An aircraft windshield structure

Abstract

The application belongs to the technical field of aircraft windshield glass structure design, and particularly relates to an aircraft windshield glass structure, which comprises an electromagnetic film, an outer glass, an inner glass, a metal frame, a metal sinking frame and a curved wave-transparent fairing. The electromagnetic film is located between the outer glass and the inner glass. The inner glass is arranged in the metal frame, and the electromagnetic film is in flush contact with the outer side surface of the metal frame. The metal sinking frame is installed in a windshield window and has an L-shaped cross section. The metal frame is arranged in an L-shaped opening of the metal sinking frame, and the outer side surfaces of the metal frame and the metal sinking frame are in flush contact with the surface skin of an aircraft body. The outer glass protrudes from the surface skin of the aircraft body. The curved wave-transparent fairing is arranged around the outer periphery of the outer glass and smoothly transitions between the outer glass and the surface skin of the aircraft body.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft cabin windshield glass structure design, and particularly relates to an aircraft cabin windshield glass structure. BACKGROUND

[0002] In order to reduce the radar scattering characteristics of the aircraft cabin, at present, an electromagnetic film is plated on the outer surface of the windshield glass to shield the incident electromagnetic wave and convert the scattering effect of the cavity of the aircraft cabin into the shape scattering characteristics of the windshield glass.

[0003] However, the electromagnetic film is usually fragile and has poor environmental adaptability, and is easily detached, damaged or failed when plated on the outer surface of the windshield glass.

[0004] The application is proposed in view of the above technical defects. SUMMARY

[0005] The application aims to provide an aircraft cabin windshield glass structure to overcome or alleviate at least one aspect of the known technical defects.

[0006] The technical solution of the application is as follows:

[0007] An aircraft cabin windshield glass structure comprises an electromagnetic film, an outer layer glass, an inner layer glass, a metal frame, a metal sunken frame and a curved wave-transparent fairing.

[0008] The electromagnetic film is located between the outer layer glass and the inner layer glass.

[0009] The inner layer glass is arranged in the metal frame, and the electromagnetic film is in flush contact with the outer side surface of the metal frame.

[0010] The metal sunken frame is installed in the windshield window and has an L-shaped cross section.

[0011] The metal frame is arranged in the L-shaped opening of the metal sunken frame, and the outer side surfaces of the metal frame and the metal sunken frame are in flush contact with the surface skin of the aircraft body, and the outer layer glass protrudes from the surface skin of the aircraft body.

[0012] The curved wave-transparent fairing is arranged around the outer periphery of the outer layer glass and smoothly transitions between the surface skin of the aircraft body and the outer layer glass.

[0013] According to at least one embodiment of the application, the aircraft cabin windshield glass structure described above is characterized in that the electromagnetic film is connected to the outer layer glass and the inner layer glass by cementing.

[0014] According to at least one embodiment of the application, the aircraft cabin windshield glass structure described above is characterized in that the electromagnetic film is a nano-level transparent electromagnetic film.

[0015] According to at least one embodiment of the present application, in the aircraft windshield glass structure, the inner layer glass edge and the metal frame are connected by cementing.

[0016] According to at least one embodiment of the present application, in the aircraft windshield glass structure, the gap between the metal sinking frame and the windshield window is filled with conductive sealant and polished.

[0017] According to at least one embodiment of the present application, in the aircraft windshield glass structure, the metal frame and the metal sinking frame are connected by a plurality of countersunk screws, and the gap is filled with conductive sealant and polished.

[0018] According to at least one embodiment of the present application, in the aircraft windshield glass structure, the curved wave-transparent fairing is connected between the outer layer glass, the metal frame, the metal sinking frame, and the surface skin of the aircraft body by cementing.

[0019] According to at least one embodiment of the present application, in the aircraft windshield glass structure, the curved wave-transparent fairing is made of glass fiber or epoxy resin.

[0020] According to at least one embodiment of the present application, in the aircraft windshield glass structure, the curved wave-transparent fairing is made of glass fiber or epoxy resin.

[0021] According to at least one embodiment of the present application, in the aircraft windshield glass structure, the electromagnetic film, the outer layer glass, the inner layer glass, the metal frame, the metal sinking frame, and the curved wave-transparent fairing are hexagonal sawtooth structures.

[0022] According to at least one embodiment of the present application, in the aircraft windshield glass structure, the projections of the two edges of the electromagnetic film, the outer layer glass, the inner layer glass, the metal frame, the metal sinking frame, and the curved wave-transparent fairing on the horizontal plane are parallel to the projections of the left and right front edges of the fuselage on the horizontal plane.

[0023] According to at least one embodiment of the present application, in the aircraft windshield glass structure, the left and right front edges of the fuselage are symmetrically arranged in front of the fuselage and connected to the surface skin of the aircraft body, and the gap after connection is filled with conductive sealant and polished.

[0024] The present application has at least the following technical effects:

[0025] The present application provides an aircraft windshield glass structure, which is designed by embedding an electromagnetic film, protruding an outer layer glass, and applying a curved wave-transparent fairing, thereby ensuring the aerodynamic performance of the aircraft while meeting environmental adaptability and reducing radar scattering characteristics. BRIEF DESCRIPTION OF DRAWINGS

[0026] Fig. 1is a schematic view of an aircraft windshield structure provided by an embodiment of the present application;

[0027] Fig. 2 is a partial cross-sectional view of an aircraft windshield structure provided by an embodiment of the present application;

[0028] wherein:

[0029] 1 - electromagnetic film; 2 - outer glass; 3 - inner glass; 4 - metal frame; 5 - metal sunken frame; 6 - curved wave-transparent fairing; 7 - body surface skin; 8 - left side fuselage leading edge; 9 - right side fuselage leading edge.

[0030] In order to better illustrate the present embodiment, some components in the drawings can be omitted, enlarged or reduced, and do not represent the actual product size. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0031] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly and completely described below in conjunction with the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design.

[0032] In addition, unless otherwise defined, the technical terms or scientific terms used in the present application description should be the general meaning understood by the general technical personnel in the field to which the present application belongs. The words indicating the direction used in the present application description are only used to indicate the relative direction or positional relationship, and when the absolute position of the described object changes, the relative positional relationship may also change accordingly. In the present application description, "including" indicates that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, and other elements or objects are not excluded.

[0033] In addition, it should be noted that, unless otherwise explicitly specified and limited, the "installation", "connection" and similar words used in the present application description should be interpreted broadly, for example, the connection can be fixed connection, or detachable connection; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through an intermediate medium, and the skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0034] An aircraft windshield structure, as shown in Figs. 1-2 includes an electromagnetic film 1, an outer glass 2, an inner glass 3, a metal frame 4, a metal sunken frame 5, and a curved wave-transparent fairing 6.

[0035] The electromagnetic film 1 is located between the outer glass 2 and the inner glass 3. The electromagnetic film 1 is cemented with the outer glass 2 and the inner glass 3. The electromagnetic film 1 is a nanometer-level transparent electromagnetic film, which can achieve electromagnetic shielding performance while meeting the optical transparency requirements inside the cabin.

[0036] The inner glass 3 is arranged in the metal frame 4, and the electromagnetic film 1 is in flush contact with the outer side surface of the metal frame 4. The edge of the inner glass 3 is cemented with the metal frame 4.

[0037] The metal sunken frame 5 is installed in the windshield window and has an L-shaped cross section. The gap between the metal sunken frame 5 and the windshield window is filled with a conductive sealant and polished smooth.

[0038] The metal frame 4 is arranged in the L-shaped opening of the metal sunken frame 5, and the outer side surfaces of the metal frame 4 and the metal sunken frame 5 are in flush contact with the surface skin 7 of the aircraft body, and the outer glass 2 protrudes from the surface skin 7 of the aircraft body. The metal frame 4 and the metal sunken frame 5 are connected by a plurality of countersunk screws, and the gap is filled with a conductive sealant and polished smooth.

[0039] The curved wave-transparent fairing 6 surrounds the outer periphery of the outer glass 2 and smoothly transitions between the surface skin 7 of the outer glass 2. The curved wave-transparent fairing 6 is cemented with the outer glass 2, the metal frame 4, the metal sunken frame 5, and the surface skin 7 of the aircraft body. The curved wave-transparent fairing 6 is made of a composite material such as glass fiber or epoxy resin.

[0040] In the aircraft cabin windshield glass structure disclosed in the above embodiment, the electromagnetic film 1 is designed to be located between the outer glass 2 and the inner glass 3, which can be effectively protected by the outer glass 2 and the inner glass 3. On the basis of ensuring the shielding performance of the cabin glass, the influence of the external environment on the electromagnetic film 1 is avoided, and phenomena such as shedding, damage, and failure can be effectively avoided, thereby improving the environmental adaptability of the cabin glass. In addition, through the protruding design of the outer glass 2, the electromagnetic film 1 is in flush contact with the outer surfaces of the metal frame 4 and the metal sunken frame 5, as well as the surface skin 7 of the aircraft body, thereby avoiding the destruction of the step structure to the electrical continuity and ensuring the smooth electrical continuity between the electromagnetic film 1 and the surface skin 7 of the aircraft body, thereby avoiding the generation of electromagnetic defects, reducing the radar scattering characteristics, and designing the curved wave-transparent fairing 6 to smoothly transition between the surface skin 7 of the outer glass 2, thereby avoiding the aerodynamic loss caused by the protrusion of the outer glass 2 from the surface skin 7 of the aircraft body.

[0041] The aircraft cabin windshield glass structure disclosed in the above embodiment ensures the aerodynamic performance of the aircraft on the basis of meeting the environmental adaptability and reducing the radar scattering characteristics through the design of the built-in electromagnetic film 1, the outward protrusion of the outer glass 2, and the application of the curved wave-transparent fairing 6.

[0042] Further, the aircraft windshield structure disclosed in the above embodiment has a hexagonal sawtooth structure as a whole, including the electromagnetic film 1, the outer layer glass 2, the inner layer glass 3, the metal frame 4, the metal sunken frame 5, and the curved wave-transparent fairing 6, so as to further reduce the radar scattering characteristics and ensure the openness of the cabin view in all directions.

[0043] Further, the aircraft windshield structure disclosed in the above embodiment has a hexagonal sawtooth structure as a whole, including the electromagnetic film 1, the outer layer glass 2, the inner layer glass 3, the metal frame 4, the metal sunken frame 5, and the curved wave-transparent fairing 6, so as to further reduce the radar scattering characteristics and ensure the openness of the cabin view in all directions.

[0044] The left and right front edges 8 and 9 of the fuselage are symmetrically arranged in front of the fuselage and connected with the body surface skin 7, and the gap after the connection is filled with conductive sealant and polished smooth, so as to further reduce the radar scattering characteristics.

[0045] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings, and those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without deviating from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the related technical features, and the technical solutions after these changes or replacements will fall within the protection scope of the present application.

Claims

1. An aircraft windshield structure, characterized in that, It comprises: An electromagnetic film (1), an outer layer glass (2), an inner layer glass (3), a metal frame (4), a metal sunken frame (5), a curved wave-transparent fairing (6); The electromagnetic film (1) is located between the outer layer glass (2) and the inner layer glass (3); The inner layer glass (3) is arranged in the metal frame (4), and the electromagnetic film (1) is flush with the outer side surface of the metal frame (4); The metal sunken frame (5) is installed in the windshield window and has an L-shaped cross section; The metal frame (4) is arranged in the L-shaped opening of the metal sunken frame (5), and the outer side surfaces of the metal frame (4) and the metal sunken frame (5) are flush with the surface skin (7) of the machine body, and the outer layer glass (2) protrudes from the surface skin (7) of the machine body; The curved wave-transparent fairing (6) surrounds the outer periphery of the outer layer glass (2) and smoothly transitions between the surface skin (7) of the machine body.

2. The aircraft cockpit windshield glass structure according to claim 1, wherein the electromagnetic film (1) is connected with the outer layer glass (2) and the inner layer glass (3) through cementing.

3. The aircraft cockpit windshield glass structure according to claim 2, wherein the electromagnetic film (1) is a nano-level transparent electromagnetic film.

4. The aircraft cockpit windshield glass structure according to claim 3, wherein the inner layer glass (3) is connected with the metal frame (4) through cementing.

5. The aircraft cockpit windshield glass structure according to claim 4, wherein the gap between the metal sunken frame (5) and the windshield window is filled with conductive sealant and polished smooth.

6. The aircraft cockpit windshield glass structure according to claim 5, wherein the metal frame (4) and the metal sunken frame (5) are connected through a plurality of countersunk screws, and the gap is filled with conductive sealant and polished smooth.

7. The aircraft cockpit windshield glass structure according to claim 6, wherein the curved wave-transparent fairing (6) is connected with the outer layer glass (2), the metal frame (4), the metal sunken frame (5) and the surface skin (7) of the machine body through cementing.

8. The aircraft cockpit windshield glass structure according to claim 7, wherein the curved wave-transparent fairing (6) is made of glass fiber or epoxy resin.

9. The aircraft cockpit windshield glass structure according to claim 7, wherein the curved wave-transparent fairing (6) is made of glass fiber or epoxy resin.

10. The aircraft cockpit windshield glass structure according to claim 9, wherein the electromagnetic film (1), the outer layer glass (2), the inner layer glass (3), the metal frame (4), the metal sunken frame (5) and the curved wave-transparent fairing (6) have a hexagonal sawtooth structure.

11. The aircraft cockpit windshield glass structure according to claim 10, wherein the projections of the two edges in front of the electromagnetic film (1), the outer layer glass (2), the inner layer glass (3), the metal frame (4), the metal sunken frame (5) and the curved wave-transparent fairing (6) on the horizontal plane are parallel to the projections of the left and right front edges (8, 9) of the machine body on the horizontal plane.

12. The aircraft cockpit windshield glass structure according to claim 11, wherein ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ The left side fuselage front edge (8) and the right side fuselage front edge (9) are symmetrically arranged in front of the fuselage and are connected with the fuselage surface skin (7), and the gap after connection is filled with conductive sealant and polished smooth.

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