Aircraft leading edge tower bird strike resistant structure

Abstract

This invention relates to the field of aircraft structural design technology, specifically to a leading-edge tower-type bird strike protection structure for aircraft. It includes a leading-edge skin assembly, a first protective assembly, a second protective assembly, a third protective assembly, and a rear beam assembly. The leading-edge skin assembly and the rear beam assembly are located at the front and rear ends of the sequentially connected first, second, and third protective assemblies, respectively, and are wrapped around them. The rear end of the first protective assembly is fixedly connected to the front end of the second protective assembly and is used to resist high-speed bird impacts. The rear end of the second protective assembly is fixedly connected to the front end of the third protective assembly and is used to resist medium-speed bird impacts. The rear end of the third protective assembly is fixedly connected to the rear beam assembly and is used to resist low-speed bird impacts. The purpose of this leading-edge tower-type bird strike protection structure is to solve the problem of low structural efficiency in existing aircraft leading-edge bird strike protection structures.

Description

Technical Field

[0001] This invention relates to the field of aircraft structural design technology, specifically to a leading-edge tower-type bird strike protection structure for aircraft. Background Technology

[0002] Bird strikes are a critical and high-risk condition that must be considered in aircraft structural design. At the moment of a bird strike, a massive dynamic load is generated in a localized area of ​​the aircraft structure, lasting from 1 to 10 microseconds. This enormous transient load causes severe damage to the aircraft structure. Bird strikes typically occur on the aircraft's frontal structures, including the leading edges of the wings and tail, the cockpit windshield, and the radome. Bird strikes to these areas often lead to serious flight safety accidents. Therefore, careful and meticulous design of these structures, and the development of novel design solutions, have always been a primary concern for aircraft designers.

[0003] Bird strikes involve high-speed impacts from birds onto aircraft structures, and these high-speed impacts involve the dynamic behavior of both materials and structures. Different materials, or even different structural designs using the same materials, significantly affect an aircraft's bird strike resistance. Some large passenger aircraft, considering the characteristics of the leading-edge structure, have designed auxiliary load-bearing buffer boxes to resist bird strikes, or have a thick metal baffle at the leading edge of the aircraft structure, supplemented by a stainless steel or titanium alloy plate bonded to the leading-edge skin, as a form of bird strike resistance. However, this type of bird strike resistance structure is not very efficient and does not take into account the fact that the bird becomes fluid upon high-speed impact.

[0004] Therefore, the inventors have provided a leading-edge tower-type bird strike protection structure for aircraft. Summary of the Invention

[0005] (1) Technical problems to be solved

[0006] This invention provides a tower-type bird strike protection structure for the leading edge of an aircraft, which solves the technical problem of low structural efficiency in existing bird strike protection structures for the leading edge of aircraft.

[0007] (2) Technical solution

[0008] This invention provides a leading-edge tower-type bird strike protection structure for aircraft, comprising a leading-edge skin assembly, a first protective assembly, a second protective assembly, a third protective assembly, and a rear beam assembly. The leading-edge skin assembly and the rear beam assembly are respectively located at the front and rear ends of the first protective assembly, the second protective assembly, and the third protective assembly, which are connected sequentially, and are wrapped around the first protective assembly, the second protective assembly, and the third protective assembly; wherein...

[0009] The rear end of the first protective component is fixedly connected to the front end of the second protective component and is used to resist high-speed impacts from birds. The rear end of the second protective component is fixedly connected to the front end of the third protective component and is used to resist medium-speed impacts from birds. The rear end of the third protective component is fixedly connected to the rear beam assembly and is used to resist low-speed impacts from birds.

[0010] Furthermore, the first protective component includes a triangular block, a first inclined plate, and a second inclined plate, with the first inclined plate and the second inclined plate located on opposite sides of the triangular block; one end of the first inclined plate is connected to the triangular block, and the other end of the first inclined plate is connected to the second protective component; one end of the second inclined plate is connected to the triangular block, and the other end of the second inclined plate is connected to the second protective component.

[0011] Furthermore, the first protective component is made of metal.

[0012] Furthermore, both the first protective component and the second protective component are made of metal or composite materials.

[0013] Furthermore, the apex angle of the triangular block is 120°.

[0014] Furthermore, the second protective component includes a first horizontal plate, a second horizontal plate, and a plurality of first vertical plates. Each of the first vertical plates is fixedly connected to the first horizontal plate and the second horizontal plate at both ends, and the cavity between the first horizontal plate, the second horizontal plate, and the first vertical plate is filled with a fiberglass board.

[0015] The first horizontal plate is fixedly connected to the rear end of the first protective component, and the second horizontal plate is fixedly connected to the front end of the third protective component.

[0016] Furthermore, the first horizontal plate, the second horizontal plate, and the first vertical plate are all made of -T material.

[0017] Furthermore, the third protective component includes a third horizontal plate, a fourth horizontal plate, a third inclined plate, a fourth inclined plate, and a plurality of second vertical plates, with both ends of the third inclined plate, the fourth inclined plate, and the plurality of second vertical plates respectively fixedly connected to the third horizontal plate and the fourth horizontal plate;

[0018] The third horizontal plate is fixedly connected to the rear end of the second protective component, and the fourth horizontal plate is fixedly connected to the rear beam component.

[0019] Furthermore, the cavity between the third horizontal plate, the fourth horizontal plate, the third inclined plate, the fourth inclined plate, and the second vertical plate is filled with fiberglass board.

[0020] Furthermore, the first protective component, the second protective component, and the third protective component are all axisymmetric structures.

[0021] (3) Beneficial effects

[0022] In summary, this invention designs a first protective component, a second protective component, and a third protective component with different structures and materials to counteract high-speed, medium-speed, and low-speed impacts of birds by taking into account the different characteristics exhibited by birds at different stages during the impact of a bird on the leading edge of an aircraft. This prevents and reduces the speed and kinetic energy of the bird impact, thereby protecting the rear beam of the leading edge. Attached Figure Description

[0023] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments of the present invention will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a schematic diagram of a bird strike pylon structure for an aircraft leading edge provided by an embodiment of the present invention;

[0025] Figure 2 This is a schematic diagram of the structure of the first protective component in an aircraft leading-edge tower-type bird strike protection structure provided in an embodiment of the present invention;

[0026] Figure 3 This is a schematic diagram of the structure of the second protective component in an aircraft leading-edge tower-type bird strike protection structure provided in an embodiment of the present invention;

[0027] Figure 4 This is a schematic diagram of the third protective component in an aircraft leading-edge tower-type bird strike protection structure provided in an embodiment of the present invention.

[0028] In the picture:

[0029] 1-Leading edge skin assembly; 2-First protective assembly; 201-Triangular block; 202-First inclined plate; 203-Second inclined plate; 3-Second protective assembly; 301-First horizontal plate; 302-Second horizontal plate; 303-First vertical plate; 4-Third protective assembly; 401-Third horizontal plate; 402-Fourth horizontal plate; 403-Third inclined plate; 404-Fourth inclined plate; 405-Second vertical plate; 5-Rear beam assembly. Detailed Implementation

[0030] The embodiments of the present invention will be further described in detail below with reference to the accompanying drawings and examples. The following detailed description of the embodiments and the accompanying drawings are used to illustrate the principles of the present invention by way of example, but should not be used to limit the scope of the present invention. That is, the present invention is not limited to the described embodiments, and any modifications, substitutions and improvements to the parts, components and connection methods are covered without departing from the spirit of the present invention.

[0031] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0032] In the description of this invention, it should be understood that the terms "upper," "lower," "front," "rear," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this invention is in use, or the orientation or positional relationship commonly understood by those skilled in the art. They are only used to facilitate the description of this invention and to simplify the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0033] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set" and "install" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0034] Figure 1 This is a schematic diagram of a bird strike stabilization structure for an aircraft leading edge provided by an embodiment of the present invention, as shown below. Figure 1 As shown, the bird strike protection structure may include a leading edge skin assembly 1, a first protective assembly 2, a second protective assembly 3, a third protective assembly 4, and a rear beam assembly 5. The leading edge skin assembly 1 and the rear beam assembly 5 are located at the front and rear ends of the first protective assembly 2, the second protective assembly 3, and the third protective assembly 4, which are connected in sequence, and are wrapped around the first protective assembly 2, the second protective assembly 3, and the third protective assembly 4, respectively.

[0035] The rear end of the first protective component 2 is fixedly connected to the front end of the second protective component 3 and is used to resist high-speed impacts from birds. The rear end of the second protective component 3 is fixedly connected to the front end of the third protective component 4 and is used to resist medium-speed impacts from birds. The rear end of the third protective component 4 is fixedly connected to the rear beam component 5 and is used to resist low-speed impacts from birds.

[0036] In the above embodiments, based on the different characteristics exhibited by the bird at different stages during the impact of the bird on the leading edge of the aircraft, the first protective component 2, the second protective component 3, and the third protective component 4 with different structures and materials are designed to resist the bird impacts at high speed, medium speed, and low speed respectively, thereby preventing and reducing the speed and kinetic energy of the bird impact and achieving the function of protecting the rear beam component 5.

[0037] As an optional implementation method, such as Figure 2 As shown, the first protective component 2 includes a triangular block 201, a first inclined plate 202, and a second inclined plate 203. The first inclined plate 202 and the second inclined plate 203 are located on both sides of the triangular block 201, respectively. One end of the first inclined plate 202 is connected to the triangular block 201, and the other end of the first inclined plate 202 is connected to the second protective component 3. One end of the second inclined plate 203 is connected to the triangular block 201, and the other end of the second inclined plate 203 is connected to the second protective component 3.

[0038] Specifically, the first protective component 2 is made of metal material, which utilizes the high-speed dynamic characteristics of metal to resist the high-speed impact of the bird; it adopts a triangular structure, which is conducive to cutting and dispersing the bird's kinetic energy; and its horizontal end facilitates the removal of bird fragments.

[0039] The first inclined plate 202 and the second inclined plate 203 have an included angle greater than 90 degrees and are symmetrically distributed on the left and right sides of the triangular block 201. The ends of the first inclined plate 202 and the second inclined plate 203 have horizontal bends. The first inclined plate 202 and the second inclined plate 203 are connected to the triangular block 201 by welding. The first protective component 2 is connected to the second protective component 3 by bolts at the bends. The first protective component 2 uses the triangular block to resist the high-speed impact of the bird. The broken bird body is diverted out of the leading edge structure to the maximum extent through the first inclined plate 202 and the second inclined plate 203.

[0040] As an optional implementation, the apex angle of the triangular block 201 is 120°. The height of the triangular block 201 is 10mm, the thickness of the first inclined plate 202 and the second inclined plate 203 is 2mm, the horizontal bending length is 20mm, and the first protective component 2 and the second protective component 3 are connected by MS21250-03 bolts.

[0041] As an optional implementation method, such as Figure 3 As shown, the second protective component 3 includes a first horizontal plate 301, a second horizontal plate 302, and a plurality of first vertical plates 303. Both ends of each first vertical plate 303 are fixedly connected to the first horizontal plate 301 and the second horizontal plate 302, respectively. The cavity between the first horizontal plate 301, the second horizontal plate 302, and the first vertical plate 303 is filled with fiberglass board. The first horizontal plate 301 is fixedly connected to the rear end of the first protective component 2, and the second horizontal plate 302 is fixedly connected to the front end of the third protective component 4.

[0042] Specifically, the second protective component 3 is made of metal or composite material, which utilizes the elastic-plastic failure of the material to resist the medium-speed impact of the bird; the box-shaped structure is conducive to further uniformly and dispersing the bird body, reducing the bird's kinetic energy; and the horizontal end facilitates the removal of bird fragments.

[0043] The fiberglass board and the horizontal board can be glued or bolted together. The second protective component 3 is bolted to the first protective component 2 and the third protective component 4. The second protective component 3 is used to resist bird fragments that impact at a medium speed after penetrating the first protective component 2.

[0044] As an optional implementation method, such as Figure 4 As shown, the third protective component 4 includes a third horizontal plate 401, a fourth horizontal plate 402, a third inclined plate 403, a fourth inclined plate 404, and a plurality of second vertical plates 405. The two ends of the third inclined plate 403, the fourth inclined plate 404, and the plurality of second vertical plates 405 are respectively fixedly connected to the third horizontal plate 401 and the fourth horizontal plate 402. The third horizontal plate 401 is fixedly connected to the rear end of the second protective component 3, and the fourth horizontal plate 402 is fixedly connected to the rear beam component 5.

[0045] Specifically, the third protective component 4 is made of metal or composite material, which uses the elastic deformation or damage of the material to resist the low-speed impact of the bird; the box-shaped structure is conducive to further uniform and dispersing the bird's body, reducing the bird's kinetic energy; the cavity-filled plate is conducive to utilizing the high impact resistance of the composite material plate; and the horizontal end is conducive to the removal of bird fragments.

[0046] The carbon fiber plate and the horizontal plate can be glued or bolted together. The third protective assembly 4 is bolted to the second protective assembly 2 and the rear beam assembly 5. The third protective assembly 5 is used to resist bird fragments that impact at low speed after penetrating the second protective assembly 3, ultimately protecting the aircraft's leading edge rear beam assembly.

[0047] As an optional implementation, the cavity between the third horizontal plate 401, the fourth horizontal plate 402, the third inclined plate 403, the fourth inclined plate 404, and the second vertical plate 405 is filled with fiberglass board. The filling with fiberglass board improves the overall impact resistance of the third protective component 4.

[0048] As an optional implementation method, such as Figure 1 As shown, the first protective component 2, the second protective component 3, and the third protective component 4 are all axisymmetric structures. The symmetrical structure facilitates manufacturing and results in more even stress distribution.

[0049] In one specific embodiment, the triangular block 201 in the first protective component 2 is manufactured using 7075-T7451 material, and the first inclined plate 202 and the second inclined plate 203 are manufactured using 2024-T351 material. The left inclined plate, the right inclined plate, and the triangular block are connected by welding.

[0050] The second protective component 3 is manufactured using 2024-T351 material. The horizontal and vertical plates are connected by welding. The thickness of each plate is 2mm. The cavity between the horizontal and vertical plates is filled with glass fiber board with a thickness of 4mm. The external dimensions are determined according to the size of the cavity. The layup adopts transverse isotropic laying.

[0051] The fiberglass board and the horizontal board are bonded together. The horizontal board, vertical board, and left and right inclined boards are connected by welding, all with a thickness of 2mm. The cavity between the horizontal board, vertical board, and left and right inclined boards is filled with carbon fiber board, which is designed to be 2mm thick and is laid isotropically in the transverse direction. The external dimensions are determined according to the dimensions of the cavity.

[0052] The assembled protective assembly is placed between the front edge skin assembly 1 and the rear beam assembly 5, and the entire protective assembly is connected to the rear beam assembly 5 by bolts.

[0053] The bird strike resistant leading edge structure fabricated using this embodiment is used in aircraft to resist 1.8kg leading edge bird strikes and can effectively protect the leading edge rear beam.

[0054] It should be noted that the various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the figures. Furthermore, for the sake of brevity, detailed descriptions of known methods and techniques are omitted here.

[0055] The above are merely embodiments of this application and are not intended to limit the scope of this application. Various modifications and variations can be made to this application by those skilled in the art without departing from the scope of the invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of this application should be included within the scope of the claims of this application.

Claims

1. An aircraft leading edge pylon bird strike resistant structure, characterized in that, The application relates to a bird-proof assembly, which comprises a front edge skin assembly (1), a first protection assembly (2), a second protection assembly (3), a third protection assembly (4) and a rear beam assembly (5), wherein the front edge skin assembly (1) and the rear beam assembly (5) are respectively arranged at the front and rear ends of the first protection assembly (2), the second protection assembly (3) and the third protection assembly (4) which are sequentially connected and wrapped in the first protection assembly (2), the second protection assembly (3) and the third protection assembly (4). The rear end of the first protection assembly (2) is fixedly connected with the front end of the second protection assembly (3) and is used for resisting high-speed impact of a bird body, the rear end of the second protection assembly (3) is fixedly connected with the front end of the third protection assembly (4) and is used for resisting medium-speed impact of a bird body, and the rear end of the third protection assembly (4) is fixedly connected with the rear beam assembly (5) and is used for resisting low-speed impact of a bird body. The first protection assembly (2) comprises a triangular block (201), a first inclined plate (202) and a second inclined plate (203), the first inclined plate (202) and the second inclined plate (203) are respectively arranged at the two sides of the triangular block (201), one end of the first inclined plate (202) is connected with the triangular block (201), the other end of the first inclined plate (202) is connected with the second protection assembly (3), one end of the second inclined plate (203) is connected with the triangular block (201), and the other end of the second inclined plate (203) is connected with the second protection assembly (3). The second protection assembly (3) comprises a first horizontal plate (301), a second horizontal plate (302) and a plurality of first vertical plates (303), the two ends of each first vertical plate (303) are respectively fixedly connected with the first horizontal plate (301) and the second horizontal plate (302), the first horizontal plate (301) is fixedly connected with the rear end of the first protection assembly (2), and the second horizontal plate (302) is fixedly connected with the front end of the third protection assembly (4). The third protection assembly (4) comprises a third horizontal plate (401), a fourth horizontal plate (402), a third inclined plate (403), a fourth inclined plate (404) and a plurality of second vertical plates (405), the two ends of the third inclined plate (403), the fourth inclined plate (404) and the plurality of second vertical plates (405) are respectively fixedly connected with the third horizontal plate (401) and the fourth horizontal plate (402), the third horizontal plate (401) is fixedly connected with the rear end of the second protection assembly (3), and the fourth horizontal plate (402) is fixedly connected with the rear beam assembly (5).

2. The aircraft leading edge pylon bird strike structure of claim 1, wherein, The first protection assembly (2) is made of metal.

3. Aircraft leading edge pylon bird strike resistant structure according to claim 1 or 2, characterized in that, The second protection assembly (3) and the third protection assembly (4) are made of metal or composite material.

4. Aircraft leading edge pylon bird strike resistant structure according to claim 1 or 2, characterized in that, The top angle of the triangular block (201) is 120 degrees.

5. The aircraft leading edge pylon bird strike structure of claim 1, wherein, The cavities between the first horizontal plate (301), the second horizontal plate (302) and the first vertical plate (303) are filled with glass fiber plates.

6. The aircraft leading edge pylon bird strike structure of claim 1, wherein, The cavity between the third horizontal plate (401), the fourth horizontal plate (402) and the third inclined plate (403), the fourth inclined plate (404) and the second vertical plate (405) is filled with a glass fiber plate.

7. The aircraft leading edge pylon bird strike structure of claim 1, wherein, The first protection assembly (2), the second protection assembly (3) and the third protection assembly (4) are all axisymmetric structures.

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