38 in the pre-consolidation zone 42. Guides 40 or other tool elements can be used to pre-align and guide layers 34, 36 to the zone pre-consolidation 42.
    [0031] The pre-consolidation zone 42 can include suitable tooling 45, which can be similar to the tools 20, 24 previously described, which work to compress the layers 34, 36 with each other during the pre-consolidation cycle which results in pre - consolidation and compaction of layers 34, 36. The pre-consolidation zone 42 can also include a heater 47 which is used to heat the layers 34, 36 to the pre-consolidation temperature. The heater 47 may comprise an oven in which the pre-consolidation tool 45 is contained, or it may be a device that heats the tool 45 in order to provide contact heating of layers 34, 36 while layers 34, 36 are being compressed by tooling 45. In some embodiments, it may be possible to combine the pre-consolidation zone 42 with the pre-forming zone 44, in which case the tooling used to pre-form layers 34, 36 is also used to pre-consolidate the layers before they are heated to the melting temperature in the consolidation station 48.
    [0032] Guides 40 can also be used to pre-align and guide the pre-consolidated stack of layers together with mandrels 38, as well as optional loading materials (not shown) for the pre-forming zone 44. The pre-forming layers formed 34, 36 and mandrels 38 can be passed through an oven (not shown) to raise the temperature of the layer materials in order to facilitate pre-forming operations in the pre-forming zone 44. Various features such as flanges of the part 14 (Figure 1), for example, can be preformed in the preforming zone 44 using pressure applied to layers 34, 36 by rollers 40 or other forming tools.
    [0033] The preformed part 46, which has the general shape of the final part, leaves the preform zone 44 and goes to the consolidation operation 28. The consolidation operation 48 includes a plurality of standard tool dies in the general indicated by 55, which are individually combined with tool elements (not shown) that have smooth outer surfaces fitted by standardized dies, and internal surfaces that have tool-made features. These tool-made features are checked in the preformed part 46 during the consolidation process. The common attributes of the surfaces between the standardized dies 55 and the external surfaces of the tool elements eliminate the need for matrices matched to specific parts.
    [0034] The consolidation operation 48 includes a pulsating drive mechanism 60 that moves the preformed part 46 forward in the consolidation operation 48 and out of the preforming zone 44, in continuous incremental steps. As the preformed piece 46 moves forward, the preformed piece 46 first enters a heating zone 52 that heats the preformed piece 46 to a temperature that allows free flow of the polymeric component of the resin from the matrix in layers 34, 36.
    [0035] Then, the preformed part 46 goes forward to a zone or pressing operation 54 where standardized dies 55 collectively or individually descend to pre-defined pressures sufficient to compress and consolidate (that is, allow free flow of the matrix resin) the various layers 34, 36 in the desired shape and thickness. As the dies 55 are opened, the preformed part 46 is advanced incrementally in the consolidation operation 48, after which the dies 55 are closed again, causing successive sections of the piece 46 to be compressed in different zones of temperature, and thereby consolidate the laminated layers in the compressed section. This process is repeated for each temperature zone of the dies 55 as the part 46 is advanced incrementally through the consolidation operation 48.
    [0036] The fully formed and compressed (consolidated) part 46 then enters a cooling zone 56 that is separated from the pressing zone 54, in which the temperature is brought below the free flow temperature of the resin matrix in layers 34, 36 , thereby causing the cast or consolidated part 46 to harden to its final pressed shape. The consolidated and cooled part 58 then leaves the consolidation operation 48, where the mandrels 38 are accepted in rolls 62. The final formed part 64 is removed at the end of the CCM machine 32.
    [0037] Figure 7 illustrates in general the steps of forming a TPC 10 laminated part using the aforementioned CCM 32 machine which includes pre-consolidation and compacting of the layer 16 pile before it is completely consolidated and formed. Starting at step 66, a stack of TPC layers 16 is assembled, either by pre-stacking layers or by feeding them as a stack on CCM machine 32, or separately feeding layers on machine 32, as previously described. In step 68, layers 18 in the layer stack 16 are heated to a temperature that softens them, but below the melting point of the thermoplastic resin. Softening of layers 18 is done in the pre-consolidation zone 42 (Figure 6).
    [0038] In step 70, the stack of layers 16 is compressed in the pre-consolidation zone 42, resulting in pre-consolidation of the stack of layers 16, and compaction of the layer materials. In step 72, the softened layer stack 16 is preformed in the preform zone 44, after which the preformed layer stack 16 is heated to the melting temperature of the resin, as shown in step 74. In step 76, the heated layer stack 16 is consolidated and formed into the desired part shape at the consolidation station 48. As previously mentioned, this consolidation and formation process can be done by passing the heated layer stack through conjugated matrices that compress and sequentially form the stack of layers 16 in the shape of the desired part. In step 78, the formed and consolidated part is cooled. The part is incrementally advanced, as shown in step 80, so that it progressively moves through the pre-consolidation zone 42, the pre-formation zone 44 and the consolidation station 48 in an incremental manner, dragged by the mechanism pulsing drive 60 (Figure 6).
    [0039] It should be noted here that, although a CCM process has been described for purposes of illustration, it may be possible to incorporate the pre-consolidation and compacting method described in other types of molding processes, such as, without limitation, pultrusion and roll forming.
    [0040] Modalities of the description can find use in a variety of potential applications, particularly in the transportation industry, including, for example, aerospace, marine, automotive and other applications where autoclaving of composite parts can be used. Thus, referring now to figures 8 and 9, modalities of the description can be used in the context of an aircraft manufacturing and service method 82 shown in figure 8 and an aircraft 84 shown in figure 9. Aircraft applications of the described mode can include, for example, without limitation, formation of reinforcement elements such as, without limitation, beams, wing spars and measuring devices with aerodynamic properties like sting, to name just a few. During pre-production, exemplary method 82 may include aircraft specification and design 86 prior to material acquisition 88. During production, component and subassembly manufacturing 90 and system integration of aircraft 84 take place. Then, aircraft 84 can pass certification and delivery 96 in order to be put into service 96. While in service by a customer, aircraft 84 is scheduled for routine maintenance and service 98, which may also include modification, reconfiguration, remodeling, and so on.
    [0041] Each of the method 82 processes can be performed or done by a system integrator, a third part and / or an operator (for example, 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 part may include, without limitation, any number of salespeople, subcontractors and suppliers; and an operator can be an airline, rental company, military entity, service organization, and so on.
    [0042] As shown in figure 9, aircraft 84 produced by exemplary method 82 can include a main frame 100 with a plurality of systems 102 and an interior 104. Examples of high-level systems 102 include one or more of a propulsion system 106, an electrical system 108, a hydraulic system 110 and an environmental system 112. Any number of other systems can be included. Although an aerospace example is shown, the principles of the description can be applied to other industries, such as the marine and automotive industries.
    [0043] Systems and methods designed herein may be employed during any one or more of the stages of the production and service method 82. For example, components or subassemblies corresponding to the production process 90 may be manufactured or produced in a manner similar to the components or subassemblies produced while aircraft 96 is in service. Also, one or more apparatus modalities, method modalities, or a combination of these can be used during production stages 90 and 92, for example, substantially dispatching the assembly or reducing the cost of an aircraft 84. Similarly, one or more of apparatus modalities, method modalities, or a combination thereof can be used while aircraft 96 is in service, for example, and without limitations, maintenance and service 98.
    [0044] Thus, in summary, according to a first aspect of the present invention, A1 is provided. A method for making a thick thermoplastic composite part, comprising: assembling a stack of layers including a plurality of thermoplastic composite layers; pre-consolidating the layer stack, including softening the layers by heating the layers in the layer stack to a temperature below the melting temperature of the thermoplastic and compressing the layer stack; and consolidating the pre-consolidated layer stack, including heating the layer stack to at least the melting temperature of the thermoplastic.
    [0045] A2. Also provided is the method of paragraph A1, in which compressing the stack of layers of softened layers includes applying sufficient pressure to the layers to compact the stack of layers.
    [0046] A3. Also provided is the method of paragraph A2, in which compression of the pile of layers of softened layers is done: placing the pile of layers between two tools, and forcing the tools against each other.
    [0047] A4. Also provided is the method of any of the previous paragraphs, in which compression of the pile of softened layers is done in a continuous compression molding machine.
    [0048] A5. Also provided is the method of any of the previous paragraphs, in which consolidation of the pre-consolidated layer stack is done by compacting the layer stack, and the method further comprises: forming the layer stack into a desired shape as the stack of layers is being consolidated.
    [0049] A6. Also provided is the method of any of the preceding paragraphs, in which the formation of the layer stack in the desired shape is done on a continuous compression molding machine.
    [0050] In accordance with a further aspect of the present invention, B1 is provided. A method for forming a thick thermoplastic composite part, comprising: assembling a stack of layers having a plurality of thermoplastic composite layers on top of each other; pre-consolidating the layer stack using a first set of parameters, the first set of parameters including a first pre-selected temperature, a first pre-selected pressure and a first pre-selected time interval; and consolidating the stack of pre-consolidated layers using a second set of parameters, the second set of parameters including a second pre-selected temperature, a second pre-selected pressure and a second pre-selected time interval.
    [0051] B2. Also provided is the method of paragraph B1, in which assembly of the layer stack is done by continuously feeding multiple thermoplastic composite layers in a continuous compression molding machine.
    [0052] B3. Also provided is the method of paragraph B1 or paragraph B2, in which: the first pre-selected temperature is a temperature sufficient to soften the layers, but is below the melting temperature of the thermoplastic.
    [0053] B4. Also provided is the method of any of paragraphs B1 to B3, in which the first preselected pressure is sufficient to compact the stack of layers.
    [0054] B5. Also provided is the method of any one of paragraphs B1 to B4, in which the first pre-selected time interval is sufficient to allow the layers in the layer stack to soften at the first pre-selected temperature, and to allow compaction of the layer stack at the first preselected pressure.
    [0055] B6. Also provided is the method of any of paragraphs B1 to B5, in which: the second pre-selected temperature is high enough to result in the fusion of the thermoplastic layers in the layer stack; and the second preselected pressure is high enough to completely consolidate the layer stack.
    [0056] In accordance with a further aspect of the present invention, C1 is provided. A method for molding thermoplastic composite parts by continuous compression, comprising: assembling a stack of layers including a plurality of thermoplastic pre-preg layers; compact the layer stack by heating the layers to a temperature below their melting point and compressing the layer stack; and molding the compacted layer stack into a desired part shape, including heating the layers at least at their melting point and additionally compressing the layer stack to fully consolidate the layers.
    [0057] C2. Also provided is the method of paragraph C1, in which compression of the layer stack is done: placing the layer stack between a pair of tools; and using the tools to apply a compaction pressure to the layer stack.
    [0058] C3. Also provided is the method of paragraph C2, in which layer stack compaction and layer stack molding are done on a continuous compression molding machine.
    [0059] C4. Also provided is the method of any one of paragraphs C1 to C3, in which compaction of the layer pile and molding of the pile of compacted layers are carried out substantially continuously.
    [0060] In accordance with a further aspect of the present invention, it is provided: D1. An apparatus for continuous compression molding of a thick thermoplastic composite part, comprising: a pre-consolidation zone into which a stack of layers of thermoplastic layers can be fed, the pre-consolidation zone including a heater to heat the stack of layers and pre-consolidation tooling to compress the stack of layers; and a consolidation zone including consolidation tools to consolidate and form the stack of pre-consolidated layers in the shape of the part.
    [0061] D2. The apparatus of paragraph D1 is also provided, further comprising: a pre-forming zone for pre-forming the layer stack after the layer stack has been pre-consolidated.
    [0062] D3. The apparatus of paragraph D1 or paragraph D2 is also provided, further comprising: a pulsating drive mechanism for moving the stack of layers through the pre-consolidation zone and through the consolidation zone in continuous incremental steps.
    [0063] D4. The apparatus of any one of paragraphs D1 to D3 is also provided, in which the pre-consolidation tool includes resources to preform the stack of layers.
    [0064] The description of the different illustrative modalities has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the modalities in the manner described. Many modifications and variations will be apparent to those skilled in the art. In addition, different illustrative modalities can provide different advantages compared to other illustrative modalities. The selected modality or modalities are chosen and described in order to better explain the principles of the modalities, their practical application and to enable those skilled in the art to understand the description for various modalities with various modifications that are suitable for the particular use contemplated.
    权利要求:
    Claims (8)
    [0001]
    1. Method for manufacturing a thermoplastic composite part, characterized by the fact that it comprises the steps of: assembling (66) a stack of layers (16) having a plurality of thermoplastic composite layers (18) on top of each other; pre-consolidating the layer stack, including softening the layers, heating (68) the layers in the layer stack to a pre-consolidation temperature below the melting temperature of the thermoplastic, keeping the layer stack at the pre-consolidation temperature for a pre-consolidation dwell time, and compressing (70) the layer stack at the pre-consolidation temperature; preforming (72) at least one element in the pre-consolidated layer stack at a temperature below the melting temperature of the thermoplastic so that the preformed layer stack takes on a general shape of a final piece; and consolidating (76) the preformed layer stack, including heating (74) the layer stack at least to the melting temperature of the thermoplastic.
    [0002]
    2. Method according to claim 1, characterized in that compressing the pile of layers of softened layers includes applying pressure to the layers sufficient to compact the pile of layers.
    [0003]
    3. Method, according to claim 2, characterized by the fact that compression of the pile of layers of softened layers is done: placing the pile of layers between two tools (20,24); and forcing the tools against each other.
    [0004]
    Method according to any one of claims 1 to 3, characterized in that the compression of the pile of softened layers is done in a continuous compression molding machine (32).
    [0005]
    5. Method according to any one of claims 1 to 4, characterized in that consolidation of the pre-consolidated layer stack is done by compacting the layer stack, and the method additionally comprises the steps of: forming the layer stack in a desired shape as the layer stack is being consolidated.
    [0006]
    6. Method, according to claim 5, characterized by the fact that the formation of the layer pile in the desired shape is done in a continuous compression molding machine.
    [0007]
    7. Apparatus for continuous compression molding of a thermoplastic composite part, characterized by the fact that it comprises: a pre-consolidation zone (42) in which a stack of layers (16) of thermoplastic layers (18) arranged one above the another is fed, the pre-consolidation zone including a heater (47) installed to heat the layer stack to a pre-consolidation temperature below the melting temperature of the thermoplastic and to keep the layer stack at the pre-consolidation temperature for a pre-consolidation dwell time, and pre-consolidation tooling (45) installed to compress the stack of layers at pre-consolidation temperature; a pre-forming zone (44) in which the pre-consolidated layer stack is fed, the pre-forming zone installed to act on at least one element in the pre-consolidated layer stack at a temperature below the melting temperature the thermoplastic in which the pre-formed layer stack (46) takes on a general shape of the final piece; and a consolidation zone (48) installed to heat the preformed layer stack to at least the melting temperature of the thermoplastic and including consolidation tool (55) installed to consolidate and form the preform layer stack in the form of the final piece (64).
    [0008]
    8. Apparatus according to claim 7, characterized by the fact that it additionally comprises: a pulsating drive mechanism (60) for moving the stack of layers through the pre-consolidation zone, the pre-formation zone and through the consolidation zone in continuous incremental steps.
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    同族专利:
    公开号 | 公开日
    BR112015009406A2|2017-07-04|
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    CA2886216A1|2014-05-08|
    US20160144578A1|2016-05-26|
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    PT2914415T|2020-02-14|
    KR20150079589A|2015-07-08|
    US20140117582A1|2014-05-01|
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3545370A|1968-07-01|1970-12-08|Weyerhaeuser Co|Continuous press for laminating materials|
    DE2421955A1|1974-05-07|1975-12-04|Sandco Ltd|BELT PRESS, IN PARTICULAR HYDRAULIC DOUBLE BELT PRESS, FOR CONTINUOUSLY TREATED MATERIAL|
    GB2160467B|1984-06-22|1987-09-23|Rolls Royce|Moulding of composite materials|
    GB8519297D0|1985-07-31|1985-09-04|Smith Tech Dev|Laminate production|
    DE3739611A1|1987-11-23|1989-06-01|Basf Ag|METHOD AND DEVICE FOR PRODUCING HOLLOW PROFILES FROM FIBER-REINFORCED PLASTICS|
    DE4017978C2|1990-06-05|1993-09-30|Dornier Luftfahrt|Manufacture of profiled stringers|
    US5078821A|1990-08-13|1992-01-07|The United States Of America As Represented By The United States Department Of Energy|Method and apparatus for producing composites of materials exhibiting thermoplastic properties|
    US5328744A|1990-10-09|1994-07-12|E. I. Du Pont De Nemours And Company|Panel having a core with thermoplastic resin facings|
    US5236646A|1991-02-28|1993-08-17|The United States Of America As Represented By The Secretary Of The Navy|Process for preparing thermoplastic composites|
    DE4342279C2|1993-12-11|2002-04-18|Siempelkamp Gmbh & Co Kg G|Continuous press for the production of particle board, fiberboard, laminate board and similar pressed boards|
    JP3672043B2|1994-10-13|2005-07-13|東洋紡績株式会社|Thermoplastic composite continuous molding and continuous molding method|
    US6312247B1|1999-01-29|2001-11-06|Alliant Techsystems Inc.|Vacuum debulking table for thermoplastic materials|
    EP2324999A1|2000-07-28|2011-05-25|Hypercar, Inc.|Process and equipment for manufacture of advanced composite structures|
    US7906176B2|2004-12-17|2011-03-15|Flexform Technologies, Llc|Methods of manufacturing a fire retardant structural board|
    US7249943B2|2003-08-01|2007-07-31|Alliant Techsystems Inc.|Apparatus for forming composite stiffeners and reinforcing structures|
    CA2580995C|2004-10-08|2012-12-04|Bell Helicopter Textron Inc.|Apparatus and method for ultrasonic processing of laminates|
    US7429305B2|2004-12-08|2008-09-30|Hossein Borazghi|Process and machine for producing lightweight thermoplastic composite products in a continuous manner|
    US9102103B2|2006-02-02|2015-08-11|The Boeing Company|Thermoplastic composite parts having integrated metal fittings and method of making the same|
    US8333858B2|2006-02-02|2012-12-18|The Boeing Company|Method for fabricating curved thermoplastic composite parts|
    US7807005B2|2006-02-02|2010-10-05|The Boeing Company|Fabrication process for thermoplastic composite parts|
    US8491745B2|2007-02-03|2013-07-23|The Boeing Company|Method and material efficient tooling for continuous compression molding|
    US7871553B2|2007-09-21|2011-01-18|The Boeing Company|Process for forming curved thermoplastic composite material|
    FR2929167B1|2008-03-27|2010-04-23|Airbus France|METHOD FOR MANUFACTURING FLAN OF THERMOPLASTIC COMPOSITE MATERIAL, ASSOCIATED TOOLING FOR MANUFACTURING AND APPLICATION OF PROCESS TO REALIZATION OF AIRCRAFT STRUCTURE PARTS|
    US8691137B2|2009-03-04|2014-04-08|The Boeing Company|Method of molding partus using a tool sleeve for mold die|
    GB0903805D0|2009-03-05|2009-04-22|Airbus Uk Ltd|Method of manufacturing composite parts|
    US10821653B2|2010-02-24|2020-11-03|Alexander M. Rubin|Continuous molding of thermoplastic laminates|
    US9248613B2|2012-10-30|2016-02-02|The Boeing Company|Method for forming thick thermoplastic composite structures|US9248613B2|2012-10-30|2016-02-02|The Boeing Company|Method for forming thick thermoplastic composite structures|
    GB2510340B|2013-01-30|2017-12-06|Rtl Mat Ltd|Apparatus and method for manufacturing a composite product from plural components|
    US9994008B2|2014-09-19|2018-06-12|The Boeing Company|Method and system for compacting composite part layup utilizing a single release film layer|
    US10124546B2|2015-03-04|2018-11-13|Ebert Composites Corporation|3D thermoplastic composite pultrusion system and method|
    US9616623B2|2015-03-04|2017-04-11|Ebert Composites Corporation|3D thermoplastic composite pultrusion system and method|
    US10449737B2|2015-03-04|2019-10-22|Ebert Composites Corporation|3D thermoplastic composite pultrusion system and method|
    US9963978B2|2015-06-09|2018-05-08|Ebert Composites Corporation|3D thermoplastic composite pultrusion system and method|
    KR101888358B1|2016-12-28|2018-08-14|한국국제대학교 산학협력단|Manufacturing method using pulse motion|
    US10618213B2|2017-02-17|2020-04-14|The Boeing Company|Method and apparatus for continuously fabricating a composite sandwich structure|
    US10821651B2|2017-02-17|2020-11-03|The Boeing Company|Method and apparatus for continuously fabricating a composite sandwich structure|
    US10773430B2|2017-04-25|2020-09-15|The Boeing Company|Thermoplastic composite part manufacturing system and method|
    EP3616873A4|2017-04-28|2021-01-20|Subaru Corporation|Composite-material molding tool, composite-material molding method and composite material|
    US20190210338A1|2018-01-09|2019-07-11|The Boeing Company|Thermoplastic Composite Laminate with Ultraviolet Protection and Method of Forming the Same|
    法律状态:
    2018-03-06| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2018-03-13| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2018-03-20| B06I| Technical and formal requirements: publication cancelled|Free format text: ANULADA A PUBLICACAO CODIGO 6.6.1 NA RPI NO 2462 DE 13/03/2018 POR TER SIDO INDEVIDA. |
    2020-03-24| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2021-02-02| B09A| Decision: intention to grant|
    2021-03-16| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 09/09/2013, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/663,660|2012-10-30|
    US13/663,660|US9248613B2|2012-10-30|2012-10-30|Method for forming thick thermoplastic composite structures|
    PCT/US2013/058670|WO2014070305A1|2012-10-30|2013-09-09|Method and apparatus for forming thick thermoplastic composite structures|
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