Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
  • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
  • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
  • B29C70/28—Shaping operations therefor
  • B29C70/40—Shaping or impregnating by compression not applied
  • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
  • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
  • B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
  • B29C33/00—Moulds or cores; Details thereof or accessories therefor
  • B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
  • B29C33/48—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
  • B29C33/50—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling elastic or flexible
  • B29C33/505—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling elastic or flexible cores or mandrels, e.g. inflatable
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
  • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
  • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
  • B29C70/28—Shaping operations therefor
  • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
  • B29C70/544—Details of vacuum bags, e.g. materials or shape
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
  • B29D99/00—Subject matter not provided for in other groups of this subclass
  • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
  • B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
  • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
  • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
  • B29L2031/00—Other particular articles
  • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
  • B29L2031/3076—Aircrafts
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/40—Weight reduction

Definitions

• This disclosure generally relates to manufacturing composite parts, and deals more particularly with a method and apparatus for co-curing composite skins and stiffeners in an autoclave.
• a composite skin may be compressed against and co-cured with multiple stiffeners having a hat shaped cross-section using a vacuum bag and autoclave pressure.
• the bladders may be vented to the autoclave environment so that the internal pressure in the bladders is substantially that applied by the autoclave.
• One technique for venting the bladders is to place holes in the bladders which are vented through the vacuum bag. Venting the bladders through the vacuum bag increases the possibility of leakage into the bag, and can also lead to undesirable pre-loading of vent pipes, as well as potential distortion of fiber stiffeners during curing, and possible resin starvation issues.
• the disclosed embodiments provide a method and apparatus for distributing autoclave pressure to an array of a bladders in order to compact fiber reinforced resin stiffeners during an autoclave cure cycle.
• a manifold system distributes autoclave pressure to the bladders through vent tubes which pass through a reusable vacuum bag at locations outside of area of the bag that overlies the parts being cured. The number of penetrations of the bag for venting purposes is reduced by venting more than one bladder through each vent tube.
• the manifold system may comprise a plurality of removable manifold boxes arranged end-to-end that may be reconfigured to suit the number of bladders requiring venting. Pre-loading of the vent tubes is avoided, and potential distortion of fibers and/or resin starvation is substantially reduced, or eliminated
• apparatus for autoclave curing composite stiffeners against a composite skin.
• the apparatus comprises a tool having a tool surface on which a composite skin may be placed, and at least one channel adapted to have a composite stiffener placed therein beneath the skin; at least one pressurizable bladder adapted to be placed inside the channel for reacting autoclave pressure applied to the stiffener; a vacuum bag adapted to be sealed over the tool for compacting the skin against the stiffener; and a manifold system coupled with the bladder for pressurizing the bladder using autoclave pressure, the manifold system including a vent tube passing through the vacuum bag and exposed to autoclave pressure.
• the bag may be a reusable bag and is attached to the frame.
• the bladder includes a vent fitting on one end thereof, and the manifold system is coupled with the vent fitting.
• the manifold system includes a manifold box, and the vent tube is mounted on the manifold box and coupled with the vent fitting.
• the manifold box includes a top wall located beneath and in contact with the vacuum bag when the vacuum bag is sealed over the tool, and the vent tube passes through the top wall.
• the apparatus may further comprise a seal between the vacuum bag and the vent tube.
• the manifold system and the vent tube are located along a side of the tool, and the vacuum bag is adapted to be sealed to the vent tube.
• an apparatus for autoclave curing of a plurality of composite stiffeners and a composite skin.
• the apparatus comprises a tool adapted to have a composite skin placed thereon, the tool including a plurality of channels therein, each of the channels adapted to have a composite stiffener placed therein and contact with the skin.
• the apparatus further comprises a bag adapted to be placed over the skin and exposed to autoclave pressure for compacting the skin against the stiffeners, and a plurality of bladders respectively adapted to be placed within the stiffeners for reacting autoclave pressure applied to the stiffeners through the vacuum bag.
• the apparatus also includes a manifold system located along one end of the tool channels and disposed beneath the bag for coupling the bladders with autoclave pressure.
• the manifold system includes a manifold box having a top wall adapted to be engaged by the bag, a vent tube passing through the top wall of the manifold box and through the bag, and lines coupling the vent tube with ends of the bladders.
• the apparatus may further comprise a seal between the vent tube and the bag for sealing the bag to the vent tube, as well as a frame, and clamps for clamping the periphery of the bag between the tool and the frame.
• the manifold system is located inside of the sealed periphery of the bag.
• Each of the bladders is elongate and includes a vent fitting on one end thereof, and the manifold system is releasably coupled with each of the vent fittings.
• the manifold system includes a plurality of manifold boxes arranged end-to- end and each having a top, a plurality of vent tubes respectively passing through the tops of the manifold boxes and through the bag.
• the vent tubes are coupled with ends of the bladders and are sealed to the bag.
• a method is provided of co-curing composite stiffeners and a skin within an autoclave.
• the method comprises placing the uncured stiffeners on a tool, placing bladders respectively in the uncured stiffeners, placing an uncured skin over the tool and in contact with the stiffeners, coupling the bladders with a manifold, sealing a bag over the tool and the manifold, venting the manifold to autoclave pressure through the bag, and pressurizing the bladders using autoclave pressure through the manifold.
• Coupling the bladders with the manifold includes coupling the ends of the bladders with a vent tube exposed to the autoclave pressure. Sealing the bag includes sealing the bag around the vent tube.
• Coupling the bladders with the manifold includes coupling the ends of multiple ones of the bladders with the vent tube. Sealing the bag includes placing a frame over the bag and the tool, and clamping the bag between the frame and the tool.
• the manifold may include a plurality of manifold boxes and the method may further comprise placing the manifold boxes end-to-end on the tool and along one end of the bladders, and coupling each of the manifold boxes with a plurality of the bladders.
• a method of distributing the pressure applied to composite parts during autoclave curing of the parts.
• the method comprises placing the composite parts on a tool, placing bladders within the parts to react autoclave pressure, arranging multiple manifold boxes along one side of the tool, coupling each of the manifold boxes to at least one of the bladders, sealing a vacuum bag over the tool and the manifold boxes, and venting each of the manifold boxes through the vacuum bag.
• venting each of the manifold boxes through the vacuum bag includes passing vent tubes through the vacuum bag and sealing each of the vent tubes to the vacuum bag.
• Coupling each of the manifold boxes to at least one of the bladders includes using a quick disconnect to connect a manifold line to a vent inlet fitting on the bladder.
• Figure 1 is an illustration of a top perspective view of a stiffened composite skin.
• Figure 2 is an illustration of a bottom perspective view of the stiffened skin shown in Figure 1 , revealing stiffeners that are co-cured with the skin in an autoclave.
• Figure 3 is an illustration of a perspective view of a hat type stiffener that may be used to stiffen the skin shown in Figures 1 and 2.
• Figure 4 is an illustration of a portion of a blade type stiffener.
• Figure 5 is an illustration of a functional block diagram of apparatus for co-curing a skin and stiffeners in an autoclave.
• Figure 6 is an illustration of a top perspective view of one embodiment of the apparatus shown in Figure 5.
• Figure 7 is an illustration of a bottom perspective view of the apparatus shown in Figure 6, the tool and tool base not shown for clarity.
• Figure 8 is an illustration of a sectional view taken along the line 8-8 in Figure 6.
• Figure 9 is an illustration of a top perspective view of a tool forming part of the apparatus shown in Figures 5-8.
• Figure 10 is an illustration of a bottom perspective view of the apparatus shown in Figures 5-8, also showing the tool.
• Figure 1 1 is an illustration of an exploded perspective view of the bottom tool shown in Figure 10.
• Figure 12 is an illustration of a perspective view of an array of stiffeners used to stiffen the skin shown in Figures 1 and 2.
• Figure 13 is an illustration of a perspective view of an array of bladders respectively placed in the stiffeners shown in Figure 12 during autoclave curing.
• Figure 14 is an illustration of a perspective, end view of one of the bladders shown in Figure 13, illustrating the bladder vent fitting.
• Figure 15 is an illustration of a perspective view of the apparatus, the frame and vacuum bag removed for clarity to reveal the location of the stiffeners and the bladders.
• Figure 16 is an illustration of a perspective view of one of the manifold boxes forming part of the manifold system.
• Figure 17 is an illustration of a sectional view taken along the line 17-17 in Figure 16.
• Figure 18 is an illustration similar to Figure 16, but showing the cover of the manifold box having been removed, the connecting hoses for the fittings not shown for clarity.
• Figure 19 is an illustration of a sectional view taken along the line 19-19 in Figure 6, the connecting hoses between the fittings not shown for clarity.
• Figure 20 is an illustration of an isometric view of a portion of one of the manifold boxes with the cover removed to reveal a vent tube and two adjoining manifold fittings.
• Figure 21 is an illustration of a flow diagram of a method of co-curing a composite skin and stiffeners in an autoclave.
• Figure 22 is an illustration of a flow diagram of aircraft production and service methodology.
• Figure 23 is an illustration of a block diagram of an aircraft.
• the disclosed embodiments relate to a method and apparatus for fabricating a fiber reinforced, composite laminate skin 30 stiffened with composite laminate stiffeners 32 which are co-cured with the bottom side 34 of the skin 30.
• the skin 30 and the stiffeners 32 are laid up and formed to shape, as required, and then co-cured in an autoclave (not shown in Figures 1 and 2).
• the stiffeners 32 sometimes referred to as stiffener ribs, may be any of several well-known types.
• the stiffeners 32 may be a hat shaped stiffener 32 having a hat section 36 and a flange section 38 that is attached to the bottom side 34 of the skin 30 during the co- curing process.
• Figure 4 illustrates another type of stiffener 32a referred to as a blade stiffener 32a having a blade or web section 40 and a flange section 38.
• the apparatus 42 broadly comprises a tool 46 over which a reusable vacuum bag 48 may be sealed.
• the tool 46 is configured to have a plurality of uncured composite stiffeners 32, sometimes referred to as stiffener charges, placed therein.
• a bladder 52 is placed inside each of the stiffeners 32 in order to react compaction pressure applied by the autoclave 44 and by the vacuum bag 48.
• An uncured composite skin (not shown in
• FIG 5 is placed on the tool 46, overlying and in contact with the flange sections 38 of the uncured stiffeners 32.
• a vacuum system 63 coupled with the apparatus 42 is used to draw a vacuum within the vacuum bag 48 in order to draw the vacuum bag 48 down against the skin 30, compacting the skin 30 against the flange sections 38 ( Figures 3 and 4) of the stiffeners 32 during the curing process.
• a manifold system 54 is coupled 47 with each of the bladders 52.
• the manifold system 54 includes one or more manifold boxes 57 which may be arranged end-to- end along one side 65 of the tool 46, spaced slightly from the ends of the bladders 52.
• Each of the manifold boxes 57 is positioned beneath the vacuum bag 48 during a curing cycle, and includes a vent tube 56 that extends upwardly through the vacuum bag 48 at a location that is outside of the boundaries of the tool 46.
• the vent tubes 56 extends into the environment of the autoclave 44, allowing autoclave pressure to be internally applied to the bladders 52; in other words, the manifold system 54 equalizes the pressure between environment of the autoclave 44 and the internal volume of the bladders 52. Attention is now directed to Figures 6, 7, 8 which illustrate additional details of the apparatus 42.
• the apparatus 42 broadly comprises a frame assembly 50 to which a reusable vacuum bag 48 is attached.
• the vacuum bag 48 may comprise, for example and without limitation, an elastomer or other material that may withstand repeated pressure cycling and reuse.
• the frame assembly 50 comprises a generally rectangular outer frame 53 formed of rigid material such as a metal, and reinforcing cross frame members 51 attached to the outer frame 53.
• the vacuum bag 48 may be attached to the outer frame 53 and covers the entire area of both the tool 46 and the manifold system 54.
• the frame assembly 50 may also include handles 59 as well as clamps 58 around the periphery of the outer frame 53. The handles 59 allow the frame assembly 50, along with the vacuum bag 48, to be manually lifted away to permit loading and unloading of the skin 30 and the stiffeners 32 (not shown in Figures 6- 8).
• the outer frame 53 may be also provided with guides 62 order to aid assembly alignment when the frame assembly 50 is lowered down over the tool 46 ( Figure 5).
• the vacuum bag 48 includes a peripheral flat bag edge 64 that is adapted to be clamped against a tool base plate 68 by a clamping plate 67 forming part of the frame assembly 50. Actuation of the clamps 58 load the outer frame 53 against the tool 46, thus clamping plate 67 against the peripheral flat bag edge 64 to create a vacuum tight seal between the vacuum bag 48 and the tool 46.
• vent tubes 56 are arranged along one side 65 of the vacuum bag 48 and pass upwardly through openings in the vacuum bag 48 defined by circular, vent tube ring seals 60.
• the vent tube ring seals 60 slidably receive the vent tubes 56 when the frame assembly 50 is lowered down onto the tool 46 in preparation for a curing cycle, and form a substantially vacuum tight peripheral seal between the vacuum bag 48 and the vent tubes 56.
• One or more vacuum line fittings 66 may be provided to connect the interior of the vacuum bag 48 with a suitable vacuum system 63 ( Figure 3) in order to evacuate the vacuum bag 48, causing the vacuum bag 48 to be drawn down against the tool 46 and the manifold boxes 57.
• FIGs 9, 10a and 1 1 illustrate additional details of one typical form of the tool 46 shown in Figure 5.
• the tool 46 includes a tool billet 70 and an underlying tool base plate 68 that is attached to the tool billet 70, as by welding or other suitable techniques.
• the tool billet 70 may comprise a solid piece of material, such as metal in which channels 74 may be formed, as by machining.
• the channels 74 each have a cross-sectional shape corresponding to a portion of the stiffener 32, such as the hat section 36 of the stiffener 32.
• the tool billet 70 also has an upper tool surface 72 against which the flange section 38 of the stiffener 32 rests, along with the skin 30.
• the tool base plate 68 may include a plurality of tool base plate openings 76 therein which, in the illustrated example are generally rectangular in shape.
• the tool base plate openings 76 allow access to the bottom side of the tool billet 70 and allow air to circulate around the backside of the tool billet 70 in order to promote more even heating/cooling, as well as quicker heat up and cool down of the tool 46.
• the tool base plate 68 provides the tool billet 70 with the required rigidity, allowing a thinner tool billet 70 to be used which may reduce material costs and tool weight. However, in other embodiments, a tool base plate 68 may not be required where the tool billet 70 is sufficiently thick to provide the required rigidity.
• Figure 10 also reveals the placement of vacuum lines 78 through the tool base plate 68 which are coupled with the vacuum line inlet fittings 66 and top of the tool billet 70 to allow evacuation of the vacuum bag 48.
• uncured stiffeners 32 are placed in the channels 74 of the tool billet 70, in preparation for a curing cycle.
• the tool billet 70 is loaded with an array of uncured stiffeners 32, as shown in Figure 12.
• Figure 13 illustrates a corresponding array of bladders 52 that are respectively placed in the uncured stiffeners 32 which have been previously seated in the channels 74 of the tool billet 70.
• the bladders 52 will have a cross-sectional shape and length that substantially match that of the uncured stiffeners 32.
• the various ones of the stiffeners 32, along with the bladders 52 may have differing cross-sectional shapes and/or lengths.
• Figure 14 illustrates one of the bladders 52 that has a generally square cross-sectional shape suited to form the hat section 36 of the stiffener 32 shown in Figures 2 and 3.
• the bladder 52 may be formed of a generally flexible, impermeable material such as an elastomeric rubber.
• Each of the bladders 52 includes a bladder vent fitting 80 which may form part of a quick disconnect adapted to releasably connect the bladders 52 with the manifold system 54 ( Figure 5).
• Figure 15 illustrates the tool 46 supported on a tool base 81 , with uncured stiffeners 32 having been loaded into the channels 74 of the tool billet 70, with bladders 52 placed inside of the stiffeners 32.
• Each of the manifold boxes 57 includes manifold fittings 82 that are coupled with the bladder vent fittings 80 ( Figure 14), with each other and with a vent tube 56 by later discussed air lines or hoses (not shown in Figure 15).
• the manifold boxes 57, including the manifold fittings 82 and the vent tubes 56 are located along one side of the tool 46, at one end of the bladders 52, beneath the vacuum bag 48 when the frame assembly 50 is installed over the tool 46.
• the manifold box 57 may be formed of any suitable rigid material, such as sheet metal, and has a generally open interior. When arranged end-to-end, end walls 90 of the manifold boxes 57 are positioned side-by- side. As best seen in Figure 16 and 17, the manifold box 57 includes a substantially flat top wall 84, and an outer, inclined sidewall 88. The top wall 84 includes a vent tube opening 86 through which a vent tube 56 extends upwardly beyond the top wall 84.
• the vent tube 56 may extend downwardly through the bottom of the manifold box 57 and the tool base 81 ( Figure 15), thereby avoiding penetration of the vacuum bag 48.
• the top wall 84 and the inclined sidewall 88 may be of one-piece construction, or may be separate pieces, and are each removable to allow service personnel to access the open interior of the manifold box 57.
• the manifold box 57 may further include a plurality of longitudinally spaced, stiffening ribs 98.
• the vent tube 56 is mounted on a vent tube base 100 which has a generally open interior and is provided with fittings 95 that may be connected to fittings 82 by suitable hoses or airlines 102, as shown in Figure 20.
• the manifold box 57 has sidewall openings 94 facing the tool 46 which permit the fittings 82 to be connected to the vent fittings 80 on each bladder 52 using the quick disconnects 96.
• the quick disconnects 96 allow each of the manifold boxes 57 to be disconnected from the bladders 52. Once disconnected, one or more of the manifold boxes 57 may be removed, as necessary in order to reconfigure the manifold system 54 to suit the particular part assembly to be cured.
• the stiffened skin shown in Figures 1 and 2 employ four of the manifold boxes 57 arranged end-to-end in order to deliver autoclave pressure to the bladders 52 (Figure 13) placed in the corresponding stiffeners 32 ( Figure 12).
• one or more of the manifold boxes 57 may be removed simply by lifting them away from the tool base 81 ( Figure 15).
• the apparatus 42 described above may be employed to co-cure skins 30 and stiffeners 32 in an autoclave using the method shown in Figure 21 .
• preformed, uncured composite laminate stiffeners 32 are placed on a tool 46, following which bladders 52 are placed in the stiffeners 32 at 106.
• an uncured composite laminate skin 30 is placed over the tool 46, and brought into contact with the stiffeners 32.
• each of the bladders 52 is coupled with a manifold system 54 that is capable of supplying autoclave pressure to the bladder 52.
• a vacuum bag 48 is sealed over the tool 46 and over the manifold system 54.
• the vent tubes 56 pass through and are sealed to the vacuum bag 48.
• the bladders 52 are vented to autoclave pressure through the vacuum bag 48 using the manifold system 54.
• the bladders 52 are pressurized using autoclave pressure delivered through the vent tubes 56.
• Embodiments of the disclosure may find use in a variety of potential applications, particularly in the transportation industry, including for example, aerospace, marine, automotive applications and other application where autoclave curing of composite parts may be used.
• FIGS. 22 and 23 embodiments of the disclosure may be used in the context of an aircraft manufacturing and service method 94 as shown in Figure 22 and an aircraft 120 as shown in Figure 23.
• Aircraft applications of the disclosed embodiments may include, for example, without limitation, curing of stiffeners and stiffened skins such as, without limitation beams, spars stringers and wing skins, to name only a few.
• exemplary method 1 18 may include specification and design 122 of the aircraft 120 and material procurement 124.
• component and subassembly manufacturing 126 and system integration 128 of the aircraft 120 takes place. Thereafter, the aircraft 120 may go through certification and delivery 130 in order to be placed in service 132. While in service by a customer, the aircraft 120 is scheduled for routine maintenance and service 134, which may also include modification, reconfiguration, refurbishment, and so on.
• Each of the processes of method 1 18 may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer).
• 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
• an operator may be an airline, leasing company, military entity, service organization, and so on.
• the aircraft 120 produced by exemplary method 1 18 may include an airframe 136 with a plurality of systems 138 and an interior 140.
• high-level systems 138 include one or more of a propulsion system 142, an electrical system 144, a hydraulic system 146, and an environmental system 148. Any number of other systems may be included.
• an aerospace example is shown, the principles of the disclosure may be applied to other industries, such as the marine and automotive industries.
• Systems and methods embodied herein may be employed during any one or more of the stages of the production and service method 1 18. For example, components or subassemblies corresponding to production process 126 may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft 120 is in service.
• one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during the production stages 126 and 128, for example, by substantially expediting assembly of or reducing the cost of an aircraft 120.
• one or more of apparatus embodiments, method embodiments, or a combination thereof may be utilized while the aircraft 120 is in service, for example and without limitation, to maintenance and service 34.
• Apparatus for autoclave a plurality of composite stiffeners and a composite skin comprising:
• a tool adapted to have a composite skin placed thereon, the tool including a plurality of tool channels therein, each of the tool channels adapted to have a composite stiffener placed therein and contact with the skin;
• a bag adapted to be placed over the skin and exposed to autoclave pressure for compacting the skin against the stiffeners; a plurality of bladders respectively adapted to be placed within the stiffeners for reacting autoclave pressure applied to the stiffeners through the bag; and
• manifold system located along one end of the tool channels and disposed beneath the bag for coupling the bladders with autoclave pressure.
• a manifold box having a top wall adapted to be engaged by the bag
• A1 1 The apparatus of claim A8, further comprising:
• clamps for clamping the periphery of the bag between the tool and the frame.
• each of the bladders is elongate and includes a vent fitting on one end thereof, and
• the manifold system is releasably coupled with each of the vent fittings.
• vent tubes are coupled with ends of the bladders and are sealed to the bag.

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