Airplane curved surface windshield

Abstract

The invention provides an airplane curved surface windshield which comprises composite laminated glass, and the composite laminated glass comprises a PET anti-splashing film layer, inner layer glass, a first PU film layer, an electromagnetic shielding film coating layer, middle layer glass, a second PU film layer, an electric heating ITO film coating layer, outer layer glass and an anti-static film coating layer which are sequentially arranged in a laminated mode. The two ends of the inner-layer glass, the first PU film layer, the electromagnetic shielding coating layer and the middle-layer glass are connected with an aramid fiber area through longitudinal PU film layers, and the aramid fiber area comprises a first aramid fiber reinforced phenolic resin area, a transverse PU film layer and a second aramid fiber reinforced phenolic resin area which are sequentially stacked; one side, far away from the inner-layer glass, of the PET anti-splashing film layer is connected with a third aramid fiber reinforced phenolic resin area through a two-component polysulfide waterproof sealant layer; the anti-static coating layer is connected with an aluminum frame through a conductive copper net, and the aluminum frame is connected with an airplane body aluminum frame through conductive rubber.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft windshields and relates to an aircraft curved windshield. Background Art

[0002] Aircraft windshields bear the aircraft's airtight load, aerodynamic load, bird strike load, as well as vibration, impact, fatigue load, etc., and can serve safely in any weather environment, provide pilots with a clear and good optical field of view, and ensure the safety of pilots in extreme situations where bird strikes occur. The reliability, safety, and durability of aircraft windshields depend on the structural design of the aircraft windshield and the corresponding materials and process technologies.

[0003] There are three main reasons for the failure of aircraft windshields: bird strikes damage the windshield; lightning strikes damage the windshield surface, and subsequent damage expands, leading to failure; as the windshield is extended in service, the sealing of the polyurethane (PU) film layer decreases due to erosion by wind and rain, and this process continues to develop: moisture enters the polyurethane layer, the glass and the polyurethane layer are partially separated, more moisture enters, corrosion occurs at the junction of the conductive busbar and the ITO film, and the conductive busbar peels off the glass surface. At this time, the windshield is powered on and heated, and arc discharge occurs at the junction of the conductive busbar and the ITO film, resulting in local overheating, which causes the outer glass to break. The third category is the most common reason for the failure of aircraft windshields.

[0004] CN111268090A discloses a fast-lifting and replaceable front windshield of an aircraft, comprising a windshield body, wherein the windshield body is mounted in a casing, wherein the upper and lower ends of the windshield body are respectively engaged in slots on the surface of the casing, wherein a sealing layer is fixedly provided in the slot, wherein the sealing layer is sealingly attached to the edge of the windshield body, wherein a first slot is provided inside the casing above the windshield body, and a second slot is provided inside the casing below the windshield body.

[0005] CN214688322U discloses an aircraft windshield with an organic silica gel waterproofing agent, which solves the problem that the windshield cannot quickly remove surface moisture, and comprises an outer layer and a heating layer bonded to the inner side of the outer layer, the inner side of the heating layer is bonded to the middle layer through an adhesive layer, the inner side of the middle layer is bonded to the inner layer through another adhesive layer, clamping mechanisms are arranged at the edges of the outer layer, the middle layer and the inner layer, waterproof structures are arranged at the edges of the adhesive layers between the outer layer and the middle layer and between the middle layer and the inner layer, and the outer side of the outer layer is covered with a waterproof layer formed by the organic silica gel waterproofing agent.

[0006] The aircraft windshield described in the above solution has single performance and low safety, which poses a potential safety hazard. Summary of the invention

[0007] The purpose of the present invention is to provide an aircraft curved windshield. The aircraft curved windshield of the present invention realizes the functions of anti-static, lightning protection, electromagnetic shielding, electric heating, and bird strike and splash protection of the aircraft windshield, thereby improving the safety, reliability and durability of the aircraft windshield.

[0008] In order to achieve the purpose of the invention, the present invention adopts the following technical solutions:

[0009] In a first aspect, the present invention provides an aircraft curved windshield, the aircraft curved windshield comprising a composite laminated glass, the composite laminated glass comprising a PET anti-splash film layer, an inner glass layer, a first PU film layer, an electromagnetic shielding coating layer, a middle glass layer, a second PU film layer, an electric heating ITO coating layer, an outer glass layer and an antistatic coating layer which are sequentially stacked;

[0010] The inner glass, the first PU film layer, the electromagnetic shielding coating layer and the two ends of the middle glass are connected to the aramid fiber area through the longitudinal PU film layer, and the aramid fiber area includes a first aramid fiber reinforced phenolic resin area, a transverse PU film layer and a second aramid fiber reinforced phenolic resin area which are stacked in sequence;

[0011] The side of the PET anti-splash film layer away from the inner glass is connected to the third aramid fiber reinforced phenolic resin area through a two-component polysulfide waterproof sealant layer;

[0012] The antistatic coating layer is connected to the aluminum frame through a conductive copper mesh, and the aluminum frame is connected to the aluminum frame of the aircraft fuselage through conductive rubber.

[0013] In the aircraft curved windshield described in the present invention, an antistatic coating layer is arranged on the outer surface of the outer layer of glass, the antistatic coating layer is connected to the aluminum frame through a conductive copper mesh, and the aluminum frame is connected to the aluminum frame of the aircraft fuselage through conductive rubber for conduction, so as to achieve antistatic and lightning protection functions; an electric heating ITO coating layer is arranged on the inner surface of the outer layer of glass, so as to achieve electric heating deicing and defogging; an electromagnetic shielding coating layer is arranged on the inner surface of the middle layer of glass, so as to achieve electromagnetic shielding function; a PET anti-splash film layer is bonded on the inner surface of the inner layer of glass, so as to achieve anti-bird collision and splashing function; an aramid fiber reinforced phenolic resin frame is coated around the glass, and the three layers of glass and the aramid fiber reinforced phenolic resin frame are bonded together by high-performance PU film at high temperature and high pressure to achieve glass edge sealing, and at the same time, serve as a connecting material between the windshield and the aircraft body.

[0014] Foreign aircraft windshields generally use glass fiber reinforced phenolic resin as the edge sealing material of the windshield and the connecting material with the aircraft body. The present invention uses aramid fiber reinforced phenolic resin material with better comprehensive performance. Aramid fiber is a high-performance material that can be used in bulletproof helmets. It has much higher impact resistance and fatigue resistance than glass fiber, and has high strength and high modulus: the tensile strength of aramid fiber is 6 times that of ordinary steel wire, the modulus is 2 to 3 times that of glass fiber, and the density is only 1.45g / mm 2 , the continuous use temperature range is -196℃~204℃, known as "bulletproof fiber", aramid fiber is inherently flame retardant and meets the flame retardancy requirements of aircraft materials. Using aramid fiber reinforced phenolic resin instead of glass fiber reinforced phenolic resin can significantly improve the overall impact resistance of aircraft windshields.

[0015] Preferably, the inner layer of glass, the middle layer of glass and the outer layer of glass are all made of chemically toughened inorganic silicate aviation glass.

[0016] Preferably, a Z-shaped stainless steel pressure frame is arranged on the side of the composite laminated glass close to the aluminum frame.

[0017] Preferably, the inner surfaces of the composite laminated glass, the Z-shaped stainless steel pressure frame and the aluminum frame are filled with a two-component polysulfide waterproof sealant.

[0018] The present invention uses a two-component polysulfide waterproof sealant to bond a Z-shaped stainless steel pressure frame around the outer periphery of the windshield to prevent water vapor in the air from penetrating into the PU film layer, and simultaneously uses the two-component polysulfide waterproof sealant to perform waterproof sealing treatment on the periphery of the windshield. The two-component polysulfide waterproof sealant is a high-performance glue specially used for aviation, and has excellent bonding strength with materials such as glass, phenolic resin, and PU. The temperature resistance range of the glue layer after curing is -54°C to +120°C, and it also has excellent weather resistance and UV resistance.

[0019] Preferably, a two-component polysulfide waterproof sealant is provided on the side of the aramid fiber area away from the composite laminated glass.

[0020] Preferably, the thickness of the two-component polysulfide waterproof sealant arranged on the side of the aramid fiber area away from the composite laminated glass is 1~2mm, for example: 1mm, 1.2mm, 1.5mm, 1.8mm or 2mm, etc., not limited to the listed values, and other unlisted values ​​within the numerical range are also applicable.

[0021] Preferably, the two-component polysulfide waterproof sealant filled on the inner surface of the composite laminated glass, the Z-shaped stainless steel pressure frame and the aluminum frame is integrally and sealedly connected with the two-component polysulfide waterproof sealant arranged on the side of the aramid fiber area away from the composite laminated glass.

[0022] Preferably, conductive rubber is provided on the side of the aluminum frame away from the composite laminated glass.

[0023] Preferably, the width of the aluminum frame is 55-60 mm, for example, 55 mm, 56 mm, 57 mm, 58 mm, 59 mm or 60 mm, etc., but is not limited to the listed values, and other unlisted values ​​within the numerical range are also applicable.

[0024] Preferably, the thickness of the aluminum frame is 6-7 mm, for example, 6 mm, 6.2 mm, 6.5 mm, 6.8 mm or 7 mm, etc., and is not limited to the listed values, and other values ​​not listed within the numerical range are also applicable.

[0025] Preferably, the first PU film layer, the longitudinal PU film layer and the transverse PU film layer are integrally arranged to form a cross-shaped PU film area.

[0026] Preferably, the cross-shaped PU adhesive area connects the inner layer of glass, the middle layer of glass, the first aramid fiber reinforced phenolic resin area, the second aramid fiber reinforced phenolic resin area and the PET anti-splash film layer.

[0027] Preferably, the thickness of the PET anti-splash film layer is 1-3 mm, for example, 1 mm, 1.5 mm, 2 mm, 2.5 mm or 3 mm, etc., and is not limited to the listed values, and other unlisted values ​​within the numerical range are also applicable.

[0028] The present invention adds a bird-impact splash-proof functional layer on the inner surface of an aircraft windshield, and uses high-performance PU to bond an optical-grade PET splash-proof film on the inner surface of the windshield, thereby realizing the splash-proof function of the windshield when a bird hits, and improving the safety of pilot protection.

[0029] Preferably, the thickness of the inner layer of glass is 5-10 mm, for example, 5 mm, 6 mm, 8 mm or 10 mm, etc., but is not limited to the listed values, and other values ​​not listed within the numerical range are also applicable.

[0030] Preferably, the thickness of the first PU film layer is 3-5 mm, for example, 3 mm, 4 mm or 5 mm, etc., and is not limited to the listed values, and other values ​​not listed within the numerical range are also applicable.

[0031] Preferably, the thickness of the middle layer of glass is 5-10 mm, for example, 5 mm, 6 mm, 8 mm or 10 mm, etc., but is not limited to the listed values, and other values ​​not listed within the numerical range are also applicable.

[0032] Preferably, the thickness of the second PU film layer is 3-5 mm, for example, 3 mm, 3.5 mm, 4 mm, 4.5 mm or 5 mm, etc., and is not limited to the listed values, and other values ​​not listed within the numerical range are also applicable.

[0033] Preferably, the thickness of the outer layer of glass is 3-5 mm, for example, 3 mm, 3.5 mm, 4 mm, 4.5 mm or 5 mm, etc., but is not limited to the listed values, and other values ​​not listed within the numerical range are also applicable.

[0034] Preferably, the electromagnetic shielding coating layer comprises an ITO conductive film and a shielding mesh, the ITO conductive film and the shielding mesh are connected by silver paste, and the ITO conductive film is close to one side of the middle glass.

[0035] The invention plates an ITO conductive film on the inner surface of the middle glass to obtain a block resistor with a certain resistance value, and then uses silver paste to bond a shielding net, which is then connected to an aluminum frame of an aircraft fuselage with conductive rubber to achieve an electromagnetic shielding function.

[0036] Preferably, the thickness of the electromagnetic shielding coating layer is 200nm~400nm, for example: 200nm, 250nm, 300nm, 350nm or 400nm, etc., but is not limited to the listed values, and other unlisted values ​​within the numerical range are also applicable.

[0037] Preferably, the material of the shielding mesh includes copper wire.

[0038] Preferably, the shielding net is connected to the aluminum frame of the aircraft fuselage through conductive rubber.

[0039] Preferably, the electrically heated ITO coating layer comprises an ITO conductive film and a bus bar arranged on the ITO conductive film.

[0040] According to the technical requirements of windshield electric heating power density, the present invention plates an ITO conductive film with a certain resistance value on the inner surface of the outer glass, and then arranges a bus bar composed of silver paste and tinned copper wire braided wire on the coating layer. The power supply and the temperature controller are connected through wires to achieve uniform and temperature-controlled electric heating of the windshield, thereby realizing the deicing and defogging functions of the windshield.

[0041] Preferably, the thickness of the electrically heated ITO coating layer is 300nm~350nm, for example: 300nm, 310nm, 320nm, 330nm, 340nm or 350nm, etc., not limited to the listed values, and other unlisted values ​​within the numerical range are also applicable.

[0042] Preferably, the busbar comprises silver paste and tinned copper wire braided wire.

[0043] Preferably, the electrically heated ITO coating layer is connected to a power source and a temperature controller via a wire.

[0044] Preferably, the material of the antistatic coating layer includes indium tin oxide.

[0045] Preferably, the thickness of the antistatic coating layer is 200nm~300nm, for example: 200nm, 220nm, 250nm, 280nm or 300nm, etc., not limited to the listed values, other unlisted values ​​within the numerical range are also applicable.

[0046] Preferably, the thickness of the first aramid fiber reinforced phenolic resin zone is the same as the thickness of the middle layer of glass.

[0047] Preferably, the thickness of the second aramid fiber reinforced phenolic resin zone is the same as the thickness of the inner layer of glass.

[0048] Preferably, the widths of the first aramid fiber reinforced phenolic resin zone and the second aramid fiber reinforced phenolic resin zone are independently 20-22 mm, for example, 20 mm, 20.5 mm, 21 mm, 21.5 mm or 22 mm, etc., not limited to the listed values, and other unlisted values ​​within the numerical range are also applicable.

[0049] Preferably, the thickness of the longitudinal PU film layer and the transverse PU film layer are both the same as the thickness of the first PU film layer.

[0050] Preferably, the thickness of the two-component polysulfide waterproof sealant layer is 2-4 mm, for example, 2 mm, 2.5 mm, 3 mm, 3.5 mm or 4 mm, etc., not limited to the listed values, and other unlisted values ​​within the numerical range are also applicable.

[0051] Preferably, the thickness of the third aramid fiber reinforced phenolic resin zone is 3-5 mm, for example, 3 mm, 3.5 mm, 4 mm, 4.5 mm or 5 mm, etc., and is not limited to the listed values, and other values ​​not listed within the numerical range are also applicable.

[0052] Preferably, the width of the third aramid fiber reinforced phenolic resin zone is 35-45 mm, for example, 35 mm, 38 mm, 40 mm, 42 mm or 45 mm, etc., and is not limited to the listed values, and other unlisted values ​​within the numerical range are also applicable.

[0053] Preferably, the third aramid fiber reinforced phenolic resin area is connected to the inner aluminum frame via a silicone rubber sealing gasket.

[0054] Preferably, the aircraft curved windshield further includes aviation bolts.

[0055] Preferably, the aviation bolts penetrate the aluminum frame, the two-component polysulfide waterproof sealant, the Z-shaped stainless steel pressure frame, the first aramid fiber reinforced phenolic resin area, the transverse PU film layer, the second aramid fiber reinforced phenolic resin area, the PET anti-splash film layer, the two-component polysulfide waterproof sealant layer, the third aramid fiber reinforced phenolic resin area, the silicone rubber sealing pad and the inner aluminum frame.

[0056] Compared with the prior art, the present invention has the following beneficial effects:

[0057] (1) The present invention adopts magnetron sputtering coating technology to prepare a hard, wear-resistant, anti-oxidation and weather-resistant antistatic coating layer on the outer surface of the windshield outer glass sheet, and then connects the antistatic coating layer to the aluminum frame of the windshield through a copper mesh, and the aluminum frame is connected to the aluminum frame of the aircraft fuselage through conductive rubber. In this way, the static charge on the outer surface of the windshield can be timely guided to the grounding spikes at the tip of the main wing or tail wing of the aircraft through the conductive path, that is, the "static discharger", and the static electricity is released into the atmosphere, reducing the probability of being struck by lightning. In the event that the windshield is struck by lightning, the above-mentioned conductive path and grounding spikes can also discharge the lightning current into the air, thereby realizing the functions of anti-static and lightning protection.

[0058] (2) The present invention uses a two-component polysulfide waterproof sealant to bond the Z-shaped stainless steel press frame around the outer periphery of the windshield to prevent water vapor in the air from penetrating into the PU film layer. At the same time, the two-component polysulfide waterproof sealant is used to waterproof and seal the periphery of the windshield, thereby significantly reducing the possibility of glass cracking caused by arc discharge caused by water vapor penetrating into the electric heating busbar, which is the most likely to occur in the above-mentioned aircraft windshield, thereby improving the durability and service life of the aircraft windshield.

[0059] (3) The present invention adds a bird-impact splash-proof functional layer on the inner surface of the aircraft windshield, and uses high-performance PU to bond an optical-grade PET splash-proof film on the inner surface of the windshield, thereby realizing the splash-proof function of the windshield when a bird hits, thereby improving the safety of pilot protection.

[0060] (4) The present invention plates an ITO conductive film on the inner surface of the middle glass to obtain a block resistor with a certain resistance value, and then uses silver paste to bond the shielding mesh, which is then connected to the aluminum frame of the aircraft fuselage with conductive rubber to achieve an electromagnetic shielding function.

[0061] (5) In accordance with the technical requirements for windshield electric heating power density, the present invention plates an ITO conductive film with a certain resistance value on the inner surface of the outer glass, and then arranges a bus bar composed of silver paste and tinned copper wire braided wire on the coating layer, and connects the power supply and temperature controller through wires to achieve uniform and temperature-controlled electric heating of the windshield, thereby realizing the deicing and defogging functions of the windshield. BRIEF DESCRIPTION OF THE DRAWINGS

[0062] Figure 1It is a schematic diagram of the cross-sectional structure of the aircraft curved windshield provided in an embodiment of the present invention.

[0063] Among them, 1 is a PET anti-splash film layer, 2 is an inner glass layer, 3 is a first PU film layer, 4 is an electromagnetic shielding coating layer, 5 is a middle glass layer, 6 is a second PU film layer, 7 is an electric heating ITO coating layer, 8 is an outer glass layer, 9 is an anti-static coating layer, 10 is a longitudinal PU film layer, 11 is a first aramid fiber reinforced phenolic resin area, 12 is a transverse PU film layer, 13 is a second aramid fiber reinforced phenolic resin area, 14 is a two-component polysulfide waterproof sealant layer, 15 is a third aramid fiber reinforced phenolic resin area, 16 is a conductive copper mesh, 17 is an aluminum frame, 18 is a Z-shaped stainless steel pressure frame, 19 is a two-component polysulfide waterproof sealant, 20 is a conductive rubber, 21 is an aviation bolt, 22 is a silicone rubber sealing gasket, and 23 is an inner aluminum frame. DETAILED DESCRIPTION

[0064] The technical solution of the present invention is further described below by specific implementation methods. It should be understood by those skilled in the art that the embodiments are only to help understand the present invention and should not be regarded as specific limitations of the present invention.

[0065] The inner layer glass, the middle layer glass and the outer layer glass described in the embodiment of the present invention are all made of chemically toughened inorganic silicate aviation glass.

[0066] The material model of the two-component polysulfide waterproof sealant layer and the two-component polysulfide waterproof sealant described in the embodiment of the present invention is PR-1425.

[0067] Example 1

[0068] This embodiment provides an aircraft curved windshield, the cross-sectional structure diagram of the aircraft curved windshield is as follows: Figure 1 As shown, the aircraft curved windshield includes a composite laminated glass, and the composite laminated glass includes a PET anti-splash film layer 1, an inner glass layer 2, a first PU film layer 3, an electromagnetic shielding coating layer 4, a middle glass layer 5, a second PU film layer 6, an electric heating ITO coating layer 7, an outer glass layer 8 and an antistatic coating layer 9 which are sequentially stacked;

[0069] The inner glass 2, the first PU film layer 3, the electromagnetic shielding coating layer 4 and the two ends of the middle glass 5 are connected to the aramid fiber area through the longitudinal PU film layer 10, and the aramid fiber area includes a first aramid fiber reinforced phenolic resin area 11, a transverse PU film layer 12 and a second aramid fiber reinforced phenolic resin area 13 which are stacked in sequence;

[0070] The side of the PET anti-splash film layer 1 away from the inner glass 2 is connected to the third aramid fiber reinforced phenolic resin area 15 through a two-component polysulfide waterproof sealant layer 14;

[0071] The antistatic coating layer 9 is connected to the aluminum frame 17 via a conductive copper mesh 16;

[0072] A Z-shaped stainless steel pressing frame 18 is arranged on the side of the composite laminated glass close to the aluminum frame 17, and a two-component polysulfide waterproof sealant 19 is filled on the inner surfaces of the composite laminated glass, the Z-shaped stainless steel pressing frame 18 and the aluminum frame 17, and a two-component polysulfide waterproof sealant 19 is arranged on the side of the aramid fiber area away from the composite laminated glass, and the composite laminated glass, the Z-shaped stainless steel pressing frame 18, and the two-component polysulfide waterproof sealant 19 filled on the inner surface of the aluminum frame 17 are integrally and sealedly connected with the two-component polysulfide waterproof sealant 19 arranged on the side of the aramid fiber area away from the composite laminated glass;

[0073] A conductive rubber 20 is disposed on the side of the aluminum frame 17 away from the composite laminated glass, the width of the aluminum frame 17 is 58 mm, and the thickness of the aluminum frame 17 is 6.5 mm;

[0074] The first PU film layer 3, the longitudinal PU film layer 10 and the transverse PU film layer 12 are integrally arranged to form a cross-shaped PU adhesive area, and the cross-shaped PU adhesive area connects the inner glass 2, the middle glass 5, the first aramid fiber reinforced phenolic resin area 11, the second aramid fiber reinforced phenolic resin area 13 and the PET anti-splash film layer 1;

[0075] The thickness of the PET anti-splash film layer 1 is 2 mm, the thickness of the inner glass 2 is 8 mm, the thickness of the first PU film layer 3 is 2.5 mm, the thickness of the middle glass 5 is 8 mm, the thickness of the second PU film layer 6 is 4 mm, and the thickness of the outer glass 8 is 4 mm.

[0076] The electromagnetic shielding coating layer 4 includes an ITO conductive film and a shielding mesh. The ITO conductive film and the shielding mesh are connected by silver paste. The ITO conductive film is close to the middle layer of glass. The thickness of the electromagnetic shielding coating layer 4 is 300nm. The material of the shielding mesh includes copper wire. The shielding mesh is connected to the aluminum frame of the aircraft fuselage through conductive rubber.

[0077] The electrically heated ITO coating layer 7 includes an ITO conductive film and a bus bar disposed on the ITO conductive film, the thickness of the electrically heated ITO coating layer is 320 nm, the bus bar includes silver paste and tinned copper braided wire, and the electrically heated ITO coating layer 7 is connected to a power source and a temperature controller through a wire;

[0078] The material of the antistatic coating layer 9 includes indium tin oxide, and the thickness of the antistatic coating layer 9 is 250nm;

[0079] The thickness of the first aramid fiber reinforced phenolic resin area 11 is the same as that of the middle glass 5, the thickness of the second aramid fiber reinforced phenolic resin area 13 is the same as that of the inner glass 2, and the widths of the first aramid fiber reinforced phenolic resin area 11 and the second aramid fiber reinforced phenolic resin area 13 are both 21 mm;

[0080] The thickness of the longitudinal PU film layer 10 and the transverse PU film layer 12 are the same as the thickness of the first PU film layer 3, which is 3 mm;

[0081] The thickness of the two-component polysulfide waterproof sealant layer 14 is 3 mm, the thickness of the third aramid fiber reinforced phenolic resin area 15 is 4 mm, the width of the third aramid fiber reinforced phenolic resin area 15 is 40 mm, the third aramid fiber reinforced phenolic resin area 15 is connected to the inner aluminum frame 23 through a silicone rubber sealing pad 22, and the aviation bolt 21 penetrates the aluminum frame 17, the two-component polysulfide waterproof sealant 19, the Z-shaped stainless steel pressing frame 18, the first aramid fiber reinforced phenolic resin area 11, the transverse PU film layer 12, the second aramid fiber reinforced phenolic resin area 13, the PET anti-splash film layer 1, the two-component polysulfide waterproof sealant layer 14, the third aramid fiber reinforced phenolic resin area 15, the silicone rubber sealing pad 22 and the inner aluminum frame 23.

[0082] Example 2

[0083] This embodiment provides an aircraft curved windshield, the cross-sectional structure diagram of the aircraft curved windshield is as follows: Figure 1 As shown, the aircraft curved windshield includes a composite laminated glass, and the composite laminated glass includes a PET anti-splash film layer 1, an inner glass layer 2, a first PU film layer 3, an electromagnetic shielding coating layer 4, a middle glass layer 5, a second PU film layer 6, an electric heating ITO coating layer 7, an outer glass layer 8 and an antistatic coating layer 9 which are sequentially stacked;

[0084] The inner glass 2, the first PU film layer 3, the electromagnetic shielding coating layer 4 and the two ends of the middle glass 5 are connected to the aramid fiber area through the longitudinal PU film layer 10, and the aramid fiber area includes a first aramid fiber reinforced phenolic resin area 11, a transverse PU film layer 12 and a second aramid fiber reinforced phenolic resin area 13 which are stacked in sequence;

[0085] The side of the PET anti-splash film layer 1 away from the inner glass 2 is connected to the third aramid fiber reinforced phenolic resin area 15 through a two-component polysulfide waterproof sealant layer 14;

[0086] The antistatic coating layer 9 is connected to the aluminum frame 17 via a conductive copper mesh 16;

[0087] A Z-shaped stainless steel pressing frame 18 is arranged on the side of the composite laminated glass close to the aluminum frame 17, and a two-component polysulfide waterproof sealant 19 is filled on the inner surfaces of the composite laminated glass, the Z-shaped stainless steel pressing frame 18 and the aluminum frame 17, and a two-component polysulfide waterproof sealant 19 is arranged on the side of the aramid fiber area away from the composite laminated glass, and the thickness of the two-component polysulfide waterproof sealant 19 arranged on the side of the aramid fiber area away from the composite laminated glass is 1 mm, and the two-component polysulfide waterproof sealant 19 filled on the inner surfaces of the composite laminated glass, the Z-shaped stainless steel pressing frame 18 and the aluminum frame 17 are integrally and sealedly connected with the two-component polysulfide waterproof sealant 19 arranged on the side of the aramid fiber area away from the composite laminated glass;

[0088] A conductive rubber 20 is disposed on the side of the aluminum frame 17 away from the composite laminated glass, the width of the aluminum frame 17 is 55 mm, and the thickness of the aluminum frame 17 is 6 mm;

[0089] The first PU film layer 3, the longitudinal PU film layer 10 and the transverse PU film layer 12 are integrally arranged to form a cross-shaped PU adhesive area, and the cross-shaped PU adhesive area connects the inner glass 2, the middle glass 5, the first aramid fiber reinforced phenolic resin area 11, the second aramid fiber reinforced phenolic resin area 13 and the PET anti-splash film layer 1;

[0090] The thickness of the PET anti-splash film layer 1 is 1 mm, the thickness of the inner glass 2 is 5 mm, the thickness of the first PU film layer 3 is 2 mm, the thickness of the middle glass 5 is 5 mm, the thickness of the second PU film layer 6 is 3 mm, and the thickness of the outer glass 8 is 3 mm.

[0091] The electromagnetic shielding coating layer 4 includes an ITO conductive film and a shielding mesh. The ITO conductive film and the shielding mesh are connected by silver paste. The ITO conductive film is close to the middle layer of glass. The thickness of the electromagnetic shielding coating layer 4 is 300nm. The material of the shielding mesh includes copper wire. The shielding mesh is connected to the aluminum frame of the aircraft fuselage through conductive rubber.

[0092] The electrically heated ITO coating layer 7 includes an ITO conductive film and a bus bar disposed on the ITO conductive film, the thickness of the electrically heated ITO coating layer is 320 nm, the bus bar includes silver paste and tinned copper braided wire, and the electrically heated ITO coating layer 7 is connected to a power source and a temperature controller through a wire;

[0093] The material of the antistatic coating layer 9 includes indium tin oxide, and the thickness of the antistatic coating layer 9 is 250 nm.

[0094] The thickness of the first aramid fiber reinforced phenolic resin area 11 is the same as that of the middle glass 5, the thickness of the second aramid fiber reinforced phenolic resin area 13 is the same as that of the inner glass 2, and the widths of the first aramid fiber reinforced phenolic resin area 11 and the second aramid fiber reinforced phenolic resin area 13 are both 20 mm;

[0095] The thickness of the longitudinal PU film layer 10 and the transverse PU film layer 12 are the same as the thickness of the first PU film layer 3, which is 2 mm;

[0096] The thickness of the two-component polysulfide waterproof sealant layer 14 is 3 mm, the thickness of the third aramid fiber reinforced phenolic resin area 15 is 3 mm, the width of the third aramid fiber reinforced phenolic resin area 15 is 35 mm, the third aramid fiber reinforced phenolic resin area 15 is connected to the inner aluminum frame 23 through a silicone rubber sealing pad 22, and the aviation bolt 21 penetrates the aluminum frame 17, the two-component polysulfide waterproof sealant 19, the Z-shaped stainless steel pressing frame 18, the first aramid fiber reinforced phenolic resin area 11, the transverse PU film layer 12, the second aramid fiber reinforced phenolic resin area 13, the PET anti-splash film layer 1, the two-component polysulfide waterproof sealant layer 14, the third aramid fiber reinforced phenolic resin area 15, the silicone rubber sealing pad 22 and the inner aluminum frame 23.

[0097] Example 3

[0098] This embodiment provides an aircraft curved windshield, the cross-sectional structure diagram of the aircraft curved windshield is as follows: Figure 1 As shown, the aircraft curved windshield includes a composite laminated glass, and the composite laminated glass includes a PET anti-splash film layer 1, an inner glass layer 2, a first PU film layer 3, an electromagnetic shielding coating layer 4, a middle glass layer 5, a second PU film layer 6, an electric heating ITO coating layer 7, an outer glass layer 8 and an antistatic coating layer 9 which are sequentially stacked;

[0099] The inner glass 2, the first PU film layer 3, the electromagnetic shielding coating layer 4 and the two ends of the middle glass 5 are connected to the aramid fiber area through the longitudinal PU film layer 10, and the aramid fiber area includes a first aramid fiber reinforced phenolic resin area 11, a transverse PU film layer 12 and a second aramid fiber reinforced phenolic resin area 13 which are stacked in sequence;

[0100] The side of the PET anti-splash film layer 1 away from the inner glass 2 is connected to the third aramid fiber reinforced phenolic resin area 15 through a two-component polysulfide waterproof sealant layer 14;

[0101] The antistatic coating layer 9 is connected to the aluminum frame 17 via a conductive copper mesh 16;

[0102] A Z-shaped stainless steel pressing frame 18 is arranged on the side of the composite laminated glass close to the aluminum frame 17, and a two-component polysulfide waterproof sealant 19 is filled on the inner surfaces of the composite laminated glass, the Z-shaped stainless steel pressing frame 18 and the aluminum frame 17, and a two-component polysulfide waterproof sealant 19 is arranged on the side of the aramid fiber area away from the composite laminated glass, and the thickness of the two-component polysulfide waterproof sealant 19 arranged on the side of the aramid fiber area away from the composite laminated glass is 2 mm, and the two-component polysulfide waterproof sealant 19 filled on the inner surfaces of the composite laminated glass, the Z-shaped stainless steel pressing frame 18 and the aluminum frame 17 are integrally and sealedly connected with the two-component polysulfide waterproof sealant 19 arranged on the side of the aramid fiber area away from the composite laminated glass;

[0103] A conductive rubber 20 is disposed on the side of the aluminum frame 17 away from the composite laminated glass, the width of the aluminum frame 17 is 60 mm, and the thickness of the aluminum frame 17 is 7 mm;

[0104] The first PU film layer 3, the longitudinal PU film layer 10 and the transverse PU film layer 12 are integrally arranged to form a cross-shaped PU adhesive area, and the cross-shaped PU adhesive area connects the inner glass 2, the middle glass 5, the first aramid fiber reinforced phenolic resin area 11, the second aramid fiber reinforced phenolic resin area 13 and the PET anti-splash film layer 1;

[0105] The thickness of the PET anti-splash film layer 1 is 3 mm, the thickness of the inner glass 2 is 10 mm, the thickness of the first PU film layer 3 is 4 mm, the thickness of the middle glass 5 is 10 mm, the thickness of the second PU film layer 6 is 5 mm, and the thickness of the outer glass 8 is 5 mm.

[0106] The electromagnetic shielding coating layer 4 includes an ITO conductive film and a shielding mesh. The ITO conductive film and the shielding mesh are connected by silver paste. The ITO conductive film is close to the middle layer of glass. The thickness of the electromagnetic shielding coating layer 4 is 300nm. The material of the shielding mesh includes copper wire. The shielding mesh is connected to the aluminum frame of the aircraft fuselage through conductive rubber.

[0107] The electrically heated ITO coating layer 7 includes an ITO conductive film and a bus bar disposed on the ITO conductive film, the thickness of the electrically heated ITO coating layer is 320 nm, the bus bar includes silver paste and tinned copper braided wire, and the electrically heated ITO coating layer 7 is connected to a power source and a temperature controller through a wire;

[0108] The material of the antistatic coating layer 9 includes indium tin oxide, and the thickness of the antistatic coating layer 9 is 250nm;

[0109] The thickness of the first aramid fiber reinforced phenolic resin area 11 is the same as that of the middle glass 5, the thickness of the second aramid fiber reinforced phenolic resin area 13 is the same as that of the inner glass 2, and the widths of the first aramid fiber reinforced phenolic resin area 11 and the second aramid fiber reinforced phenolic resin area 13 are both 22 mm;

[0110] The thickness of the longitudinal PU film layer 10 and the transverse PU film layer 12 are the same as the thickness of the first PU film layer 3, which is 4 mm;

[0111] The thickness of the two-component polysulfide waterproof sealant layer 14 is 4 mm, the thickness of the third aramid fiber reinforced phenolic resin area 15 is 5 mm, the width of the third aramid fiber reinforced phenolic resin area 15 is 45 mm, the third aramid fiber reinforced phenolic resin area 15 is connected to the inner aluminum frame 23 through a silicone rubber sealing pad 22, and the aviation bolt 21 penetrates the aluminum frame 17, the two-component polysulfide waterproof sealant 19, the Z-shaped stainless steel pressing frame 18, the first aramid fiber reinforced phenolic resin area 11, the transverse PU film layer 12, the second aramid fiber reinforced phenolic resin area 13, the PET anti-splash film layer 1, the two-component polysulfide waterproof sealant layer 14, the third aramid fiber reinforced phenolic resin area 15, the silicone rubber sealing pad 22 and the inner aluminum frame 23.

[0112] Aiming at the main failure modes of aircraft windshields, the present invention develops an aircraft windshield with anti-static, lightning protection, electromagnetic shielding, electric heating, and bird strike and splash protection functions, thereby improving the safety, reliability, and durability of the aircraft windshield.

[0113] The applicant declares that the above is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Those skilled in the art should understand that any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention shall fall within the protection scope and disclosure scope of the present invention.

Claims

1. An aircraft curved windshield, characterized in that: The aircraft curved windshield comprises a composite laminated glass, which comprises a PET anti-splash film layer, an inner glass layer, a first PU film layer, an electromagnetic shielding coating layer, a middle glass layer, a second PU film layer, an electric heating ITO coating layer, an outer glass layer and an antistatic coating layer which are stacked in sequence; The inner glass, the first PU film layer, the electromagnetic shielding coating layer and the two ends of the middle glass are connected to the aramid fiber area through the longitudinal PU film layer, and the aramid fiber area includes a first aramid fiber reinforced phenolic resin area, a transverse PU film layer and a second aramid fiber reinforced phenolic resin area which are stacked in sequence; The side of the PET anti-splash film layer away from the inner glass is connected to the third aramid fiber reinforced phenolic resin area through a two-component polysulfide waterproof sealant layer; The antistatic coating layer is connected to the aluminum frame through a conductive copper mesh, and the aluminum frame is connected to the aluminum frame of the aircraft fuselage through conductive rubber.

2. The aircraft curved windshield according to claim 1, characterized in that: A Z-shaped stainless steel pressing frame is arranged on the side of the composite laminated glass close to the aluminum frame; The inner surfaces of the composite laminated glass, the Z-shaped stainless steel press frame and the aluminum frame are filled with a two-component polysulfide waterproof sealant; A two-component polysulfide waterproof sealant is provided on the side of the aramid fiber area away from the composite laminated glass; The thickness of the two-component polysulfide waterproof sealant on the side of the aramid fiber area away from the composite laminated glass is 1-2 mm; The two-component polysulfide waterproof sealant filled on the inner surface of the composite laminated glass, the Z-shaped stainless steel pressure frame and the aluminum frame is integrally and sealedly connected with the two-component polysulfide waterproof sealant arranged on the side of the aramid fiber area away from the composite laminated glass.

3. The aircraft curved windshield according to claim 1, characterized in that: Conductive rubber is arranged on the side of the aluminum frame away from the composite laminated glass; The width of the aluminum frame is 55-60 mm; The thickness of the aluminum frame is 6-7 mm.

4. The aircraft curved windshield according to claim 1, characterized in that: The first PU film layer, the longitudinal PU film layer and the transverse PU film layer are integrally arranged to form a cross-shaped PU film area; The cross-shaped PU adhesive area connects the inner layer glass, the middle layer glass, the first aramid fiber reinforced phenolic resin area, the second aramid fiber reinforced phenolic resin area and the PET anti-splash film layer.

5. The aircraft curved windshield according to claim 1, characterized in that: The thickness of the PET anti-splash film layer is 1-3 mm; The thickness of the inner glass is 5-10 mm; The thickness of the first PU film layer is 2-4 mm; The thickness of the middle layer of glass is 5-10 mm; The thickness of the second PU film layer is 3-5 mm; The thickness of the outer layer of glass is 3-5 mm.

6. The aircraft curved windshield according to claim 1, characterized in that: The electromagnetic shielding coating layer includes an ITO conductive film and a shielding net, wherein the ITO conductive film and the shielding net are connected by silver paste, and the ITO conductive film is close to one side of the middle glass; The thickness of the electromagnetic shielding coating layer is 200-400nm; The material of the shielding net includes copper wire; The shielding mesh is connected to the aluminum frame of the aircraft fuselage via conductive rubber.

7. The aircraft curved windshield according to claim 1, characterized in that: The electrically heated ITO coating layer comprises an ITO conductive film and a bus bar arranged on the ITO conductive film; The thickness of the electrically heated ITO coating layer is 300-350nm; The busbar comprises silver paste and tinned copper wire braid; The electrically heated ITO coating layer is connected to a power source and a temperature controller via a wire.

8. The aircraft curved windshield according to claim 1, characterized in that: The material of the antistatic coating layer includes indium tin oxide; The thickness of the antistatic coating layer is 200-300 nm.

9. The aircraft curved windshield according to claim 1, characterized in that: The thickness of the first aramid fiber reinforced phenolic resin zone is the same as the thickness of the middle glass; The thickness of the second aramid fiber reinforced phenolic resin zone is the same as the thickness of the inner glass layer; The widths of the first aramid fiber reinforced phenolic resin region and the second aramid fiber reinforced phenolic resin region are independently 20 to 22 mm; The thickness of the longitudinal PU film layer and the transverse PU film layer are both the same as the thickness of the first PU film layer.

10. The aircraft curved windshield according to claim 1, characterized in that: The thickness of the two-component polysulfide waterproof sealant layer is 2-4 mm; The thickness of the third aramid fiber reinforced phenolic resin zone is 3-5 mm; The width of the third aramid fiber reinforced phenolic resin zone is 35-45 mm; The third aramid fiber reinforced phenolic resin area is connected to the inner aluminum frame via a silicone rubber sealing pad; The aircraft curved windshield also includes aviation bolts; The aviation bolts penetrate the aluminum frame, the two-component polysulfide waterproof sealant, the Z-shaped stainless steel pressure frame, the first aramid fiber reinforced phenolic resin area, the transverse PU film layer, the second aramid fiber reinforced phenolic resin area, the PET anti-splash film layer, the two-component polysulfide waterproof sealant layer, the third aramid fiber reinforced phenolic resin area, the silicone rubber sealing pad and the inner aluminum frame.

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