WO2013186477A1 - Ensemble d'outillage pour la fabrication d'une pièce composite - Google Patents
Ensemble d'outillage pour la fabrication d'une pièce composite Download PDFInfo
- Publication number
- WO2013186477A1 WO2013186477A1 PCT/FR2013/051347 FR2013051347W WO2013186477A1 WO 2013186477 A1 WO2013186477 A1 WO 2013186477A1 FR 2013051347 W FR2013051347 W FR 2013051347W WO 2013186477 A1 WO2013186477 A1 WO 2013186477A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- keys
- core
- skin
- assembly
- wall
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Ceased
Links
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
-
- 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
- B29C33/485—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 cores or mandrels
-
- 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
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
- B32B37/24—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer not being coherent before laminating, e.g. made up from granular material sprinkled onto a substrate
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B38/00—Ancillary operations in connection with laminating processes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B2038/0052—Other operations not otherwise provided for
- B32B2038/0076—Curing, vulcanising, cross-linking
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2305/00—Condition, form or state of the layers or laminate
- B32B2305/02—Cellular or porous
- B32B2305/024—Honeycomb
Definitions
- the invention relates to a tool assembly for manufacturing a composite part and to a method for manufacturing a composite part.
- the manufacture of a piece of composite material can be achieved by a ply draping step against a male form, that is to say by pressing against a male form of several folds of carbon, prepreg or not of a resin, then by a polymerization step, that is to say by heating the assembly in an oven to give the plies the desired rigidity.
- the part thus formed is then able to be demolded by removal of the mold.
- An example of a particularly difficult piece to be made of composite material by this type of process is an external turbojet engine nacelle structure such as a movable thrust reverser cowl, for a so-called "O-Duct" nacelle structure.
- An aircraft is driven by several turbojet engines each housed in a nacelle for channeling the air flows generated by the turbojet, and that it can also house a set of devices performing various functions such as a thrust reversal device which is The role is to improve the braking ability of the aircraft by redirecting forward at least a portion of the secondary flow air.
- a nacel generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section housing the thrust reverser means and intended to surround the chamber. combustion of the turbojet engine, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
- a nacelle intended to be supported by a pylon of the turbojet comprising a thrust reverser device having a substantially single peripheral and substantially annular one-piece mobile cover, slidably mounted on rails disposed on either side of said pylon.
- a thrust reverser device having a substantially single peripheral and substantially annular one-piece mobile cover, slidably mounted on rails disposed on either side of said pylon.
- Such a hood is often referred to by the Anglo-Saxon terms "O-duct”, alluding to the ferrule shape of such hood, as opposed to "D-duct”, which actually comprises two half-hoods. each extending on a half-circumference of the nacelle.
- Such tools generally have three, four or five parts called “keys” whose fixing between them is done internally of the structure, either mechanically by bolting, or by a system of automatic isons and key manipulation. all wrapped by a plastic bladder.
- the keys ensure the structural strength of the tooling.
- the tooling comprises an internal central core on which is positioned a plurality of unsealed keys.
- the impermeability is directly carried out on the internal core, which makes it possible to avoid problems with the bulk of the bladder because it is no longer necessary to wrap the inner part of the mold.
- the inner wall of the keys adopts substantially the same shape as the outer wall of the core, and the keys are bolted together at their side walls.
- micro-slits result, during baking, for example from skins pre-impregnated with a resin, a flow of the resin between the micro-slots, which can create aerodynamic accidents of the composite structure manufactured.
- the present invention proposes to solve the aforementioned drawbacks, by proposing a tooling for the manufacture of a composite material part that can not be removed from the mold, the bladder of which is of reduced size and its easy installation, and of which it tooling makes it possible to respect precisely the dimensions of the composite parts to be manufactured.
- the present invention relates to a tool assembly for manufacturing a composite part greater than 180 ° circumference having at least one convex surface that can not be demolded, said assembly comprising at least one core and a plurality key wrenches, at least one of said wrenches comprising at least one support wall having a profile substantially similar to that of a working wall of said core, at least one support wall intended to support at least part of a first skin of said workpiece composite to be manufactured, and at least one side wall comprising holding means shaped to keep at least two adjacent keys between them, said tool assembly being remarkable in that the means for holding the keys allow at least a circumferential clearance between minus two adjacent side walls of the keys.
- said holding means comprise elastic means.
- the holding means comprise at least one movable bolt between a position of prominence and a retracted position.
- At least one side wall of at least one key comprises at least one hooking ramp of the holding means.
- the working wall of the core is of substantially cylindrical shape and said core comprises at least one handling wall of diameter substantially greater than the diameter of the working wall.
- the core includes a positioning stop of the set of keys.
- the tool assembly includes at least two distinct contact areas between the key set and the core.
- the core comprises inside a handling base intended to be handled by an external handling device.
- a handling base inside the core, it avoids having a base that protrudes from the mold, which reduces the floor area necessary for the installation of the tool assembly and a better accessibility of the operator during the draping phase.
- a centralizer at the upper and lower parts of the core, advantageously positioning the assembly in the vertical position or horizontal position.
- At least one of the keys comprises at least one lifting ring intended to cooperate with at least one lifting sling.
- the invention also relates to a method of manufacturing a composite part, remarkable in that it comprises the following steps aimed at:
- such a first skin makes it possible not to drape the composite folds on the discontinuous keys, and advantageously avoids aerodynamic accidents that may occur during the polymerization of the assembly.
- FIG. 3 is a detail view centered on the positioning stop of the keys on the core
- FIG. 4 is a view of the set of keys
- FIG. 5 represents a key in isometric view
- Figure 6 is a cross-sectional view of the keys along the line 6-6 of Figure 4; - Figure 7 is a detail view illustrating the maintenance of the keys together according to a first embodiment;
- FIG. 10 is a detail view illustrating the maintenance of the keys together according to a first embodiment
- FIG. 11 illustrates the installation of keys on the core when the maintenance between the keys is carried out according to the second embodiment
- FIG. 18 details the method of disassembly of the keys when the maintenance between them is realized by the first embodiment
- FIG. 21 represents the composite part resulting from the manufacturing method according to the invention.
- identical or similar references designate the same or similar organs or sets of members.
- the tool assembly 1 comprises a core 3 of substantially cylindrical shape, on which is positioned a plurality of keys 5.
- the core 3 comprises an outer wall 7 whose upper part 8 forms a so-called working wall 9.
- the core also comprises a handling wall 10 at the bottom 1 1 of the outer wall 7.
- the handling wall 10 is substantially cylindrical, of diameter substantially greater than that of the working wall 9.
- the handling wall allows the handling of the core through an external handling device (not shown in this figure).
- the handling wall has a positioning stop 13 allowing the keys to be held on the core 3.
- said stop has a groove 14 for receiving the part. lower keys.
- the positioning stop may, according to a variant not shown in the figures, be made directly on the working wall.
- the working wall is flared at its lower part, so as to allow contact between the keys and the core only at the end of positioning the keys on the core.
- the lower part January 1 of the core comprises inside a handling base 15, cooperating with the handling device, as explained in more detail in the following description.
- the core is directly placed on the ground, the inner wall is then no longer equipped with the handling base.
- the core for example metal, is preferably made of a low coefficient of expansion material in order to limit its deformation during the autoclave of the assembly.
- a set 16 of keys is made by assembling several keys 5 between them.
- the set of keys may comprise a different number of keys according to the needs of the skilled person.
- the keys 5 each comprise a support wall 17 forming all the surface of the part to be manufactured when the keys are assembled together.
- Figure 5 illustrates a key in isometric view.
- the key 5 comprises a support wall 19 substantially similar to the profile of the working wall of the core.
- a slight clearance can be provided between the working wall of the core and the support wall of the keys, to allow removal of the core or keys when the polymerization phase is performed, as described in more detail in the following the description.
- the key 5 comprises a lower portion 20 intended to be supported by the positioning stop 13 of the core, as shown in FIG.
- the key 5 is also intended to come into contact with an upper portion 21 of the working wall of the core, visible in FIG.
- the zones 13 and 21 of the core thus represent the two contact zones between the set of keys and the core.
- the key 5 is preferably hollow so as to minimize the mass of the assembly.
- the keys 5 are preferably made of composite materials also for the sake of limiting the mass of the assembly.
- the key 5 further comprises structural reinforcements 22 ensuring the rigidity of the tool assembly.
- each key 5 includes two substantially planar side walls 23 and 25, each engaging adjacent sidewalls to form the key assembly 16.
- the side walls 23 and 25 are shown parallel to each other, but can be indifferently inclined.
- the holding means between the keys 5 are positioned at the side wall 23 of the key 5.
- the holding means comprise an assembly consisting of a screw 27 and a nut 29 cooperating with the screw and housed inside the adjacent key.
- the screw 27 further comprises elastic means such as a spring 31, allowing a circumferential clearance J between the side walls 23 and 25 of the adjacent keys when the set of keys is constituted.
- the game J makes it possible to ensure a good centering of the keys on the core.
- the keys are assembled together before positioning them on the core.
- the set of keys is self-supporting before being placed on the core, the side walls 23 being in contact with the side walls 25.
- the positioning of the keys on the core is achieved through a handling device such as a mobile forklift 33.
- the forklift 33 comprises gripping lugs 35 for gripping the set of keys at the lower part 20 of the keys.
- the gripping lugs 35 are in the form of two flexible clamps 35a and 35b mounted fixed on the forklift.
- clamps are rigid and pivotally mounted each around a longitudinal axis of the carriage.
- the handling device is fixed and integrated into the workstation of an operator.
- the holding means comprise a bolt 37 supported by the side wall 23 of the key 5.
- the bolt 37 is shown in position of prominence. In such a position, an end portion 39 of the bolt 37 cooperates with a hooking ramp 41 integral with the key 5 adjacent, ensuring the locking in vertical downward translation of a key 5 relative to the adjacent key.
- the sliding bolt is between a position of prominence and a retracted position allowing the disassembly of the keys.
- the bolt 37 also allows circumferential clearance between the adjacent keys to ensure proper centering of the keys around the core.
- the assembly of the keys is performed by positioning one by one the keys on the core, as shown in Figure 1 1.
- a first key is positioned on the core 3.
- the bolt 37 is placed in a prominent position.
- the successive positioning of the keys is achieved by positioning one by one the adjacent keys.
- the hooking ramp 41 of the second key is positioned opposite the bolt 37, then the end portion of the bolt is slid inside the hooking ramp. Simultaneously, the lower part 20 of the key is inserted into the positioning stop 13 of the core.
- This method is iterated until all the keys are positioned on the core and the support walls 17 form the surface of the part to be manufactured.
- the part that one seeks to manufacture is for example an acoustic panel intended to equip a turbojet engine nacelle to reduce the noise from certain portions of the assembly constituted by the nacelle and the turbojet engine.
- an acoustic panel also called “sandwich panel” in reference to its structure, comprises a first skin, called “inner skin” on which is fixed a honeycomb core structure or honeycomb structure, intended to mitigate a noise, on which is fixed a second skin, called “outer skin”.
- the outer skin refers to the skin that is in contact with the circulation vein of the secondary air flow.
- the outer skin is perforated so as to pass the sound waves from the area to be attenuated acoustically, while the inner skin is full.
- the manufacturing method according to the invention comprises a first step of draping and autoclave polymerization of a first skin.
- the first skin referred to in the aforementioned step of the manufacturing method is an external skin, that is to say an acoustic skin.
- said first skin may be either the inner skin of the acoustic panel, or the outer skin of said panel, depending on the area of the nacelle that the acoustic panel is intended to equip.
- an acoustic panel is produced for a one-piece thrust reverser cowl, for a so-called "O-Duct" nacelle structure.
- the first step of the manufacturing process of the acoustic panel is aimed at producing a skin having a continuous surface that makes it possible to guarantee, as explained in greater detail in the remainder of the description, a clean aerodynamic surface when it is integrated into the assembly. tooling according to the invention.
- the skin which can be acoustic is manufactured according to the required sound attenuation needs by means of a mold external to the tooling assembly according to the invention, the outer surface of which draping said mold is sim ilaire to the external surface formed by the support walls of the assembled keys.
- the outer surface of the mold is a continuous surface that has no surface discontinuity on the drape area.
- the draping is carried out for example by pressing against the mold several plies carbon, prepreg or not of a resin. Then, the mold and the carbon folds follow a polymerization step, that is to say heating in an oven to give the folds the desired rigidity.
- the acoustic skin has a surface of revolution of about 330 °, corresponding to the angle between the sides of the rails along which slides the one-piece thrust reverser cowl.
- the acoustic skin resulting from the first step of the manufacturing process is open, preferably flexible and of limited thickness, so that it can be removed from the mold by elastic deformation of its structure.
- the acoustic skin may have a surface of revolution greater than 330 °, for example 360 °, the extraction of said skin from its mold may for example be achieved by a device of the type of that defined in the patent application No. 12/50482 belonging to the applicant and not yet published.
- FIG. 12 represents the tool assembly 1 according to the invention, the keys 5 being mounted on the core 3.
- the mounting of the keys on the core is carried out indifferently according to one either of the aforementioned methods of assembly with reference to FIGS. 7 and 10.
- Figure 13 illustrates the manufacturing phase of an acoustic panel.
- the first skin 43 constituted here by an acoustic skin previously draped and polymerized as previously described, is positioned on the support walls 17 of the set of keys 5.
- the positioning of the acoustic skin is carried out by example through the handling device referred to in the description, or manually by an operator.
- the positioning of the acoustic skin on the tool assembly is made possible by the opening provided on said acoustic skin, as previously described.
- the tolerances of the mold on which it has been manufactured may differ from the tolerances of the assembly. tooling according to the invention.
- the holding operation is carried out for example by means of straps which are positioned at the level of the upper and lower ends of the assembly, outside the draping areas. Maintaining the level of the central zone of the skin is carried out either by virtue of a belting by straps or by depositing folds so-called fees "closing" that is installed in the open area of the acoustic skin.
- acoustic skin is suitably plated on the tool assembly according to the invention, is fixed, for example by gluing, a honeycomb core structure 45 on said skin.
- the second skin 47, the inner skin of the acoustic panel, is then draped to form the panel.
- acoustic 48 is fixed, for example by gluing, carbon folds, pre-impregnated or not with a resin.
- the assembly consisting of the tool assembly according to the invention and the draped acoustic panel is now placed under a bladder, as illustrated in FIG. 14.
- a bladder 49 is positioned around the assembly comprising the tool assembly and the draped acoustic panel.
- the bladder is sealed with sealant on the core 3 and allows, during the polymerization of the autoclave assembly, a good pressurization, allowing good adhesion between the various components of the part to be manufactured.
- the bladder 49 is typically positioned at the end portions of the core, corresponding to areas not covered by the keys 5.
- the tool assembly and the precooked acoustic panel is autoclaved to polymerize the draped carbon folds.
- the polymerization step consists in heating the assembly in a pressure oven in order to give the plies the desired rigidity. During this step, the acoustic skin seals the assembly and constitutes a smooth surface obtained by means of a mold having no discontinuous surface.
- Continuous acoustic skin advantageously prevents the resin from entering between the spaces defined by the clearances between the keys during the polymerization.
- the continuous acoustic skin ensures the tightness of the whole.
- the fact of not directly draping the acoustic skin on the keys, d iscontinues, avoids aerodynamic accidents that may occur during the polymerization of the whole.
- the bladder is removed from the assembly and the lift truck 33 is positioned so as to allow the lower part 20 of the set of keys to be gripped by the gripping tabs 35.
- the clearance provided between the support wall of the keys and the working wall of the core allows the extraction of the assembly constituted by the keys 5 and by the acoustic panel 48 manufactured, said assembly can then deposited outside the core.
- the disassembly of the keys is carried out key by key.
- a first key 5 is first disconnected, which is removed as illustrated in step 1 of the disassembly process.
- the key adjacent to the first key 5 is disengaged from its adjacent key and removed from the assembly, as illustrated in steps 2 and 3.
- the operation is repeated for all the keys forming the set of keys.
- FIG. 19 illustrates the dismantling of the keys when they are held together by the bolts, corresponding to the aforementioned second embodiment of the means for holding the keys together.
- Disassembly of the keys is achieved here by switching the bolt 37 between the position of prominence to the retracted position.
- the end portion 39 of the bolt 37 is integrally enclosed in a first key 5, thus releasing the latching ramp 41 of the adjacent key, allowing the release of the key 5.
- a withdrawal device is provided on a side wall 25 of each of the keys. As shown in FIG. 20, this device comprises a lifting ring 51 allowing the attachment of a lifting sling 53. Of course, several lifting rings can be positioned on the side walls of the keys, then cooperating with several lifting slings. .
- the acoustic panel 48 resulting from the manufacturing method according to the invention is then ready for a cutting and machining operation in order to make the part conform to the assembly need, as represented in FIG. Thanks to the present invention, the dimensions of the composite part to be manufactured can be precisely respected thanks to the clearance provided between the keys mounted on the core, allowing a movement of the keys around the core, ensuring a good centering of the keys on the core.
- the invention is not limited to the only embodiments of this tool assembly, described above only as illustrative examples, but on the contrary embraces all variants, and in particular the variant according to which the tooling assembly no longer comprises a male core but a female core, the working wall of the core being then constituted by its inner wall and receiving the support wall of the keys.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Description
Claims
Priority Applications (6)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA2874959A CA2874959A1 (fr) | 2012-06-12 | 2013-06-11 | Ensemble d'outillage pour la fabrication d'une piece composite |
| CN201380030702.8A CN104379327B (zh) | 2012-06-12 | 2013-06-11 | 用于生产复合部件的工具组件 |
| RU2014153352A RU2014153352A (ru) | 2012-06-12 | 2013-06-11 | Комплект оснастки для изготовления композитной детали |
| EP13733387.8A EP2858812A1 (fr) | 2012-06-12 | 2013-06-11 | Ensemble d'outillage pour la fabrication d'une pièce composite |
| BR112014029250-7A BR112014029250A2 (pt) | 2012-06-12 | 2013-06-11 | conjunto de ferramentas para a produção de uma parte compósita e método para produzir uma parte compósita. |
| US14/567,006 US20150090396A1 (en) | 2012-06-12 | 2014-12-11 | Set of tools for producing a composite part |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1255463A FR2991628A1 (fr) | 2012-06-12 | 2012-06-12 | Ensemble d'outillage pour la fabrication d'une piece composite et procede de fabrication d'une piece composite. |
| FR12/55463 | 2012-06-12 |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US14/567,006 Continuation US20150090396A1 (en) | 2012-06-12 | 2014-12-11 | Set of tools for producing a composite part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2013186477A1 true WO2013186477A1 (fr) | 2013-12-19 |
Family
ID=46963843
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/FR2013/051347 Ceased WO2013186477A1 (fr) | 2012-06-12 | 2013-06-11 | Ensemble d'outillage pour la fabrication d'une pièce composite |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US20150090396A1 (fr) |
| EP (1) | EP2858812A1 (fr) |
| CN (1) | CN104379327B (fr) |
| BR (1) | BR112014029250A2 (fr) |
| CA (1) | CA2874959A1 (fr) |
| FR (1) | FR2991628A1 (fr) |
| RU (1) | RU2014153352A (fr) |
| WO (1) | WO2013186477A1 (fr) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106794640A (zh) * | 2014-10-07 | 2017-05-31 | 赛峰航空器发动机 | 脱模具有有机基质的复合材料的方法 |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10105940B2 (en) * | 2016-04-18 | 2018-10-23 | The Boeing Company | Formation of composite laminates having one or more divergent flanges |
| US20190091948A1 (en) * | 2017-09-26 | 2019-03-28 | Rohr, Inc. | Manufacturing a shaped structural panel with a mandrel and a pressure vessel |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1375111A2 (fr) * | 2002-06-27 | 2004-01-02 | Airbus France | Outillage de moulage à clef notamment pour la réalisation d'entrée d'air sans éclisse |
| US20060145049A1 (en) * | 2004-12-01 | 2006-07-06 | The Boeing Company | Segmented flexible barrel lay-up mandrel |
| GB2460741A (en) * | 2008-06-13 | 2009-12-16 | Advanced Composites Group Ltd | Tooling for the manufacture of composite structures |
| EP2181823A1 (fr) * | 2008-11-03 | 2010-05-05 | Rohr, Inc. | Outil multi-segments et procédé de formation composite |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4416440A (en) * | 1979-09-24 | 1983-11-22 | Harold M. Bowman | Ingot mold and method |
| US5746553A (en) * | 1996-04-08 | 1998-05-05 | The Boeing Company | Dual purpose lay-up tool |
| US7707708B2 (en) * | 2005-09-21 | 2010-05-04 | Rohr, Inc. | Apparatus for making a tubular composite structure |
| US20090033013A1 (en) * | 2007-07-31 | 2009-02-05 | Vought Aircraft Industries, Inc. | Multi-piece automated fiber placement mandrel automated clamping and indexing system |
| US7640961B2 (en) * | 2008-03-21 | 2010-01-05 | Rohr, Inc. | Apparatus and method for making a tubular composite barrel |
| FR2940176B1 (fr) * | 2008-12-22 | 2011-02-11 | Aircelle Sa | Procede de fabrication d'un panneau d'attenuation acoustique, notamment pour l'aeronautique |
-
2012
- 2012-06-12 FR FR1255463A patent/FR2991628A1/fr active Pending
-
2013
- 2013-06-11 EP EP13733387.8A patent/EP2858812A1/fr not_active Withdrawn
- 2013-06-11 BR BR112014029250-7A patent/BR112014029250A2/pt not_active Application Discontinuation
- 2013-06-11 CN CN201380030702.8A patent/CN104379327B/zh not_active Expired - Fee Related
- 2013-06-11 RU RU2014153352A patent/RU2014153352A/ru not_active Application Discontinuation
- 2013-06-11 WO PCT/FR2013/051347 patent/WO2013186477A1/fr not_active Ceased
- 2013-06-11 CA CA2874959A patent/CA2874959A1/fr not_active Abandoned
-
2014
- 2014-12-11 US US14/567,006 patent/US20150090396A1/en not_active Abandoned
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1375111A2 (fr) * | 2002-06-27 | 2004-01-02 | Airbus France | Outillage de moulage à clef notamment pour la réalisation d'entrée d'air sans éclisse |
| US20060145049A1 (en) * | 2004-12-01 | 2006-07-06 | The Boeing Company | Segmented flexible barrel lay-up mandrel |
| GB2460741A (en) * | 2008-06-13 | 2009-12-16 | Advanced Composites Group Ltd | Tooling for the manufacture of composite structures |
| EP2181823A1 (fr) * | 2008-11-03 | 2010-05-05 | Rohr, Inc. | Outil multi-segments et procédé de formation composite |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106794640A (zh) * | 2014-10-07 | 2017-05-31 | 赛峰航空器发动机 | 脱模具有有机基质的复合材料的方法 |
| US10166708B2 (en) * | 2014-10-07 | 2019-01-01 | Safran Aircraft Engines | Method for demoulding a composite material with an organic matrix |
Also Published As
| Publication number | Publication date |
|---|---|
| US20150090396A1 (en) | 2015-04-02 |
| CN104379327A (zh) | 2015-02-25 |
| CN104379327B (zh) | 2017-08-01 |
| EP2858812A1 (fr) | 2015-04-15 |
| FR2991628A1 (fr) | 2013-12-13 |
| CA2874959A1 (fr) | 2013-12-19 |
| BR112014029250A2 (pt) | 2018-04-24 |
| RU2014153352A (ru) | 2016-08-10 |
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