CN112061371A - Aircraft windshield - Google Patents
Aircraft windshield Download PDFInfo
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- CN112061371A CN112061371A CN202010877712.7A CN202010877712A CN112061371A CN 112061371 A CN112061371 A CN 112061371A CN 202010877712 A CN202010877712 A CN 202010877712A CN 112061371 A CN112061371 A CN 112061371A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
- B64C1/1492—Structure and mounting of the transparent elements in the window or windscreen
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Abstract
The embodiment of the invention provides an aircraft windshield glass, which comprises a transparent composite plate element and an edge connecting piece, wherein the edge connecting piece is arranged outside the edge of the transparent composite plate element and covers the areas of two outer surfaces of the transparent composite plate element close to the edge; the transparent composite plate element comprises at least two first transparent layers, at least one second transparent layer and at least two annular reinforcing layers; a second transparent layer is bonded between two adjacent first transparent layers, and an annular reinforcing layer is bonded to each of two surface regions of at least one of the first transparent layers near the edges. When the first transparent layer is broken, the fragments of the first transparent layer positioned in the middle area are adhered to the second transparent layer, and the fragments of the first transparent layer positioned in the edge area can be fixed and protected through the annular reinforcing layer, so that the integrity of the airplane windshield glass is kept, the time for the airplane windshield glass to be stripped is further delayed, and sufficient time is provided for the airplane to reduce the height, reduce the cabin pressure and prepare for landing in an emergency.
Description
Technical Field
The embodiment of the invention relates to the technical field of aircrafts, in particular to an aircraft windshield.
Background
Aircraft windscreens employ a fail-safe design having multiple layers of transparent sheets and organic transparencies. In the flying process, the windshield glass of the airplane bears the internal and external pressure difference, and has a certain deformation degree. If one layer of transparent sheet breaks, it will fragment into many small fragments under the action of pressure differential, but the organic transparent film can connect the fragments together, and the aircraft windshield will still be safe as long as the remaining transparent sheet remains intact.
However, when the transparent sheet of an aircraft windshield is completely broken, it is initially pressed together by the volume increment created by the crack, and then the integrity of the windshield can only be maintained by the adhesive action of the organic clear film. And the inside and the outside of the cabin of the airplane have larger air pressure difference, under the action of the pressure difference, the windshield glass of the airplane losing the integral rigidity can rapidly bulge outwards and continuously deform, the area of the organic transparent film is continuously increased, and the thickness is thinned. Along with the organic transparent film continuously pulls the outside of the transparent plate close to the edge, fragments of the transparent plate are gradually pulled away, the structure is gradually loosened, the clamping force of the pressing plate on the periphery of the airplane windshield glass is continuously reduced, the airplane windshield glass can be integrally pulled out from the edge connection part through the expansive force, the airplane windshield glass is separated from the frame and flies out of the window, and major safety accidents are caused.
Disclosure of Invention
In view of the above, an object of the present invention is to provide an aircraft windshield, so as to overcome the problem of poor safety performance of the prior art.
The embodiment of the invention provides an aircraft windshield glass, which comprises a transparent composite plate element and an edge connecting piece, wherein the edge connecting piece is arranged outside the edge of the transparent composite plate element and covers the areas of two outer surfaces of the transparent composite plate element close to the edge; the transparent composite plate element comprises at least two first transparent layers, at least one second transparent layer and at least two annular reinforcing layers; a second transparent layer is bonded between two adjacent first transparent layers, and an annular reinforcing layer is bonded to each of two surface regions of at least one of the first transparent layers near the edges.
Optionally, in a specific embodiment of the present invention, an annular reinforcing layer is bonded to each of two surface regions of the entire first transparent layer near the edge.
Optionally, in a specific embodiment of the present invention, the thickness of the annular stiffening layer is less than the thickness of the second transparent layer adjacent to the annular stiffening layer.
Optionally, in a specific embodiment of the present invention, the thickness of each of the at least two annular reinforcing layers is greater than or equal to 0.5mm and less than or equal to 3 mm.
Optionally, in a specific embodiment of the present invention, the annular reinforcing layer is a closed loop.
Optionally, in a specific embodiment of the present invention, the annular reinforcing layer is adapted to the shape of the two surfaces to which the first transparent layer is bonded.
Optionally, in a specific embodiment of the present invention, the material of the annular reinforcing layer is one of stainless steel, aluminum alloy, glass fiber board, polyester fiber board, carbon fiber board, organic glass, and polycarbonate board.
Alternatively, in a specific embodiment of the present invention, when the material of the annular reinforcing layer is a non-transparent material, the maximum width of the annular reinforcing layer is not more than 100 mm.
Alternatively, in a specific embodiment of the present invention, the edge of the annular reinforcing layer does not exceed the edge of the edge connector on the side toward the central region of the first transparent layer.
Optionally, in a specific embodiment of the present invention, the transparent composite plate member further comprises a third transparent layer, and a third transparent layer and a first transparent layer are respectively bonded to both surfaces of a second transparent layer.
In view of the above, embodiments of the present invention provide a transparent composite plate element for an aircraft windshield, wherein a second transparent layer is bonded between two adjacent first transparent layers, and an annular reinforcing layer is bonded to each of two surface regions of the first transparent layers near the edges. Therefore, when the first transparent layer is broken, the fragments of the first transparent layer positioned in the middle area are adhered to the second transparent layer, and the fragments of the first transparent layer positioned in the edge area can be fixed and protected through the annular reinforcing layer, so that the integrity of the airplane windshield glass is maintained, the time for the airplane windshield glass to be stripped is further delayed, and sufficient time is provided for the airplane to reduce the height, reduce the cabin pressure and prepare for landing in an emergency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the embodiments of the present invention, and it is also possible for a person skilled in the art to obtain other drawings based on the drawings.
FIG. 1 is a schematic view of an aircraft windshield according to an embodiment of the present disclosure;
FIG. 2 is a schematic structural view of a windshield of an aircraft according to a second embodiment of the present application;
FIG. 3 is a schematic structural view of a first aircraft windshield according to a third embodiment of the present application;
fig. 4 is a schematic structural view of a second aircraft windshield according to a third embodiment of the present application.
Detailed Description
Of course, it is not necessary for any particular embodiment of the invention to achieve all of the above advantages at the same time.
In order to make those skilled in the art better understand the technical solutions in the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments obtained by a person skilled in the art based on the embodiments of the present invention shall fall within the scope of the protection of the embodiments of the present invention.
The following further describes specific implementation of the embodiments of the present invention with reference to the drawings.
Example one
An aircraft windscreen, as shown in fig. 1, in this embodiment comprising a transparent composite plate element 100 and an edge connector 200, wherein the edge connector 200 is mounted outside the edges of the transparent composite plate element 100 and covers the areas of the two outer surfaces of the transparent composite plate element 100 near the edges. Transparent composite plate element 100 includes at least two first transparent layers 101, at least one second transparent layer 102, and at least two annular reinforcing layers 103. A second transparent layer 102 is adhered between two adjacent first transparent layers 101, and an annular reinforcing layer 103 is adhered to each of two surface areas of at least one of the first transparent layers 101 near the edges.
In this embodiment, the edge connector 200 is mounted outside the edge of the transparent composite panel element 100 and is fixedly connected to the support window frame 300 of the aircraft cabin, thereby achieving a fixed mounting and moisture sealing of the aircraft windshield.
In this embodiment, transparent composite panel element 100 has a high light transmission, which provides the pilot with an adequate field of view. Moreover, the transparent composite plate element 100 is a composite layer structure composed of the first transparent layer 101, the second transparent layer 102, the annular reinforcing layer 103 and the like, so that the transparent composite plate element 100 has high structural strength to isolate the internal and external environments of the cabin, and has good safety breakage performance to ensure that the aircraft windshield glass cannot be catastrophically damaged when an accident occurs.
In this embodiment, the first transparent layer 101 is a structural load-bearing layer of an aircraft windshield, and is used for bearing cabin pressure, aerodynamic loads, structural loads, and the like.
Alternatively, as shown in fig. 1, a transparent composite plate element 100 includes two first transparent layers 101, the two first transparent layers 101 being bonded together by a second transparent layer 102 to form a composite layer structure having redundancy. When one of the first transparent layers 101 is broken, the remaining first transparent layers 101 can also carry the loads to which the aircraft windshield is subjected without catastrophic failure, thereby improving the structural strength and fail-safe performance of the transparent composite plate element 100.
Alternatively, in order to make the first transparent layer 101 have higher strength, the first transparent layer 101 may be tempered glass. Preferably, the material of the first transparent layer 101 may be at least one of inorganic silicate glass, inorganic aluminosilicate glass, organic glass, and polycarbonate plate.
Optionally, an annular reinforcing layer 103 is bonded to each of the two surface regions of the first transparent layers 101 adjacent to the edge, so that each of the first transparent layers 101 is protected by the annular reinforcing layer 103 to further improve the structural strength of the aircraft windshield edge joint.
In this embodiment, the second transparent layer 102 is used to adhere other transparent layers adjacent thereto. When the first transparent layer 101 is broken, the second transparent layer 102 can bond the fragments of the first transparent layer 101 in situ to maintain the integrity of the transparent composite plate element 100, prevent accidents such as air leakage and frame dropping of the aircraft windshield glass, and improve the failure safety performance of the aircraft windshield glass.
Optionally, in order to improve the adhesive property and the structural strength of the second transparent layer 102, the material of the second transparent layer 102 is polyvinyl butyral PVB or polyurethane PU.
In this embodiment, one surface of the annular reinforcing layer 103 is bonded to two surface regions of the first transparent layer 101 near the edge, and the other surface is bonded to the second transparent layer 102, so that the edge of the first transparent layer 101 is protected by blocking the pulling force of the second transparent layer 102 to the edge of the first transparent layer 101. And, two layers of reinforcement rings are provided to wrap the composite layer structure composed of the first transparent layer 101 and the second transparent layer 102, and further to be fixedly connected with the edge connector 200, thereby improving the connection strength of the transparent composite plate element 100 and the edge connector 200.
For example, when the first transparent layer 101 is broken, the two annular reinforcing layers 103 can clamp the first transparent layer 101 therebetween and block the pulling force of the second transparent layer 102 on the edge region of the first transparent layer 101, so that fragments of the edge region of the first transparent layer 101 do not scatter to maintain the integrity of the first transparent layer 101 for a certain period of time to delay the unfreezing of the aircraft windshield. A large number of tests prove that under the conditions that the aircraft windshield is broken in all the first transparent layers 101 and the pressure difference between the inside and the outside of the cabin is 60kPa, the aircraft windshield is kept for at least 10 minutes without being detached from the frame, so that the height of the aircraft is reduced, the cabin pressure is reduced, the time is provided for emergency landing, and the failure safety performance of the aircraft windshield is improved.
Optionally, the thickness of the annular reinforcing layer 103 is smaller than the thickness of the second transparent layer 102 adjacent to the annular reinforcing layer 103. Thereby, both sides of the second transparent layer 102 are brought into sufficient contact with both the first transparent layers 101 at the same time, increasing the area of the bonding area between the first and second transparent layers 101, 102, so that the bonding between the first and second transparent layers 101, 102 is stronger, thereby improving the structural strength of the transparent composite plate element 100.
Optionally, after a large number of tests, the thicknesses of the at least two annular reinforcing layers 103 are both greater than or equal to 0.5mm and less than or equal to 3mm, which can improve the structural strength of the annular reinforcing layers 103.
Optionally, the thickness of the annular reinforcing layer 103 is greater than or equal to 0.5mm and less than or equal to 1mm, so that the weight of the annular reinforcing layer 103 can be reduced while maintaining the structural strength of the annular reinforcing layer 103.
Optionally, at least two annular reinforcing layers 103 have the same thickness, so as to facilitate industrial production and practical application of the annular reinforcing layers 103.
Optionally, the thickness of at least two annular stiffening layers 103 is different, so that the thickness of the annular stiffening layers 103 at different positions can be designed according to the actual requirements of the transparent composite plate element 100.
For example, the annular reinforcing layer 103 located at the outermost side in the transparent composite plate member 100 may be fixedly coupled to the edge connector 200, so that the annular reinforcing layer 103 can bear stronger force by appropriately increasing the thickness of the annular reinforcing layer 103, thereby further enhancing the fixed coupling between the transparent composite plate member 100 and the edge connector 200.
Optionally, the annular reinforcing layer 103 is a closed ring to improve the structural strength of the annular reinforcing layer 103.
Optionally, the annular reinforcing layer 103 is an annular formed by splicing segments, so that the annular reinforcing layer 103 can be produced, processed, installed and used conveniently.
Optionally, the shape of the two surfaces of the annular reinforcing layer 103 bonded to the first transparent layer 101 is adapted to increase the area of the bonding region between the annular reinforcing layer 103 and the first transparent layer 101 and reduce the gap therebetween, thereby improving the structural strength of the transparent composite layer element.
For example, when the surface of the first transparent layer 101 is a planar glass, the surface of the annular reinforcement layer 103 may be a plane such that the first transparent layer 101 is attached to the annular reinforcement layer 103. Alternatively, when the surface of the first transparent layer 101 is a curved surface, the surface of the annular reinforcing layer 103 may be a curved surface, and the curvature of the surface of the annular reinforcing layer 103 coincides with the curvature of the surface of the first transparent layer 101 to which it is bonded.
Optionally, in order to improve the strength of the annular reinforcing layer 103, the annular reinforcing layer 103 is made of one of stainless steel, aluminum alloy, a glass fiber plate, a polyester fiber plate, a carbon fiber plate, organic glass, and a polycarbonate plate.
The polyester fiber plate or the glass fiber has the characteristics of high strength and light weight, and the annular reinforcing layer 103 can be manufactured to improve the structural strength and reduce the weight of the annular reinforcing layer 103, so the polyester fiber plate or the glass fiber is preferably selected as the material of the annular reinforcing layer 103.
Optionally, when the material of the annular reinforcing layer 103 is a non-transparent material, the maximum width of the annular reinforcing layer 103 is not greater than 100 mm. This prevents the annular reinforcing layer 103 from obstructing the light transmitting area of the transparent composite panel element 100, which would allow the pilot an adequate field of view when the aircraft windscreen is mounted on the upper supporting window frame 300 of the aircraft cabin.
Alternatively, the edge of the annular reinforcing layer 103 does not exceed the edge of the edge connector 200 at a side toward the central region of the first transparent layer 101. Thereby, the area of the bonding between the first and second transparent layers 101 and 102 is increased to further improve the bonding strength between the first and second transparent layers 101 and 102.
Optionally, the transparent composite plate element 100 further comprises a third transparent layer 104, and two surfaces of a second transparent layer 102 are respectively connected to the third transparent layer 104 and the first transparent layer 101.
Due to the fact that the temperature of the high altitude is low, when the aircraft flies at high altitude, the windshield glass of the aircraft can be frozen, and therefore the visibility of the visual field of a pilot is reduced. Therefore, in order to solve the problem of icing of the aircraft windshield, the third transparent layer 104 may be an electrical heating functional layer, and the ice layer attached to the aircraft windshield is melted by electrical heating, so as to improve the visibility of the pilot.
For example, as shown in fig. 1, in the middle region of the transparent composite plate element 100, there are five layers of composite layer structure, which are, in order from top to bottom, a third transparent layer 104, a second transparent layer 102, a first transparent layer 101, a second transparent layer 102, and a first transparent layer 101. Wherein the two first transparent layers 101 are bonded together by the second transparent layer 102 to form a composite layer structure for bearing loads experienced by the aircraft windshield. The third transparent layer 104, which is a functional layer for electrically heating the aircraft, is bonded to the first transparent layer 101 by a second transparent layer 102. When the aircraft windscreen is mounted to the supporting window frame 300 of an aircraft, the third transparent layer 104 faces the outside of the aircraft and the two first transparent layers 101 face the inside of the aircraft.
In the edge region of the transparent composite plate element 100, the edge of the first transparent plate protrudes beyond the edge of the third transparent plate. So as to exert a force on the first transparent plate of the protruding portion to fix the transparent composite plate element 100. And, an annular reinforcing layer 103 is adhered to edge regions of both surfaces of each of the first transparent layers 101. When the annular reinforcing layer 103 is positioned between the two first transparent layers 101, both surfaces thereof are adhered to the first and second transparent layers 101 and 102, respectively. When the annular reinforcing layer 103 is located outside the first transparent layer 101, one surface thereof is adhered to the first transparent layer 101 and the edge connector 200, respectively. Thus, in the edge region of the transparent composite plate element 100, the annular reinforcing layer 103 blocks the second transparent layer 102 and the edge connector 200 to block the force of the second transparent layer 102 and the edge connector 200 from directly acting on the first transparent layer 101, thereby protecting the first transparent layer 101.
The edge connector 200 is installed outside the edge of the transparent composite plate member 100, the inner side of the edge connector 200 is adhered to the outer surface of the annular reinforcing layer 103 outside the two first transparent layers 101, and the edge connector 200 also covers a portion of the outer surface of the third transparent layer 104 near the edge to protect and fix the outer surface of the third transparent layer 104.
One surface of the edge connector 200 facing the outside of the cabin is provided with a half groove for easy mounting and fixing. When the edge connector 200 is pressed against the support window frame 300 of the airplane by the pressing plate, the fixing pressing plate may be engaged in the half groove, thereby fixing the position of the edge connector 200. One surface of the edge connector 200 facing the interior of the chamber is provided with a sealing groove. The sealing groove is closely attached to the surface of the support window frame 300, and thus, the moisture seal between the support window frame 300 and the windshield of the aircraft can be realized.
In the transparent composite plate element 100 of an aircraft windshield according to the present embodiment of the invention, a second transparent layer 102 is bonded between two adjacent first transparent layers 101, and an annular reinforcing layer 103 is bonded to each of two surface regions of the first transparent layers 101 near the edges. Therefore, when the first transparent layer 101 is broken, the fragments of the first transparent layer 101 in the middle area are adhered to the second transparent layer 102, and the fragments of the first transparent layer 101 in the edge area can be fixed and protected by the annular reinforcing layer 103, so that the integrity of the airplane windshield glass is maintained, the time for the airplane windshield glass to be unframed is delayed, and sufficient time is provided for the airplane to reduce the height, the cabin pressure and the emergency landing.
Example two
As shown in fig. 2, an aircraft windscreen in this embodiment comprises a transparent composite plate element 100 and an edge connector 200, wherein the transparent composite plate element 100 comprises at least two first transparent layers 101, at least one second transparent layer 102, one third transparent layer 104 and at least two annular reinforcing layers 103. A second transparent layer 102 is adhered between two adjacent first transparent layers 101, and an annular reinforcing layer 103 is adhered to each of two surface areas of at least one of the first transparent layers 101 near the edges. One surface of a first transparent layer 101 is a first outer surface of transparent composite plate element 100. A third transparent layer 104 and a first transparent layer 101 are respectively adhered to both surfaces of a second transparent layer 102, one surface of the third transparent layer 104 being the second outer surface of the transparent composite plate element 100. The edge connector 200 includes a pressing plate 201 and a sealing member 202, the pressing plate 201 is mounted inside the sealing member 202, one end is press-fitted to a surface of one of the annular reinforcing layers 103, and the other end is press-fitted to an edge region of the second outer surface. A seal 202 is mounted outside the edges of transparent composite plate element 100 covering the areas of the first and second outer surfaces near the edges.
In this embodiment, please refer to the related contents in the first embodiment for the detailed description of the transparent composite plate element 100, the first transparent layer 101, the second transparent layer 102, and the annular reinforcing layer 103.
Optionally, the number of the first transparent layers 101 and the second transparent layers 102 is two; the thickness of the first transparent layer 101 is 10 mm; the thickness of the third transparent layer 104 is 3 mm; one second transparent layer 102 located between the third transparent layer 104 and one first transparent layer 101 has a thickness of 5mm, and one second transparent layer 102 located between two first transparent layers 101 has a thickness of 1.25 mm.
Here, by providing two first transparent layers 101, a composite layer structure having redundancy is formed. And the thickness of the first transparent layer 101 is increased, the structural strength of the single-layer first transparent layer 101 is improved, and further the structural strength of the aircraft windshield is improved. This provides aircraft windshields with greater fail-safe performance while reducing the difficulty of producing the transparent composite sheet element 100.
Optionally, the number of the first transparent layers 101 and the number of the second transparent layers 102 are three; the two first transparent layers 101 in the middle are both 8mm thick, and the thickness of one first transparent layer 101 including the first outer surface is 5 mm; the thickness of the third transparent layer 104 is 3 mm; one second transparent layer 102 located between the third transparent layer 104 and one first transparent layer 101 has a thickness of 5mm, and one second transparent layer 102 located between the two first transparent layers 101 has a thickness of 1.88 mm.
Wherein, through setting up three first transparent layer 101, further increased aircraft windshield's redundancy, improved aircraft windshield's fail safe performance. Also, by reducing the thickness of the first transparent layer 101, the thickness and weight of the aircraft windshield is reduced to meet aircraft design requirements.
In this embodiment, the second transparent layer 102, the third transparent layer 104 and the annular reinforcing layer 103 are described in detail in the first embodiment.
In this embodiment, the edge connector 200 is mounted outside the edge of the transparent composite panel element 100, and the transparent composite panel element 100 may be fixed to a support window frame 300 of an aircraft cabin. The edge connector 200 includes a pressure plate 201 and a seal 202, the pressure plate 201 and the seal 202 cooperating to provide a secure mounting and moisture seal for the aircraft windshield.
Wherein the pressing plate 201 is mounted inside the sealing member 202 with one end pressed against a surface of one of the annular reinforcing layers 103 and the other end pressed against an edge region of the second outer surface, thereby pressing the third transparent layer 104 under the pressing plate 201, preventing the third transparent layer 104 from being detached from the aircraft windshield, and improving the integrity and structural strength of the aircraft windshield.
Wherein a seal 202 is mounted outside the edges of the transparent sheet element and covers the areas of the first and second outer surfaces near the edges, and wherein upon securing the aircraft windscreen in the support window by means of bolts 204 through the perforated metal sheet, the perforated metal sheet presses the seal 202 from a direction towards the second outer surface of the transparent composite sheet element 100, causing the seal 202 to deform and abut against the support window frame 300, thereby achieving a moisture tight seal between the aircraft windscreen and the support window frame 300. In addition, the elastic force generated by the deformation of the sealing element 202 is used as a pre-tightening force, so that the position of the airplane windshield glass can be fixed, and the airplane windshield glass is firmly installed.
Optionally, a plurality of sealing grooves are formed on the contact surface of the sealing member 202 and the support window frame 300. When an aircraft windshield is installed on an aircraft, the plurality of seal grooves on seal 202 contact the support window of the aircraft. When the windshield is fixed in the support window by using the bolt 204 to penetrate through the perforated metal plate, the sealing element 202 is pressed to elastically deform the sealing groove, so that the gap between the sealing element 202 and the support window is reduced, and the water vapor sealing effect of the aircraft windshield is further improved.
Optionally, the material of the sealing element 202 is at least one of a silicone elastic sealant, a polysulfide elastic sealant, or a polyurethane elastic sealant. Thereby improving the anti-seepage and anti-leakage effects of the sealing element 202 and better realizing the water vapor sealing.
For example, as shown in fig. 2, in the middle region of the transparent composite plate element 100, there are seven layers of composite layer structure, which are, in order from top to bottom, a third transparent layer 104, a second transparent layer 102, a first transparent layer 101, a second transparent layer 102, and a first transparent layer 101. Wherein the three first transparent layers 101 are bonded together by the second transparent layer 102 to form a composite layer structure for collectively carrying loads experienced by the aircraft windshield. The third transparent layer 104, which is the functional layer for electrically heating the aircraft windscreen, is bonded to the first transparent layer 101 by a second transparent layer 102. When the aircraft windscreen is mounted to the supporting window frame 300 of an aircraft, the third transparent layer 104 faces the outside of the aircraft and the two first transparent layers 101 face the inside of the aircraft.
In the edge region of the transparent composite plate element 100, the edge of the first transparent plate protrudes beyond the edge of the third transparent plate. So as to exert a force on the first transparent plate of the protruding portion to fix the transparent composite plate element 100. And, an annular reinforcing layer 103 is adhered to edge regions of both surfaces of each of the first transparent layers 101. When the annular reinforcing layer 103 is positioned between the two first transparent layers 101, both surfaces thereof are adhered to the first and second transparent layers 101 and 102, respectively. When the annular reinforcing layer 103 is located outside the first transparent layer 101, one surface thereof is adhered to the first transparent layer 101 and the edge connector 200, respectively. Thus, in the edge region of the transparent composite plate element 100, the annular reinforcing layer 103 blocks the second transparent layer 102 and the edge connector 200 to block the force of the second transparent layer 102 and the edge connector 200 from directly acting on the first transparent layer 101, thereby protecting the first transparent layer 101.
The edge connector 200 includes a pressure plate 201 and a seal 202. The pressing plate 201 comprises a first section, a second section and a bending section, the first section and the second section are connected through the bending section, the extending direction of the first section and the extending direction of the second section are perpendicular to the extending direction of the bending section, so that the first section of the pressing plate 201 is bonded with the surface of the annular reinforcing layer 103, and the second section is bonded with the surface of the third transparent layer 104, so that the third transparent layer 104 is fixed on the annular reinforcing layer 103.
The inner side of the sealing member 202 is adhered to the outer surface of the annular reinforcing layer 103 outside the two first transparent layers 101, and the sealing member 202 also covers a region of a portion of the outer surface of the third transparent layer 104 near the edge to protect and fix the outer surface of the third transparent layer 104.
One surface of the seal 202 facing the exterior of the cabin is provided with a half groove for mounting and fixing. When the sealing member 202 is pressed against the support window frame 300 of the aircraft by the fixing pressure plate, the fixing pressure plate may be clamped in the half groove, thereby fixing the position of the edge connector 200. One surface of the edge connector 200 facing the interior of the chamber is provided with a sealing groove. The sealing groove is closely attached to the surface of the support window frame 300, and thus, the moisture seal between the support window frame 300 and the windshield of the aircraft can be realized.
According to the embodiment of the invention, the edge connector 200 of the aircraft windshield glass in the embodiment realizes the fixed installation and the water vapor sealing of the aircraft windshield glass through the matching of the sealing element 202 and the pressing plate 201. Thereby improving the safety of the windshield. In the transparent composite plate element 100, a second transparent layer 102 is bonded between two adjacent first transparent layers 101, and an annular reinforcing layer 103 is bonded to each of two surface regions of the first transparent layers 101 near the edges. When the first transparent layer 101 is broken, the fragments of the first transparent layer 101 in the middle area are adhered to the second transparent layer 102, and the fragments of the first transparent layer 101 in the edge area are protected by the annular reinforcing layer 103, so that the integrity of the aircraft windshield glass is maintained, the time for the aircraft windshield glass to be unframed is delayed, and sufficient time is provided for the aircraft to reduce the height, the cabin pressure and the emergency landing.
EXAMPLE III
An aircraft windscreen as shown in fig. 3 and 4, comprising a transparent composite plate element 100 and an edge connector 200, wherein the transparent composite plate element 100 comprises at least two first transparent layers 101, at least one second transparent layer 102, one third transparent layer 104 and at least two annular reinforcing layers 103; the material of the middle area and the material of the edge area of the first transparent layer 101 are different, a second transparent layer 102 is adhered between two adjacent first transparent layers 101, and an annular reinforcing layer 103 is adhered to each of two surfaces of at least one first transparent layer 101, which are close to the edge area; one surface of a first transparent layer 101 is a first outer surface of transparent composite plate element 100; a third transparent layer 104 and a first transparent layer 101 are respectively adhered to both surfaces of a second transparent layer 102, one surface of the third transparent layer 104 being a second outer surface of the transparent composite plate element 100; the edge connector 200 comprises a connection frame 203, a sealing member 202 and bolts 204, the sealing member 202 is mounted outside the edge of the transparent composite plate element 100, covering the areas of the first and second outer surfaces near the edge; the coupling frame 203 is mounted to the outside of the sealing member 202, and the coupling frame 203, the sealing member 202, the annular reinforcing layer 103 and the edge region of the first transparent layer 101 include bolt holes communicating with each other, through which bolts 204 are mounted on the coupling frame 203.
In this embodiment, the middle area and the edge area of the first transparent layer 101 are made of different materials, and the edge area is cut to have bolt holes for fixing and installing, so that stable fastening force can be provided by cooperating with the bolts 204, and the middle area of the first transparent layer 101 is not damaged, so that the middle area of the first transparent layer 101 has high structural strength.
In which, since different materials are used for the middle area and the edge area of the first transparent layer 101, when the middle area of the first transparent layer 101 is cracked, its damage does not spread to the edge area of the first transparent layer 101. At this point, the edge region of the first transparent layer 101 and the annular reinforcing layer 103 may sandwich the second transparent layer 102, thereby maintaining the integrity of the aircraft windshield for a period of time.
Optionally, the thicknesses of the middle region and the edge region of the first transparent layer 101 are the same, where the material of the middle region of the first transparent layer 101 is tempered glass, and the material of the edge region of the first transparent layer 101 is phenolic resin.
Wherein, making the thickness of the middle area and the edge area of the first transparent layer 101 the same, the first transparent layer 101 can be bonded with the second transparent layer 102, the annular reinforcing layer 103, etc. more closely into a whole, thereby improving the structural strength of the transparent composite plate element 100.
The complete tempered glass has high structural strength and light transmittance, and is used for manufacturing the middle area of the first transparent layer 101, so that the structural strength of the middle area of the first transparent layer 101 can be improved.
The phenolic resin has high hardness and high plasticity, the edge area of the first transparent layer 101 is made of the phenolic resin, bolt holes can be conveniently made in the edge area of the first transparent layer 101, and therefore the difficulty in making the first transparent layer 101 is reduced.
Optionally, the number of the first transparent layers 101 and the second transparent layers 102 is two; the thickness of the first transparent layer 101 is 10 mm; the thickness of the third transparent layer 104 is 3 mm; one second transparent layer 102 located between the third transparent layer 104 and one first transparent layer 101 has a thickness of 5mm, and one second transparent layer 102 located between two first transparent layers 101 has a thickness of 1.25 mm.
Here, by providing two first transparent layers 101, a composite layer structure having redundancy is formed. The thickness of the first transparent layer 101 is increased to increase the structural strength of the single layer first transparent layer 101, thereby increasing the structural strength of the aircraft windshield. This provides aircraft windshields with greater fail-safe performance while reducing the difficulty of producing the transparent composite sheet element 100.
Optionally, the number of the first transparent layers 101 and the number of the second transparent layers 102 are three; the two first transparent layers 101 in the middle are both 8mm thick, and the thickness of one first transparent layer 101 including the first outer surface is 5 mm; the thickness of the third transparent layer 104 is 3 mm; one second transparent layer 102 located between the third transparent layer 104 and one first transparent layer 101 has a thickness of 5mm, and one second transparent layer 102 located between the two first transparent layers 101 has a thickness of 1.88 mm.
Wherein, through setting up three first transparent layer 101, further increased aircraft windshield's redundancy, improved aircraft windshield's fail safe performance. Also, by reducing the thickness of the first transparent layer 101, the thickness and weight of the aircraft windshield is reduced to meet aircraft design requirements.
In this embodiment, please refer to the related contents of the first embodiment for the details of the second transparent layer 102, the third transparent layer 104, and the annular reinforcing layer 103.
Optionally, the first transparent layer 101, the second transparent layer 102, the third transparent layer 104, and the annular reinforcing layer 103 are formed into a transparent composite layer element by a thermocompression bonding process, so that the structural strength of the transparent composite layer element can be improved.
In this embodiment, the edge connector 200 is used to mount the transparent composite panel to the support window frame 300 of the aircraft cabin by means of the bolts 204, thereby improving the safety of the aircraft windshield. The edge connector 200 includes a connection frame 203, a seal 202, and a bolt 204.
Wherein the connection frame 203 is installed outside the sealing member 202, and the connection frame 203, the sealing member 202, the annular reinforcing layer 103 and the edge region of the first transparent layer 101 include bolt holes communicating with each other. The aircraft support window frame 300 is provided with bolt holes cooperating with the bolts 204, through which the bolts 204 pass into the bolt holes of the support window frame 300 when the aircraft windscreen is fixed to the support window frame 300 of the aircraft cabin of the aircraft. By screwing the bolt 204, stable fastening force can be provided, and the safety of the airplane windshield glass is improved.
Optionally, the material of the connection frame 203 may be an aluminum alloy, so as to improve the structural strength of the connection frame 203 and reduce the weight of the connection frame 203.
In this embodiment, the sealing member 202 is mounted outside the edge of the transparent composite sheet element and covers the area of the first and second outer surfaces near the edge, and in use to secure an aircraft windscreen in the support window, the connecting frame 203 presses the sealing member 202 from a direction towards the second outer surface of the transparent composite sheet element 100, causing the sealing member 202 to deform and abut against the support window frame 300, thereby achieving a moisture tight seal between the aircraft windscreen and the support window frame 300. In addition, the elastic force generated by the deformation of the sealing element 202 is used as a pre-tightening force, so that the position of the airplane windshield glass can be fixed, and the airplane windshield glass is firmly installed.
Optionally, a plurality of sealing grooves are disposed on the first surface of the sealing element 202, and the first surface and the second surface of the sealing element 202 are located on the same side. When an aircraft windshield is installed on an aircraft, the plurality of seal grooves on seal 202 contact the support window of the aircraft. When the bolt 204 is used to penetrate through the perforated metal plate to fix the windshield in the support window, the sealing element 202 is pressed to elastically deform the sealing groove, so that the gap between the sealing element 202 and the support window is reduced, and the water vapor sealing effect of the aircraft windshield is further improved.
Optionally, the sealing member 202 is an elastic sealing rubber ring. Thereby improving the anti-seepage and anti-leakage effects of the sealing element 202 and better realizing the water vapor sealing.
Optionally, the edge connector 200 further comprises a pressure plate 201, the pressure plate 201 is installed inside the sealing element 202, one end of the pressure plate 201 is pressed on the surface of one annular reinforcing layer 103, and the pressure plate comprises bolt holes for bolts 204 to pass through; the other end is pressed on the edge area of the second outer surface. Thereby pressing the third transparent layer 104 under the pressing plate 201 to prevent the third transparent layer 104 from being detached. Thereby improving the integrity and structural strength of the aircraft windshield.
Optionally, a plurality of sealing grooves are formed on the contact surface of the sealing member 202 and the support window frame 300. When an aircraft windshield is installed on an aircraft, the windshield is fixed in a window by using bolts 204 through the perforated metal pressing plate 201, and the effect of moisture sealing is further improved by elastic deformation of the sealing member 202.
In this embodiment, tests show that the aircraft windshield has better fail-safe performance under the condition that all of the first transparent layer 101 is broken.
For example, when the entire first transparent layer 101 of a conventional aircraft windshield is broken at a differential pressure of 40kPa between the interior and exterior of the cabin, the aircraft windshield deforms significantly and local air leakage occurs. The aircraft windshield of the embodiment shown in fig. 3 can be kept for at least 15 minutes without being framed under the condition that all the first transparent layers 101 are broken, so that time is provided for the aircraft to reduce the height, reduce the cabin pressure and prepare for landing in emergency.
According to the embodiment of the invention, the edge connector 200 of the aircraft windshield glass in the embodiment improves the effects of fixing and mounting the aircraft windshield glass and sealing water vapor through the matching of the connecting frame 203, the sealing element 202 and the bolt 204, so that the safety of the windshield glass is improved. In the transparent composite plate element 100, a second transparent layer 102 is bonded between two adjacent first transparent layers 101, and an annular reinforcing layer 103 is bonded to each of two surface regions of the first transparent layers 101 near the edges. When the first transparent layer 101 is broken, the fragments of the first transparent layer 101 located at the middle area are adhered to the second transparent layer 102, and the fragments of the first transparent layer 101 located at the edge area are protected by the annular reinforcing layer 103. Thereby delaying the time for the frame of the windshield glass of the airplane to be removed. Therefore, when the windshield glass of the airplane is broken, time is provided for the airplane to reduce the height, reduce the cabin pressure and emergently prepare for landing, and therefore the safety of the windshield glass of the airplane is improved.
Of course, it is not necessary for any particular embodiment of the invention to achieve all of the above advantages at the same time.
It should be noted that, according to the implementation requirement, each component/step described in the embodiment of the present application may be divided into more components/steps, and two or more components/steps or partial operations of the components/steps may also be combined into a new component/step to achieve the purpose of the embodiment of the present application.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the embodiments of the invention. It will be apparent to those skilled in the art that various modifications and variations can be made in the embodiments of the present invention without departing from the spirit or scope of the embodiments of the invention. Thus, if such modifications and variations of the embodiments of the present invention fall within the scope of the claims of the embodiments of the present invention and their equivalents, the embodiments of the present invention are also intended to encompass such modifications and variations.
Claims (10)
1. An aircraft windscreen, comprising a transparent composite plate element and an edge connector, wherein,
the edge connectors are installed outside the edges of the transparent composite plate elements and cover the areas of the two outer surfaces of the transparent composite plate elements close to the edges;
the transparent composite sheet element comprises at least two first transparent layers, at least one second transparent layer and at least two annular reinforcing layers;
and a second transparent layer is adhered between two adjacent first transparent layers, and the two surface areas close to the edges of at least one first transparent layer are respectively adhered with one annular reinforcing layer.
2. An aircraft windscreen according to claim 1 wherein a respective one of said annular reinforcing layers is bonded to each of the two edge-adjacent surface regions of all of said first transparent layers.
3. An aircraft windshield according to claim 1, wherein the thickness of the annular reinforcing layer is less than the thickness of the second transparent layer adjacent the annular reinforcing layer.
4. An aircraft windscreen according to claim 1 wherein the thickness of each of said at least two annular reinforcing layers is greater than or equal to 0.5mm and less than or equal to 3 mm.
5. An aircraft windscreen according to claim 1 wherein said annular reinforcing layer is closed annular.
6. An aircraft windscreen according to claim 1 wherein the annular reinforcing layer is form-fitted between the two faces to which the first transparent layer is bonded.
7. An aircraft windscreen according to claim 1 wherein the material of the annular reinforcing layer is one of stainless steel, aluminium alloy, fibreglass board, polyester fibre board, carbon fibre board, perspex, polycarbonate board.
8. An aircraft windscreen according to claim 7 wherein the maximum width of the annular reinforcing layer is no more than 100mm when the material of the annular reinforcing layer is non-transparent.
9. An aircraft windscreen according to claim 1 wherein the edge of said annular reinforcing layer does not extend beyond the edge of said edge connector on the side facing towards the mid-region of said first transparent layer.
10. An aircraft windshield according to claim 1, wherein said transparent composite sheet element further comprises a third transparent layer, one of said third and one of said first transparent layers being adhered to each of the two surfaces of a second transparent layer.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010877712.7A CN112061371A (en) | 2020-08-27 | 2020-08-27 | Aircraft windshield |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010877712.7A CN112061371A (en) | 2020-08-27 | 2020-08-27 | Aircraft windshield |
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| CN112061371A true CN112061371A (en) | 2020-12-11 |
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| CN110914053A (en) * | 2017-07-06 | 2020-03-24 | 法国圣戈班玻璃厂 | Suppression of electrostatic discharge noise by conduction between layered metal elements and wiring system of glazing device |
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| US3953630A (en) * | 1972-03-13 | 1976-04-27 | Triplex Safety Glass Company Limited | Laminated transparent assemblies |
| CN1043913A (en) * | 1988-12-30 | 1990-07-18 | Ppg工业公司 | The moisture seal of aircraft windows |
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