AIRCRAFT GLAZING SEAL

Abstract

The present invention relates to a sealing gasket for an aircraft glazing element, the gasket being configured to receive an edge of a first glazing unit, the first glazing unit having a first face, the gasket comprising a first surface adapted to be mounted on the first face so as to receive the first glazing unit, the gasket comprising a first damping portion, the first damping portion comprising the first surface, a first material forming the first damping portion having a first loss factor η1 strictly greater than 0.10. Figure for the abstract: Fig. 2

Description

Title of the invention: SEALING SEAL FOR AN AIRCRAFT GLAZING ELEMENT FIELD OF INVENTION

[0001] The present invention relates to a sealing gasket for an aircraft glazed element having acoustic insulation properties, and more particularly to an aircraft window or windshield having such properties. STATE OF THE ART

[0002] With reference to [Fig. 1], it is known to mount a glazed element 2, preferably a window 14 or a windshield, to the fuselage of an aircraft. The window 14 may comprise a first outer pane of glass 3 and a second inner pane of glass 10, which are mounted on a metal frame 19 within a sealing gasket 1. The sealing gasket 1 covers the edge of each of the first pane 3 and the second pane 10. The sealing gasket 1 is held in place by a metal profile 18 mounted on a hinge 20, which is fixed to the metal frame 19.

[0003] The acoustic insulation of an aircraft glazing element can depend on several parameters: temperature variations outside the aircraft, temperature variations inside the aircraft, mechanical stresses at the boundaries of the glazing element, the geometry and composition of the glazing element, and / or variations in the material characteristics of the glazing element with temperature and the mechanical stresses imposed on the glazing element. Therefore, modeling the acoustic insulation properties of a glazing element can be complex.

[0004] It is known to improve the acoustic insulation of an aircraft glazed element by increasing the thickness of the glazing of the glazed element.

[0005] However, the increase in the thickness of the first outer pane 3 is limited by the size of the first pane 3 in the porthole 14 and by the costs involved in increasing this thickness during the manufacture of the porthole 14. Description of the invention

[0006] An object of the invention is to provide a sealing gasket enabling a glazed element to exhibit acoustic insulation properties superior to those of known glazed elements, at least in a range of frequencies within the audible frequency spectrum.

[0007] This objective is achieved within the framework of the present invention by means of a sealing gasket for an aircraft glazing element, the gasket being configured to receive an edge of a first glazing, the first glazing having a first face, the gasket comprising a first surface adapted to be mounted on the first face so as to receive the first glazing, the seal comprising a first damping part, the first damping part comprising the first surface, a first material forming the first damping part having a first loss factor rp strictly greater than 0.10.

[0008] The present invention is advantageously complemented by the following features, taken individually or in any of their technically possible combinations:

[0009] - the first surface is adapted to be mounted on the first face and on a second face of the first glazing, opposite the first face, so as to receive the first glazing.

[0010] - the seal is configured to receive an edge of a second glazing, the second glazing having a third face and a fourth face opposite the third face, the seal comprising a second surface adapted to be mounted on the third face and preferably on the fourth face so as to receive the second glazing, the seal comprising a second damping part, the second damping part comprising the second surface, a second material forming the second damping part having a second loss factor r|2 strictly greater than 0.10,

[0011] - the joint includes a first housing adapted to receive the edge of the first glazing so as to surround the first glazing, the first housing comprising the first damping part,

[0012] - the seal includes a second housing adapted to receive a rim of a second glazing so as to surround the second glazing, the second housing having a second surface suitable for contacting the edge of the second glazing, the second housing comprising a second damping part, the second damping part comprising the second surface, a second material forming the second damping part having a second loss factor rp greater than 0.10,

[0013] - the first housing forms a notch in the joint,

[0014] - the second housing forms a notch in the joint,

[0015] - a value of the real part E' of the Young's modulus of the first material is less than 100 MPa, in particular less than 10 MPa,

[0016] - a value of the real part E' of the Young's modulus of the second material is less than 100 MPa, in particular less than 10 MPa,

[0017] - the joint is formed from a single material in a monolithic manner,

[0018] - the seal comprises a retaining part different from the first part damping, the retaining part being configured to be in contact with an element integral to a wall of the aircraft, a third material forming the part of maintenance exhibiting a third loss factor r|3 strictly less than the first loss factor, and in particular strictly less than 0.10,

[0019] - the first loss factor ip is greater than 0.20 and preferably greater than 0.50,

[0020] - a value of the real part E' of the Young's modulus of the first material is less than 10 MPa, in particular strictly less than 1 MPa,

[0021] Another aspect of the invention is an aircraft glazed element, comprising a seal according to an embodiment of the invention, and a first glazing, the first surface being mounted on the first face so that the seal receives the first glazing.

[0022] Advantageously, the first surface is mounted on the second face of the first glazing so that the seal receives the first glazing.

[0023] Advantageously, the glazed element comprises a second glazing, the second glazing having a third face and a fourth face opposite to the third face, the second surface of the seal being mounted on the third face and preferably on the fourth face of the second glazing so that the seal receives the second glazing.

[0024] Another aspect of the invention is an aircraft window, comprising a glazed element according to an embodiment of the invention, the glazed element further comprising a second glazing, the second glazing having a third face and a fourth face, the seal comprising a second surface adapted to be mounted on the third face and preferably on the fourth face so as to receive the second glazing.

[0025] Advantageously, the first glazing and / or the second glazing of the porthole is a monolith, preferably formed of polymethyl methacrylate.

[0026] Another aspect of the invention is an aircraft windscreen, comprising a glazed element according to an embodiment of the invention, in which the first glazing is laminated glazing. DESCRIPTION OF THE FIGURES

[0027] Other features, objectives and advantages of the invention will become apparent from the following description, which is purely illustrative and not limiting, and which should be read in conjunction with the accompanying drawings on which:

[0028] [Fig. 1] [Fig. 1] schematically illustrates the cross-section of a known aircraft window,

[0029] [Fig.2] Fig.2 schematically illustrates the detail of a cross-section of a glazed element according to one embodiment of the invention,

[0030] [Fig.3] Fig.3 schematically illustrates the detail of a cross-section of a glazed element according to one embodiment of the invention,

[0031] [Fig.4] Fig.4 schematically illustrates the detail of a cross-section of a glazed element according to one embodiment of the invention,

[0032] [Fig. 5] [Fig. 5] schematically illustrates the detail of a cross-section of a glazed element according to one embodiment of the invention,

[0033] [Fig.6] Fig.6 schematically illustrates the detail of a cross-section of a glazed element according to one embodiment of the invention,

[0034] [Fig.7] [Fig.7] illustrates acoustic insulation as a function of the frequency of a sound wave through known portholes and through a porthole according to an embodiment of the invention,

[0035] [Fig.8] [Fig.8] illustrates acoustic insulation as a function of the frequency of a sound wave through a known windshield and through a windshield according to an embodiment of the invention.

[0036] Throughout the figures, similar elements bear identical reference numerals. DEFINITIONS

[0037] The term "loss factor q" of a material, in the case of a material with a complex Young's modulus, refers to the ratio between the imaginary part E' of the material's Young's modulus and the real part E' of the material's Young's modulus. The loss factor q of a material is defined by the international standard ISO 18437-2:2005 (Mechanical vibration and shock — Characterization of the dynamic mechanical properties of viscoelastic materials — Part 2: Resonance method, section 3.2). Preferably, the loss factor q can be defined for a predetermined frequency. In this context, "a material has a first loss factor q greater than a certain value" means that the material has a first loss factor q greater than the specified value for each frequency in the audible frequency range, that is, in a frequency range extending from 20 Hz inclusive to 20,000 Hz inclusive, and preferably from 20 Hz inclusive to 10 kHz included.

[0038] The term "a value of the real part E' of the Young's modulus of a material is greater than a value" means that a value of the real part E' of the Young's modulus of the material is greater than the value of the real part E' of the Young's modulus of the material for each of the frequencies in the audible frequency range, that is to say in a frequency range extending between 20 Hz inclusive and 20,000 Hz inclusive, and preferably between 20 Hz inclusive and 10 kHz inclusive.

[0039] The real part E' and the imaginary part E” of Young's modulus can be defined for a predetermined temperature. The temperature range considered in the present invention is between -90°C and 60°C. In this invention, "the real part E' of Young's modulus of a material is greater than a certain value" means that the material has a real part E' of Young's modulus greater than the specified value for each of the temperatures between -90°C and 60°C. In this invention, "a material has a first loss factor" means that the material has a real part E' of Young's modulus greater than the specified value. ï] greater than a value » that the material has a first loss factor q greater than the value for each of the temperatures between -90°C and 60°C.

[0040] A dynamic characterization of a material is performed on a Metravib-type viscoanalyzer under the following measurement conditions. A sinusoidal load is applied to the material. A measurement sample of the material to be measured consists of two rectangular parallelepipeds, each parallelepiped having a thickness of 3.31 mm, a width of 10.38 mm, and a height of 6.44 mm. Each parallelepiped formed by the material is also referred to as a shear specimen. The excitation is implemented with a dynamic amplitude of 5 pm around the rest position, traversing the frequency range from 5 Hz to 700 Hz, and traversing a temperature range from -90°C to +60°C.

[0041] The viscoanalyzer allows each specimen (each sample) to be subjected to deformations under precise temperature and frequency conditions, and the displacements of the specimen, the forces applied to the specimen and their phase shift to be measured, which allows the measurement of rheological quantities characterizing the material of the specimen.

[0042] The exploitation of the measurements makes it possible in particular to calculate the Young's modulus E of the material, and particularly the real part E' of the Young's modulus and the imaginary part E” of the Young's modulus of the material, and thus to calculate the tangent of the loss angle (or loss factor) q (also designated by tan 0).

[0043] A value of the real part E' of Young's modulus and / or a loss factor q of a material are measured without the material being prestressed.

[0044] The term “glazing” means a structure comprising at least one sheet of organic or mineral glass, preferably adapted for mounting in an aircraft.

[0045] The glazing may comprise a single sheet of glass or a multi-layered glazed assembly of which at least one layer is a sheet of glass.

[0046] A glazing unit may include a sheet of organic glass. Preferably, the organic glass is formed from a compound comprising acrylates, preferably polymethyl methacrylate (PMMA). It may also be formed from polycarbonate.

[0047] A glazing unit may comprise a glazing assembly. The glazing assembly comprises at least one sheet of glass. The glass may be organic or mineral glass. The glass may be tempered. The glazing assembly is preferably laminated glazing. "Laminated glazing" is understood to mean a glazing assembly comprising at least two sheets of glass and an interlayer film made of plastic, preferably viscoelastic, separating the two sheets of glass. The plastic interlayer film may comprise one or more layers of a viscoelastic polymer such as polyvinyl butyral (PVB) or an ethylene-vinyl acetate (EVA) copolymer. The interlayer film is preferably made of standard PVB or acoustic PVB (such as single-layer or three-layer acoustic PVB). Acoustic PVB may comprise three layers: two outer layers of standard PVB and an inner layer of PVB with added plasticizer to make it less rigid than the outer layers. DETAILED DESCRIPTION OF THE INVENTION

[0048] General architecture of the seal 1 and the glazed element 2

[0049] With reference to [Fig.2], a seal 1 according to an embodiment of the invention is configured to receive an edge of a first glazing 3. The first glazing 3 comprises a first face 4 and a second face 5 opposite to the first face 6.

[0050] The seal 1 includes a first surface 6 adapted to be mounted on the first face 4 of the first glazing 3 so as to receive the first glazing 3. When the first glazing 3 is mounted to the seal 1, the first glazing 3 is in contact with the seal 1 on the first surface 6.

[0051] The joint 1 comprises a first damping part 7. The first damping part 7 comprises the first surface 6.

[0052] A first material forming the first damping part 7 has a first loss factor qi strictly greater than 0.10, in particular greater than 0.15, and preferably greater than 0.20.

[0053] Indeed, the inventors have discovered that when the glazing is held, preferably only, by a first material having a loss factor greater than 0.10, particularly greater than 0.15, and preferably greater than 0.20, the sound insulation through the glazed element 2 increases significantly, at least in frequency ranges within the audible frequency range. Thus, due to the viscous dissipation properties of the seal 1, the sound insulation of an aircraft glazed element 2 can be increased.

[0054] Another aspect of the invention is an aircraft glazed element 2 comprising a seal 1 and a first glazing 3, the first surface 6 being mounted on the first face 4 so that the seal 1 receives the first glazing 3.

[0055] With reference to figures 2 to 6, the first surface 6 can be adapted to be mounted on the first face 4 and on a second face 5 of the first glazing 3 opposite to the first face 4, so as to receive the first glazing 3. Thus, the first damping part 7 can hold two opposite faces of the first glazing 3 so as to avoid the gluing of the first glazing 3 on the seal 1 while allowing an increase in acoustic insulation through a glazed element formed at least by the first glazing 3 and by the seal 1.

[0056] The seal 1 can be configured to receive an edge of a second glazing unit 10. The second glazing unit 10 has a third face 15 and a fourth face 16 opposite the third face 15. The seal 1 then includes a second surface 11 adapted to be mounted on the third face 15, and preferably on the fourth face 16, so as to receive the second glazing unit 10. Thus, it is possible to increase the acoustic insulation of a double-glazed assembly including the seal 1.

[0057] The seal 1 may include a second damping part 12. The second damping part 12 comprises the second surface 11. A second material forms the second damping part 12. The second material has a second loss factor r|2 strictly greater than 0.10, in particular greater than 0.15, and preferably greater than 0.20. Thus, it is possible to increase the sound insulation of each of the panes of a double-glazed unit comprising the seal 1.

[0058] With reference to [Fig.2] and [Fig.3], the seal 1 may include a first housing 8 suitable for receiving the edge of the first glazing 3 and preferably a second housing 9 suitable for receiving the edge of the second glazing 10, so as to surround the first glazing and / or the second glazing 10. Thus, it is possible to simplify the manufacture of the seal 1, by manufacturing a single seal surrounding all the glazing of a glazed assembly.

[0059] With reference to [Fig.2], the first housing 8 and / the second housing 9 can each form a notch in the seal 1. Thus, the housing 8 allows the first glazing 3 to be installed by surrounding the edge of the first glazing 3 on the first face 4, on the second face 5, and on the periphery of the first glazing 3.

[0060] The first housing 8 and / or the second housing 9 can each form a recess in the gasket 1, allowing control over the position in which the first glazing 3 and / or the second glazing 10 is installed in the glazed element 2. Figure 3 illustrates a second glazing 10 held in the glazed element 2 by the gasket 1, the second glazing 10 being arranged in the second housing 9 formed by a recess. Preferably, when a glazing is arranged in a recess of the gasket 1, the glazing can be bonded to the first surface 6 and / or to a second surface 11.

[0061] The second housing 9 may have a second surface 11 suitable for contacting the edge of the second glazing 10. The second housing 9 may include the second damping part 12. The second damping part 12 includes the second surface 11. The second material forming the second damping part 12 may have a second loss factor rp greater than 0.10, in particular greater than 0.15, and preferably greater than 0.20.

[0062] A value of the real part E' of the Young's modulus of the first material and / or the second material is less than 100 MPa, in particular less than 10 MPa, and preferably less than 1 MPa. Thus, it is possible to dissipate the energy of the bending waves of the glazing 10 by viscoelastic losses.

[0063] With reference to [Fig. 2], the seal 1 can be formed from a single material, in a monolithic manner. Thus, it is possible to simplify the manufacture of the seal 1, for example by using a single material during extrusion or injection molding. The inventors discovered that it was possible to choose the characteristics of the material forming the seal 1 so that the seal 1 could hold the glazing(s) when clamped and fixed to an element attached to a wall of the aircraft, while having a loss factor that increases the acoustic insulation of a glazed element 2 comprising the first glazing 3 and the seal 1. Preferably, when the seal 1 is formed of a single material in a monolithic manner, the first loss factor qi is strictly greater than 0.10, in particular greater than 0.15, and preferably greater than 0.20, and the value of the real part E' of the Young's modulus of the material forming the seal 1 is greater than 1 MPa.

[0064] With reference to [Fig.4], the joint 1 can be formed by one or more parts without covering the end of the edge of the first glazing 3 and / or the second glazing 10.

[0065] With reference to [Fig. 5] and [Fig. 6], the seal 1 may comprise a retaining portion 13 that differs from the first damping portion 7. Preferably, the retaining portion 13 and the first damping portion 7 do not share any common area. The retaining portion 13 is fixedly mounted on the damping portion 7. The retaining portion 13 may be configured to be in contact with an element integral with an aircraft wall. A third material forming the retaining portion 13 has a third loss factor rp that is strictly lower than the first loss factor, and in particular strictly less than 0.10, preferably less than 0.05. Thus, the seal 1 can be configured both to be fixedly mounted on an aircraft wall in a manner similar to known seals, and to have characteristics that increase acoustic insulation compared to known seals through viscous dissipation.

[0066] Preferably, a seal 1 comprising a retaining portion 13 may have a first loss factor rp greater than 0.20 and preferably greater than 0.50. Indeed, if the seal 1 includes a retaining portion 13, it is possible to adapt the first material and preferably the second material, so as to increase acoustic insulation without complicating the implementation of the fixing of the seal 1 to an element integral with the aircraft wall. Thus, it is possible to increase the acoustic insulation of a glazed assembly 2 comprising the seal 1 while facilitating the fixing of the glazed assembly 2 to an element integral with the aircraft wall.

[0067] A joint 1 comprising a retaining part 13 may comprise a first damping part 7 and / or a second damping part 12, having a value of the real part E' of Young's modulus strictly less than 10 MPa, in particular strictly less than 1 MPa. Thus, it is possible to dissipate the energy of the bending waves of the glazing 10 by viscoelastic losses.

[0068] The first material and / or the second material are preferably selected from silicone, nitrile, and polyurethane. The viscoelastic properties of known materials can be measured by the methods described herein. The first material and / or the second material may have a glass transition temperature between -80°C and -50°C inclusive. For example, the first material and / or the second material may comprise methyl vinyl silicone (MVQ) crosslinked with benzoyl peroxide. The first material and / or the second material may also be a porous material. The loss factor of the first material and / or the second material may also be adjusted by a tackifying agent, for example, a glycerin ester, calcium carbonate, or carbon nanotubes.For example, Weber's Weberseal PU 40 polyurethane sealant (registered trademark) has a loss factor q of 0.41 and a Young's modulus E' of 7.2 MPa. For example, Sikaflex PRO-11 FC polyurethane sealant (registered trademark) has a loss factor q of 0.20 and a Young's modulus E' of 1.2 MPa.

[0069] With reference to [Fig. 5] and [Fig. 6], the seal 1 preferably comprises a spacer 21 suitable for separating the first glazing 3 from the second glazing 10 by a predetermined thickness. The spacer 21 may be a portion of the seal 1 arranged between the first housing 8 and the second housing 9. With reference to [Fig. 5], the spacer 21 may be formed by the first damping portion 7 and by the second damping portion 12. With reference to [Fig. 6], the spacer 21 may be formed by the retaining portion 13 and by the first damping portion 7 and / or the second damping portion 12. With reference to [Fig. 6], the first damping portion 7 and / or the second damping portion 12 may be formed by a layer of polymer material deposited on the retaining portion 13.

[0070] Hublot 14

[0071] Another aspect of the invention is an aircraft window 14, comprising a glazed element 2, the glazed element 2 comprising a second glazing 10. The second glazing 10 has a third face 15 and a fourth face 16. The second surface 11 is adapted to be mounted on the third face 15 and preferably on the fourth face 16 so as to receive the second glazing 10.

[0072] Preferably, the first glazing 3 and / or the second glazing 10 of a porthole 14 are each a monolith, preferably formed of polymethyl methacrylate (acronym PMMA).

[0073] With reference to [Fig. 6], the porthole 14 increases sound insulation in the audible mid and high frequencies, particularly in a frequency range between 200 Hz and 1300 Hz, and preferably in a frequency range between 350 Hz and 450 Hz. These frequency ranges may include the resonance frequency of the two panes of glass in the porthole 14.

[0074] Figure 7 illustrates a finite element method simulation of the sound insulation (TL for transmission loss) through three portholes. Each of the three simulated portholes comprises panes of glass with a maximum diameter of 520 mm. The first pane, 3, is made of PMMA and has a thickness of 12.7 mm. The second pane, 10, is also made of PMMA and has a thickness of 6.1 mm. The first pane, 3, and the second pane, 10, are separated by a 5 mm air gap. The seal of each of the simulated portholes has a real part E' value of Young's modulus equal to 3 MPa and a Poisson's ratio equal to 0.49.

[0075] Curve (a) illustrates the sound insulation for a known porthole that does not include a seal.

[0076] Curve (b) illustrates the acoustic insulation for a known porthole, including a seal formed by a material having a loss factor q equal to 0.001. Curve (b) illustrates an increase in the decoupling frequency between the first glazing 3 and the second glazing 10 when using a known porthole, compared to a porthole without a seal.

[0077] Curve (c) illustrates the sound insulation for a porthole 14 according to an embodiment of the invention, which includes a seal comprising a first damping part 7 and a second damping part 12 having respectively a first loss factor qi and a second loss factor r|2 each equal to 0.7. Curve (c) illustrates an increase in sound insulation when using a porthole according to an embodiment of the invention compared to known portholes.

[0078] Windshield

[0079] Another aspect of the invention is an aircraft windshield, comprising a glazed element 2. The first glazing 3 of the glazed element 2 may be laminated glass. The windshield may comprise only the first glazing 3, or not comprise a second glazing 10.

[0080] With reference to [Fig.8], the windscreen increases acoustic insulation, particularly in the low and medium audible frequencies, especially in a frequency range between 50 Hz and 3 kHz.

[0081] Figure 8 illustrates a finite element method simulation of sound insulation through two windshields. Each of the two simulated windshields comprises a first laminated pane of glass.

[0082] Curve (d) illustrates the sound insulation for a known windscreen, including a seal formed by a material having a loss factor q equal to 0.001.

[0083] Curve (e) illustrates the acoustic insulation for a windshield according to an embodiment of the invention, which includes a seal 1 comprising a first damping part 7 having a first loss factor qi equal to 0.5. Curve (e) illustrates an increase in acoustic insulation when using a windshield according to an embodiment of the invention compared to a known windshield.

[0084] Method for manufacturing the seal 1 and fixing a glazed element 2 in an aircraft

[0085] Another aspect of the invention is a method for manufacturing the seal 1.

[0086] The manufacturing process of the seal 1 may include a step of extruding the seal 1. The extrusion of the seal 1 may be carried out from the first material so as to form the first damping part 7 and preferably from the second material so as to form the second damping part 12.

[0087] The manufacturing process for the seal 1 may include a co-extrusion step of the seal 1. The co-extrusion of the seal 1 may be carried out from the first material having a first loss factor ip strictly greater than 0.10 so as to form the first damping part 7, and from the third material having a third loss factor r|3 strictly less than the first loss factor, and in particular strictly less than 0.10, so as to form the retaining part 13. The co-extrusion may also be carried out from the second material having a third loss factor rp strictly greater than 0.10 so as to form the second damping part 7.

[0088] Following the extrusion or co-extrusion step of the seal 1, the seal 1 may have two ends. The manufacturing process for the seal 1 may include a step subsequent to the extrusion or co-extrusion step, in which the two ends of the seal 1 are welded together.

[0089] Alternatively, the manufacturing process for seal 1 may include a step of injecting seal 1 onto the edge of a glazing. Preferably, the manufacturing process includes a first step of injecting the first material and a second step of injecting the second and / or third material.

Claims

Demands

1. A sealing gasket (1) for a glazed element (2) of an aircraft, the gasket (1) being configured to receive an edge of a first glazing (3), the first glazing (3) having a first face (4), the gasket (1) comprising a first surface (6) adapted to be mounted on the first face (4) so ​​as to receive the first glazing (3), characterized in that the gasket comprises a first damping portion (7), the first damping portion (7) comprising the first surface (6), in that a first material forming the first damping portion (7) has a first loss factor Pi strictly greater than 0.10, and in that the gasket (1) comprises a retaining portion (13) different from the first damping portion (7), the retaining portion (13) being configured to be in contact with an element integral with a wall of the aircraft,a third material forming the retaining part (13) having a third loss factor r|3 strictly less than the first loss factor rp, and in particular strictly less than 0.

10.

2. Joint (1) according to the preceding claim, wherein the first surface is adapted to be mounted on the first face (4) and on a second face (5) of the first glazing (3) opposite the first face (4), so as to receive the first glazing (3).

3. Joint (1) according to claim 1 or 2, comprising a first housing (8) adapted to receive the edge of the first glazing (3) so as to surround the first glazing (3), the first housing (8) comprising the first damping part (7).

4. Joint (1) according to any one of the preceding claims, comprising a second housing (9) adapted to receive an edge of a second glazing (10) so as to surround the second glazing (10), the second housing (9) having a second surface (11) suitable for being in contact with the edge of the second glazing (10), the second housing (9) comprising a second damping part (12), the second damping part (12) comprising the second surface (11), a second material forming the second damping part (12) having a second loss factor rp greater than 0.

10.

5. Joint (1) according to any one of the preceding claims, wherein the first housing (8) forms a notch in the joint (1).

6. Joint (1) according to any one of the preceding claims, wherein a value of the real part E' of the Young's modulus of the first material is less than 100 MPa, in particular less than 10 MPa.

7. Joint (1) according to any one of the preceding claims, formed from a single material in a monolithic manner.

8. Joint (1) according to any one of claims 1 to 7, wherein the first loss factor qi is greater than 0.20 and preferably greater than 0.

50.

9. Joint (1) according to any one of claims 1 to 8, wherein a value of the real part E' of the Young's modulus of the first material is less than 10 MPa, in particular strictly less than 1 MPa.

10. Aircraft glazed element (2), comprising: - a seal (1) according to any one of claims 1 to 9, - a first glazing (3), the first surface (6) being mounted on the first face (4) so ​​that the seal (1) receives the first glazing (3).

11. Aircraft window (14), comprising a glazed element (2) according to claim 10, the glazed element (2) further comprising a second glazing (10), the second glazing (10) having a third face (15) and a fourth face (16), the seal (1) comprising a second surface (11) adapted to be mounted on the third face (15) and preferably on the fourth face (16) so as to receive the second glazing (10).

12. Aircraft windscreen, comprising a glazed element (2) according to claim 10, wherein the first glazing (3) is laminated glazing.

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