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
• • 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
  • B29C70/02—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements, e.g. non-specified reinforcements, fibrous reinforcing inserts and fillers, e.g. particulate fillers, incorporated in matrix material, forming one or more layers and with or without non-reinforced or non-filled layers
  • B29C70/021—Combinations of fibrous reinforcement and non-fibrous material
• • 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
  • B29C70/06—Fibrous reinforcements only
  • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
  • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
  • B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
  • B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
• • 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
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
  • B29B11/00—Making preforms
  • B29B11/14—Making preforms characterised by structure or composition
  • B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
• • 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
  • B29C67/00—Shaping techniques not covered by groups B29C39/00 - B29C65/00, B29C70/00 or B29C73/00
  • B29C67/0014—Shaping techniques not covered by groups B29C39/00 - B29C65/00, B29C70/00 or B29C73/00 for shaping tubes or blown tubular films
  • B29C67/0018—Turning tubes inside out
• • 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
  • B29K2105/25—Solid
  • B29K2105/253—Preform
  • B29K2105/258—Tubular
• • 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
  • B29L2023/00—Tubular articles
• • 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
  • B29L2031/772—Articles characterised by their shape and not otherwise provided for

Definitions

• the present invention relates to a method of manufacturing composite parts. It also relates to a manufacturing facility implementing such a method, and composite parts thus manufactured. It finds application in the field of aeronautical construction, particularly in the field of jet engine nacelles and more particularly in the field of revolution or circumferential structures of nacelles such as air intake lips or frames of inverter structures. of aircraft nacelles.
• a workpiece has a preform in a woven or braided piece that is shaped to the shape of the desired workpiece. Then, the preform is impregnated with a polymerizable resin to obtain the final piece.
• the decadration consists of changing the angles between the warp and the weft initially by 90 ° at angles between 35 ° and 125 °), which is typically obtained when stretching a fabric in at least one direction not parallel to a direction of fibers of said fabric. It is then not possible to cover complex shapes such as non-developable surfaces of composite parts used in aeronautics such as an air inlet lip, a nacelle front frame, a "C” profile stiffener, a radial partition in "C”, etc .. all forms of axisymmetric parts or similar to axisymmetric parts.
• a toric core including in its surfaces the shape of the part, and realize a tubular braid directly around this core.
• the axis of the tubular braid being substantially at every point of the part perpendicular to the toric section of the piece.
• This technique allows, if the toric section of the piece is convex, to obtain a preform perfectly matching the surface of the piece.
• this process is relatively slow in implementation and the management of fiber orientations is limited.
• the solution proposed by the present invention consists in obtaining the preform according to the weaving contour principle, and with a particular mandrel definition which is different from the final piece to be draped.
• the present invention therefore aims at providing a technique for weaving or braiding a textile so as to continuously cover a surface of revol ution, or substantially of revolution, leq uel textile is ens ite drapable, without cutting on said surface of revolution.
• part of revolution or circumferential piece By part of revolution or circumferential piece is meant an axisymmetrical part extending over 360 ° or over an angular sector of less than 360 °, whose section, by cutting the part along a plane parallel to the axis of revolution present with at least one line perpendicular to the axis of revolution at least 2 points of intersection.
• a toric piece for example, responds to this definition.
• the toric section of a part according to the invention can be open or closed regularly or irregularly.
• the "inflexion point” means a point of a generatrix of a preform or mandrel on which the weaving or braiding of the preform is wound, presenting a tangent traversing from side to side the generator or two half-tangents placed on either side of the generator.
• the present invention relates to a method of manufacturing composite material parts with preforms obtained by weaving contour of the kind consisting of winding at least one piece of sheet weaving or braiding around a mandrel under a given tension field .
• the method of the invention consists of:
• the first phase also comprises at least from a determined geometry of the preform to be manufactured:
• a step of defining an architecture of the sheet of the preform to be manufactured the section of which comprises at least one end line separating at least two parts of the preform;
• the non-woven final surface is transformed with a conventional weaving means into a wearable surface with a conventional loom on mandrels of particular shapes.
• the weaving can thus be fast because a loom has good productivity.
• the mandrel has a particular shape in direct relation to the final shape of the piece to be draped.
• the winding mandrel of the weaving according to the invention with the point of inflection allows the use of a conventional loom, and to obtain a fabric from one side to the other of the point of inflection. This makes it possible to obtain a continuous fabric on the final piece.
• the resulting fabric has a specific shape, which is adapted to drape without stretching on the shape of the piece.
• the orientations of the fibers on the final part are thus controlled.
• the profile of the mandrel does not contain a tangent normal to the axis, which would make it very difficult to weave on such a shape, this being obtained by the axial homothety associated with the linear expansion of the surface.
• the fibers of the fabric are then distributed in circumferential fibers (typically warp threads) and transverse or radial fibers (typically weft threads), these circumferential and radial fibers being perpendicular to each other.
• circumferential fibers typically warp threads
• transverse or radial fibers typically weft threads
• the solution of the method of the invention therefore uses a textile architecture associated with a type of shape, and the process making it possible to obtain it.
• the textile architecture is a woven or braided textile, covering in a single coupon, a geometric shape whose envelope surface comprises, in at least one plane perpendicular to the axis of revolution or comparable to an axis of revolution, at least two generators circumferential, such as a shape "C", or torus. Associated with this feature of the surface, there is therefore also on the surface at least one generator whose all points of the generator are, compared to their neighbors at an abscissa extrema along the axis of revolution of construction of the surface, this generator constituting a line of cusp profile profile.
• the solution of the method of the invention makes it possible to cover the surface of such parts by textile weaving in one piece, without distortion or stretching of the preform.
• the characteristics of fiber densities and fiber orientations are mastered and thus impart to the workpiece an excellent and optimized structural strength that other conventional 2D fabric draping methods or 2D braids that require stretching to match non-developable form of such parts.
• the solution of the method of the invention is based on a modeling process giving the links between the final surface to be draped, and the definition of the weaving winding mandrels, and the weaving that will be obtained on the piece according to the wound fabric. on mandrel during weaving.
• the method of the invention is such that the first phase comprises at least some of the following steps:
• the transverse fibers have a defined angle with respect to the circumferential fibers, which is not necessarily at 90 ° of angle and in that one generates on the whole of the surface of the piece, gradually, quadrilaterals retaining sides of the same ratio between long (circumferential) and cross (radial) direction.
• the invention also relates to an installation for manufacturing composite parts implementing the method of the invention.
• the installation essentially comprises:
• the invention also relates to parts of revolution of which at least one layer has been obtained using the method of the invention by means of the manufacturing facility of the invention.
• FIG. 1 shows part of a part realizable by means of the method of the invention
• Figures 2a to 2c show a plurality of sections of parts that can be made using the method of the invention
• FIGS. 3a to 3h show other examples of section shapes that can be made using the method of the invention
• Figures 4a and 4b show two fabric architectures during the step of winding a fabric on a mandrel in a preform manufacturing facility according to the invention
• Figures 5a to 5e show subsequent steps performed in a preform manufacturing facility according to the invention
• Figures 6 and 7 show the steps of modeling a preform to obtain ir and transformation to deduce the shape of the associated mandrel in a first embodiment of the method of the invention
• FIGS. 8a, 8b, 9 to 10 represent the modeling steps of a preform to be obtained and of transformation to deduce the form of the associated mandrel in a second embodiment of the method of the invention.
• Figures 1 1 and 12 show the modeling steps of a preform to obtain and transformation to deduce the shape of the associated mandrel in a third embodiment of the method of the invention.
• FIG. 1 there is shown a part of a composite material part made using the method of the invention.
• a piece 1 has a symmetry of revolution about the axis A.
• Its inner portion 3 comprises two lateral wings joined by a connecting portion 2, a line represents the cusp of its radial section. For a coordinate counted along the axis of revolution A of part 1, no point in the section of the part extends beyond the line marked on part 2.
• FIG. 2a there is shown a half schematic view of the section of each piece of revolution about its axis of revolution A, which has been shown as an embodiment.
• FIG. 2a there is shown such a section of a hollow or "C" shaped piece 6 of revolution around the axis A and that has two connected wings that contact a radial tangent line 4a in FIG. a point 5 of cusp of the section.
• the "C" hollow part 7 has a larger contact zone 8 with the radial tangent line 4b.
• the composite part has a closed section 9. It is made from two "C" hollow parts 10 and 11. Each hollow part 10 or 11 has at least one cusp or contact area 5c or 5d along a line of greater distance respectively 4c and 4d, each line 4c or 4d constituting a radial tangent line for the hollow part 10 or 11 corresponding thereto.
• the homologous edges 12 and 13 of the preforms of these hollow parts 10 and 11 are jointed, edge to edge or as here in recovery.
• FIG 3a there is shown the section of a composite material part 14, 15 of current section in the form of "S", according to another geometry.
• the part 14, 15 is composed of two hollow parts C, each similar to the hollow part 6 of Figure 2a or the hollow part 7 of Figure 2b.
• the "S" shaped section of the piece 14, 15 is therefore composed of two "C” shaped section areas 14 and 15 of opposite concavities and which are connected to the junction point 16.
• the junction point 16 can be achieved in the two ways described for the connecting bridges 12 or 13 of parts 10 and 11 of the embodiment of Figure 2c.
• the S-shaped part is finally the concatenation of two C-shapes.
• the part having an S-shaped section is made using integral fabric preforms which are made with the method of the invention. .
• FIG. 3b there is shown the open section of a part 17-19 made according to the method of the invention composite material.
• Room 17-19 is shaped like a "W" in its current section. It is the concatenation of multiple “C” sections, each similar to the hollow part 6 of Figure 2a or the hollow part 7 of Figure 2b. The various "C” sections do not interfere with each other.
• Each hollow part 17, 18 or 19 is produced according to the method of the invention so that no point of its section exceeds the radial tangent line 4h, 4g or 4f respectively.
• the hollow parts 17 and 18 are connected to the junction point 16a, the hollow parts 18 and 19 are connected to the junction point 16b, the junction points 16a or 16b being similar to that 16 described in FIG. 3a.
• FIGS. 3c, 3d, 3e, 3f, 3g, 3h show closed sections of O-rings made according to the method of the invention. These O-piece sections have two extrema generators.
• the method of the invention performs in the same way as previously the draping in one piece of the entire toric surface of the piece.
• the closure of the section is obtained edge to edge or overlap as shown in the figures.
• Figure 3c which is like Figures 3a to 3h a schematic half view
• the piece of revolution about the axis A is manufactured with two boundary points 5c on the normal plane 4c and 5d on the normal plane 4d.
• the two normal planes 4c and 4d are taken with respect to the axis of revolution A of the part thus manufactured.
• the edges of the sheet of the preform are placed in overlapping of the edges 12a and 12b arranged on the outside (towards the top of FIG. 3c) of the part of revolution which is then obtained by impregnation of the preform.
• edges 1 2a and 12b are disposed edge to edge within the workpiece, facing the axis of revolution A;
• the overlap of the edges 12a and 12b is carried out on one side of the piece of revolution, and is on the limit point 5d on the normal plane 4d of the part;
• edges 12a and 12b are disposed edge to edge on the point 5d limit.
• the revolution section of the workpiece affects a substantially quadrangular shape and the edges 1 2a and 1 2b are placed edge to edge on a corner of the workpiece to the outside relative to the axis of revolution AT.
• the manufacturing process of the invention takes place in three distinct phases.
• a first phase at the same time, the design of the part, the calculation of the geometry of the sheet preform and the calculation of a forming mandrel of a first state of manufacture of the preform are performed.
• the manufacturing facility of the preform is configured by associating the previously calculated mandrel with the sheet manufacturing device. We realize the sheet that is rolled as it is manufactured on led it chuck.
• the preform is maintained in this geometrical state on the appropriate tooling and the preform is impregnated with a resin and cured to obtain the desired composite material part.
• Figures 4a and 4b there is shown a step of the method of the invention during the second phase of its implementation of performing the weaving or braiding of the preform wound on or around the weaving mandrel or braiding.
• the sheet is a fabric that has, once wound around the mandrel 20, a determined architecture of warp threads 24 and weft threads 23, which are substantially orthogonal and which depends on the preform and / or the workpiece. of revolution that it is desired to produce with the method of the invention.
• the fabric sheet which is wound on the mandrel 20 is produced in a weaving machine not shown in the drawing and which is arranged on the right and comprises in particular a device for tensioning the chains 21 and distributing the tensions in the frame. of sheet so as to assist its winding around the mandrel 20, and a weft insertion mechanism 22 which injects with controlled angles the weft yarn on the cloth sheet 21.
• the architecture of the sheet containing the warp 21, the control of the insertion of the weft yarn into the weft weaving mechanism 22 and the geometry of the mandrel 20 have been calculated during of the first phase of the process of the invention and which will be described later.
• the warp 25, and any other element that takes its place according to the type of sheet used as will be described later, is shown and described as a point, because the warp or any similar element is represented by a dot in the section shown in the drawing.
• the point 25 is defined on the sheet of the preform.
• the point 25 coincides with the homologous point of the mandrel 20 and no other reference is used to simplify the drawing and because the shape of the mandrel is determined by the calculated shape of the preform that the mandrel serves to produce.
• the architecture of the sheet is determined in particular by the choice and the relative arrangement of the warp son and the weft son, especially in terms of surface density and number of layers.
• the wrapping of the drape extends over a portion or the entire circumference of the mandrel 20 in one or more layers.
• control of the architecture of the sheet and the choice of the shape or profile of the mandrel 20 uses a set of rules to determine the quality of weaving along the length of the fabric. winding around the mandrel.
• control rules we note:
• FIG. 4b there is shown the same second phase of the manufacturing method of the invention, in the state of FIG. 4a, but in which the weaving of FIG. 4a is replaced by a braided or braided sheet in which weft yarns 27 and 28 are interwoven around a direction perpendicular to the warp yarn 21 at the angles determined by the architecture of the fabric calculated during the first phase of the process of the invention.
• the same type of warp thread 25 is on a point of inflection of the contour of the mandrel 20 and the same arrangements for making the preform as for that of Figure 4a can be taken.
• a preform in fabric or braid is thus obtained in a first state of manufacture.
• FIG. 5a shows the operations of the second phase of the method of the invention for a type of part whose section comprises a radial tangent, during which a second state of manufacture of the preform is produced.
• the warp yarn 25 is in a plane which divides the mandrel 20 into two parts 20A and 20B on either side of the plane of change of inflection of the profile of the mandrel.
• the point 25 is a point of inflection of the lines described by the son of frames or the trace of a cross section of the preform on the mandrel.
• the inflection is marked by the tangent T25 local on the intersection of the mandrel and the plane that divides the mandrel 20 into two parts 20A and 20B.
• the frame directions when they are positioned perpendicularly at the ends of the chines, follow the generators 29a, 25 and 29b.
• FIG 5b there is shown the woven sheet preform of Figure 4a when it was formed in its second state after the operations of Figure 5d for a 360-degree revolution.
• the warp threads 32 of the woven sheet are substantially arranged in circles centered on the axis of revolution (not shown) of the preform 30, while the weft threads 31 are curves determined in radial sections relative to this axis of rotation. revol ution. It is then possible to achieve the impregnation of the preform with resin.
• FIG. 5c the braided preform of FIG. 4b is shown when it has been formed in its second state after the operations of FIG. 5d.
• the warp threads are substantially arranged in circles centered on the axis of revolution (not shown) of the preform 33, while the threads of work 34 and 35 are defined and inclined relative to sections radial relative to this axis of revolution.
• FIG. 5d shows the geometric transformations successively applied to the preform to bring it from its first state of manufacture to its second and last state of manufacture.
• the sheet preform in a first state of manufacture is first deployed from the mandrel in a radial extension E, bearing the point 25 of a carrier radius rm or chuck radius at the point 25 'of final radius Rm required for the piece obtained from the preform in its final state as will be explained later.
• the preform then takes a form of revolution whose sections or generatrices are shaped "S" according to the contours 29a'-25'-29b '.
• the point 25 of the sheet on the mandrel 20 then passes from the radius rm to the radius Rm by the extension E on the point 25 'whose tangent T25 'has rotated due to the extension E at most in the plane normal to the axis A of the mandrel 20.
• a geometrical transformation R is then applied to the second portion 20b of the first state of manufacture of the preform on the mandrel 20, which has been enlarged by the extension E along the profile 25 '- 29b'.
• Said second part 20b of the first state of manufacture of the preform is between the point of inflection or cusp 25 'of tangent T25' and the end 29b 'of the sheet extended to the right of the drawing.
• the second transformation R includes in particular a translation parallel to the mandrel axis, so as to bring the second extended portion 25 '- 29b' in the position 25 '- 29b ", so that the preform is in a second and last
• the transformation R can be understood as a folding of the second portion 25 '- 29b' of the sheet of the preform which terminates its production or manufacture properly removed.
• Figure 5e shows the transformations that apply to a form whose extrema generator does not constitute a radial tangent but is similar to an angular edge.
• the chain position 25 will be characterized by two semantics T25a and T25b respectively towards 29a and 29b.
• the sheet from the mandrel 20 is deployed in an extension E l imitated to the final radius value corresponding to the chain 25 ', with the half-tangents T25a' and T25b 'respectively to 29a' and 29b '.
• the geometric transformation R symmetrically transposes 25'-29b 'of the sheet 25'-29b' to the plane of the generator 25 '.
• the second part 25-29b of the preform is, in this embodiment , subjected to an extension E to pass from the first state of manufacture 25-29b to the mandrel 20 to intermediate manufacturing state 25 '- 29b', so that the curvilinear lengths of the sheet elements composed by the weft yarns and This manufacturing constraint and others, alternatives or not, will be more completely defined further.
• the folding R is then applied, as in the embodiment of Figure 5d, but so that the second portion 25 '- 29b' of the extended preform is folded into 25 '- 29b "respecting a half tangent T25b" which forms a given angle, less than 180 ° with the half-tangent T25a ', and to the left of the plane normal to the axis A of the preform and the mandrel 20 and passes through the dots or sheet elements 25 and 25' .
• the expanded and folded preform 29a "- 25 '- 29b" is then in its second and last manufacturing state.
• the preform thus manufactured has an angular edge at 25 'which constitutes the most extreme point of the preform behind the plane normal to the axis of revolution A of the preform.
• the preform properly maintained on a forming tool can be further completed:
• non-structural filler material such as filling foam, or
• the manufacturing facility of revolution parts made of composite material of the invention provides the means for implementing the three main phases of the process mentioned above.
• the installation comprises a device for calculating an architecture of a fabric on the basis of a given shape of a piece of revolution to be made of a composite material and at least one mandrel for producing a fabric preform of said piece of revolution.
• This device comprises at least one CAD computer equipped with a log running the method of the invention, or at least one device for geometric description and geometric layout of the forms.
• the installation then comprises a device for producing a fabric reproducing the fabric architecture. determined.
• the weaving or braiding installation comprising the device for weaving and winding around mandrels made from the dimensions calculated during the first phase of the process.
• such a weaving or braiding device may be at the disposal of a supplier and its product stored and transported for the remainder of the process of the invention.
• the installation then comprises a mechanism for deploying the weaving from the garment mandrel, to the final form by applying the various transformations E and R previously described.
• This device may also include cutting means, means for securing layers between them or with local reinforcements.
• the installation then comprises a device for applying a polymerizable resin to the preform to produce the part of revolution.
• FIGS. 6 to 12 show the various calculation techniques used, in which the surfaces of the piece are cut into stitches according to rules which will be detailed below, and the cloth or weaving sheet will follow these same transformations during the different steps of the process which have been described previously.
• FIG. 6 we show the topology of a surface of the workpiece, the preform or mandrel covered by profile curves designated by the stitches of the stitches.
• a profile comprises a plurality of points (a, b, c, ...) to which, if appropriate, an index i ranging from 1 to n is assigned to describe the n curved profiles of the final part, the preform and / or chuck.
• an index i ranging from 1 to n is assigned to describe the n curved profiles of the final part, the preform and / or chuck.
• the radial scaling factor is such that one can reach for all the generators (a'i, b'i, ...) to compatible rays of mand ri ns of rolling of fabric, typically diameters between 50 mm and preferably less than 300 mm. But we can also make sure to have diameters between 200 and 800 mm for example depending on the dimensions of the final part. It is therefore common to have coefficients of the order of 0.1 to 0.3.
• the reduced generators (a "i, b" i, c “i, 7) are spaced apart by distances such that:
• the textile is wound which leaves suitably contextured by the aforementioned weaving machine.
• the mandrel having a non-cylindrical shape of "toroidal" shape the fibers are pulled (or called) by the mandrel in a differential manner throughout the width of the loom.
• the preform is thus created by a textile that conforms to a non-developable shape, namely, the shape of the mandrel, or the shape of the previous layer already wound on the mandrel if several turns are wound on the same shape.
• contour weaving or capstan contour weaving, or captsan contour braiding in the case of braiding.
• the proposed solution is particularly suitable for toric or substantially toric geometric shapes.
• the shapes described with reference to FIGS. 1 to 3 can be used.
• a geometric shape in the form of a "C" around an axis of revolution, a layer of fabric covering a part of the surface may be defined generically as, at a point on the surface, have an axis of so-called circumferential fibers, and an axis of fibers called transverse or radial.
• the purpose of transposition to weaving is to associate warp yarns, circumferential fibers and weft yarns with transverse fibers. The transposition to the case of braiding will be explained later.
• the transverse fibers have a defined angle with respect to the circumferential fibers, which is not necessarily at 90 ° angle.
• the part surface can be assimilated to a cone.
• This cone is a large diameter carrier, to facilitate its weaving on a loom, it is expected to reduce the diameter to an order of magnitude of 30 to 300 mm radius. This defines a factor of homothety between the considered cone of the part, and the necessary cone of mandrel.
• the fibers, in particular frames will be caused to glide relative to one another and with respect to the warp yarns of variations of length itaire, and in the case of a weave pattern has symmetrical embossing thickness, such as a canvas or twill 2x2 or 3x3, the different fibers of frames, have an identical length when considering the course with the embuvage .
• the turnaround there is no fiber that expresses an overvoltage compared to another.
• the concept developed above for a warp / weft fabric can also be applied to braiding, either biaxially at positive and negative angles around the axis, or triaxially, so that the third direction corresponds to the strings of the woven texture. will wrap around the mandrel.
• the principle of transposition of the shapes and textures remaining the same, the density and the orientations of the braid on the mandrel depending on the braiding devices upstream of the mandrel and the change in diameter of the mandrel.
• This variable surface mass being established, and depending on the density of the material and its volume distribution, create a virtual surface corresponding to the mid-thickness of the weave provided.
• the surface of the weaving mandrel is then deduced from the preceding virtual surface by removing the half-thickness of fabric as a function of its local surface area.
• the manufacturing method of the invention also applies to parts made of multiple layers of tissue, which is very often necessary. It can be observed that, for relatively small piece thicknesses relative to the radiuses of final pieces, for example for a part about 10 mm thick, the generatrices of which are on carrier spokes of at least 500 mm, the distortions fiber lengths resulting from the use of the same fabric defined on a mandrel, to achieve the different layers, are low and absorbed by compacting the layers before impregnation of resin, which simplifies industrialization fabric. We can therefore apply a simplified method of applying the method to the surface corresponding to a single layer and make the same fabric for all layers. The surface corresponding to the half-thickness of the room may preferably be used according to the degree of distortion that is allowed.
• the method described above allows mandrel definition and fabric weaving to achieve a substantially orthogonal orientation of the fabric on the workpiece surface.
• This limitation is sometimes penalizing to withstand the mechanical stresses to which such a part can be subjected.
• a geometry can often be subjected to torsional stresses, for which it is preferable to have at least one part of fibers arranged at helix angles alternately positively and negatively around the revolution.
• the method illustrated in FIGS. 11 and 12 is applied. It must therefore be considered that on the final shape the weave fibers of the weave will have an angle different from 90 ° with the warp fibers whereas during weaving we have naturally created such an angle of 90 °.
• the transposition between the mandrel and the final shape is done by changing the distance formulation between the different circumferences of the mandrel relative to the workpiece surface.
• the principle to be adopted is to consider a quadrilateral ma il lage of the surface of the room, in which the circumferential generatrices (ai, bi, ci, 7) correspond to the circumferences of the different chains of weaving obtained. ir, and for which the steps of surface reversal (symmetry) and diameter reduction are successively applied; and the segments ab, bc, cd, ... are oriented to follow the desired orientation in each region of the surface, the segments a "b", b "c" of lengths equal to segments ab, bc, .. defined on the surface, corresponding on the mandrels are arranged in a plane parallel to the axis of the mandrel.
• An almost angularly symmetrical draping assembly can be obtained by alternately decadrating in a positive or negative direction the successive layers of the stack. If different angles are desired for different layers, they will require, for the same part surface, as many mandrels of different profiles.
• Parts such as “C” sections of revolution (FIGS. 2a, 2b) and “S” of revolution can thus be mentioned (FIG. 3).
• Parts with closed sections can also be made by this method, the coverage of the part surface being obtained by different decompositions of the form either in two parts in “C” ( Figure 2c) or in a single part opening the shape ( Figures 3c - 3g).
• FIG. 6 there is shown an axis of revolution surface 46 representing a portion of a workpiece 40 to be manufactured.
• a meridian (a, b, c, d, e, ...) along a preform weft yarn 43 has been shown which undergoes a geometric transformation that passes the surface 40 into a transformed surface 44 which represents the mandrel.
• the meridian (a, b, c, d, ...) of the mesh surface 40 has been transformed into a meridian (a ", b", c ", %) on the mandrel surface 44 by a determined ratio homothety on the angles intercepted by each of the profile arcs ab, bc, cd, ...
• FIGS. 8a, 8b, 9 to 10 represent the modeling steps of a preform to be obtained and of transformation to deduce the form of the associated mandrel in a second embodiment of the method of the invention.
• the shape of the part to be obtained or of its fabric preform 50 is partially shown in FIG. 8a with its mesh by the warp yarns and the meridians aligned here on the weft yarns.
• the mesh points (a, b, c, ...) are repeated with current indices i ranging from 1 to n and the points (fi) are arranged on a warp thread representing an extremum of the points of the piece or of the preform 50 along its axis of revolution.
• FIG. 8b the mesh deduced by the geometric transformation described above and defined by the points of the current meridian (a'i, b'i, c'i, ...) is represented.
• the points (fi) along the shape 51 will correspond to points of inflection on the first state of the preform on its mandrel (see plane 25, on the mandrel 20, Figure 5a).
• a preform section is represented in that it is in one of the two states, respectively 55, 56 for the first unfolded state, and 55, 57 on its folded final form, corresponding to the marks respectively 50 and Figures 8a and 8b.
• Figures 1 1 and 12 show the modeling steps of a preform to obtain and transformation to deduce the shape of the associated mandrel in a third embodiment of the method of the invention.
• Figure 1 there is shown for a part to be produced with its preform 70, several weft son 71 belonging to a frame on warp son 72 with a given angulation during the manufacture of the fabric and determined during the design of the preform.
• the angle made with the reference direction is the angle a for the curvilinear segment ab, the angle ⁇ for the curvilinear segment bc, etc.
• the initial mesh is established according to the profiles (ai, bi, ci, di, ...) thus inclined with respect to normal to the circumferential lines.
• angles ⁇ ... must be smaller than the decadding capacity of the tissue that is planned to be produced (generally less than 35 °). It is desirable not to change too many angles along the profile which would make it more difficult to set up the shape.
• FIG. 12 shows in correspondence a profile 73 meshed by the series of points (ai, bi, ci, ...) and the derived mandrel profile 74, 75 with the points (a'i, b'i, this, ).
• point of inflexion fi which will correspond to the plane of reversal R or folding (See Figure 5a).
• the method comprises the choice of symmetrical weave patterns covering both sides of the sheet, such as linen or twill weaves.
• the method also comprises a step of decading the fabric in at least a portion of the sheet.
• weaving patterns such as taffeta or canvas pattern, twill patterns, satin patterns and any derived or hybrid patterns are used.
• the warp-weft weave is replaced by braiding, either biaxially at positive and negative angles around the axis, or triaxially, whose third direction corresponding to the woven texture strings will wrap around the mandrel.
• the method comprises a step to form multiple layers of sheet during manufacture of the preform.
• the method consists in producing the sheet used for the preform in a combination of a weaving technique with a braiding technique.
• the sheet is shaped in order to properly cover the surface, the frame son then following the profiles (a, b, c, . h) at defined angles.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Composite Materials (AREA)
• Mechanical Engineering (AREA)
• Textile Engineering (AREA)
• Moulding By Coating Moulds (AREA)
• Woven Fabrics (AREA)
• Braiding, Manufacturing Of Bobbin-Net Or Lace, And Manufacturing Of Nets By Knotting (AREA)

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• 2012
  • 2012-09-18 FR FR1258720A patent/FR2995557A1/fr active Pending
• 2013
  • 2013-09-17 RU RU2015113957A patent/RU2015113957A/ru unknown
  • 2013-09-17 EP EP13779249.5A patent/EP2897784A2/de not_active Withdrawn
  • 2013-09-17 WO PCT/FR2013/052133 patent/WO2014044963A2/fr active Application Filing
  • 2013-09-17 BR BR112015003567A patent/BR112015003567A2/pt not_active IP Right Cessation
  • 2013-09-17 CN CN201380048497.8A patent/CN104837608A/zh active Pending
  • 2013-09-17 CA CA2881118A patent/CA2881118A1/fr not_active Abandoned
• 2015
  • 2015-03-04 US US14/638,386 patent/US20150174833A1/en not_active Abandoned

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