• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A film tube (45) installed and sealed in a composite part (20) serves as an internal vacuum bag (44) which eliminates the need for an internal mandrel to withstand compaction forces applied by autoclave pressure during hardening of the workpiece (20).
    公开号:FR3043586A1
    申请号:FR1660266
    申请日:2016-10-22
    公开日:2017-05-19
    发明作者:Richard Heath；Andrew Elmer Modin
    申请人:Boeing Co；
    IPC主号:
    专利说明:

    THERMO-RETRACTABLE FILM TUBE AND METHOD FOR MANUFACTURING HOLLOW COMPOSITE PARTS
    The present disclosure generally relates to the treatment of composite parts, and more particularly relates to a method of curing composite parts that are hollow or have a cavity therein.
    Composite parts that are hollow or contain cavities / recesses can be hardened using a combination of heat and pressure in an autoclave. In order to withstand autoclave pressure and prevent flattening of the workpiece, a chuck-like tool, such as an inflatable bladder packaged in a monolayer release film, is placed in the cavity. As the part hardens, the bladder is deflated to allow it to be removed from the room. The bladders used in this application are typically made of flexible, airtight materials, such as elastomers, which can degrade over time due to the high temperatures to which they are subjected during thermal curing processes.
    In other applications, airtight vacuum bags with release films have been installed inside the cavity without a backing mandrel, however this approach may not provide adequate structure to resist forces. applied compaction. In yet other applications, oversize tubular type bags have been installed on internal chucks, however this solution to the problem can lead to unacceptable results as the oversize bags fold and leave marks.
    Therefore, a method of curing composite parts that are hollow / contain cavities, which eliminates the need for a mandrel providing internal structural support to withstand applied compaction forces, is necessary. A film tube that can be installed in a room cavity that serves as a sealed interior vacuum bag that applies an autoclave compaction force to the workpiece is also required.
    The disclosed embodiments provide a method of processing composite parts, which are hollow or have cavities therein, which eliminates the need for internal mandrels which are normally required to provide structural support to withstand applied compaction forces. . An inner vacuum bag comprising a tube of film installed within the cavity is exposed to autoclave pressure during curing to apply compacting forces to the workpiece. The film tube is heat-shrunk around an installation tool, such as a mandrel, and results in a smooth, uncrimped, substantially defect-free surface on cavity walls of the workpiece. The film tube comprises a release film on the outer surface, and an impermeable barrier film on the inner surface of the tube. The release film and the barrier film may be coextruded to form a film tube having a diameter that is slightly larger than the largest cross-sectional dimension of the installation tool. Following the installation of the film tube, the installation mandrel is removed, exposing the film tube to autoclave pressure.
    According to a disclosed embodiment, a method of processing a composite part is proposed. The method includes placing a composite part on a tool having a tool cavity, applying a film to an outer surface of a mandrel, and placing the mandrel within a cavity in a cavity. the composite part. The method also includes attaching the film to walls of the tool cavity, and removing the mandrel from the cavity in the composite part. Application of the film to the outer surface of the mandrel may include sleeving a film tube on the mandrel and retracting the film onto the mandrel. Attaching the film to the walls of the cavity may include sealing opposite ends of the film tube on the tool. The method may further include sealing a vacuum bag on the composite member and attaching opposite ends of the film tube to the vacuum bag. The method may further include curing the composite member, including applying pressure in an autoclave to the film within the cavity. The application of the film includes the shrink wrapping of a release film and an impermeable barrier film on the mandrel
    According to another disclosed embodiment, a method of applying a vacuum bag to a composite part is proposed. The method includes placing the composite part on a tool having a tool cavity, applying a film to an outer surface of a mandrel, and placing the mandrel within a cavity in the composite part. The method also includes attaching the film to walls of the tool cavity, and removing the mandrel from the cavity in the composite part.
    According to an additional disclosed embodiment, a method of bagging a composite part, having a cavity therein, is provided, including applying a cavity vacuum bag to the interior surface of the cavity in a cavity. the composite part, the application of an external vacuum bag to the composite part, the sealing of the cavity vacuum bag on the external vacuum bag and a tool, and the sealing of the external vacuum bag on the tool .
    According to yet another disclosed embodiment, a method of manufacturing a composite part, having a cavity therein, is provided. The method includes placing a flexible inner bag around a mandrel, retracting the inner bag on an outer surface of the mandrel, and placing the composite part on a tool. The method also includes placing the mandrel in the cavity, sealing the inner bag on the tool, and removing the mandrel from the cavity. The method further includes sealing the outer bag on the composite member, sealing the inner bag on the outer bag, and curing the composite member in an autoclave. Placement of the flexible inner bag around a mandrel can be accomplished by wrapping the mandrel with an air impervious inner film, and wrapping the inner film with an outer release film. The placement of the flexible inner bag can be achieved by cuffing a film tube on the mandrel. Sealing of the inner bag on the tool can be achieved by sealing outer ends of the film on the tool substantially on the entire circumference of the tube. The retractable package of the inner bag can be made by applying heat to the flexible inner bag until the inner bag retracts to the mandrel surface. Sealing of the inner bag to the outer bag may be accomplished by exposing portions of an inner side of the inner bag by folding opposite ends of the inner bag, and adhering the portions of the inner side to the outer bag. Curing the workpiece can be accomplished by placing the composite workpiece and tool in an autoclave, and exposing the outer bag and inner bag to autoclave pressure.
    According to yet another disclosed embodiment, a method of manufacturing a composite rail having a cavity therein is provided. The method includes placing a composite stringer load on a tool, and installing a flexible outer film bag on the composite slurry load covering the cavity. The method further includes placing a flexible inner film bag in the cavity, and compacting the composite web load by applying pressure to the inner vacuum bag and the outer vacuum bag. Placement of the inner film bag inside the cavity can be achieved by shrink wrapping an airtight barrier film tube around the mandrel, placing the mandrel within the cavity, attaching the barrier film on the tool and removing the mandrel from the cavity. The application of pressure to the inner film bag and the outer film bag can be accomplished by placing the composite wick load and the tool in an autoclave, and subjecting the inner and outer film bags to a pressure of autoclave. The pressure can be applied using a common pressure source. Applying pressure using a common pressure source may include placing the composite slurry load in an autoclave, and subjecting the inner film bag and the outer film bag to autoclave pressure.
    According to yet another embodiment, a method of producing a vacuum bag adapted to wrap a mandrel is provided, comprising coextruding an inner film tube and an outer film tube. The coextrusion may include liquefying a barrier material, liquefying a release material, supplying the liquefied barrier material and release material to an extrusion machine, and extruding the liner material. barrier and liquefied mold release material through an extrusion die. The method may also include extruding an adhesive layer between the inner film tube and the outer film tube.
    According to another embodiment disclosed, a vacuum bag is proposed which is adapted to be sleeved on a mandrel. The vacuum bag comprises an airtight inner barrier film tube adapted to conform to the outer surface of the mandrel, and an outer take-off film tube surrounding the inner barrier film tube. The inner barrier film tube may be bonded to the outer film tube. Each of the inner barrier film tube and the outer take-off film tube is formed of heat-shrinkable materials.
    The features, functions, and advantages may be achieved independently in various embodiments of the present disclosure or may be combined in still other embodiments in which further details may be seen with reference to the following description and drawings. .
    Illustrative embodiments, however, as well as a preferred mode of use, additional objectives and advantages thereof, will be better understood by referring to the following detailed description of an illustrative embodiment of the present disclosure. when read in conjunction with the accompanying drawings, in which: Figure 1 is an illustration of a simplified block diagram of an apparatus for curing a composite part; Fig. 2 is an illustration of a perspective view of a curing tool, showing a composite web about to be placed in a cavity in the tool; Fig. 3 is an illustration of a perspective view of a film tube; Figure 4 is an illustration of a perspective view of a mandrel used to install the film tube into the tool cavity; Fig. 5 is an illustration of an end view of a mandrel having the film tube of Fig. 3 loosely threaded thereon; Fig. 6 is an illustration of the area designated by Fig. 6 in Fig. 5; Figure 7 is an illustration similar to Figure 5, but showing the film tube having been shrink wrapped on the outer surface of the mandrel; Fig. 8 is an illustration of a cross-sectional view of the tool shown in Fig. 2 after the smooth and packaged film mandrel has been installed on the tool; Fig. 9 is an illustration of a perspective view of the tool with the outer vacuum bag having been installed on the tool covering the beam; Fig. 10 is an illustration of a cross-sectional view taken along line 10-10 in Fig. 9; Fig. 11 is an illustration of a cross-sectional view taken along the line 11-11 in Fig. 9; Fig. 12 is an illustration of a schematic longitudinal view of the assembly shown in Fig. 11, in which parts are slightly exploded to show how the ends of the film tube are folded over themselves to face. to the outer bag; Fig. 13 is an illustration of the area designated in Fig. 13 in Fig. 9, with parts of the outer bag removed to reveal a folded end of the film tube, and base folds of the bar not shown for clarity; Fig. 14 is an illustration of a block diagram of the apparatus for coextruding the film tube; Fig. 15A is an illustration of a schematic side view showing how a film sheet can be rolled into a film tube; Fig. 15B is an illustration of the area designated "Fig. 15B" in Fig. 15; Fig. 16 is an illustration of an end view of the mandrel, showing the manner in which two separate film tubes can be sleeved and shrink wrapped on the outer surface of the mandrel; Fig. 17 is an illustration of a flowchart of a method of curing a composite part; Fig. 18 is an illustration of a flowchart of a method of curing a composite rail; Fig. 19 is an illustration of a flowchart of another method for curing a composite part; Fig. 20 is an illustration of a flow diagram of aircraft production and maintenance methodology; Figure 21 is an illustration of a schematic diagram of an aircraft.
    Referring to Figure 1, the disclosed embodiments relate to methods for processing a composite part 20, where the part 20 is hollow or contains one or more cavities 32, or similar recesses, which are open to the surrounding atmosphere. The methods may include, but are not limited to, compaction and / or hardening of the workpiece. During the manufacturing process, the workpiece 20 may be placed in a tool, such as a curing tool 22 in which a composite preform is cured in an autoclave (not shown). The curing tool 22 includes a tool cavity 32a formed to complement the cavity 32 in the workpiece 20. As will be described below in more detail, a flexible inner vacuum bag 44 is placed in the cavity 32 of the piece 20, and an outer bag 54 is placed on the piece 20 and sealed on the curing tool 22. The inner bag 44 is sealed by seals 60 on both the curing tool 22 and on the bag under external vacuum 54. During the hardening of the piece 20 in the autoclave, an autoclave pressure Pa is applied to the outer bag 54, which causes a compacting pressure to be applied to the piece 20 from the Outside of the tool 22. The outer bag 54 can also be emptied.
    In addition, since the cavity 32 is open to the surrounding atmosphere, an autoclave pressure Pa is also applied to the inner bag 44, causing a compaction pressure to be applied to the workpiece 20 from the inside. of the cavity 32. The inner bag 44 may, but need not be, emptied. The ability of the inner bag 44 to apply compacting pressure to the workpiece 20 avoids the need for an internal mandrel (not shown). In addition, eliminating the need for an internal mandrel reduces room variations caused by the thermal expansion of the mandrel.
    The disclosed method can be used to process a wide range of composite parts 20, formed from thermoplastic or thermosetting composite laminates. For example, Fig. 2 illustrates a preformed raw bar 20, sometimes also referred to as a smooth load 20 or a smooth preform 20, which can be placed on a curing tool 22 which is used to cure the bar 20 in an autoclave (no represent). The bar 20, sometimes referred to as a "cap bar", includes a cap section 24 formed by a cap 28 connected by webs 30 to outwardly facing flanges 26. The bar 20 may also have a base 61 (see FIGS. 8 and 10) which extends across the flanges 26. The curing tool 22 includes a cavity 32a which is formed to complement the shape of the bonnet section 24. A pair of recesses 38 in the upper portion 36 of the curing tool 22 receives respectively the flanges 26 of the heald 20. The opposite ends of the cavity 32a are open 34. The curing tool 22 maintains the preformed shape of the heald 20 during curing and resists curing forces. compaction applied to the beam during a compaction process and / or the curing process. Although a substantially straight liner 20 has been illustrated, the disclosed method may be used to compact and / or harden heddles and similar stiffeners which have one or more curves or one or more contours, Z-folds and / or fold thickness along their length.
    Referring now to FIGS. 3 to 6, the inner bag 44 may comprise a flexible film tube 45 (FIG. 3) having an inner diameter Di which is at least slightly greater than the widest cross-sectional dimension D2 (FIG. 4) a mandrel 48 used to install the film tube 45 in the smooth cavity 32 (Figure 2). The film tube 45 has open ends 46 and a length L1B which is greater than the length Lm (Fig. 12) of the mandrel 48.
    As best seen in Fig. 6, the film tube 45 includes an outer demold film layer 50, and an inner barrier film layer 52. The total thickness of the film tube 45 will vary with the application, and depends on the thicknesses fi, t2 of the film layers 50, 52 respectively. The outer mold release film layer 50 may comprise any suitable heat-shrinkable material commonly used as a release film, such as, without limitation, FEP (fluorinated ethylene-propylene), ETFE (ethylene-tetrafluoroethylene) or PTFE (polytetrafluoroethylene). The inner barrier film layer 52 may comprise any suitable heat-shrinkable air-impervious material commonly used as vacuum bags, including but not limited to, "nylon" (registered trademark) and polyethylene . As will be described below in more detail, the film tube 45 may be produced by coextruding the release film material and the barrier film material, however other manufacturing techniques may be employed.
    In use, the film tube 45 is sleeved to the mandrel 48 or other suitable installation tool having a cross-sectional shape that is complementary to the cross-sectional shape of the workpiece cavity 32 in which the inner bag 44 must be installed. In the present example, the mandrel 48 may comprise an inflatable bladder having a trapezoidal cross-sectional shape that is complementary to the cavity 32 in the rail 20. After the sleeving of the film tube 45 on the mandrel 48, as shown in FIG. In Figure 5, heat H is applied to the film tube 45, as shown in Figure 7, causing it to retract into and take on the shape of the outer surface 55 of the mandrel 48. The heat It can be applied using any suitable technique, such as using hot air guns or heat lamps to direct heat onto the film tube 45, or by placing the mandrel 48 in a furnace (not shown). ).
    Next, with reference to Fig. 8, a preformed (not completely hardened) green composite web 20 is placed on the tool 22, and the mandrel 48, having the film tube 45 retracted on its outer surface 55, is placed in Thus, one or more base pleats 53 may be placed 57 over the wrapped mandrel of film 48 and the flanges 26. The base plies 53 form a base 61 on the stringer 20 which extends transversely from the outer edge of one of the flanges 26 to the outer edge of the other flange 26, and substantially the entire length of the beam 20. The mandrel 48 provides an internal structure which maintains the shape of the film tube 45, with the barrier film layer 50 in face-to-face contact with the cap 28, the webs 30 and the base plies 53 of the rail 20, until the film tube installation process has been completed. completed.
    Referring now to Figures 9 to 13, as mentioned before, and as best seen in Figure 12, the length Lpr of the film tube 45 is greater than the length Lm of the mandrel 48, therefore the ends The outer ends 58 of the film tube 45 are folded on themselves such that a portion 65 of the barrier film layer 52 at each end and over the entire circumference of the film tube 45 face walls 22a (Figures 12 and 13) of the tool 22 and the external vacuum bag 54. An adhesive seal 60, which may include, for example, and without limitation, an adhesive sealing tape is applied between the barrier film layer portions 65 and the tool 22 and outer vacuum bag walls 22a, thereby forming a substantially airtight seal between the f tube ilm 45 and both the outer vacuum bag 54 and the tool 22. Optionally, spacer tools 68 may be temporarily installed 70 in the ends of the film tube 45 to prevent the outer ends 58 of the tube film 45 to flatten when the outer ends 58 are folded on themselves. In fact, the film tube 45 forms an inner vacuum bag 44 which is sealed to both the outer vacuum bag 54 and the tool 22. A seal 56 is installed between the outer vacuum bag 54 and tool 22, which seals the bag under external vacuum 54 on its entire periphery on the upper portion 36 (Figure 2) of the tool 22.
    With the inner vacuum bag 44 having been installed inside the smooth cavity 32 and sealed on both the tool 22 and the outer bag 54, the mandrel 48 is removed by sliding it through one of the ends. When the mandrel 48 comprises an inflatable bladder, the bladder is deflated to facilitate the easy removal of the bladder. Depending on the construction of the mandrel 48, a lubricant may be applied to the mandrel 48 to allow the mandrel 48 to slide on the surface of the inner bag 44 during the removal process. The assembly of the tool 22, the rail 20 and the inner and outer bags 44, 54 is placed in an autoclave (not shown) where the rail 20 is subjected to an autoclave pressure PA (see FIGS. 1 and 11). . As the ends of the inner bag 44 are opened, an autoclave pressure PA is applied in the open interior 62 (FIGS. 11 and 13) of the inner bag 44. The applied autoclave pressure PA causes the inner bag 44 to maintain its without requiring an internal structure, such as a pressurized bladder or other pressurized system other than the autoclave, while applying a compaction force on the cap 28 and the webs 30. Pressure in an autoclave PA is also applied on the outer vacuum bag 54 which ensures that the flanges 26 of the arm 20 are compacted against the upper part 36 of the tool 22.
    As mentioned before, the inner and outer film layers 52, 50 of the film tube 45 may be coextruded. For example, with reference to Fig. 14, a liquefied barrier film material 76 and a liquefied mold release film material 80 may be provided to an extrusion machine 72 which extrudes these materials through an extrusion die 74 producing a double-layered film tube 45 of any desired length. During extrusion, the two films bind together, and form a single film.
    Depending on the melt compatibility of the extruded materials, it may be necessary or desirable to extrude an adhesive 78 between the two film layers 50, 52 to adhere to each other. Various other methods and machines can be used to produce the film tube 45 including, but not limited to, injection molding and compression molding processes and the like.
    FIG. 15A illustrates another possible technique for producing the film tube 45 in which a flat sheet 82 of material is rolled onto the surface of a cylindrical mandrel 84. The flat sheet 82 may comprise two layers of film 50, 52 (FIG. 15B) which adhere to each other through an adhesive layer (not shown). In one embodiment, the ends of the flat sheet 82 may be rolled over one another to form an overlapped seal (not shown) while in another embodiment both ends of the flat sheet may be joined together using any suitable method to form an end-to-end joint (not shown). Other types of joints may be possible.
    It may also be possible to form the film tube 45 using a technique illustrated in Figure 16 in which two separate film tubes 86, 88, respectively comprising a release film and a barrier film, are separately shrink wrapped on mandrel 48. In some embodiments, the inner film tube 88 may be heat-shrunk onto the mandrel 48, and the outer film tube 86 may be installed by wrapping and adhesively adhering a sheet of film to the tube In still other embodiments, the inner film tube 88 may be formed by wrapping a film sheet around the mandrel 48, and then heat shrinking the outer film tube 86 around it. of the inner film tube 88. Fig. 17 generally illustrates the general steps of a method of curing a composite part 20. At 90, a composite part 20 is t is placed on a tool 22 having a tool cavity 32a. At 92, a film 45 is applied to the outer surface 55 of a mandrel 48, such as by cuffing a film tube 45 on the mandrel 48 and then shrink-wrapping the film tube 45 on the surface of the mandrel 48. 93, the mandrel 48 having the film tube 45 shrink wrapped thereon is placed inside a cavity 32 in the composite part 20. At 94, the film 45 is attached to a tool bag inside the tool cavity 32a, as by adhesively sealing it to the walls. At 96, the mandrel 48 is removed from the cavity 32a while the film 45 remains inside the cavity 32a attached to the cavity walls. At 98, the composite part 20 is cured.
    Figure 18 generally illustrates the general steps of a method of manufacturing a composite rail 20. At 91, a composite rail preform 20 is placed on a tool 22 and, at 93B, an external vacuum bag 54 is installed on the rail 20, covering a cavity 32 in the rail 20. At 95, an inner vacuum bag 44 is placed inside the cavity 32. At 97, the rail 20 is compacted by applying a pressure on the vacuum bag 44 inside and outside vacuum bag 54.
    Figure 19 illustrates another method of curing a composite part 20. At 100, an inner vacuum bag 44 is formed using any of several techniques. For example, at 102, a single coextruded double-layered film tube 45 may be sleeved on a mandrel 48. Alternatively, two film layers 50, 52 may be wrapped around the mandrel 48 to 104 or 106 two separate film tubes 86, 88 may be sleeved on the mandrel 48. Then, at 108, the inner bag 44 is heat-shrunk onto the mandrel 48. At 110, a composite part preform 20 is placed on the tool 22, and, at 112, the film covered mandrel 48 is placed in the cavity 32 inside the composite part 20. At 114, the inner bag 44 is sealed to the tool 22. At 116, a bag under Outside vacuum 54 is installed on the composite part 20, and at 118, the inner vacuum bag 44 is sealed to the outer vacuum bag 54. At 120, the outer vacuum bag 54 is emptied and, at 122, the coin composite 20 is cured in an autoclave where an autoclave pressure PA is applied to the workpiece 20 through its indoor and outdoor exterior 44, 54.
    Embodiments of the disclosure can be used in a variety of potential applications, particularly in the transportation industry, including for example, aerospace, naval, automotive and other applications where elongated composite members, such as stiffeners, can be used. Thus, with reference now to Figures 20 and 21, embodiments of the disclosure may be used in the context of an aircraft manufacturing and maintenance process 124, as shown in Figure 20. and an aircraft 126, as shown in FIG. 21. Aircraft applications of the disclosed embodiments may include, for example, without limitation, composite spars, beams, and composite beams. During the pre-production, an illustrative method 124 may include the specification and design 128 of the aircraft 126 and the material supply 130. During production, the manufacture of components and subassemblies 132 and the system integration 134 of FIG. the aircraft 126 take place. After that, the aircraft 126 may go through the certification and delivery 136 to be put into service 138. While in service by a customer, the aircraft 126 may be scheduled for maintenance and servicing. 140 currents, which may also include modification, reconfiguration, refurbishment, and so on. Components and composite parts produced according to the disclosed embodiments may be used in any of component and subassembly manufacturing 132, system integration 134, commissioning 138, and during maintenance and service. the interview 140.
    Each of the steps of the method 124 may be performed or executed by a system integrator, a third party, and / or an operator (eg, a customer). For purposes of this disclosure, a system integrator may include, without limitation, any number of aircraft manufacturers and major system subcontractors; a third party may include, without limitation, any number of vendors, subcontractors, and suppliers; and an operator may include an airline, a rental company, a military entity, a maintenance organization, and so on.
    As shown in Fig. 21, the aircraft 126 produced by the illustrative method 124 may include a cell 142 with a plurality of systems 144 and an interior 146. Examples of high level systems 144 include one or more of a system propulsion system 148, an electrical system 150, a hydraulic system 152 and an environmental system 154. Any number of other systems may be included. Although an aerospace example is represented, the principles of disclosure can be applied to other industries, such as the naval and automotive industries. Composite parts produced according to the disclosed embodiments may be used in the cell 142 or in the interior 146.
    Systems and methods embodied herein may be employed during any one or more of the stages of the production and maintenance process 124. For example, components or subassemblies corresponding to the production process 136 may be manufactured or produced from similar to components or subsets produced while the aircraft 126 is in service. Also, one or more apparatus embodiments, process embodiments, or a combination thereof, may be used during production stages 132 and 134, for example, substantially accelerating assembly or reducing the cost of an aircraft 126. Similarly, one or more of aircraft embodiments, process embodiments, or a combination thereof, may be used while the aircraft 126 is in operation. service, for example and without limit, for maintenance and upkeep 140.
    As used herein, the phrase "at least one of", when used with a list of items, means that different combinations of one or more of the items listed may be used. and only one of each item in the list may be needed. For example, "at least one of Article A, Article B, and Article C" may include, without limitation, Article A, Article A and Article B, or Article B. This example may also include Article A, Article B, and Article C or Article B and Article C. The article may be a particular object, a thing, or a particular category. In other words, at least one of them means that any combination of items and any number of items can be used, from the list, but not all items in the list are needed. .
    Thus, in summary, according to a first aspect of the present invention, is proposed:
    Al. A method of processing a composite part (20), comprising: placing a composite part (20) on a tool (22) having a tool cavity (32a); applying a film (52) to an outer surface (55) of a mandrel (48); placing the mandrel (48) within a cavity (32) in the composite part (20); attaching the film (52) to walls (22a) of the tool (22) within the tool cavity (32a); and removing the mandrel (48) from the cavity (32) in the composite part (20). A2. The method of paragraph A1 is also provided, wherein the application of the film (52) to the outer surface (55) of the mandrel (48) includes: the sleeving of a film tube (45) on the mandrel (48) and retracting the film (52) on the mandrel (48). A3. The method of paragraph A2 is also provided wherein the attachment of the film (52) to the walls (22a) of the cavity (32a) includes sealing opposite ends (46) of the film tube (45) on the tool (22). A4. The method of paragraph A2 is also provided, further comprising: sealing a vacuum bag (54) on the composite member (20); and attaching opposite ends (46) of the film tube (45) to the vacuum bag (54). AT 5. The method of paragraph A1 is also provided, further comprising: curing the composite part (20), including applying an autoclave pressure (Pa) on the film (52) within the cavity ( 32). A6. The method of paragraph A1 is also provided, wherein the application of the film (52) includes the shrink wrapping of a release film (50) and an impermeable air barrier film (52) on the mandrel (48). According to a further aspect of the present invention is proposed:
    Bl. A method of applying a vacuum bag (44) to a composite part (20), comprising: placing the composite part (20) on a tool (22) having a tool cavity (32a) ; applying a film (52) to an outer surface (55) of a mandrel (48); placing the mandrel (48) within a cavity (32) in the composite part (20); attaching the film (52) to walls (22a) of the tool cavity (32a); and removing the mandrel (48) from the cavity (32) in the composite part (20).
    According to a further aspect of the present invention is proposed:
    A method of bagging a composite part (20) having a cavity (32) therein, comprising: applying a cavity vacuum bag (44) to an interior surface of the cavity ( 32) in the composite part (20); applying an outer vacuum bag (54) to the composite member (20); sealing the cavity vacuum bag (44) on the outer vacuum bag (54) and on a tool (22); and sealing the outer vacuum bag (54) on the tool (20).
    According to a further aspect of the present invention is proposed:
    Dl. A method of manufacturing a composite part (20) having a cavity (32) therein, comprising: placing a flexible inner bag (44) around a mandrel (48); shrink wrapping the inner bag (44) on an outer surface (55) of the mandrel (48); placing the composite part (20) on a tool (22); placing the mandrel (48) in the cavity (32); sealing the inner bag (44) on the tool (22); removing the mandrel (48) from the cavity (32); sealing an outer bag (54) on the composite piece (20); sealing the inner bag (44) on the outer bag (54); and curing the composite part (20) in an autoclave. D2. The method of paragraph D1 is also provided, wherein placing the flexible inner bag (44) around the mandrel (48) includes: wrapping the mandrel (48) with an air impervious inner film (52), and wrapping the inner film (52) with an outer demolding film (50). D3. The method of paragraph D1 is also provided, wherein the placement of the flexible inner bag (44) includes the sleeving of a film tube (45) on the mandrel (48). D4. The method of paragraph D3 is also provided, wherein sealing of the inner bag (44) on the tool (22) includes sealing outer ends (58) of the film tube (45) on the tool (22) substantially on an entire circumference of the film tube (45). D4. The method of paragraph D1 is also provided, wherein the shrink wrap of the inner bag (44) includes applying heat to the flexible inner bag (44) until the inner bag (44) retracts onto the surface (55) of the mandrel (48). D5. The method of paragraph D1 is also provided, wherein the sealing of the inner bag (44) on the outer bag (54) includes: exposing portions (65) of an inner face of the inner bag (44) by folding opposing ends (58) of the inner bag (44), and adhering the portions (65) of the inner face to the outer bag (54). D6. The method of paragraph DI is also provided, wherein the curing of the composite part (20) includes: placing the composite part (20) and tool (22) in an autoclave, and exposing the outer bag (54) and the inner bag (44) at autoclave pressure (AP).
    According to a further aspect of the present invention is proposed:
    A method of manufacturing a composite rail (20) having a cavity (32) therein, comprising: placing a composite rail load (20) on a tool (22); installing a flexible outer film bag (54) on the composite stringer load (20) covering the cavity (32); placing a flexible inner film bag (44) in the cavity (32); and compacting the composite stringer load (20) by applying pressure (PA) to the inner film bag (44) and the outer film bag (54). E2. The method of paragraph E1 is also provided, wherein placing the inner film bag (44) within the cavity (32) includes: shrink wrapping a barrier film tube impervious to air (52) around mandrel (48), placement of mandrel (48) within cavity (32), attachment of barrier film tube (52) to tool (22) and removing the mandrel (48) from the cavity (32). E3. The method of paragraph E1 is also provided wherein the application of a pressure (PA) to the inner film bag (44) and the outer film bag (54) is performed by placing the composite stringer load (20). and the tool (22) in an autoclave, and subjecting the inner and outer film bags (44, 54) to autoclave pressure (AP). E4. The method of paragraph E1 is also provided, wherein the application of a pressure (PA) is performed using a common pressure source. E5. The method of paragraph E4 is also provided, wherein the application of a pressure (PA) using a common pressure source includes: placing the composite stringer load (20) in an autoclave, and submitting the bag inner film (44) and outer film bag (54) at autoclave pressure (Pa).
    According to a further aspect of the present invention is proposed:
    A method of producing a vacuum bag (44) adapted to wrap a mandrel (48), comprising: coextruding an inner film tube (52) and an outer film tube (50); ). F2. The method of paragraph F1 is also provided, wherein the coextrusion includes: liquefying a barrier material (76), liquefying a release material (80), providing barrier materials (76) and material process (80) liquefied at an extrusion machine (72), and extrusion of the liquefied barrier materials (76) and mold release material (80) through an extrusion die (74). F3. The method of paragraph F1 is also provided, further comprising: extruding an adhesive layer (70) between the inner film tube (52) and the outer film tube (50).
    According to a further aspect of the present invention is proposed:
    Gl. A vacuum bag (44) adapted to be sleeved on a mandrel (48), comprising: an air impervious inner barrier film tube (52) adapted to fit the mandrel (48); and an outer take-off film tube (50) surrounding the inner barrier film tube (52). G2. The vacuum bag (44) of paragraph G1, wherein the inner barrier film tube (52) is bonded to the outer film tube (50). G3. The vacuum bag (44) of paragraph G1, wherein each of the inner barrier film tube (52) and the outer take-off film tube (50) is formed of heat-shrinkable materials (76, 80).
    The description of the various illustrative embodiments has been presented for illustrative and descriptive purposes, and is not intended to be exhaustive or limited to the embodiments of the disclosed form. Many modifications and variations will be obvious to the ordinary person skilled in the art. In addition, various illustrative embodiments may provide different advantages over other illustrative embodiments. The selected embodiment or embodiments are selected and described to best explain the principles of the embodiments, the practical appuecation, and to enable other ordinary persons of the art to understand the disclosure, for various purposes. embodiments with various modifications, as appropriate for the particular use envisaged.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    A method of processing a composite part (20), comprising: placing a composite part (20) on a tool (22) having a tool cavity (32a); applying a film (52) to an outer surface (55) of a mandrel (48); placing the mandrel (48) within a cavity (32) in the composite part (20); attaching the film (52) to walls (22a) of the tool (22) within the tool cavity (32a); and removing the mandrel (48) from the cavity (32) in the composite part (20).
    [2" id="c-fr-0002]
    The method of claim 1, wherein applying the film (52) to the outer surface (55) of the mandrel (48) includes: cuffing a film tube (45) on the mandrel (48), and retracting the film (52) onto the mandrel (48).
    [3" id="c-fr-0003]
    The method of any of the preceding claims, wherein the attachment of the film (52) to the walls (22a) of the cavity (32a) includes sealing opposite ends (46) of the film tube (45). on the tool (22).
    [4" id="c-fr-0004]
    The method of any of the preceding claims, further comprising: sealing an outer vacuum bag (54) on the composite member (20); and attaching opposite ends (46) of the film tube (45) to the outer vacuum bag (54).
    [5" id="c-fr-0005]
    The method of any of the preceding claims, further comprising: curing the composite part (20), including applying autoclave pressure (Pa) to the film (52) within the the cavity (32).
    [6" id="c-fr-0006]
    The method of any of the preceding claims, wherein the application of the film (52) includes the shrink wrap of a release film (50) and an air impermeable barrier film ( 52) on the mandrel (48).
    [7" id="c-fr-0007]
    An inner vacuum bag (44) adapted to be sleeved on a mandrel (48) according to the method of any one of claims 1 to 6, comprising: an airtight inner barrier film tube (52) adapted to fit the mandrel (48); and an outer take-off film tube (50) surrounding the inner barrier film tube (52).
    [8" id="c-fr-0008]
    The inner vacuum bag (44) of claim 7, wherein the inner barrier film tube (52) is bonded to the outer film tube (50).
    [9" id="c-fr-0009]
    The interior vacuum bag (44) of claim 7 or claim 8, wherein each of the inner barrier film tube (52) and the outer take-off film tube (50) is formed of heat-shrinkable materials (76). , 80).
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    同族专利:
    公开号 | 公开日
    US10293552B2|2019-05-21|
    RU2016133881A|2018-02-21|
    FR3043586B1|2021-02-26|
    RU2664999C2|2018-08-24|
    US20170136687A1|2017-05-18|
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    法律状态:
    2017-10-25| PLFP| Fee payment|Year of fee payment: 2 |
    2018-10-25| PLFP| Fee payment|Year of fee payment: 3 |
    2019-03-08| PLSC| Publication of the preliminary search report|Effective date: 20190308 |
    2019-10-25| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-26| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-25| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/943,516|US10293552B2|2015-11-17|2015-11-17|Heat shrinkable film tube and method for manufacturing hollow composite parts|
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