Glazed assembly for an aircraft, manufacturing process for such a glazed assembly, and aircraft comprising such a glazed assembly

Abstract

Glazed assembly for an aircraft, method of manufacturing such a glazed assembly, and aircraft comprising such a glazed assembly. The invention relates to a glazed assembly (100) for an aircraft, said glazed assembly comprising laminated glazing (110) including a first structural ply (111) and a second structural ply (113) bonded to the first structural ply by means of an interlayer adhesive layer (115). Said glazed assembly also includes: - a retaining element (120) a first portion (121) of which is fixedly inserted into at least said interlayer adhesive layer, and a second portion (122) of which extends the first portion outside the glazing, - a plurality of catches (130) arranged in respective cavities (140) formed in the glazing such that said catches extend through the first portion as well as into each of said structural plies. Figure for the abridged version: Fig. 3

Description

Title of the invention: Glazed assembly for an aircraft, method for manufacturing such a glazed assembly, and aircraft comprising such a glazed assembly Previous technique

[0001] The present invention belongs to the general field of aircraft glazing design. More particularly, it relates to a glazed assembly for an aircraft (i.e., intended to equip an aircraft). It also relates to a method for manufacturing such a glazed assembly, as well as an aircraft equipped with it. The invention finds a particularly advantageous, though by no means limiting, application in the design of glazing for commercial aircraft.

[0002] Aeronautical glazing (cockpit glazing, including frontal or Windshields, side windows, and cabin windows (commonly called portholes) for aircraft designed to withstand pressure differentials between an external environment (atmosphere) and the aircraft's interior are laminated glass composed of multiple structural layers, typically at least two. In practice, an additional layer may be used, whose contribution to the glass's mechanical behavior is not significant, but which serves to ensure aerodynamic continuity and protection against certain conditions affecting the glass's environment (icing, abrasive conditions, hail, etc.).

[0003] By "structural fold of the glazing", classically reference is made to a rigid sheet constituting the laminated glazing and capable of constituting by itself a monolithic glazing, of ensuring its mechanical resistance, in particular, and having an elastic modulus of at least 1500 MPa for example.

[0004] Such a sheet can optionally be completed, to form the structural fold, by a heel and a wedge arranged on the entire periphery of the sheet, at the level of its edge, said wedge being further positioned between the sheet and the heel; reference is then made to a configuration of "structural bonding glazing".

[0005] Such a rigid sheet can either be a sheet of mineral glass, or a sheet of polymer materials, typically PMMA (acronym for "polymethyl methacrylate") of aeronautical grade or PC (acronym for "polycarbonate").

[0006] Furthermore, the structural plies are joined together by layers of interlayer adhesives, for example TPU (acronym for "thermoplastic polyurethane"), PVB (acronym for "polyvinyl butyral"), etc. It should be noted that such interlayer adhesive layers are not configured to exhibit an elastic modulus minimal as previously indicated. Consequently, an intercalary adhesive layer does not form a structural fold.

[0007] The overall design of an aircraft can be implemented in such a way as to ensure that the glazing contributes significantly to the transmission of pressure forces experienced by the aircraft. To this end, aircraft glazing is "stretched" on all sides. It is also said that the "glazing acts as a membrane," it being understood that it must allow the tangential stresses to circulate around the aircraft's envelope (i.e., the skin, or the hull, or the fuselage).

[0008] Also, among the functional requirements that aircraft glazing must meet is pressure resistance, which must be guaranteed not only when the glazing is intact (standard case) but also in the event of breakage of a structural fold of the glazing (the so-called "fail-safe" case). Put another way, the breakage of one of the folds must not result in the loss of the glazing or depressurization of the aircraft's interior, for example, the cockpit.

[0009] Another functional requirement lies in the ability to withstand bird impacts.

[0010] Compliance with these two requirements depends on several factors, such as the thickness of the structural plies, but also, and above all, on the configuration of the attachment system that allows the connection between the aeronautical glazing and the aircraft structure.

[0011] Known attachment systems each include external retention means in contact with the external surface (i.e., facing the external environment) of the glazing, and internal retention means in contact with the internal surface (i.e., facing the interior of the aircraft) of the glazing. Each of these external and internal retention means functions to ensure the support and stability of the glazing against the pressure forces to which it is subjected, as well as at least a partial seal (water, air) against the interior of the aircraft.

[0012] Generally, said internal and external retaining means (also called “retainers” in English) generally take the form of a screw / nut / washer (bolt) assembly, possibly supplemented by a metal band (for example, aluminum a few millimeters thick), which can be connected directly or indirectly to the aircraft structure.

[0013] Figures 1 and 2 schematically illustrate two variants of attachment systems according to the prior art.

[0014] In the case of [Fig. 1], a first glazing unit 1a (on the left in [Fig. 1]) and a second glazing unit 2a (on the right in [Fig. 1]) are arranged on either side of a structural element 3a of an aircraft. More particularly, in this example of [Fig. 1], said first and second glazing units 1a, 2a are side glazing units of the cockpit. Each window 2a is attached to this structural element 3a by means of an attachment system.

[0015] The first glazing attachment system la comprises a bolt 4a passing through the glazing from the outside to the inside of the aircraft. The head of the bolt 4a is fixed through a projection 8a of the structural element 3a, said projection 8a being in contact with the external surface of the first glazing la. The assembly formed by the head of the bolt 4a and said projection 8a constitutes the external retention means for said first glazing attachment system la. Furthermore, the nut and washer of the bolt 4a are fixed to a thin strip 7a in contact with the internal surface of the first glazing la. The assembly formed by the nut, washer, and said thin strip 7a constitutes the internal retention means for said first glazing attachment system la. It should be noted that the head of the bolt is fixed directly to the aircraft structural element 3a. Conversely, the nut and washer are fixed indirectly (via the glazing) to said element 3a of the aircraft structure.

[0016] The attachment system for the second glazing unit 2a is in the form of a bolt 5a, substantially similar to that of the attachment system for the first glazing unit 1a. However, the head of the screw of the bolt 5a (respectively the nut and washer of the bolt 5a) is here indirectly fixed via a band 6a (respectively directly, via a projection 9a of the structural element 3a) to the structural element 3a. Thus, the assembly formed by the head of the screw of the bolt 5a and said band 6a (respectively the nut, the washer, and said projection 9a) constitutes the external retaining means (respectively the internal retaining means) of said attachment system for the second glazing unit 2a.

[0017] In the case of [Fig. 2], a glazing 1b is used to form, at least in part, an aircraft windshield. Said glazing 1b is attached to an aircraft structural element 2b by means of an attachment system. The attachment system for the glazing 1b comprises a bolt 3b. The assembly formed by the head of the bolt 3b and a thin strip 5b constitutes the external retaining means of this attachment system. Furthermore, the assembly formed by the nut and washer of the bolt 3b, as well as a projection 4b of the structural element 2b to which said nut and washer are attached, constitutes the internal retaining means of this attachment system. It should be noted that, in this case, the strip 5b is directly attached to the structural element 2b by bolting.

[0018] It should be noted that other attachment systems exist. Thus, for example, in the case of pinched aeronautical glazing (i.e. glazing linked to the aircraft structure only by pinching a peripheral seal of the glazing), it is common to use an attachment system in which both the internal and external retaining elements are fixed directly to the aircraft structure.

[0019] Although widely deployed today, the attachment systems described above are still far from representing solutions that are very well suited to the functional requirements mentioned above for aeronautical glazing.

[0020] Indeed, the attachment system of [Fig. 1] transmits the pressure forces created within the aircraft through a single surface of the glazing (i.e., the external surface of the first glazing 1a and the internal surface of the second glazing 2a), which has the effect of inducing: - a torque at the level of the attachment system that can lead to failures due to delamination, - bending stresses at the level of the attachment system, which requires a thickening of this system and / or at least one structural fold of the glazing (mass constraints, and associated costs, particularly with regard to structural folds made of PMMA), - a very asymmetrical transmission of forces and therefore singularities of stress at the level of the attachment system, which limits the ability to transmit forces through the membrane.

[0021] The attachment system of [Fig. 2], on the other hand, is capable of transferring the pressurization forces more evenly across the two surfaces of the glazing, which tends to compensate at least partially for the shortcomings of the attachment system of [Fig. 1]. However, this attachment system of [Fig. 2] is also very rigid in bending, which, in the event of a bird strike near the attachment system, results in a high concentration of stresses in the glazing close to the impact.

[0022] Furthermore, as is common to all known attachment systems, aerodynamic continuity is predominantly affected by the configuration of the external retention means. For example, in the case of glazing la of [Fig. 1], the moment induced by the asymmetrical loading subjecting the protruding element la to bending forces it to thicken compared to the strip 6a, which is not subjected to bending. This results in an increased thickness of the first glazing la relative to the second glazing 2a, so as to ensure aerodynamic continuity between said first glazing la and its retention means.

[0023] Furthermore, in the case of glazing with an anti-frost function (i.e., glazing with an external heated fold), in order to maximize the viewing area of ​​the glazing, electrical elements enabling the implementation of said anti-frost function are positioned at the edge of the transparent area of ​​the glazing (example: space 6b illustrated in [Fig. 2] and through which said electrical elements pass). This configuration implies that the heated fold (example: fold 7b illustrated in [Fig. 2]) cannot extend to the edges of the structural folds it protects. This results in a weakness in terms of sealing at the point where the retaining means meet. external and external surfaces of the glazing, which is problematic given the sensitivity of electrical components to humidity. Some state-of-the-art solutions propose correcting this weakness by introducing a "Zed" element that forms a barrier at this intersection point. However, such a Zed element, in addition to creating an aerodynamic discontinuity, is a metallic component whose electrostatic charge must be managed, and which is expensive to produce. Description of the invention

[0024] The present invention aims to remedy all or part of the disadvantages of the prior art, in particular those set out above, by proposing a solution which makes it possible to obtain a glazed assembly capable of balancing the transmission of pressure forces in the membrane much more effectively than the solutions of the prior art, which greatly limits the risk of delamination, which does not require the use of an excessive thickness of structural ply, which complies with the "fail safe" requirement, which is capable of ensuring aerodynamic continuity with the aircraft envelope, and which is also particularly resistant to bird strikes, while being simple to manufacture and inexpensive.

[0025] To this end, and according to a first aspect, the invention relates to a glazed assembly for an aircraft, said glazed assembly comprising laminated glazing comprising a set of structural folds, including a first structural fold and a second structural fold fixed to the first structural fold by means of an interlayer. Said glazed assembly also comprises: - a retaining element, a first part of which is fixedly inserted into at least said interlayer at the edge of the laminated glazing and on at least a portion of its periphery, preferably on the entire periphery of the laminated glazing, and a second part of which extends the first part outside the laminated glazing, - a plurality of cleats arranged in respective cavities made in the laminated glazing so that said cleats extend substantially perpendicularly through the first part of the retaining element as well as in each of said structural folds.

[0026] Having such cleats proves particularly advantageous in that, in combination with the retaining element through which they extend, it allows the membrane forces to be smoothed (i.e., distributed evenly) between all the plies in the laminated glass, this smoothing being homogeneous throughout the thickness of said plies. Consequently, the permissible loads are considerably increased compared to the prior art, which makes it possible, in particular, to ensure very high resistance to pressure loads. than to bird impacts, as well as compliance with the "fail safe" requirement.

[0027] This also allows the membrane forces to pass through the center of the laminated glazing.

[0028] In this way, the introduction of a bending couple at the periphery of the laminated glazing is avoided, thus greatly reducing the risks of delamination.

[0029] Furthermore, by avoiding the occurrence of such a bending couple and by homogenizing the transmission of forces between the structural plies, it is no longer necessary to use structural plies of different thicknesses, as is often the case in the prior art, particularly with regard to plastic glazing, in order to increase flexural stiffness and limit the risk of delamination. It then becomes possible to use thinner structural plies than those generally used in the prior art, which not only helps to reduce the cost of manufacturing the glazing assembly according to the invention but also to simplify its production, since thick structural plies are known to be complex to manufacture (for example: simplified handling during mass production operations, reduced stretching processes for stretched PMMA and extrusion processes for PC, and reduced shaping complexities).

[0030] In addition, the presence of thick structural folds made of drawn PMMA is known to be detrimental to shear failures along the stretch plane of said folds (particularly low compared to other cracking directions). Consequently, the invention also reduces the risk of such failures occurring, particularly during bird strikes.

[0031] Moreover, since it becomes possible to use thinner structural plies in greater numbers, as a substitute for thicker plies, it follows that it is possible to further strengthen compliance with the "fail safe" requirement.

[0032] Another important aspect of the invention lies in the fact that the presence of an external retaining element is eliminated here, compared to prior art solutions. This results in a plurality of advantages, namely: - ease of ensuring aerodynamic continuity without creating a weak point in terms of sealing at the aircraft envelope level, and therefore no need for a "Zed" element, - possibility of taking advantage of a greater length of external glass, in particular external glass supporting an anti-icing function, which, for example, allows for greater flexibility in positioning, outside the cockpit's field of vision, the power supply electrodes of an anti-icing system, - in the case where a glass sheet coated with a heating layer is used (see below), minimizing the thickness of the interlayer layer used to fix this glass sheet to the first structural ply, which is advantageous with regard to the threat of hail.

[0033] Another important aspect of the invention lies in the fact that the glazing assembly according to the invention makes it possible to avoid a pinch-fit mounting. In other words, attaching the glazing assembly according to the invention to the aircraft structure does not generate any compression of the laminated glass. This advantageously eliminates the defects inherent in a pinch-fit mounting, such as typically peripheral thinning problems (flow of the interlayer layer outside the laminated glass, irreversible compression of the joints, etc.) which are responsible, in particular, for loss of sealing, bubbling due to negative pressure in the interlayer layers, degradation of the optics due to loss of parallelism of the structural plies, etc.

[0034] In particular embodiments, the glazed assembly may further comprise one or more of the following characteristics, taken individually or according to all technically possible combinations.

[0035] In particular embodiments, at least one cleat comprises a body made of metallic material, for example titanium or steel.

[0036] In particular embodiments, at least one cleat comprises a peripheral sleeve to said body and made of elastic material, for example elastomer.

[0037] The implementation of such a peripheral sleeve is advantageous in that it further contributes to smoothing the membrane stresses between all the plies that make up the laminated glass. Furthermore, if several cleats are equipped with their respective peripheral sleeves, this stress smoothing also occurs between these cleats.

[0038] In particular embodiments, the retaining element is made of metallic material, for example titanium, aluminum, or stainless steel, or is made of composite material, for example carbon or glass fiber reinforced composite material.

[0039] In particular embodiments, at least one cleat is arranged in the cavity associated with it with a play.

[0040] In this way, it is possible to have a degree of rotational freedom for the cleat inside the cavity in which it is placed, which not only further promotes the uniform distribution of membrane forces on the structural folds, but also avoids the appearance of a bending couple likely to create a delamination problem (said bending couple refers to a stress on the laminated glazing linked to a rotation with respect to the plane in which the retaining element extends).

[0041] In particular embodiments, said set of structural folds comprises at least three structural folds, for example four structural folds, preferably four structural folds distributed in pairs on either side of the element of retained, an intercalary layer being arranged between each pair of structural folds.

[0042] As mentioned above, having more than two structural folds makes it possible, in particular, to further strengthen compliance with the "fail safe" requirement.

[0043] In particular embodiments, the structural folds have identical thicknesses, or at least two structural folds have distinct thicknesses.

[0044] In particular embodiments, at least one cavity housing a cleat is strictly included in the laminated glazing, or opening through a single structural fold, or opening through all the structural folds.

[0045] In particular embodiments, when said at least one cavity is through all structural folds, the body of the cleat arranged in said at least one cavity is hollow.

[0046] Such arrangements are advantageous in that they allow the transmission of electrical elements (heating, probes, etc.) through the thickness of the laminated glazing.

[0047] In particular embodiments, the glass sheet of a structural ply is made of mineral glass or organic glass.

[0048] In particular embodiments, each interlayer is an adhesive layer made of thermoplastic polyurethane (TPU), polyvinyl butyral (PVB), ethylene-vinyl acetate copolymer (EVA), ionomer resin, or casting resin.

[0049] In particular embodiments, the laminated glazing further comprises a sheet of glass coated with a heating layer, intended to be in contact with the external environment and fixed to the set of structural folds by means of an intermediate adhesive layer.

[0050] Such a heated glass sheet is advantageous in that it protects the laminated glazing from frost, and also provides additional protection for the entire set of structural folds against projections of sand, gravel, wiper scratches, etc.

[0051] In particular embodiments, the first part of the retaining element is embedded in the intercalated layer through which the first structural fold is bonded to the second structural fold.

[0052] In particular embodiments, the first part of the retaining element is fixed by bonding in a peripheral housing machined in said interlayer, or even also in at least one of said first and second structural plies, for example symmetrically in said first and second structural plies.

[0053] These arrangements have the advantage that it is possible to construct the said peripheral housing once the laminated glazing is completely assembled. In other words, at the Unlike the case where the first part of the retaining element is embedded in the interlayer, it is not necessary here to consider fixing said first part from the assembly stage of the laminated glazing.

[0054] In particular embodiments, the glass sheets of the structural folds are made of polymer material, the cavities being arranged in said glass sheets.

[0055] In particular embodiments, the glass sheets of the structural folds are made of mineral glass, each structural fold comprising: - a heel made of composite material and a wedge made of flexible material, the heel and the wedge being arranged around the entire periphery of the glass sheet at its edge, said wedge being further positioned between the glass sheet and the heel, - inserts made of composite material, arranged on either side of the structural fold and fixed against the heel, the wedge and part of the glass sheet. Furthermore, the cavities extend through the heels as well as the inserts, the retaining element being embedded in the intercalated layer through which the first structural fold is bonded to the second structural fold

[0056] According to a second aspect, the invention relates to a method for manufacturing a glazed assembly according to the invention. Said method comprises the following steps: - assembly of the structural folds together, so as to form said laminated glazing, - assembly of the retaining element with said laminated glazing, such that said first part is fixedly inserted into at least said interlayer through which the first structural ply is fixed to the second structural ply, at the edge of the laminated glazing as well as around its entire periphery, and such that said second part extends the first part outside the laminated glazing, - drilling through the laminated glass and the retaining element, so as to form said cavities, - arrangement of said cleats in said cavities.

[0057] In particular embodiments, the manufacturing process may further include one or more of the following characteristics, taken individually or in all technically possible combinations.

[0058] In particular embodiments, the step of assembling the retaining element with the laminated glazing is carried out during the implementation of the step of assembling the first and second structural layers together, by embedding the first part of the retaining element in the interlayer layer through which the first structural layer is fixed to the second structural layer.

[0059] In particular embodiments, the step of assembling the retaining element with the laminated glazing is carried out once the step of assembling the first and second structural layers together is completed, and comprises: - machining of a peripheral housing in said interlayer, or even also in at least one of said first and second structural plies, for example symmetrically in said first and second structural plies, - fixing by gluing the first part of the retaining element in said peripheral housing.

[0060] According to a third aspect, the invention relates to an aircraft comprising a glazed assembly according to the invention arranged in aerodynamic continuity with the envelope of said aircraft, the second part of the retaining element, called the "attachment part", being fixed to the internal structure of the aircraft.

[0061] In particular embodiments, the aircraft may further comprise one or more of the following features, taken individually or in all technically possible combinations.

[0062] In particular embodiments, the attachment part is fixed to a so-called "support" part of the internal structure of the aircraft, said support part being arranged opposite the edge of the laminated glazing, said attachment part being arranged between the envelope of the aircraft and said support part.

[0063] In particular embodiments, the attachment part is fixed to a so-called "support" part of the internal structure of the aircraft, said support part being arranged at a distance from the second structural ply towards the interior of the aircraft, said attachment part being arranged between the envelope of the aircraft and said support part, the attachment part being fixed by means of a wedge positioned between said attachment part and the support part, a contact element made of a material more ductile than the glazing being further inserted between the support part and the second structural ply.

[0064] In particular embodiments, the attachment part is fixed to a so-called "support" part of the internal structure of the aircraft, said support part being arranged between the envelope of the aircraft and said attachment part. Brief description of the drawings

[0065] Other features and advantages of the present invention will become apparent from the description below, with reference to the accompanying drawings, which illustrate an example of an embodiment without being limiting in any way. In the figures:

[0066] [Fig-1] [Fig.1] schematically represents a variant embodiment of a attachment system according to the state of the art;

[0067] [Fig.2] [Fig.2] schematically represents another embodiment of a attachment system according to the state of the art;

[0068] [Fig.3] [Fig.3] schematically represents, in its environment, a mode particular method of constructing a glazed assembly according to the invention, as well as a method by- particular method of fixing said glazed assembly to the structure of an aircraft;

[0069] [Fig.4] Fig.4 schematically represents another embodiment of the entire glass enclosure;

[0070] [Fig. 5] [Fig. 5] schematically represents another embodiment of the entire glass enclosure;

[0071] [Fig.6] Fig.6 schematically represents another embodiment of the entire glass enclosure;

[0072] [Fig.7] [Fig.7] schematically represents another embodiment of the entire glass enclosure;

[0073] [Fig.8] Fig.8 schematically represents another embodiment of the entire glass enclosure;

[0074] [Fig.9] Fig.9 schematically represents another embodiment of the entire glass enclosure;

[0075] [Fig. 10] [Fig. 10] represents, in the form of a flowchart, a particular method of implementing a manufacturing process for the glazed assembly of [Fig. 3];

[0076] [Fig. 11] [Fig. 11] represents, in the form of a flowchart, a particular method of implementing the manufacturing process of the glazed assembly of [Fig.4];

[0077] [Fig. 12] [Fig. 12] schematically represents another particular method of fixing the glazed assembly of [Fig.3] to the aircraft structure;

[0078] [Fig. 13] [Fig. 13] schematically represents another particular method of fixing the glazed assembly of [Fig.3] to the aircraft structure.

[0079] Description of embodiments

[0080] Figure 3 schematically represents, in its environment, a particular mode for the production of a glazed assembly 100 according to the invention.

[0081] In the following description, the vertical, horizontal and transverse orientations are considered, without limitation, with reference to the trihedron (V, H, T) shown in [Fig. 3]. Also, the glazed assembly 100 of [Fig. 3] is shown there in a cross-section (i.e. through the thickness of said glazed assembly 100).

[0082] By convention, the terms "upper" and "lower" or "top" and "bottom" or "above" and "below" are used with reference to the transverse orientation. The terms "left" and "right" are used with reference to the horizontal orientation.

[0083] In [Fig. 3], the glazed assembly 100 is shown as already integrated (fixed) to an aircraft. The remainder of the description refers more specifically to a commercial airplane, also referred to more simply as an "airplane". The invention nevertheless applies, in no way limitingly, to any type of aircraft intended to be subjected to pressure differentials between an external environment 10 and the interior 20 of said aircraft, such as, for example, a cargo aircraft, a commercial aircraft hunting, a helicopter, etc.

[0084] Furthermore, for the remainder of this description, the glazed assembly 100 is considered, without limitation, to be part of the cockpit glazing of said commercial aircraft, more specifically the windshield of this cockpit glazing. However, such provisions do not limit the invention, and nothing precludes the possibility that the glazed assembly 100 could be part of another cockpit glazing, such as, for example, a side window of said cockpit (i.e., a part less exposed to the risk of a bird strike compared to the windshield), or even that it could be part of cabin glazing, such as a porthole.

[0085] First, we will describe the detailed configuration of the glazed assembly 100 alone as implemented in the embodiment of [Fig. 3], as well as several alternative embodiments thereof. Then, second, we will describe how said glazed assembly 100 is integrated into the aircraft by being fixed (i.e., secured, attached) to its structure.

[0086] In the present embodiment, the glazed assembly 100 comprises a laminated glazing 110. Said laminated glazing 110 comprises a set of structural folds of which a first structural fold 111 and a second structural fold 113 are bonded to the first structural fold 111 by means of an intermediate adhesive layer 115.

[0087] More specifically, and as illustrated by [Fig.3]: - the first structural ply 111 is a sheet of glass arranged with respect to the external environment of the aircraft. Said sheet of glass 111 has an upper face 111a and a lower face 111b; - the second structural ply 113 is a sheet of glass bonded to the first structural ply 111 by means of said intercalary adhesive layer 115. Said sheet of glass 113 has an upper face 113a as well as an lower face 113b.

[0088] It is therefore understood that the intermediate adhesive layer 115 is disposed between the lower face 111b of the glass sheet 111 and the upper face 113a of the glass sheet 113.

[0089] Said glass sheets 111, 114 are made of organic glass, more particularly, in the embodiment described here, of drawn polymethyl methacrylate (drawn PMMA).

[0090] However, nothing excludes considering another polymer material, such as, for example, unstretched polymethyl methacrylate, polycarbonate (PC), polyethylene terephthalate (PET) or polyurethane (PU).

[0091] As regards the adhesive interlayer 115, it is made of thermoplastic polyurethane, polyvinyl butyral, ethylene-vinyl acetate copolymer (acronym "EVA" in the relevant technical literature), ionomer resin, or of casting resin. These provisions also apply to any other adhesive interlayer described below.

[0092] It should be noted that, in the present embodiment, said structural fold assembly comprises only the first structural fold 111 and the second structural fold 113. However, considering such a structural fold assembly constitutes only one variant of the invention. Indeed, nothing precludes considering other embodiments in which said structural fold assembly comprises at least three structural folds, for example four structural folds, preferably four structural folds distributed in pairs on either side of a retaining element, as described later in the context of another variant of the glazed assembly.

[0093] In the embodiment described here, the first and second structural plies 111, 113 have identical thicknesses (the thickness of a structural ply being measured in the transverse direction T, and corresponding here, for this embodiment, to the thickness of the glass sheets). For example, the thickness of said first and second structural plies 111, 113 is between 3 mm and 25 mm.

[0094] Nothing, however, precludes considering other embodiments in which, for example, the first structural fold 111 has a distinct thickness (i.e. greater or lesser) than that of the second structural fold 113. By way of a non-limiting example, the thickness of the first structural fold 111 is equal to 16 mm, while the thickness of the second structural fold 113 is equal to 12 mm.

[0095] Furthermore, and as illustrated by [Fig.3], the laminated glazing 110 also comprises a glass sheet 116 coated with a heating layer, in contact with the external environment 10 and fixed to the first structural ply 111 by means of an adhesive layer 117. Such a glass sheet 116 is advantageous in that it protects the laminated glazing 110 from frost, and also provides additional protection to the first structural ply 111 against projections of sand, gravel, wiper scratches, etc.

[0096] The implementation of such a glass sheet 116, besides being optional, is well known to those skilled in the art, so it is not detailed further here. It should also be noted that said glass sheet 116 does not form a structural fold in the sense of the invention, but rather a thin external fold.

[0097] In accordance with the invention, and as illustrated by [Fig.3], the glazed assembly 100 also includes a so-called "retaining element 120" as well as a plurality of cleats 130.

[0098] The retainer 120 comprises a first part 121 inserted in a fixed (i.e., non-removable) manner into the intermediate adhesive layer 115 at the edge of the laminated glazing 110 and around its entire periphery said laminated glazing 110.

[0099] In other words, said first part 121 (but therefore a fortiori also the whole of the retaining element 120) forms a frame, which from a geometric point of view, amounts to saying that, in the plane (V, H) of the [Fig.3], said first part 121 corresponds to a doubly connected domain (i.e. a surface domain containing a hole).

[0100] The retaining element also includes a second part 122 which extends the first part 121 outside the laminated glazing 110. In other words, similarly to what has been mentioned above, said second part 122 also takes the form, in the plane (V, H) of [Fig.3], of a doubly connected domain.

[0101] As can be seen from [Fig. 3], said second part 122 is bolted to the internal structure of the aircraft, so that the expression "attachment part 122" is also used to refer to said second part 122 in the remainder of the description. These aspects are described in more detail later, but already allow it to be understood that the retaining element 120 can be described as "internal" in the sense that it is attached to the laminated glazing 110 at a surface (edge) positioned inside 20 of the aircraft, and deploys only within said interior 20.

[0102] More particularly, in the embodiment of [Fig.3], the retaining element 120 extends substantially planarly in the mean plane of the laminated glazing 110 and substantially parallel to the first and second structural plies 111, 113. In addition, the first part 121 of the retaining element 120 is here embedded (i.e. entirely contained) in the intermediate adhesive layer 115.

[0103] It should be noted that in order to obtain such a configuration of the first part 121 (i.e. embedded in the layer 115), it is necessary to consider an assembly of the retaining element 120 with the laminated glazing 110 during an assembly step (i.e. of lamination) of said laminated glazing 110. These aspects are also described in more detail later with reference to a manufacturing method according to the invention of said glazing assembly 100.

[0104] Different materials can be considered for the production of the retaining element 120. Thus, according to one embodiment, the retaining element 120 is made of metallic material, for example titanium, aluminum, or stainless steel.

[0105] According to another embodiment, the retaining element 120 is made of composite material, for example of composite material reinforced with carbon or glass fibers.

[0106] Although it is considered in the embodiment described here that the retaining element 120 is inserted (via said first part 121) in a fixed manner into the intermediate adhesive layer 115 over the entire periphery of said laminated glazing 110, other variants remain conceivable, in particular so that said insertion is carried out only on a portion of the periphery of said laminated glazing 110 (in which case, the retaining element 120 obviously no longer takes the form of a frame).

[0107] Furthermore, regardless of whether the retaining element 120 is inserted on all or part of the periphery of the laminated glazing 110, said retaining element may be made in one piece or, alternatively, in several pieces joined together, possibly with overlap. Moreover, if the retaining element 120 is inserted only on a portion of the periphery of the laminated glazing 110, said retaining element 120 may be made in several pieces, some of which may be separated from one another.

[0108] In this embodiment, it is also considered that the second part 122 is bolted to the aircraft structure. However, such provisions are not limiting to the invention, and any suitable fastening method known to those skilled in the art may of course be considered (e.g., gluing).

[0109] Furthermore, for the sake of simplification, the description of the embodiment of [Fig.3] is now made with reference to a single cleat 130. It is important to note, however, that the technical characteristics now described apply to all or part of the cleats 130 equipping the glazed assembly 100. Moreover, the cleats 130 can be distributed in different ways along the periphery of the laminated glazing 110, for example uniformly, or, in a more particular example, every 5 cm.

[0110] The cleat 130 illustrated in [Fig.3] is arranged in a cavity 140 made in the laminated glazing 110 so that said cleat 130 extends substantially perpendicularly through the first part 121 of the retaining element 120 as well as in (i.e. inside) each of the first and second structural folds 111, 113. It follows from these arrangements, as well as from the configuration of the retaining element 120, that the cleat 130 and the cavity 140 both extend in the transverse direction T substantially perpendicularly to the upper face 11a and lower face 113b belonging respectively to the first and second structural folds 111, 113.

[0111] Having such a cleat 130 proves particularly advantageous in that it allows, in combination with the retaining element 120 through which it extends, to smooth (i.e. distribute in a balanced way) the membrane forces between all the plies entering into the composition of the laminated glazing 110, but also to pass the membrane forces through the center of the laminated glazing 110. Thus, this avoids the introduction of a bending couple at the periphery of the laminated glazing 110, so as to limit the bending which, in the prior art, is at the origin of the delamination mechanisms.

[0112] More particularly, in the embodiment of [Fig.3], the cleat 130 comprises a body 131 made of metallic material, for example titanium or steel, and a sleeve 132 peripheral to said body 131 and made of elastic material, for example elastomer (the sleeve 132 is hatched on [Fig.3]).

[0113] It is important to note that the implementation of such a peripheral sleeve 132 is optional within the meaning of the present invention, and that it advantageously allows for further contribution to the smoothing of membrane forces between all the plies entering into the composition of the laminated glazing 110. In addition, other materials can be considered for the body 131 of the cleat 130, such as ceramic or a low carbon composite material.

[0114] Furthermore, in the present embodiment, the cleat 130 is inserted without play in the cavity 140. By "play", we of course refer here to a free space counted in the plane orthogonal to the direction in which the cleat 130 extends.

[0115] However, considering such a backlash-free insertion is only one variant of the invention. Thus, nothing precludes considering that the cavity 140 and the lug 130 are respectively dimensioned so that there is a gap between them (not shown in the figures). In this way, it is possible to have a degree of rotational freedom for the lug 130 inside the cavity 140, and therefore ultimately between the lug 130 and the retaining element 120, which not only further promotes the uniform distribution of membrane forces on the structural plies 111, 113, but also prevents the occurrence of a bending moment likely to create a delamination problem.

[0116] In the embodiment described here, and as illustrated by [Fig.3], the cavity 140 opens through said first and second structural folds 111, 113. In other words, the transverse housing 140 opens at the level of the upper face 111 of the first structural fold 111, as well as at the level of the lower face 113b of the second structural fold 113.

[0117] It should be noted that the notch 130 here has the same size as the cavity 140 along the T direction (in other words, the length of the notch 130 is the same as the thickness of the laminated glazing 110). It remains possible, of course, to consider variants in which the size of said notch 130 is less than or greater than that of the cavity 140 along the T direction, provided that said notch 130 extends through the first part 121 of the retaining element 120 as well as in each of said structural folds 111, 113.

[0118] Advantageously, in addition to the fact that the cavity 140 opens through said first and second structural folds 111, 113, the body 131 of the cleat 130 is hollow. Such arrangements allow the transmission of electrical components (power supply wires for a heating system, probe connection wires, etc.) to through the thickness of the 110 laminated glass.

[0119] It is understood, however, that considering a hollow body 131 is only one variant of the invention, and nothing excludes, of course, considering that it is solid.

[0120] The glazed assembly 100 has been described so far in relation to the embodiment of [Fig. 3]. The invention nevertheless covers other embodiments which are now described and illustrated, before describing how the glazed assembly 100 of [Fig. 3] is attached to the aircraft structure. It should be noted that for these other embodiments, and in comparison with [Fig. 3], only the glazed assembly 100 is shown. Furthermore, and solely for the sake of simplifying the figures, the heating element 116 and the adhesive layer 117 are also omitted.

[0121] Figure 4 schematically represents another embodiment of the assembly glazed 100.

[0122] The embodiment of [Fig.4] incorporates all the features of the embodiment of [Fig.3], except that instead of the first part 121 of the retaining element 120 being embedded in the intermediate adhesive layer 115 (during the assembly step of the laminated glazing 110), said first part 121 is now fixed by bonding in a peripheral housing 150 machined in said intermediate adhesive layer 115 (i.e. at the edge of the laminated glazing 110).

[0123] These arrangements have the advantage that it is possible to create the peripheral housing 150 once the laminated glazing 110 is fully assembled. In other words, unlike the case where the first part 121 of the retaining element 120 is embedded in the intermediate adhesive layer 115, it is not necessary here to consider fixing said first part 121 during the assembly stage of the laminated glazing 110.

[0124] It should be noted that the peripheral housing 150 is here machined only in the intermediate adhesive layer 115. However, it is possible to consider other variants, as illustrated by figures 5 and 6.

[0125] Thus, in [Fig.5], the peripheral housing 150 is machined in the intermediate adhesive layer 115 as well as in the single first structural ply 111.

[0126] It is understood of course that it is also possible to consider that the peripheral housing 150 is machined in the intermediate adhesive layer 115 as well as in the second structural ply 113 alone.

[0127] In [Fig.6], the peripheral housing 150 is machined in the intermediate adhesive layer 115 as well as symmetrically in said first and second structural plies 111, 113.

[0128] Here too, it is understood that the peripheral housing 150 can be machined in the said first and second structural plies 111, 113 without this machining being symmetrical.

[0129] Fig. 7 schematically represents yet another embodiment of the glazed assembly 100.

[0130] The embodiment of [Fig.7] takes up all the characteristics of the embodiment of [Fig.3], with the difference that the cavity 140 is here open through only the second structural fold 113 (i.e. through only the lower face 114b).

[0131] Nothing excludes however considering other modes in which the cavity 140 opens through only the first structural fold 111, or even modes in which the cavity 140 is strictly included in the laminated glazing 110 (i.e. the cavity 140 does not open through any structural fold 111,113).

[0132] Fig. 8 schematically represents yet another embodiment of the glazed assembly 100.

[0133] The embodiment of [Fig.8] incorporates all the characteristics of the embodiment of [Fig.3], except that the set of structural folds here comprises four structural folds 111_1, 111_2, 113_1, 113_2 distributed in pairs on either side of the retaining element 120, an intermediate adhesive layer 115_1, 115_2 being arranged between each pair of structural folds (these layers 115_1, 115_2 are used in addition to the layer 115 enabling the bonding between the structural folds 111, 113).

[0134] It should be noted that the structural folds are not necessarily all made of the same material. Thus, it is possible to consider configurations in which the outermost folds 111_1, 113_2 with respect to the retaining element 120 are made of stretched PMMA, while the middle folds 111_2, 113_1 are made of PC which offers better performance with respect to bird impacts.

[0135] It has also been assumed until now that the glass sheets of the structural folds are made of polymer material. However, the invention also applies in the case where said glass sheets are made of mineral glass, for example soda-lime glass, aluminosilicate, borosilicate, thermally tempered, or chemically strengthened, as illustrated in [Fig. 9]. It should be noted that in the embodiment of [Fig. 9], the structural folds 111, 113 are no longer limited to said glass sheets but also include other elements. Consequently, the glass sheet of the first structural fold 111 (respectively of the second structural fold 113) bears the reference numeral "111_f" (respectively the reference numeral "113_f") for this embodiment.

[0136] Thus, and as illustrated by [Fig.9], the first structural fold 111 comprises: - a heel 161 made of composite material, for example reinforced with glass or carbon fibers, and a wedge 171 made of flexible material, preferably viscoelastic. The heel 161 and the wedge 171 are arranged around the entire periphery of the glass sheet 11 l_f at its edge, said wedge 171 being further positioned between the glass sheet 11 l_f and the heel 161, - inserts 181a, 181b made of composite material, for example based on glass fibers or titanium sheet, arranged on either side of said first structural ply 111 and fixed against the heel 161, the wedge 171 as well as part of the glass sheet 11 l_f, for example by bonding.

[0137] As illustrated by [Fig.9], the second structural fold 113 is configured similarly to the first structural fold 111, and for this purpose includes a heel 162 and a wedge 172, as well as inserts 182a, 182b.

[0138] Furthermore, in the embodiment of [Fig.9], the cavity 140 (and therefore a fortiori the lug 130) extends through the heels 161, 162 as well as the inserts 181a, 181b, 182a, 182b. The retaining element 120, for its part, is embedded in the intermediate adhesive layer 115.

[0139] It should also be noted that, in the example of [Fig. 9], the cavity 140 opens through the first and second structural folds 111, 113 (i.e., through the insert 181a and / or through the insert 182b). However, as explained above, it is entirely possible to consider that the cavity 140 opens through only one of said structural folds 111, 113 or is strictly contained within the laminated glazing 110.

[0140] It is also noted that the use of shims 161, 162, wedges 171, 172 and inserts 181a, 181b, 182a, 182b refers to a prior art configuration known as "structural bonded glazing". However, unlike the latter, the configuration in [Fig. 9] does not use any external retaining elements.

[0141] The inserts 181a, 181b, 182a, 182b have the particular role of enabling the transmission of forces between the heels 161, 162 and the structural folds 111, 113. The shims 171, 172, for their part, make it possible to compensate, over a distance typically on the order of a centimeter, for any deviations in shape between heels 161, 162 and glass sheets 112, 114 (said deviations in shape typically resulting from hazards in the implementation of manufacturing processes of the heels 161, 162 and the glass sheets 111_f, 113_f). The spacers 171, 172 also serve to prevent any potential cracking of composite resins from inserts 181a, 181b, 182a, 182b or of glue used for fixing them.

[0142] In conclusion, it is important to note that all the embodiments described above (figures 3 to 9) can be combined with each other in any technically feasible combination.

[0143] As mentioned previously, the invention also relates to a method for manufacturing the glazed assembly 100. Different ways of implementing the method of manufacturing methods can be considered, depending on whether the retaining element 120 is embedded in the intermediate adhesive layer 115 ([Fig.3] for example) or is fixed by bonding in the peripheral housing 150 machined in said intermediate adhesive layer 115 ([Fig.4] for example).

[0144] The [Fig. 10] represents, in the form of a flowchart, a particular method of implementing the manufacturing process of the glazed assembly 100 of the [Fig.3].

[0145] As illustrated in [Fig. 10], said manufacturing process comprises the following steps: - assembly E10 between the first and second structural plies 111, 113 by means of the intercalated adhesive layer 115, so as to form said laminated glazing 110, - assembly E20 of the retaining element 120 with said laminated glazing 110, such that said first part 121 is fixedly inserted into said adhesive interlayer 115 at the edge of the laminated glazing 110 as well as around its entire periphery, and that said attachment part 122 extends the first part 121 outside the laminated glazing 110, - drilling E30 through the laminated glazing 110 and the retaining element 120, so as to form said cavities 140, - arrangement E40 of the cleats 130 in the said cavities 140.

[0146] More particularly, in the implementation method of [Fig. 10], the assembly step E20 of the retaining element 120 with the laminated glazing 110 is carried out during the implementation of the assembly step E10 between the first and second structural plies 111, 113, by embedding the first part 121 of the retaining element 120 in the intermediate adhesive layer 115.

[0147] The [Fig. 11] represents, in the form of a flowchart, a particular method of implementing the manufacturing process of the glazed assembly 100 of the [Fig.4].

[0148] As illustrated by [Fig. 11], and unlike the implementation method described with reference to [Fig. 10], the assembly step E20 of the retaining element 120 with the laminated glazing 110 is carried out here once the assembly step E10 between the first and second structural layers 111, 113 has been completed.

[0149] Furthermore, said step E20 comprises, in this implementation mode: - an E20_l machining of the peripheral housing 150 in the intermediate adhesive layer 115, - an E20_2 fixing by gluing the first part 121 of the retaining element 120 in said peripheral housing 150.

[0150] It should be noted that in this embodiment, the retaining element 120 can advantageously be made in several parts, these different parts being fixed in the machined peripheral housing 150.

[0151] The manner in which said glazed assembly 100 is integrated into the aircraft is now described by being fixed (i.e., attached, secured) to its structure. For the sake of simplicity, this description is made only with reference to the embodiment shown in [Fig. 3]. It will be obvious to those skilled in the art how to adapt (if necessary) this description for the other embodiments described above.

[0152] As illustrated by [Fig.3], the glazed assembly 100 is arranged such that: - the first structural fold 111 is in aerodynamic continuity with the aircraft's envelope, - the attachment part 122 of the retaining element 120 is fixed by bolting 190 to the internal structure of the aircraft.

[0153] More specifically, the attachment part 122 is fixed to a so-called "support" part 200 of the internal structure of the aircraft. Said support part 200 is arranged opposite the edge of the laminated glazing 110, and extends, in this embodiment, substantially parallel to the structural folds 111, 113. Furthermore, said attachment part 122 is arranged between the external envelope of the aircraft and said support part 200, the bolting 190 being carried out from the outside to the inside of the aircraft.

[0154] As can be seen in [Fig. 3], the aerodynamic continuity of the laminated glazing 110 with the aircraft envelope is achieved more specifically at a cover 210 of said envelope. This cover 210 is separated from the laminated glazing 110 by an elastomeric gasket 220 and is also fixed to the internal structure of the aircraft by bolts 230. Two other elastomeric gaskets 240, 250 ensure contact between the cover 210 and the internal structure of the aircraft.

[0155] Alternatively, the attachment of the cover 210 to the internal structure of the aircraft can be achieved by clipping or by gluing.

[0156] In addition, two further elastomer seals 260, 270 ensure contact between the attachment part 122 and the support part 200 of the internal structure of the aircraft.

[0157] It should be noted that, in the present embodiment, the attachment of the glazed assembly 100 to the structure of the aircraft, as described with reference to [Fig.3], is carried out more specifically from outside the said aircraft.

[0158] It is also important to note that this fixation represents only one particular embodiment of the invention, and other embodiments may be envisaged.

[0159] [Fig. 12] schematically represents another particular method of fixing the glazed assembly 100 of [Fig. 3] to the aircraft structure.

[0160] In the example of [Fig. 12], said support portion 200 is arranged at a distance from the second structural fold 113 towards the interior of the aircraft, and said attachment portion 122 is arranged between the outer envelope of the aircraft (i.e., the cover 210 here) and said support portion 200. The bolting 190 is carried out from the outside towards the interior of the aircraft through a spacer 280 positioned between said attachment portion 122 and the support part 200. In addition, a contact element 290 made of a material more ductile than the glazing 110, such as aluminium or a hard polymer (example: cotton-phenolic or nylon-acrylic composite), is inserted between the support part 200 and the second structural ply 113. An elastomer seal 300 ensures the contact between the support part 200 and the second structural ply 113.

[0161] Similar to [Fig.3], the attachment of the glazed assembly 100 to the aircraft structure, as described with reference to [Fig. 12], is carried out more specifically from outside the aircraft.

[0162] Fig. 13 schematically represents yet another particular method of fixing the glazed assembly 100 of Fig. 3 to the aircraft structure.

[0163] In the example of [Fig. 13], said support part 200 is arranged between the aircraft envelope (i.e. the cover 210 here) and said attachment part 122. Furthermore, the bolting 190 is carried out from the inside to the outside of the aircraft.

[0164] Thus, unlike Figures 3 and 11, the attachment of the glazed assembly 100 to the aircraft structure, as described with reference to [Fig.13], is carried out more specifically from inside the aircraft.

[0165] The invention has been described so far by considering that the glazed assembly 100 constitutes the cockpit glazing of said aircraft. However, as already stated, this is not a limitation of the invention, which can also be applied to the case of cabin glazing (window). Cabin glazing is conventionally double glazing made of two structural layers of PMMA. These two structural layers are fixed to each other by means of a peripheral seal, typically made of silicone, which also allows control of the distance between the two structural layers. Therefore, it follows from these arrangements that said peripheral seal, in this case, acts as an interlayer within the meaning of the invention, into which the retaining element 120 is inserted via its first portion 121.

Claims

Demands

1. Glazed assembly (100) for an aircraft, said glazing assembly comprising laminated glazing (110) comprising a set of structural folds including a first structural fold (111) and a second structural fold (113) fixed to the first structural fold by means of an interlayer (115), said glazing assembly being characterized in that it also comprises: - a retention element (120) a first part (121) of which is fixedly inserted into at least said interlayer at the edge of the laminated glazing and on at least a portion of its periphery, preferably on the entire periphery of the laminated glazing, and a second part (122) of which extends the first part outside the laminated glazing,- a plurality of cleats (130) arranged in respective cavities (140) made in the laminated glazing such that said cleats extend substantially perpendicularly through the first part of the retaining element as well as in each of said structural folds.

2. Glazed assembly (100) according to claim 1, in which at least one cleat (130) comprises a body (131) made of metallic material, for example titanium or steel.

3. Glazed assembly (100) according to the preceding claim 2, in which at least one cleat (130) comprises a peripheral sleeve (132) of said body (131) and made of elastic material, for example of elastomer.

4. Glazed assembly (100) according to any one of claims 1 to 3, wherein the retaining element (120) is made of metallic material, for example titanium, aluminum, or stainless steel, or is made of composite material, for example carbon fiber or glass fiber reinforced composite material.

5. Glazed assembly (100) according to any one of claims 1 to 4, wherein at least one notch (130) is arranged in the cavity (140) associated with it with a clearance.

6. Glazed assembly (100) according to any one of claims 1 to 5, wherein said structural ply assembly comprises at least three structural ply, for example four structural ply (111_1, 111_2, 113_1, 113_2), preferably four structural ply distributed in pairs on either side of the retaining element, an interlayer (115_1, 115_2) being arranged between each pair of structural folds.

7. Glazed assembly (100) according to any one of claims 1 to 6, wherein the structural folds (111, 113) have identical thicknesses, or at least two structural folds have distinct thicknesses.

8. Glazed assembly (100) according to any one of claims 1 to 7, wherein at least one cavity (140) housing a notch (130) is strictly included in the laminated glazing (110), or opening through a single structural ply (111, 113), or opening through all the structural ply.

9. Glazed assembly (100) according to the preceding claim 8, wherein, when said at least one cavity (140) is through-hole through all the structural folds (111, 113), the body (131) of the cleat (130) arranged in said at least one cavity is hollow.

10. Glazed assembly (100) according to any one of claims 1 to 9, wherein the glass sheet (112, 114) of a structural ply (111, 113) is made of mineral glass or polymer material.

11. Glazed assembly (100) according to any one of claims 1 to 10, wherein each interlayer (115) is an adhesive layer made of thermoplastic polyurethane, polyvinyl butyral, ethylene-vinyl acetate copolymer, ionomer resin, or casting resin.

12. Glazed assembly (100) according to any one of claims 1 to 11, wherein the laminated glazing (110) further comprises a sheet of glass (116) coated with a heating layer, intended to be in contact with the external environment (10) and fixed to the set of structural plies by means of an interlayer adhesive layer (117).

13. Glazed assembly (100) according to any one of claims 1 to 12, wherein the first part (121) of the retaining element (120) is embedded in the interlayer (115) through which the first structural ply (111) is bonded to the second structural ply (113).

14. Glazed assembly (100) according to any one of claims 1 to 12, wherein the first part (121) of the retaining element (120) is fixed by bonding in a peripheral housing (150) machined in said interlayer (115), or even also in at least one of said first and second structural plies (111, 113), for example symmetrically in said first and second structural plies.

15. A glazed assembly (100) according to any one of claims 1 to 14, wherein the glass sheets of the structural folds (111, 113) are made of polymer material, the cavities (140) being arranged in said glass sheets.

16. A glazed assembly (100) according to any one of claims 1 to 14, wherein the glass sheets of the structural folds (111, 113) are made of mineral glass, each structural fold comprising: - a lug (161, 162) made of composite material and a wedge (171, 172) made of flexible material, the lug and the wedge being arranged around the entire periphery of the glass sheet at its edge, said wedge being further positioned between the glass sheet and the lug, - inserts (181a, 181b, 182a, 182b) made of composite material, arranged on either side of the structural fold and fixed against the lug, the wedge, and a portion of the glass sheet, and wherein the cavities (140) extend through the lugs and the inserts, the retaining element (120) being embedded in the intercalated layer (115) through which the first structural fold is fixed to the second structural fold.

17. A method for manufacturing a glazed assembly (100) according to any one of claims 1 to 16, said method comprising the steps of: - assembling (E10) the structural plies (111, 113) together, so as to form said laminated glazing (110), - assembling (E20) the retaining element (120) with said laminated glazing, such that said first part (121) is fixedly inserted into at least said interlayer by means of which the first structural ply is fixed to the second structural ply at the edge of the laminated glazing and on at least a portion of its periphery, preferably on the entire periphery of the laminated glazing, and such that said second part (122) extends the first part beyond the laminated glazing, - drilling (E30) the laminated glazing and the retaining element, so as to form said cavities (140), - arranging (E40) of the said cleats (130) in the said cavities.

18. A method according to claim 17, wherein the assembly step (E20) of the retaining element (120) with the laminated glazing (110) is carried out during the implementation of the assembly step (E10) between the first and second structural plies (111, 113), by embedding the first part (121) of the retaining element in the interlayer layer (115) through which the first structural ply is fixed to the second structural fold.

19. A method according to claim 17, wherein the assembly step (E20) of the retaining element (120) with the laminated glazing (110) is carried out once the assembly step (E10) between the first and second structural plies (111, 113) has been completed, and comprises: - machining (E20_1) of a peripheral housing (150) in said interlayer, or even also in at least one of said first and second structural plies, for example symmetrically in said first and second structural plies, - fixing (E20_2) by bonding the first part (121) of the retaining element in said peripheral housing.

20. Aircraft comprising a glazed assembly (100) according to any one of claims 1 to 16 arranged in aerodynamic continuity with the envelope (210) of said aircraft, the second part (122) of the retaining element (120), referred to as the "attachment part", being fixed to the internal structure of the aircraft.

21. Aircraft according to claim 20, wherein the attachment part (122) is fixed to a so-called "support" part (200) of the internal structure of the aircraft, said support part being arranged opposite the edge of the laminated glazing (110), said attachment part being arranged between the envelope (210) of the aircraft and said support part.

22. Aircraft according to claim 20, wherein the attachment part (122) is fixed to a so-called "support" part (200) of the internal structure of the aircraft, said support part being arranged at a distance from the second structural ply (113) towards the interior of the aircraft, said attachment part being arranged between the envelope (210) of the aircraft and said support part, the attachment of the attachment part being achieved by means of a wedge (280) positioned between said attachment part and the support part, a contact element (290) made of a material more ductile than the glazing being further inserted between the support part and the second structural ply.

23. Aircraft according to claim 20, wherein the attachment part (122) is fixed to a so-called "support" part (200) of the internal structure of the aircraft, said support part being arranged between the envelope (210) of the aircraft and said attachment part.