Windshield glass structure of aircraft cockpit

Abstract

The invention belongs to the technical field of aircraft cockpit windshield glass structure design, and particularly relates to an aircraft cockpit windshield glass structure which comprises an electromagnetic film, outer-layer glass, inner-layer glass, a metal frame, a metal sinking frame and a curved-surface wave-transparent fairing. The electromagnetic film is positioned between the outer-layer glass and the inner-layer glass; the inner-layer glass is arranged in the metal frame; the electromagnetic film is in flush contact with the outer side surface of the metal frame; the metal sinking frame is mounted in the windshield window, and the cross section of the metal sinking frame is L-shaped; the metal frame is arranged in the L-shaped opening of the metal sinking frame, the outer side surfaces of the metal frame and the metal sinking frame are flush and contacted with the aircraft body surface skin, and the outer-layer glass protrudes out of the aircraft body surface skin; the curved-surface wave-transparent fairing surrounds the periphery of the outer-layer glass and is in smooth transition between the outer-layer glass and the surface skin of the machine body.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft cockpit windshield structure design, and in particular relates to an aircraft cockpit windshield structure. Background Art

[0002] In order to reduce the radar scattering characteristics of the aircraft cabin, currently, the outer surface of the windshield is mostly coated with an electromagnetic film to shield the incident electromagnetic waves and convert the scattering effect of the aircraft cabin cavity into the outer scattering characteristics of the windshield.

[0003] However, electromagnetic films are usually fragile and have poor environmental adaptability. When plated on the outer surface of the windshield, they are very prone to falling off, breakage, and failure.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0005] The purpose of the present application is to provide an aircraft cabin windshield structure to overcome or alleviate at least one of the known technical deficiencies.

[0006] The technical solution of this application is:

[0007] An aircraft cabin windshield structure, comprising: an electromagnetic film, an outer layer of glass, an inner layer of glass, a metal frame, a metal sinking frame, and a curved wave-transmitting fairing;

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

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

[0010] The metal sinking 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 sinking frame, the outer surfaces of the metal frame and the metal sinking frame are in flush contact with the surface skin of the body, and the outer layer of glass protrudes from the surface skin of the body;

[0012] The curved wave-transmitting fairing surrounds the outer periphery of the outer glass and smoothly transitions between the outer glass body surface skin.

[0013] According to at least one embodiment of the present application, in the above-mentioned aircraft cabin windshield structure, the electromagnetic film is bonded to the outer layer of glass and the inner layer of glass.

[0014] According to at least one embodiment of the present application, in the above-mentioned aircraft cabin windshield structure, the electromagnetic film is a nanoscale transparent electromagnetic film.

[0015] According to at least one embodiment of the present application, in the above-mentioned aircraft cabin windshield structure, the edge of the inner layer of glass is glued to the metal frame.

[0016] According to at least one embodiment of the present application, in the above-mentioned aircraft cabin windshield structure, the gap between the metal sunken frame and the windshield window is filled with conductive sealant and polished smooth.

[0017] According to at least one embodiment of the present application, in the above-mentioned aircraft cabin windshield structure, the metal frame and the metal sunken frame are connected by multiple countersunk screws, and the gap is filled with conductive sealant and polished smooth.

[0018] According to at least one embodiment of the present application, in the above-mentioned aircraft cabin windshield structure, the curved wave-transmitting fairing is glued to the outer glass, the metal frame, the metal sinking frame, and the fuselage surface skin.

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

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

[0021] According to at least one embodiment of the present application, in the above-mentioned aircraft cabin windshield structure, the electromagnetic film, outer glass, inner glass, metal frame, metal sunken frame, and curved wave-transmitting fairing have a hexagonal sawtooth structure.

[0022] According to at least one embodiment of the present application, in the above-mentioned aircraft cabin windshield structure, the projections of the electromagnetic film, outer glass, inner glass, metal frame, metal sunken frame, and the two front edges of the curved wave-transmitting fairing outline on the horizontal plane are parallel to the projections of the left fuselage leading edge and the right fuselage leading edge on the horizontal plane.

[0024] According to at least one embodiment of the present application, in the above-mentioned aircraft cabin windshield structure, the left fuselage leading edge and the right fuselage leading edge are symmetrically arranged in front of the fuselage and connected to the fuselage surface skin. After the connection, the gap is filled with a conductive sealant and polished smooth.

[0025] This application has at least the following beneficial technical effects:

[0026] Provided is an aircraft cabin windshield structure, which ensures the aerodynamic performance of the aircraft while meeting environmental adaptability and reducing radar scattering characteristics through the design of built-in electromagnetic film, convex outer glass and application of curved wave-transparent fairing. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 is a schematic diagram of an aircraft cabin windshield structure provided by an embodiment of the present application;

[0028] Figure 2 is a partial cross-sectional view of an aircraft cabin windshield structure provided by an embodiment of the present application;

[0029] in:

[0030] 1-electromagnetic film; 2-outer glass; 3-inner glass; 4-metal frame; 5-metal sinking frame; 6-curved wave-transmitting fairing; 7-fuselage surface skin; 8-front edge of the left fuselage; 9-front edge of the right fuselage.

[0031] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0032] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0033] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0034] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0035] An aircraft cabin windshield structure, such as Figure 1-Figure 2 As shown, it includes an electromagnetic film 1, an outer layer of glass 2, an inner layer of glass 3, a metal frame 4, a metal sinking frame 5, and a curved wave-transmitting fairing 6.

[0036] The electromagnetic film 1 is located between the outer glass 2 and the inner glass 3. The electromagnetic film 1 is bonded to the outer glass 2 and the inner glass 3. The electromagnetic film 1 is a nano-level transparent electromagnetic film, so that it can achieve electromagnetic shielding performance while meeting the optical transparency requirements of the interior of the cabin.

[0037] The inner glass 3 is arranged in the metal frame 4, and the electromagnetic film 1 is in flush contact with the outer surface of the metal frame 4. The edge of the inner glass 3 and the metal frame 4 are glued and connected.

[0038] The metal sinking frame 5 is installed in the windshield window, and its cross section is L-shaped. The gap between the metal sinking frame 5 and the windshield window is filled with conductive sealant and polished smooth.

[0039] The metal frame 4 is arranged in the L-shaped opening of the metal sinking frame 5, the outer surfaces of the metal frame 4 and the metal sinking frame 5 are flush with the body surface skin 7, and the outer glass 2 protrudes from the body surface skin 7. The metal frame 4 and the metal sinking frame 5 are connected by a plurality of countersunk screws, and the gap is filled with conductive sealant and polished smooth.

[0040] The curved wave-transmitting fairing 6 surrounds the outer periphery of the outer glass 2 and smoothly transitions between the outer glass 2 and the body surface skin 7. The curved wave-transmitting fairing 6 is bonded to the outer glass 2, the metal frame 4, the metal sinking frame 5, and the body surface skin 7. The curved wave-transmitting fairing 6 is made of composite materials such as glass fiber or epoxy resin.

[0041] In the aircraft cabin windshield structure disclosed in the above-mentioned embodiment, the electromagnetic film 1 is designed to be located between the outer glass 2 and the inner glass 3, and 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 the phenomena of falling off, breakage, failure, etc. 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 made to be flush with the outer surface of the metal frame 4, the metal sinking frame 5, and the body surface skin 7, thereby avoiding the damage to the electrical continuity caused by the step structure, ensuring smooth electrical continuity between the electromagnetic film 1 and the body surface skin 7, thereby avoiding the generation of electromagnetic defects, and reducing radar scattering characteristics. The curved wave-transparent fairing 6 is designed to smoothly transition between the outer glass 2 and the body surface skin 7, thereby avoiding the aerodynamic loss caused by the outer glass 2 protruding from the body surface skin 7.

[0042] The aircraft cabin windshield structure disclosed in the above embodiment, through the design of built-in electromagnetic film 1, convex outer glass 2, and application of curved wave-transparent fairing 6, ensures the aerodynamic performance of the aircraft while meeting environmental adaptability and reducing radar scattering characteristics.

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

[0044] Furthermore, the projections of the two front edges of the overall outline of the aircraft cabin windshield structure disclosed in the above embodiment on the horizontal plane are parallel to the projections of the left fuselage leading edge 8 and the right fuselage leading edge 9 on the horizontal plane, including the projections of the two front edges of the outline of the electromagnetic film 1, the outer glass 2, the inner glass 3, the metal frame 4, the metal sinking frame 5, and the curved wave-transparent fairing 6 on the horizontal plane, which are parallel to the projections of the left fuselage leading edge 8 and the right fuselage leading edge 9 on the horizontal plane, so as to further reduce the radar scattering characteristics.

[0045] The left fuselage leading edge 8 and the right fuselage leading edge 9 are symmetrically arranged in front of the fuselage and connected to the fuselage surface skin 7. After connection, the gap is filled with conductive sealant and polished smooth to further reduce radar scattering characteristics.

[0046] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. An aircraft cabin windshield structure, characterized in that: include: Electromagnetic film (1), outer glass (2), inner glass (3), metal frame (4), metal sinking frame (5), curved wave-transmitting fairing (6); The electromagnetic film (1) is located between the outer layer of glass (2) and the inner layer of glass (3); The inner glass (3) is arranged inside the metal frame (4), and the electromagnetic film (1) is in flush contact with the outer surface of the metal frame (4); The metal sinking 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 sinking frame (5); the outer surfaces of the metal frame (4) and the metal sinking frame (5) are in flush contact with the body surface skin (7); and the outer layer of glass (2) protrudes from the body surface skin (7); The curved wave-transmitting fairing (6) surrounds the outer periphery of the outer glass (2) and smoothly transitions between the outer glass (2) and the body surface skin (7).

2. The aircraft cabin windshield structure according to claim 1, characterized in that: The electromagnetic film (1) is bonded to the outer layer of glass (2) and the inner layer of glass (3).

3. The aircraft cabin windshield structure according to claim 2, characterized in that: The electromagnetic film (1) is a nano-scale transparent electromagnetic film.

4. The aircraft cabin windshield structure according to claim 3, characterized in that: The edge of the inner glass (3) is glued to the metal frame (4).

5. The aircraft cabin windshield structure according to claim 4, characterized in that: The gap between the metal sinking frame (5) and the windshield window is filled with conductive sealant and polished to be smooth.

6. The aircraft cabin windshield structure according to claim 5, characterized in that: The metal frame (4) and the metal sunken frame (5) are connected by a plurality of countersunk screws, and the gaps are filled with conductive sealant and polished smooth.

7. The aircraft cabin windshield structure according to claim 6, characterized in that: The curved wave-transmitting fairing (6) is bonded to the outer glass (2), the metal frame (4), the metal sinking frame (5), and the body surface skin (7).

8. The aircraft cabin windshield structure according to claim 7, characterized in that: The curved wave-transmitting fairing (6) is made of glass fiber or epoxy resin.

9. The aircraft cabin windshield structure according to claim 7, characterized in that: The curved wave-transmitting fairing (6) is made of glass fiber or epoxy resin.

10. The aircraft cabin windshield structure according to claim 9, characterized in that: The electromagnetic film (1), the outer layer of glass (2), the inner layer of glass (3), the metal frame (4), the metal sinking frame (5), and the curved surface wave-transmitting fairing (6) have a hexagonal sawtooth structure.

11. The aircraft cabin windshield structure according to claim 10, characterized in that: The projections of the two front edges of the electromagnetic film (1), the outer glass (2), the inner glass (3), the metal frame (4), the metal sinking frame (5), and the curved wave-transmitting fairing (6) on the horizontal plane are parallel to the projections of the left fuselage front edge (8) and the right fuselage front edge (9) on the horizontal plane.

12. The aircraft cabin windshield structure according to claim 11, characterized in that: The left fuselage front edge (8) and the right fuselage front edge (9) are symmetrically arranged in front of the fuselage and connected to the fuselage surface skin (7). After the connection, the gap is filled with a conductive sealant and polished to be smooth.

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