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
  • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
  • B29C70/304—In-plane lamination by juxtaposing or interleaving of plies, e.g. scarf joining
• • 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
  • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
  • B29C53/80—Component parts, details or accessories; Auxiliary operations
  • B29C53/8008—Component parts, details or accessories; Auxiliary operations specially adapted for winding and joining
  • B29C53/8066—Impregnating
• • 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
  • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
• • 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
  • B29C70/545—Perforating, cutting or machining during or after moulding
• • 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
• • 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
  • B29C2793/00—Shaping techniques involving a cutting or machining operation
  • B29C2793/0072—Shaping techniques involving a cutting or machining operation combined with rearranging and joining the cut parts
• • 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
  • B32B2535/00—Medical equipment, e.g. bandage, prostheses, catheter
• • 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
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
  • Y10T156/10—Methods of surface bonding and/or assembly therefor
  • Y10T156/1002—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina
  • Y10T156/1028—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina by bending, drawing or stretch forming sheet to assume shape of configured lamina while in contact therewith

Definitions

• the present invention relates to the field of manufacture of skins composites forming ferrules, that is to say substantially having a symmetrical shape of revolution about an axis.
• Such composite skins obtained by arranging folds of fabric on a tool forming a ferrule, impregnated with resin beforehand (folds of "pre-impregnated") or subsequently (so-called “post-impregnated” or “infused”) to their set-up on the tooling, are used in particular for the nacelle air intakes for aircraft turbojets, where they are then drilled and coupled to honeycomb-like honeycomb structures.
• a constant problem involved in the manufacture of such sandwich structures is that the skin forming ferrule generally has convex zones which exclude the possibility of demolding the skin of a tool in a single operation.
• the operations are complex, and give rise to numerous aerodynamic accidents on the surface of the skin obtained at the end of the process, in the connection zone or between the different keys of the tooling either between the different parts forming the skin.
• the present invention aims in particular to reduce these disadvantages, and provides for this a method of manufacturing a shell composite skin comprising the following successive steps to:
• the present invention thus makes it possible to considerably simplify the manufacture of composite skins forming non-demoldable ferrules, and to limit aerodynamic accidents on the surface of such skins.
• said separation line is produced by means of a groove formed in said shell mold, into which a cutting tool is introduced before the arrival of the resin;
• said separation line is made with at least one fixed strip integral with said shell mold, against which two edges of the draping of folds abut;
• said dividing line is made by simply cutting the ply draping in its thickness, possibly with a cut in full thickness followed by cuts in only a part of the thickness of the draping, making it possible to obtain stepped edges;
• said separation line is made by overlapping two edges of the draping
• a separator is placed between the two edges of the draping adjacent to the separation line prior to impregnation of the folds with the resin;
• said separation line is produced by covering an imprint formed on the shell mold; said dividing line is made by draping the folds on a mold forming a ferrule of dimensions greater than those of the final piece, in order to obtain an open skin, and the two edges of this drape adjacent to the separation after baking of the resin;
• said separation line is produced in a direction chosen from the group comprising the longitudinal direction, the transverse direction, and any position intermediate between these two positions;
• said resin draping is impregnated if it is dry fabric used, especially in the "infusion" version, by means of a bladder which is applied on this drapery against the mold forming a ferrule, and which is put under empty;
• said composite skin is glued inside or outside of an assembly formed of a honeycomb-like honeycomb structure fixed on another composite skin, and the splicing of the two edges of the composite is carried out; the skin on or inside this set.
• the acoustic piercing of the skin can be done after polymerization of this skin, before implantation of the honeycomb structure.
• this skin can be pierced after implantation of the alveolar structure.
• FIG. 1 is a view from above of a shell mold on which fabric folds for the formation of a composite skin have been draped, corresponding to a first embodiment of the process according to the invention
• FIG. 1a is a detailed view of zone I of FIG. 1; FIGS. 1b to 1f are views similar to those of FIG.
• FIGS. 1 g and 1 h are similar respectively to FIGS. 1 and 1 a, and relate to a variant of the first embodiment of the method according to the invention
• FIGS. 2 to 2i are similar respectively to FIGS. 1a to 1h, and relate to a second embodiment of the method according to the invention
• FIGS. 3 to 3e relate to a third embodiment of the method according to the invention, it being noted that FIG. 3b is a cross-sectional view of the separation zone of the draping disposed on the shell mold,
• FIGS. 4 to 4e are cross-sectional views of this separation zone, for a fourth embodiment of the method according to the invention.
• FIGS. 5 to 5b are cross-sectional views of this separation zone, for a fifth embodiment of the method according to the invention.
• FIGS. 6 and 6a are cross-sectional views of this separation zone, for a sixth embodiment of the embodiment method according to the invention.
• Figures 7 and 8 are views similar to those of Figures 1 and 2, in the case where the dividing line on the draping is transverse,
• FIG. 8a is a detailed view of zone VIII of FIG. 8,
• FIG. 9 schematically shows the production of a composite skin on a shell mold, when this skin is disposed outside this mold,
• FIG. 9a shows the splicing of the composite skin thus obtained, arranged outside a key tool
• FIG. 9b illustrates the placement of a honeycomb-like honeycomb structure on the composite skin spliced at the end of the step of FIG. 9a
• FIGS. 10 to 10b illustrate steps analogous to those of FIGS. 9 to 9b, when the composite skin is deposited inside a shell mold, then spliced and covered with a honeycomb-type honeycomb structure. bee inside a key tool,
• FIGS. 1 1 to 1 1 c are similar respectively to FIGS. 9 to 9b, and relate to the embodiment of FIGS. 6 or 6a, being noted that Figure 11b is an enlargement of the area XI of Figure 11a,
• FIGS. 12 to 12c are similar to FIGS. 10 to 10b, respectively, for a mode of realization analogous to that of FIGS. 6 to 6a, being noted that FIG. 12b is an enlargement of zone XII of FIG. 12a, and
• FIGS. 1a and 1b are views of another embodiment of the method according to the invention.
• a mold forming shell 1 made for example of steel or other metal alloys.
• This mold 1 is intended to be covered with a draping fabric for the formation of a piece in com posite having a substantially symmetrical shape of revolution.
• the mold 1 has a bulge 5 preventing the demolding of the composite skin simply by axial sliding of this skin on this mold.
• FIG. 1c by means of a cutting tool 9 actuated manually or automatically, the pleat draping is cut along the groove 7. Then, as can be seen in FIG. 1b, a strip 1 1 having a substantially T-shaped section inside the groove 7 is brought in so as to close this groove along its entire length.
• the polymerizable resin is introduced under pressure under the flexible bladder 14 ("post-impregnation” also known as "infusion” of resin), so that this resin impregnates all the draping.
• the temperature of the assembly thus obtained is raised, for example inside an autoclave, so as to cure the resin.
• the flexible bladder is removed, then the ruler 11, and the resulting composite skin is removed from the mold 1 by means of the dividing line previously made along the groove 7, and the relative flexibility of this skin.
• the strip 1 1 is then covered with a strip cover 15, which is in fact a female part capable of receiving this strip 1 1 while pressing on the edges adjacent to the draping 3.
• Step 2f is similar to step 1 f: this step consists in fact covering the draping and the cover-ruler 15 of a bladder 14 that is put under vacuum, then to introduce the resin under pressure if c
• the dry fabric is used in the "infusion" version, the assembly thus obtained being placed in an autoclave in order to harden the resin.
• FIG. 2g The demolding of the composite skin thus obtained is shown in FIG. 2g.
• the elasticity of this skin is used to separate the two adjacent edges of this skin of the strip 1. (Arrows F1, F2), to exit axially (arrows F3 and F4) this skin of the mold 1.
• two strips 11a and 11b can be provided, similarly to the two grooves 7a and 7b of the preceding embodiment, in which case it is necessary to envisage a two-groove strip cover, suitable for fitting respectively on these two strips 1 1 a and 1 1 b.
• no groove or ruler is provided on the surface of the mold 1.
• FIG. 3 it is possible to make a cutout 17 on a thickness of the lay-up 3, as well as a plurality of adjacent cut-outs 17a, 17b, 17c, 1 7d, on the different layers of draping.
• this cut is made, as shown in Figures 3b and 3c, is placed a sheet of a separator January 9 between the two edges 1 3a and 1 3b of the draping.
• This light which can be made, for example, from PTFE (polytetrafluoroethylene), is chosen so that its outer surface 19a is polymerizable with the resin, while its inner surface 19b (that is to say its face facing the mold 1) is not.
• PTFE polytetrafluoroethylene
• This separator 19 allows, during the resin impregnation step (see Figure 3d similar to that of Figures 1f and 2f) if it is dry fabric used in "infusion" version, to prevent the resin does not is glisse between the two edges 13a and 13b of the draping.
• the two edges of the composite skin thus obtained can be removed and removed from the mold 1, as shown in FIG. 3e.
• the protruding portion of a separator 19 may be removed, for example by cutting.
• FIGS. 4a and 4e differs from the preceding one in that provision is made for overlap between the edges 13a and 13b of the draping 3.
• this separator is glued under the edge 13b of the draping 3, which edge is kept spaced from the other edge 13a of this draping by a strip 21 of appropriate shape.
• the separator 1 9 is bonded to the edge 13a of the draping 3, to be covered by the other edge 13b of this layup.
• FIG. 4d illustrates the positioning of the flexible bladder 14, permitting the impregnation of draping by the resin under pressure if it is dry fabric used in "infusion" version.
• FIG. 4e shows the result obtained after passing through an autoclave: the separator 9 remains in the same state as the edge 1 3b of the rapag e, the effect of the polymerization of the resin, but is easily detached from the other edge 1 3a of this draping, thus allowing the spacing of the two layers of the composite layer thus obtained in view of its axial retraction of the mold 1.
• a longitudinal impression 23 integral with the shell mold 1 is provided.
• the lay-up 3 is then placed so that its edge 13a abuts between this impression 23, and its other edge 13b substantially covers this impression 23.
• Figures 6 and 6a shows that it is also possible to perform a draping on a mold forming ferrule 1, having dimensions greater than those desired for the final composite skin.
• the mold 1 is draped only over part of its periphery, so as to leave a circumferential distance d between the two edges 13a and 13b of this draping.
• FIG. 7 shows that the foregoing precepts can be applied to the realization of a transverse junction zone 25 between two halves 3a and 3b of the draping 3.
• This transverse junction line 25 is then at the right of the bulge 5 of the shell mold 1.
• FIGS. 8 and 8a illustrate the particular case in which this joining line 25 is produced according to the precepts of the embodiment of FIGS. 5a, 5b, ie with the production of a cavity 23 all around the circumference of the shell mold 1.
• this joining line 25 is produced according to the precepts of the embodiment of FIGS. 5a, 5b, ie with the production of a cavity 23 all around the circumference of the shell mold 1.
• FIGS. 5a, 5b one finds oneself with a composite skin comprising two mutually overlapping edges 1 3a and 1 3b, this covering being in the circumferential species.
• FIGS. 9a and 9b summarize the manufacture of a composite skin according to any one of the embodiments of FIGS. 1 to 5, in the case where the draping is carried out on a mold forming a male shell.
• the drape 3 is first made on the outer periphery of the mold 1.
• This skin is then placed on a tool with keys 27, that is to say on a tool having several elements movable relative to each other, allowing the removal of the composite skin including when it became monobloc that is, when these two opposite edges 13a and 13b have been joined to each other.
• the ecluder 29 is made of the two edges 13a, 13b of the composite skin.
• This splicing is typically performed by providing and polymerization of an outer composite member.
• the composite skin be covered with an acoustically absorbent structure
• a honeycomb-like honeycomb structure 31 which i will preferably be densified in the zone 33 which is opposite the splice 29.
• the key tool 27 can be dismantled so as to recover the part thus obtained.
• the acoustic piercing of the skin can be done after polymerization of this skin, before implantation of the alveolar structure.
• this skin can be pierced after implantation of the alveolar structure.
• Figures 10 to 10b are similar to Figures 9 to 9b, and relate to a variant in which the draping folds is made inside a mold 3, and then treated according to the method according to the invention. invention. More specifically, once the composite skin obtained at the end of the various steps described above, we can remove the skin from the inside of the mold 1 by elastic approximations of these two edges 13a, 13b.
• FIG. 10a honeycomb-like honeycomb structure 31
• FIGS. 9a and 9b honeycomb-like honeycomb structure 31
• Figures 11 to 11c are similar to Figures 9 to 9b, but relate to the embodiment of the method according to the invention described in Figure 6a.
• the draping of folds 3 is carried out on a mold forming a ferrule 1 having dimensions greater than those of the part which it is finally desired to obtain.
• FIG. 11b shows that splicing on a key tool 27 takes place in this case by providing a plurality of composite outer members 29a, 29b.
• FIGS. 12 to 12c is similar to that of FIGS. 11 to 11c, but in the case where the draping of folds 3 is carried out inside a shell mold 1, and / or the splice and the contribution of a honeycomb structure are made inside a key tool 27.
• the method according to the invention makes it possible to produce composite skins in the form of ferrules, that is to say at 360 °, presenting the minimum of aerodynamic accidents, with extremely simple tools.
• This method makes it possible to obtain composite skins presenting forms substantially symmetrical of revolution, that it would be impossible to obtain without complex key tools. It is possible to obtain composite skins forming ferrules having areas of hollow and bulge excluding any demolding by translation compared to a traditional mold.
• the assembly 35 constitutes a monobloc housing on which the composite skin obtained by the above process is reported by gluing.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Chemical & Material Sciences (AREA)
• Composite Materials (AREA)
• Casting Or Compression Moulding Of Plastics Or The Like (AREA)
• Moulding By Coating Moulds (AREA)
• Laminated Bodies (AREA)

Applications Claiming Priority (2)

Publications (1)

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Family Applications (1)

Country Status (8)

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Family Cites Families (8)

• 2012
  • 2012-05-10 FR FR1254258A patent/FR2990376B1/fr active Active
• 2013
  • 2013-05-02 EP EP13723893.7A patent/EP2846987A1/fr not_active Withdrawn
  • 2013-05-02 WO PCT/FR2013/050970 patent/WO2013167826A1/fr active Application Filing
  • 2013-05-02 CN CN201380022967.3A patent/CN104271336A/zh active Pending
  • 2013-05-02 BR BR112014026973A patent/BR112014026973A2/pt not_active IP Right Cessation
  • 2013-05-02 CA CA2870946A patent/CA2870946A1/fr not_active Abandoned
  • 2013-05-02 RU RU2014148725A patent/RU2014148725A/ru unknown
• 2014
  • 2014-11-07 US US14/535,466 patent/US20150059967A1/en not_active Abandoned

Non-Patent Citations (1)

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