Core for molding a hollow composite profile and molding method using such a core

Abstract

The invention relates to a molding core (110) comprising a plurality of slices (111) aligned along a longitudinal direction (X) of extension of the core and an extraction member mechanically connecting the slices together so that said slices are movable in translation along the longitudinal direction and can be brought closer to and moved away from each other, said slices being further configured to flex each around a transverse axis (Y) substantially orthogonal to said longitudinal direction, the core being configured to adopt: - a so-called molding configuration, in which the slices are brought closer to each other, so as to form together a compact core and - a so-called extraction configuration, in which said slices are successively mechanically stressed by the extraction member,so that the slices successively bend substantially around the transverse axis and are successively moved away from each other. figure for the abstract: figure 8,

Description

Title of the invention: Core for molding a hollow composite profile and molding method using such a core TECHNICAL FIELD OF THE INVENTION

[0001] The field of the invention is that of composite structures and their manufacturing processes.

[0002] More specifically, the invention relates to a core for molding a hollow composite profile on, or with, a composite part.

[0003] The invention also relates to a molding device comprising such a core.

[0004] The invention also relates to a method for molding a hollow composite profile on a composite part by means of such a molding device, itself comprising such a core.

[0005] The invention finds applications in particular in the molding of stiffeners on composite skins, to form composite parts such as aircraft fuselage panels.

[0006] The invention finds applications in the technological industries of aeronautics and space, but can also find applications in the field of land or marine vehicles, or even in the construction or energy industries. STATE OF THE ART

[0007] Aircraft structures, in particular aircraft fuselages, are generally made of composite skins reinforced by reinforcing elements.

[0008] For example, such reinforcing elements may be stiffeners, sometimes also called stringers, stringers, or spars in English terminology.

[0009] Such stiffeners may in particular themselves be made of composite material, for example of the same material as the composite skin which they are intended to reinforce.

[0010] Known stiffeners are generally in the form of hollow composite profiles, that is to say in the form of an elongated element having a section with a concave profile, called female, and a convex profile, called male, opposite the female profile. In particular, the hollow composite profile is open, that is to say it does not define a closed section but rather an open one.

[0011] Subsequently, reference is made in the presentation of the state of the art and in the statement of the invention as well as in the detailed description to the term "stiffener", the invention which will be set out below can however be generalized to any generic hollow composite profile.

[0012] For example, the section of a stiffener may have a so-called omega profile (Q), but may also have a U, V, L, Z or Delta shape, for example.

[0013] [Fig.l] schematically represents a generic composite panel 1, comprising a composite skin 2 and a plurality of stiffeners 3 with an omega profile, here three in number, which are molded onto the composite skin 2.

[0014] [Fig.2] schematically represents a stiffener 3 having an omega profile.

[0015] The stiffener 3 has a male profile 4, also called an external profile, and a profile female 5, also called internal profile, opposite male profile 4.

[0016] The male profile 4 forms a convex profile while the female profile 5 forms a concave profile of the stiffener 3.

[0017] The female profile 5 is generally oriented towards the composite skin 2, as can be seen in [Fig.l].

[0018] The female profile 5 comprises an interior space 6, which is closed by the composite skin 2 when the stiffener 3 is secured to it.

[0019] The composite panel 1 may for example be produced by a process of co-firing the composite skin 2 and one or more composite stiffeners 3, previously preformed, i.e. composite stiffener preforms.

[0020] Such a method generally comprises placing one or more preformed stiffeners in a mold comprising impressions in the shape of the male profile of a stiffener.

[0021] The stiffener may have been preformed beforehand using any known technique.

[0022] The method then comprises placing a core in each of the spokes stiffeners, the core being in the shape of the interior space of the female profile of the stiffeners.

[0023] Then, the method comprises draping the composite skin over the assembly formed by the mold, the stiffeners and the cores, with the composite skin being in contact with the stiffeners.

[0024] This step is preferably a fiber placement type step, which is carried out under pressure, in order to ensure the cohesion of the successive layers of fibers constituting the composite skin, as well as the cohesion between the composite skin and the stiffeners. This pressure can be ensured by an elastomer roller which supports the fibers to be deposited.

[0025] During this step, pressure is also applied to the cores, which must have sufficient rigidity for this purpose.

[0026] The assembly formed by the mold, the stiffeners, the cores, and the composite skin is then placed under vacuum, for example using a vacuum bag.

[0027] The vacuum-packed assembly is cooked by simultaneous cooking (also called co-cooking) in an autoclave.

[0028] The cores are then demolded and extracted from the composite panel thus formed.

[0029] The demolding and extraction of the cores is a step presenting a significant number of technical difficulties.

[0030] Indeed, the significant friction force between the stiffeners and the cores prevents the latter from being extracted from the stiffeners.

[0031] This force is increased due to the elongated nature of the stiffeners, which is synonymous with a significant friction surface between the stiffeners and the cores.

[0032] This force is also increased when the panel has a curvature, in one plane, or even in two planes.

[0033] Finally, this force is increased when the composite skin has local thickness variations, which can locally increase the friction force.

[0034] In order to overcome this drawback, several variants of cores are known in the art.

[0035] On the one hand, fusible cores are known in particular, in particular made from a metallic material having a melting point substantially higher than the firing temperature of the composite.

[0036] During the autoclave cooking process, the metal remains in solid form, and the core is rigid.

[0037] At the end of cooking, the assembly is dipped in a bath at the melting temperature of the metallic material, which becomes liquid and can be recovered.

[0038] For example, the fusible core may be made of lead-bismuth alloy.

[0039] On the other hand, soluble nuclei are known in particular, which are soluble in water or destructible by means of water pressure.

[0040] Finally, silicone cores are also known, with a rigidity and hardness sufficiently high to withstand the pressure during the draping step, but sufficiently low so that the core can be properly extracted from the stiffener.

[0041] However, these solutions have drawbacks and are not fully satisfactory.

[0042] Meltable and soluble cores have the disadvantage of different expansion of the core on the one hand and of the stiffener on the other hand during cooking, due to the difference in material between the core and the stiffener.

[0043] This can lead to the introduction of mechanical stresses into the composite structure resulting from the process, and thus to local cracking in the part.

[0044] In addition, soaking in a bath to remove the core limits the size of composite parts that can be obtained by these processes.

[0045] In an industrial setting, the dimensions of bath tanks do not allow the soaking of large structures.

[0046] Silicone cores, with constant mechanical properties during the process, have the disadvantage of being neither particularly rigid nor particularly flexible.

[0047] Thus, the silicone cores only have average rigidity while being difficult to extract from the stiffeners, in particular when the latter are extended in length.

[0048] There is thus a need for a method of molding composite parts with cores which have both excellent rigidity, i.e. resistance to pressure, and which can be easily extracted during demolding. Statement of the invention

[0049] The present invention aims to remedy all or part of the drawbacks of the state of the art cited above.

[0050] To this end, the invention relates to a core for molding a hollow composite profile on a composite part, comprising a plurality of slices aligned in a longitudinal direction of extension of the core and an extraction member mechanically connecting the slices together so that said slices are movable in translation in the longitudinal direction and can be brought closer to and moved away from each other, said slices being further configured to flex each around a transverse axis substantially orthogonal to said longitudinal direction, the core being configured to adopt: - a so-called molding configuration, in which the slices are brought together, so as to form together a compact core configured to be placed in the hollow composite profile with a view to its molding on the composite part; and - a so-called extraction configuration, in which said slices are successively mechanically stressed in the longitudinal direction by the extraction member, so that the slices successively flex substantially around the transverse axis and are successively moved away from each other in the longitudinal direction, whereby the slices can be progressively extracted from the hollow composite profile in the longitudinal direction, following the molding of the hollow preformed composite profile on the composite part.

[0051] The design of the core in the form of a stack of flexible, translationally movable slices makes it possible to carry out such extraction with less effort, while also making it possible to form a sufficiently rigid and compact core in the molding configuration.

[0052] Thus, the core according to the invention makes it possible to produce composite structures of large dimensions, the extraction of a particularly long core being possible in the extraction configuration, while requiring only limited mechanical effort during extraction.

[0053] The core allows in particular the production of composite structures having significant curvatures, in one or more planes, while allowing easy extraction of the core after molding.

[0054] Furthermore, the core, in its molded configuration, has mechanical properties, in particular pressure resistance, at least equivalent to known techniques, for example soluble or fusible cores.

[0055] Furthermore, the core according to the invention is entirely reusable at the end of a molding cycle, by simply putting it into molding configuration.

[0056] Particularly advantageous characteristics of the core according to the invention are presented below.

[0057] - The slices each comprise a first portion and a second portion which are hinged to each other, so that said portions can fold towards each other when the slice is mechanically stressed in the longitudinal direction.

[0058] In such an embodiment, the slices flex by folding around a hinge axis substantially transverse to the longitudinal direction.

[0059] - The slices each comprise a hinge by which the first portion and the second portion are hinged to each other, the hinge extending in the direction of said transverse axis of each slice.

[0060] In such an embodiment, the portions may pivot relative to each other, and the wafer may flex by folding the portions toward each other.

[0061] - The slices each comprise a portion of reduced thickness between their first portion and their second portion, forming a flexible articulation in the direction of said transverse axis of each slice.

[0062] In such an embodiment, the portion of reduced thickness forms a material hinge, the slice being able to be produced in one piece.

[0063] - The slices are each formed by a plate which is in one piece of substantially constant thickness and which is flexible, so that the slices can flex around the transverse axis when they are mechanically stressed in the longitudinal direction of each slice.

[0064] In such an embodiment, the slice has intrinsic flexibility, which can be obtained in particular by a sufficiently low thickness and / or a substantially soft and flexible constituent material, such as thermoplastic elastomer, for example Santoprene (registered trademark), so that the slice can flex around the transverse axis.

[0065] - The extraction member is configured to be stressed in traction in the direction longitudinal.

[0066] - The extraction member comprises a strip of material mechanically secured at intervals to the slices.

[0067] For example, the strip of material may be a woven strip of glass fibers.

[0068] By interlocking at intervals, it is meant that the slices are locally secured to the strip so as to be separated from each other when the strip is stretched, and to be brought together when the strip is folded, in particular in an accordion, between each of the slices.

[0069] - The extraction member comprises a strip of material comprising members support elements arranged at intervals on the strip of material and which are each configured to bear on a slice to cause it to move in the longitudinal direction when the strip of material is subjected to traction in the longitudinal direction.

[0070] For example, the strip of material may be a woven strip of glass fibers, and the support members may be overmolded onto the strip of material and be formed by support washers.

[0071] - The core further comprises a compacting member configured to maintain and / or compress the slices against each other in the molding configuration.

[0072] Such a member makes it possible to maintain the core in the molding position, with the slices which are held firmly against each other.

[0073] - The core further comprises a head heel and a tail heel, arranged on either side and other of the plurality of aligned slices, and the compacting member comprising a strip of material mechanically secured to the head heel and passing through the plurality of slices as well as the tail heel, and the tail heel preferably comprising a locking member configured to lock the strip of material in position.

[0074] According to an alternative, the compacting member can be secured to a first of the slices of the plurality of slices, without the core having a head heel and / or a tail heel.

[0075] - The slices are similar to each other and each have a first face and a second face opposite the first face, by which the slices are configured to come into contact with each other, said first face being convex, preferably in the shape of a convex spherical portion, and said second face also being convex, preferably in the shape of a convex spherical portion, or concave, preferably in the shape of a concave spherical portion.

[0076] This results in a core with identical or similar slices, which are either in contact by pairs of convex faces, or by pairs of concave and convex faces.

[0077] This makes it possible to design a core with the slices which are "articulated" with each other when they are brought together, and which allows the molding of composite structures having strong curvatures.

[0078] - The plurality of slices comprises so-called even slices and so-called odd, aligned alternately along the longitudinal direction, and which each comprise a first face and a second face opposite the first face, by which the slices are configured to come into contact with each other, said first face and second face of the odd slices being convex, preferably in the shape of a convex spherical portion, and said first face and second face of the even slices being concave, preferably in the shape of a concave spherical portion.

[0079] This makes it possible to design a core with slices that are "articulated" with each other when they are brought together, and which allows the molding of composite structures having strong curvatures.

[0080] - The slices each further comprise at least one transfer opening of pressure, extending in the longitudinal direction, the pressure transfer openings of the plurality of slices facing each other in the molding configuration, and the slices each comprising at least one pressure distribution opening, communicating with the at least one pressure transfer opening and extending transversely to the longitudinal direction.

[0081] This allows the pressure to be distributed during an autoclave co-curing step during molding, so that the pressure is applied equally inside the hollow composite profile.

[0082] - The core further comprises a tubular vacuum bag, in which the plurality of slices.

[0083] This makes it possible to carry out an autoclave co-cooking step in a particularly efficient manner, and also makes it possible to protect the core from deterioration.

[0084] According to a second aspect, the invention relates to a molding device, comprising a mold comprising at least one imprint configured to receive a hollow composite profile, and at least one core as described above, configured to be arranged in the hollow composite profile.

[0085] Such a device may also comprise a vacuum bag, and / or cooking means, and / or an additive manufacturing system for placing composite fibers.

[0086] According to a third aspect, the invention relates to a method for molding a hollow composite profile on a composite part by means of a molding device as described above, comprising the following steps: - a step of placing a preformed hollow composite profile, i.e. a hollow composite profile preform, in a mold cavity, the profile hollow composite preferably being a composite stiffener; - a step of positioning a core in the hollow composite profile, the core being in its molding configuration; - a step of draping the assembly comprising the hollow composite profile and the core with the composite part, the composite part preferably being a composite skin; - a step of co-firing the assembly comprising the hollow composite profile, the core with the composite part and the composite part; - a step of extracting the core from the hollow composite profile, in which the core is passed from its molding configuration to its extraction configuration by mechanical stressing of the extraction member in the longitudinal direction; the extraction step being implemented either following the co-curing step, or following the draping step and before the co-curing step.

[0087] It should be specified that the core according to the invention is also suitable for any use in a method of manufacturing a composite structure, or other than a composite structure, and in particular different from the method described above. BRIEF DESCRIPTION OF THE FIGURES

[0088] Other advantages, aims and particular characteristics of the present invention will emerge from the following non-limiting description of at least one particular embodiment of the devices and methods which are the subject of the present invention, with reference to the appended drawings, in which: • [Fig.l] is a schematic view of a composite panel comprising a composite skin and a plurality of stiffeners; • [Fig.2] is a schematic view of the profile of a stiffener presenting a omega profile, secured to a composite skin; • [Fig.3] is a schematic and perspective view of a molding device during a first step of a process for molding a composite stiffener on a composite skin; • [Fig.4] is similar to [Fig.3], and illustrates the molding device during of a second step of the molding process, using a molding core according to the invention; • [Fig.5] is similar to figures 3 and 4, and illustrates the molding device during a third stage of the molding process, in particular after the fibers of the composite skin have been removed; • [Fig.6] is a detailed sectional view of the molding device during the third stage of the molding process; • [Fig.7] represents schematically and in a longitudinal sectional view the molding core according to a first embodiment, the core being in a molding configuration; • [Fig.8] is a detailed view, in longitudinal section, of the molding core of [Fig.7], the core being in an extraction configuration; • [Fig.9] is a detailed perspective view of a slice of the core of [Fig.7] and [Fig.8]; • [Fig. 10] schematically represents, in a longitudinal sectional view, the molding core according to a second embodiment, the core being in a molding configuration; • [Fig. 11] is similar to [Fig. 10], with the core in an extraction configuration; • [Fig. 12] is a detailed perspective view of a slice of the core of [Fig. 10] and [Fig. 11]; • [Fig. 13] schematically represents a core extraction organ of [Fig. 10] and [Fig. 11], taken in isolation; • [Fig. 14] is a block diagram of a molding method according to the invention, implemented by means of a molding device according to the invention. DETAILED DESCRIPTION OF THE INVENTION

[0089] The present description is given without limitation, each characteristic of an embodiment being able to be combined with any other characteristic of any other embodiment in an advantageous manner.

[0090] It should be noted, from now on, that the figures are not necessarily to scale.

[0091] The subject of the invention is the production of a composite structure comprising a composite part and a preformed hollow composite profile which is molded onto the composite part.

[0092] The composite structure may be a composite panel, for example an aircraft fuselage, and the preformed hollow composite profile may be a composite stiffener, for example having an omega profile, without this example being limiting.

[0093] The [Fig.l] described above illustrates such a generic composite panel 1, comprising a composite skin 2 and a plurality of stiffeners 3, here three in number; and the [Fig.2] described above illustrates a generic stiffener 3 having an omega profile.

[0094] The composite panel 1, and more generally any other type of composite structure, can be produced by means of a molding device 100 according to the invention.

[0095] [Fig.3], [Fig.4] and [Fig.5] illustrate schematically and in perspective the device 100 at different stages of a method of molding a composite stiffener 3 on a composite skin 2, as described below.

[0096] [Fig.6] is a detailed sectional view of the device 100 at the step illustrated in [Fig.5].

[0097] The device 100 comprises a mold 105 having an outer surface 106 in the shape of the composite skin 2, and at least one imprint 107 having a female profile corresponding to the shape of the male profile 4 of a stiffener 3, which is here of the omega type without such a shape being limiting.

[0098] Here, the mold 105 comprises three cavities 107 without this number being limiting.

[0099] The prints 107 are elongated in length along a longitudinal extension direction and are here substantially rectilinear, but can also be curved along their extension direction.

[0100] In the example illustrated, the outer surface 106 of the mold 105 is substantially curved, and has a curvature in a plane transverse to the direction of extension of the cavities 107.

[0101] The imprints 107 are configured to each receive a preformed composite stiffener 3, which can be obtained using any known preforming technique.

[0102] The device 100 further comprises at least one molding core 110, and here three cores 110 in the illustrated example.

[0103] More generally, the number of cores 110 corresponds to the number of cavities 107 that the mold 105 comprises.

[0104] Each core 110 is elongated in length and extending along a longitudinal direction X of extension, which may be rectilinear or curved.

[0105] For example, the length of a core 110 is of the order of 10 to 20 meters, for example 15 meters.

[0106] Each core 110 is configured to be arranged inside the stiffener 3, in contact with the female profile 5 of the stiffener 3.

[0107] The core 110 has a profile corresponding to the profile of the interior space 6 of the stiffener 3, and is here of general trapezoidal shape.

[0108] The assembly formed by the mold 105, the stiffener(s) 3, and the core(s) 110 is configured to be draped by the composite skin 2, covering the stiffener(s) 3 and the core(s) 110, as illustrated in Figures 5 and 6.

[0109] The device 100 may further comprise a means for placing under vacuum (not shown) the assembly formed by the mold 105, the stiffener(s) 3, the core(s) 110 and the composite skin 2.

[0110] For example, the vacuum means is a vacuum bag.

[0111] The device may further comprise a cooking means (not shown), for autoclave cooking of the vacuum-packed assembly.

[0112] As shown in [Fig.7], which shows a longitudinal sectional view of a core 110 of the device 100 according to a first embodiment, the core 110 comprises a plurality of aligned “vertebrae” or slices 111, along the longitudinal direction X of the core 110.

[0113] Each of the slices 111 comprises a first face and a second face opposite the first face, by which the slices 111 are configured to come into contact with each other.

[0114] The slices 111 here have a general plate shape, of substantially constant thickness, each extending in a plane orthogonal to the longitudinal direction X. In particular, the thickness of the slices 111 is sufficiently small to allow cores 110 to be produced having a longitudinal curvature, in one plane or even in two planes.

[0115] The slices 111 together form a stack of slices, also called hereinafter a “spine” or column of slices.

[0116] In particular, the core 110 may comprise a head heel 112 and a tail heel 113, which are arranged on either side of the stack of slices 111. The head heel 112 and the tail heel 113 may be substantially different from the slices 111, and in particular have a substantially curved shape and / or be thicker than the slices 111.

[0117] The core 110 can adopt a molding configuration, in which the slices 111 of the column are brought together in the longitudinal direction X.

[0118] In particular, in this configuration, each of the slices 111 is in direct contact with its neighboring slices 111.

[0119] [Fig.7] shows the core 110 in the molding configuration, with the slices 111 which are shown slightly spaced from each other for reasons of readability of the figure.

[0120] In the molding configuration, the slices 111 form a compact and substantially rigid core, which is suitable for molding the stiffener 3 on the composite skin 2.

[0121] The slices 111 are each made of a material that is sufficiently rigid to form a molding core, in particular to ensure sufficient counterpressure during the draping of the composite part, which may be a composite skin 2.

[0122] For example, the slices 111 are made of thermoplastic material, which also allows the slices 111 to be manufactured by molding in large quantities, economically.

[0123] The core 110 may further adopt an extraction configuration, shown in detail in [Fig.8], in which at least a portion of the slices 111 are spaced apart from each other.

[0124] Furthermore, in this configuration, the slices 111 flex around a transverse direction Y, substantially orthogonal locally to the longitudinal direction X of extension of the core.

[0125] Thus, the slices 111 can be moved along the longitudinal direction X substantially without effort, allowing the extraction of the core 110.

[0126] In [Fig.8], a first of the slices 111 is moved in the longitudinal direction X and is located away from the other slices 111 which are still in contact with each other in this figure.

[0127] The core 110 comprises an extraction member 125 mechanically connecting the slices 111 to each other, so that the slices 111 can be moved closer to and further away from each other, that is to say that they are movable in translation relative to each other.

[0128] The extraction member 125 is configured to allow the core 110 to pass from the molding configuration to the extraction configuration, by mechanical stressing of the extraction member 125.

[0129] The extraction member 125 allows the progressive extraction of the slices 111 from the stiffener 3, after molding. In other words, thanks to the extraction member 125, the slices 111 can be pulled in a string out of the stiffener 3.

[0130] In particular, the extraction member 125 may be a traction element.

[0131] In the example illustrated, the extraction member 125 is formed by a first strip 126 of material.

[0132] The traction element can however also be formed by a cable, a chain, an articulated rod, a braid, etc.

[0133] In the first embodiment illustrated, the first strip 126 is mechanically secured to each of the slices 111, for example according to a pivot connection substantially orthogonal to the longitudinal direction X.

[0134] The slices 111 are mechanically secured to the first strip 126 at intervals, in particular at regular intervals.

[0135] Thus, when the first strip 126 is stretched, the slices 111 are at a distance from each other and can each be driven in translation in the longitudinal direction X.

[0136] When the core 110 is in the molding configuration, that is to say when the slices 111 are in contact with each other, the first strip 126 can be folded back on itself.

[0137] For this purpose, each of the slices 111 may comprise a housing 114 in which the first strip 126 may be housed in the molding configuration.

[0138] The core 110 may further comprise a compacting member 130, configured to hold the slices 111 against each other in the longitudinal direction. tudinale X.

[0139] For example, the compacting member 130 is a traction element.

[0140] In the example illustrated, the compacting member 130 is formed by a second strip 131 of material.

[0141] The traction element can however also be formed by a cable, a chain, a rod, a braid, etc.

[0142] In the first embodiment illustrated, the second strip 131 is mechanically secured to the head heel 112, and passes through the entire column of slices 111 as well as the tail heel 113.

[0143] For this purpose, the slices 111, as well as the tail heel 113 if applicable, can each be provided with a passage opening 115, through which the second strip 131 can pass.

[0144] The tail heel 113 may comprise a locking member 132, configured to lock the second strip 131 in position, in particular with a view to maintaining a compressive force exerted on the slices 111 by the clamping of the second strip 131.

[0145] In order to be able to flex, the slices 111 have a capacity for deformation in a plane substantially orthogonal to the longitudinal direction X.

[0146] More precisely, the slices 111 are configured to each flex around the transverse axis Y of each slice 111, which is substantially orthogonal (at least locally) to the longitudinal direction X of the core 110, when they are mechanically stressed in the longitudinal direction X.

[0147] By "flexing" is meant the fact that the slices 111 bend or fold, this may include in particular a sharp fold for example by means of a hinge, or even a general bending of the slice, for example due to the intrinsic elasticity of the slice 111, or a combination of these examples.

[0148] [Fig.9] illustrates in perspective a slice 111 according to the first mode of realization lization, taken in isolation.

[0149] The slice 111 comprises a first portion 116 and a second portion 117, which are articulated with each other.

[0150] In particular, the slice 111 here comprises a hinge 118 comprising a hinge axis 119.

[0151] Here, the hinge axis 119 also forms the pivot connection between the slice 111 and the first strip 126.

[0152] The hinge 118 here has a unidirectional articulation, that is to say that the first portion 116 and second portion 117 can only be folded towards each other in one direction along the longitudinal direction X.

[0153] In particular, the folding of the first portion 116 and the second portion 117 towards each other is here only possible in the direction opposite to the direction of extraction. in the longitudinal direction X, and the first portion 116 and the second portion 117 remain substantially aligned in the same transverse plane during a stress in the direction opposite to the extraction direction.

[0154] For this purpose, the second portion 117 may comprise one or more stop tabs 120 extending beyond the hinge 118, and bearing on the first portion 116 when the first portion 116 and second portion 117 are substantially aligned in the same plane.

[0155] According to an alternative, the hinge 118 can also be formed by local thinning of material of the slice 111.

[0156] Figures 10 and 11 show the core 110 according to a second embodiment, respectively in the molding configuration and in the extraction configuration.

[0157] [Fig. 12] illustrates a slice 111 according to the second embodiment, taken in isolation.

[0158] In the second embodiment, the slices 111 are in one piece.

[0159] The slices 111 are here deformable due to their intrinsic flexibility in a plane substantially orthogonal to the longitudinal direction X.

[0160] For example, for this purpose, the slices 111 are made of elastomer material, preferably of thermoplastic elastomer, for example Santoprene (registered trademark).

[0161] [Fig. 13] schematically illustrates the first strip 126 according to the second embodiment.

[0162] The first strip 126 here comprises support members configured to bear on the slices 111 to drive them in translation in the longitudinal direction X, when a tensile force is exerted on the first strip 126.

[0163] The support members are formed at intervals, in particular at regular intervals, on the first strip 126

[0164] For example, the support members are formed by support washers 127, which can be overmolded onto the first strip 126.

[0165] The slices 111 may comprise a passage opening 121 through which the first strip 126 can pass.

[0166] The slices 111 may also comprise a housing 122 configured to receive a support washer 127.

[0167] Furthermore, in the second embodiment, the slices 111 comprise pressure transfer openings 123, extending substantially in the longitudinal direction X, and pressure distribution openings 124, extending substantially transversely to the longitudinal direction X.

[0168] The pressure transfer openings 123 of the plurality of slices 111 are substantially opposite each other in the molding configuration, and form together a single opening axially passing through the stack of slices 111.

[0169] The pressure transfer openings 123 and the pressure distribution openings 124 communicate, that is, they are fluidically connected.

[0170] The pressure distribution openings 124 open onto the periphery of each slice 111.

[0171] The pressure transfer openings 123 and the pressure distribution openings 124 together form an autoclave pressure distribution network.

[0172] It should be emphasized that in the first embodiment, the slices 111 may also comprise such openings 123 and 124.

[0173] Whatever the embodiment considered, the core 110 may comprise a tubular vacuum bag 140, forming a casing in which the stack of slices 111 is arranged.

[0174] In particular when the slices 111 have pressure transfer openings 123 and pressure distribution openings 124, the autoclave pressure can thus be applied to the female profile 5 of the stiffener 3.

[0175] Unlike the first embodiment illustrated, the core 110 does not here comprise a compacting member 130, although it may comprise such a compacting member 130 for example similar or identical to that described in connection with the first embodiment.

[0176] Unlike the first illustrated embodiment, the core 110 does not include a head heel 112 or a tail heel 113, although it may include such head heels 112 and / or tail heels 113, for example similar or identical to those described in connection with the first embodiment.

[0177] In the illustrated examples, the slices 111 have a first face and a second face which are substantially flat.

[0178] According to an exemplary embodiment not shown, the slices 111 may however also have a first face and a second face which are not substantially flat.

[0179] For example, the slices 111 may have a first face and a second face each convex, preferably in the shape of a cylindrical or spherical convex portion.

[0180] According to another example, the slices 111 may have a first convex face, preferably in the shape of a cylindrical or spherical convex portion, and a second concave face, preferably in the shape of a cylindrical or spherical concave portion, the first and second faces of two adjacent slices being configured to come into contact with each other respectively.

[0181] Furthermore, in the illustrated examples, the slices 111 are substantially identical or similar.

[0182] According to an exemplary embodiment not shown, the plurality of slices 111 comprises slices 111 called even and slices 111 called odd, aligned alternately along the longitudinal direction X, having different faces.

[0183] In particular, the first face and second face of the odd slices 111 may be convex, preferably in the shape of a cylindrical or spherical convex portion, and the first face and second face of the even slices 111 may be concave, preferably in the shape of a cylindrical or spherical convex portion.

[0184] The composite panel 1 of [Fig.l], and more generally any generic composite structure, can be obtained by means of a molding process 200, illustrated by the block diagram of [Fig. 14].

[0185] The molding method 200 can in particular be implemented by means of a molding device 100 according to the invention, as illustrated in FIGS. 3 to 6 at different stages of the molding method 200.

[0186] The method 200 comprises a step 205 of providing a mold 105 comprising impressions 107 in the shape of the male profile 4 of a stiffener 3, as illustrated in [Fig.3] in particular.

[0187] The method 200 then comprises a step 210 of providing at least one preformed composite stiffener 3, i.e. a composite stiffener preform. Such a stiffener preform may have been obtained by any manufacturing method known in the art.

[0188] The method 200 then comprises a step 215 of placing the at least one preformed composite stiffener 3 in the mold 105, with the male profile 4 which comes into contact with the impressions 107, as illustrated in [Fig.4].

[0189] Then, the method 200 comprises a step 220 of positioning a core 110 in each preformed composite stiffener 3, so that the core 110 is then placed in the interior space 6 in contact with the female profile 5 of the stiffener 3.

[0190] The core 110 is in its molding configuration during this step, with the slices 111 which are close together and in particular in contact with each other.

[0191] For example, for this purpose, the compacting member 130 may be urged to compact the core 110 when the core comprises such a member. In particular, the second strip 131 may be stressed in tension, then locked in position by means of the locking member 132.

[0192] The method 200 then comprises a step 225 of draping the assembly comprising the at least one stiffener 3 and the core(s) 110, with a composite part, which is for example a composite skin 2.

[0193] In particular, the draping step 225 is a fiber placement step, during which the fibers of a reinforcement of a semi-finished composite material are deposited on the outer surface 106 of the mold 105, as well as on the assembly comprising the at least one stiffener 3 and the core(s) 110.

[0194] For example, the draping step 225 comprises the deposition of the fibers by a fiber placement head forming part of an additive manufacturing system. During this step, the fiber placement head locally exerts significant pressure on the mold 105 and on the cores 110.

[0195] According to a variant, the device 100 may itself comprise such an additive manufacturing system.

[0196] Figures 5 and 6 illustrate the device 100 after the draping step 225.

[0197] Then, according to a first variant of the method 200, the method 200 comprises a step 230 of extracting the core 110 from the stiffener 3.

[0198] During the extraction step 230, the core 110 has passed from its molding configuration to its extraction configuration.

[0199] For this purpose, the extraction member 125 is mechanically stressed, for example in traction in the first and second embodiments illustrated.

[0200] The first strip 126 is pulled along the longitudinal direction X, which has the effect of exerting traction on the first of the slices 111. This causes the first slice 111 to flex, for example either by folding around the hinge 119 as in the first embodiment ([Fig.8]) or by flexing the slice as a single piece as in the second embodiment ([Fig.11]), which has the effect that the first of the slices 111 can be moved along the longitudinal direction X, substantially without effort once flexed.

[0201] The first slice 111 moves in the longitudinal direction X, until the portion of the first strip 126 located between the first of the slices 111 and the second of the slices 111 is stretched, and in turn causes the second of the slices 111 to bend, then move in the longitudinal direction X, and so on (see [Fig. 11] which illustrates the first three of the slices 111 which are thus driven).

[0202] The slices 111 are thus progressively extracted from the stiffener 3 in the longitudinal direction X, in a string.

[0203] When all of the plurality of slices 111 have been extracted from the stiffener, the tubular vacuum bag 140 remains in contact with the interior profile of the stiffener in order to allow the pressure of the autoclave to be transferred during the co-curing of the composite skin - stiffener assembly.

[0204] The core 110 can then be reused, by being put back into its molding configuration.

[0205] The method 200 then comprises a step 235 of co-firing the assembly comprising the at least one stiffener, the core(s) 110 as well as the composite skin. 2.

[0206] During this co-firing step, the composite fibers of the stiffener(s) 3 as well as of the composite skin 2 are bonded and secured.

[0207] The co-cooking step 235 is preferably an autoclave cooking step, i.e. under pressure. For this purpose, the assembly can be placed in a vacuum bag.

[0208] During this step, the openings 123 and 124 of the slices 111 ensure pressurization of the interior of the stiffener 3.

[0209] According to a second alternative, the method comprises the extraction step 230 following the co-firing step 235, rather than following the draping step 225 and before the co-firing step 235.

[0210] In such a case, the core 110 advantageously comprises a tubular vacuum bag 140.

[0211] It is recalled more generally that the invention is not limited to the examples described and illustrated.

[0212] In particular, the core according to the invention can be implemented for any type of manufacturing process other than composite molding, in which a rigid molding core is used.

Claims

Claims

1. Core (110) for molding a hollow composite profile on a composite part, characterized in that the core comprises a plurality of slices (111) aligned along a longitudinal direction (X) of extension of the core and an extraction member (125) mechanically connecting the slices together so that said slices are movable in translation along the longitudinal direction and can be brought closer to and moved away from each other, said slices being further configured to flex each around a transverse axis (Y) substantially orthogonal to said longitudinal direction, and in that the core (110) is configured to adopt: - a so-called molding configuration, in which the slices (111) are brought closer to each other, so as to form together a compact core configured to be arranged in the hollow composite profile for the purpose of molding it on the composite part;and - a so-called extraction configuration, in which said slices (111) are successively mechanically stressed in the longitudinal direction by the extraction member, so that the slices successively flex substantially around the transverse axis and are successively moved away from each other in the longitudinal direction (X), whereby the slices can be progressively extracted from the hollow composite profile in the longitudinal direction, following the molding of the hollow preformed composite profile on the composite part.;

2. Core (110) according to claim 1, wherein the slices (111) each comprise a first portion (116) and a second portion (117) which are hinged with each other, so that said portions can fold towards each other when the slice is mechanically stressed in the longitudinal direction.

3. A core (110) according to claim 2, wherein the slices (111) each comprise a hinge (118) by which the first portion (116) and the second portion (117) are hinged to each other, the hinge extending in the direction of said transverse axis of each slice.

4. Core (110) according to claim 2, in which the slices (111) each comprise a portion of reduced thickness between their first portion and their second portion, forming an articulation flexible in the direction of said transverse axis of each slice.

5. The core (110) of claim 1, wherein the slices (111) are each formed by a plate which is a single piece of substantially constant thickness and which is flexible, so that the slices can flex around the transverse axis when mechanically stressed in the longitudinal direction of each slice.

6. Core (110) according to any one of claims 1 to 5, in which the extraction member (125) is configured to be stressed in tension in the longitudinal direction.

7. Core (110) according to claim 6, in which the extraction member (125) comprises a strip (126) of material mechanically secured at intervals to the slices (111).

8. Core (110) according to claim 6, in which the extraction member (125) comprises a strip (126) of material comprising support members (127) arranged at intervals on the strip of material and which are each configured to bear on a slice (111) to drive it in movement in the longitudinal direction when the strip of material is stressed in tension in the longitudinal direction.

9. A core (110) according to any one of claims 1 to 8, further comprising a compacting member (130) configured to hold and / or compress the wafers (111) against each other in the molding configuration.

10. Core (110) according to claim 9, further comprising a head heel (112) and a tail heel (113), arranged on either side of the plurality of aligned slices (111), and the compacting member (130) comprising a strip (131) of material mechanically secured to the head heel and passing through the plurality of slices as well as the tail heel, and the tail heel preferably comprising a locking member (132) configured to lock the strip of material in position.

11. Core (110) according to any one of claims 1 to 10, wherein the slices (111) are similar to each other and each comprise a first face and a second face opposite the first face, by which the slices are configured to come into contact with each other, said first face being convex, preferably in the shape of a convex spherical portion, and said second face also being convex, preferably in the shape of a convex spherical portion, or concave, preferably in the shape of a concave spherical portion.

12. Core (110) according to any one of claims 1 to 10, wherein the plurality of slices (111) comprises so-called even slices and so-called odd slices, aligned alternately along the longitudinal direction, and which each comprise a first face and a second face opposite the first face, by which the slices are configured to come into contact with each other, said first face and second face of the odd slices being convex, preferably in the shape of a convex spherical portion, and said first face and second face of the even slices being concave, preferably in the shape of a concave spherical portion.

13. A core (110) according to any one of claims 1 to 12, the slices (111) each further comprising at least one pressure transfer opening (123), extending in the longitudinal direction, the pressure transfer openings of the plurality of slices facing each other in the molding configuration, and the slices each comprising at least one pressure distribution opening (124), communicating with the at least one pressure transfer opening and extending transversely to the longitudinal direction.

14. The core (110) of any one of claims 1 to 13, further comprising a tubular vacuum bag (140), in which the plurality of wafers (111) are disposed.

15. Molding device (100), comprising a mold (105) having at least one imprint (107) configured to receive a hollow composite profile (3), and at least one core (110) according to any one of claims 1 to 14, configured to be arranged in the hollow composite profile.

16. Method (200) for molding a hollow composite profile (3) on a composite part (2) by means of a molding device (100) according to claim 15, comprising the following steps: - a step (215) of placing a preformed hollow composite profile (3) in an imprint (107) of the mold, the hollow composite profile preferably being a composite stiffener; - a step (220) of positioning a core (110) in the profile hollow composite, the core being in its molded configuration; - a step (225) of draping the assembly comprising the hollow composite profile (3) and the core (110) with the composite part (2), the composite part preferably being a composite skin; - a step (235) of co-firing the assembly comprising the hollow composite profile, the core with the composite part and the composite part; - a step (230) of extracting the core (110) from the hollow composite profile, in which the core is passed from its molding configuration to its extraction configuration by mechanical stressing of the extraction member in the longitudinal direction; the extraction step (230) being implemented either following the co-firing step (235), or following the draping step (225) and before the co-firing step (235).

Images