Bird strike test support structure for aircraft wing leading edge

Abstract

The present application belongs to the technical field of aircraft testing, and discloses an aircraft wing surface leading edge bird impact test support structure, which comprises a bottom support structure and a side support structure. The trailing edge strips of the first beam, the second beam, the third beam and the fourth beam of the bottom support structure are fixed to a test wall. Two leading edge wallboards of a test piece are respectively connected to the leading edge strips of the first beam and the second beam. The side support structure is connected to the leading edge strips of the first beam and the second beam. The top plate of the side support structure is provided with a connecting assembly which extends into the partition plate of the test piece and the leading edge rib of the test piece. The partition plate and the leading edge rib are both connected to the connecting assembly. The bottom support structure provides support for the test piece. The side support structure supports and restricts the boundary of the cut end of the test piece, so that the boundary condition is more similar to the actual structure. The deformation of the test piece during the bird impact test is more close to the deformation of the actual structure under the same working condition. The test process is closer to the actual situation, so that the anti-bird impact capability of the test piece is more accurate.

Description

Technical Field

[0001] This invention relates to the field of aircraft testing technology, and in particular to a bird strike test support structure for the leading edge of an aircraft wing. Background Technology

[0002] Aircraft face the risk of bird strikes during cruise, and bird strikes have become a significant threat to flight safety. According to airworthiness regulations, an aircraft's bird strike resistance can be verified through analysis, testing, or a combination of both. Bird strike testing is essential during the aircraft development phase. Conducting bird strike tests at different levels refines analytical methods and verifies the aircraft's bird strike resistance, ensuring that even after being damaged by a bird strike, the remaining structure can still support continued flight and a safe landing.

[0003] During the research and development phase, a typical position at the leading edge of the aircraft wing is usually selected as the test piece for bird strike testing. During the bird strike test, a support structure is required to support the test piece, maintain its cruise attitude, obtain boundary conditions close to the real structure, and prevent damage under bird strike conditions, so as to obtain the failure mode of the test piece itself and optimize the simulation analysis model.

[0004] Therefore, there is an urgent need for a device to solve the above problems. Summary of the Invention

[0005] The purpose of this invention is to provide a bird strike test support structure at the leading edge of an aircraft wing that can support the test specimen and obtain real boundary conditions.

[0006] To achieve this objective, the present invention adopts the following technical solution:

[0007] The leading edge bird strike test support structure for the aircraft wing includes:

[0008] The bottom support structure includes a first beam, a second beam, a third beam, and a fourth beam connected end to end. The rear edge strips of the first beam, the second beam, the third beam, and the fourth beam are fixed to the test wall. The first beam and the second beam are arranged opposite each other along the width direction of the bottom support structure. The two front edge panels of the test piece are respectively connected to the front edge strips of the first beam and the second beam.

[0009] A side support structure, wherein the bottom plate of the side support structure is connected to the front edge strip of the first beam and the front edge strip of the second beam, and the top plate of the side support structure is provided with a connecting assembly, the connecting assembly extending between the partition of the test piece and the front edge rib of the test piece, and both the partition and the front edge rib are connected to the connecting assembly.

[0010] Preferably, two side support structures are provided, and the two side support structures are respectively connected to the two cut ends of the test piece, and the distance between the two side support structures is adjustable.

[0011] Preferably, the first beam, the second beam, the third beam, and the fourth beam are all C-shaped beams. Each of the first beam, the second beam, the third beam, and the fourth beam includes a front edge strip, a web, and a rear edge strip. The front edge strip and the rear edge strip are arranged opposite to each other and connected by the web.

[0012] Preferably, the bottom support structure further includes a plurality of connecting plates, which are spaced apart and connected between the web of the first beam and the web of the second beam, and the plurality of ribs of the test piece are connected one-to-one to the plurality of connecting plates.

[0013] Preferably, the first beam, the second beam, the third beam, and the fourth beam each include a plurality of reinforcing ribs, which are spaced apart between the front edge strip and the rear edge strip, and the reinforcing ribs are connected to the web plate, with both ends of the reinforcing ribs connected to the front edge strip and the rear edge strip, respectively.

[0014] Preferably, the leading edge bird strike test support structure of the aircraft wing further includes L-shaped corner pieces, wherein a plurality of L-shaped corner pieces are provided, and one side of some of the L-shaped corner pieces is sequentially connected to one of the leading edge panels of the test piece, and the other side is sequentially connected to the leading edge strip of the first beam; one side of the remaining L-shaped corner pieces is sequentially connected to the other leading edge panel of the test piece, and the other side is sequentially connected to the leading edge strip of the second beam.

[0015] Preferably, one of the leading edge panels of the test piece is spaced apart from the leading edge strip of the first beam, and the other leading edge panel of the test piece is spaced apart from the leading edge strip of the second beam.

[0016] Preferably, the side support structure includes the bottom plate, the top plate, and two support plates. The two support plates are arranged opposite to each other and are connected between the bottom plate and the top plate. The bottom plate is adjustablely connected to the front edge strip of the first beam and the front edge strip of the second beam.

[0017] Preferably, the side support structure further includes a reinforcing plate connected between the two support plates.

[0018] Preferably, the connecting assembly includes a steel plate and a T-shaped corner piece, the steel plate being connected to the top plate and extending between the partition of the test piece and the leading edge rib of the test piece, the bottom of the T-shaped corner piece being connected to the steel plate, and the extended end of the T-shaped corner piece being connected to the leading edge rib.

[0019] Beneficial Effects: This invention provides a bird strike test support structure for the leading edge of an aircraft wing, including a bottom support structure and a side support structure. In the bottom support structure, the first, second, third, and fourth beams are connected end to end. The two leading edge panels of the test specimen are respectively connected to the leading edge strips of the first and second beams to support the two leading edge panels. The trailing edge strips of the first, second, third, and fourth beams are fixed to the test wall. By adjusting the angle, the test specimen can maintain the cruising attitude of the leading edge of the wing. The bottom plate of the side support structure is connected to the leading edge strips of the first and second beams, and the top plate of the side support structure is provided with a connecting component. The connecting component extends between the partition and the leading edge rib of the test specimen. Both the partition and the leading edge rib are connected to the connecting component to constrain and support the boundary of the cut-off end of the test specimen, making the boundary conditions more similar to the real structure. The bird strike test support structure for the leading edge of an aircraft wing provided by this invention can ensure that the deformation of the test specimen during the bird strike test is closer to the deformation of the actual structure under the same working conditions, and the test process is closer to the real situation, thereby obtaining a more accurate bird strike resistance capability of the test specimen. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure of the test specimen provided in Embodiment 1 of the present invention;

[0021] Figure 2 This is a schematic diagram of the bird strike test support structure at the leading edge of the aircraft wing provided in Embodiment 1 of the present invention;

[0022] Figure 3 This is a schematic diagram of the bottom support structure provided in Embodiment 1 of the present invention;

[0023] Figure 4 This is a schematic diagram of the structure of the test specimen and the bird strike test support structure at the leading edge of the aircraft wing provided in Embodiment 1 of the present invention;

[0024] Figure 5 This is a schematic diagram of the side support structure provided in Embodiment 1 of the present invention.

[0025] In the picture:

[0026] 100. Test specimen; 101. Leading edge panel; 102. Rib; 103. Partition; 104. Leading edge rib;

[0027] 1. Bottom support structure; 11. First beam; 12. Second beam; 13. Third beam; 14. Fourth beam; 15. Connecting plate; 10. Front edge strip; 20. Web plate; 30. Rear edge strip; 40. Reinforcing rib; 2. L-shaped corner piece; 3. Side support structure; 31. Bottom plate; 32. Top plate; 33. Support plate; 34. Reinforcing plate; 35. Steel plate; 36. T-shaped corner piece. Detailed Implementation

[0028] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0029] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0030] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0031] In the description of this embodiment, the terms "upper," "lower," "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not 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 the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0032] Example 1

[0033] This embodiment provides a bird strike test support structure for the leading edge of an aircraft wing, which can constrain the truncated boundary of the test piece and provide support stiffness for the test piece, making the boundary conditions more similar to the real structure. This ensures that the deformation of the test piece during the bird strike test is closer to the deformation of the actual structure under the same working conditions, and the test process is closer to the real situation, thereby obtaining a more accurate bird strike resistance of the test piece.

[0034] Before proceeding, a brief description of the test specimen's structure is necessary. The leading edge of an aircraft wing includes the leading edges of the wing and tail. The test specimen is obtained by cutting off a section at a typical location on the leading edge of the aircraft wing. This embodiment applies to cases where both ends of the test specimen's spanwise direction are cut off. Please refer to [link to relevant documentation]. Figure 1 The test specimen 100 has two leading edge panels 101, both of which are typical bird strike locations, and also has a rib 102, a partition 103, and a leading edge rib 104. The partition 103 and the leading edge rib 104 are connected between the two leading edge panels 101 to provide support for the leading edge panels 101. The rib 102 is connected to the partition 103 and extends in a direction away from the partition 103 to connect with other structures of the aircraft.

[0035] Please see Figure 2 The bird strike test support structure for the leading edge of the aircraft wing includes a bottom support structure 1 and a side support structure 3. The side support structure 3 is set on the bottom support structure 1. The bottom support structure 1 is used to support the two leading edge panels 101, and the side support structure 3 is used to support the bulkhead 103. The bottom support structure 1 provides support for the test piece 100, and the side support structure 3 provides constraint support for the cut-off boundary of the test piece 100, so that the boundary conditions are closer to the real structure. This ensures that the deformation of the test piece 100 during the bird strike test is closer to the deformation of the actual structure under the same working conditions, and the test process is closer to the real situation, thereby obtaining a more accurate bird strike resistance capability of the test piece 100.

[0036] Specifically, please refer to Figure 3 The bottom support structure 1 includes a first beam 11, a second beam 12, a third beam 13, and a fourth beam 14. The first beam 11, the second beam 12, the third beam 13, and the fourth beam 14 are connected end to end. Preferably, the first beam 11 and the second beam 12 are of equal length and are arranged opposite each other along the width direction of the bottom support structure 1, and the third beam 13 and the fourth beam 14 are of equal length and are arranged opposite each other along the length direction of the bottom support structure 1. The first beam 11, the second beam 12, the third beam 13, and the fourth beam 14 are rectangular after being connected end to end, so as to stably support the test specimen 100.

[0037] Furthermore, the first beam 11, the second beam 12, the third beam 13, and the fourth beam 14 are all C-shaped beams, and each of them includes a front edge strip 10, a web plate 20, and a rear edge strip 30. The front edge strip 10 and the rear edge strip 30 of the same beam are arranged opposite each other, and the web plate 20 connects the front edge strip 10 and the rear edge strip 30. The web plate 20 of the third beam 13 is simultaneously welded to one end of the length direction of the first beam 11 and one end of the length direction of the second beam 12, and its front edge strip 10 and rear edge strip 30 are both away from the web plate 20 of the first beam 11, the second beam 12, and the fourth beam 14. The web plate 20 of the fourth beam 14 is simultaneously welded to the other end of the length direction of the first beam 11 and the other end of the length direction of the second beam 12, and its front edge strip 10 and rear edge strip 30 are both away from the first beam 11 and the second beam 12.

[0038] Please see Figure 3 and Figure 4 Before the bird strike test, the two leading edge panels 101 of the test piece 100 are connected to the leading edge strips 10 of the first beam 11 and the second beam 12, respectively. The trailing edge strips 30 of the first beam 11, the second beam 12, the third beam 13 and the fourth beam 14 are fixed to the test wall. By adjusting the angle, the test piece 100 can maintain the cruising attitude of the leading edge of the wing, ensuring the stability of the test piece 100 during the bird strike test.

[0039] Preferably, the connection between the bottom support structure 1 and the test piece 100 is achieved through a plurality of L-shaped corner pieces 2. For details, please refer to the following document. Figure 3 and Figure 4 Some L-shaped corner pieces 2 are sequentially arranged between the first beam 11 and the test piece 100 along the length direction of the first beam 11, and one side of them is sequentially bolted to one of the front edge wall plates 101 of the test piece 100, and the other side is sequentially bolted to the front edge strip 10 of the first beam 11. The remaining L-shaped corner pieces 2 are sequentially arranged between the second beam 12 and the test piece 100 along the length direction of the second beam 12, and one side of them is sequentially bolted to the other front edge wall plate 101 of the test piece 100, and the other side is sequentially bolted to the front edge strip 10 of the second beam 12.

[0040] In this embodiment, one of the leading edge panels 101 of the test specimen 100 is spaced apart from the leading edge strip 10 of the first beam 11 by a gap of 2-5 mm, and the leading edge panel 101 is located between the first beam 11 and the second beam 12. The other leading edge panel 101 of the test specimen 100 is spaced apart from the leading edge strip 10 of the second beam 12 by a gap of 2-5 mm, and the leading edge panel 101 is located between the first beam 11 and the second beam 12. This avoids the leading edge panel 101 from deforming and contacting the first beam 11 and the second beam 12 under bird strike conditions, so that the test process is closer to the real situation, thereby obtaining a more accurate bird strike resistance capability of the test specimen 100.

[0041] More preferably, the rear edge strips 30 of the first beam 11, second beam 12, third beam 13, and fourth beam 14 are each provided with a plurality of connecting holes, and the plurality of connecting holes on the same beam are evenly spaced along its length. The rear edge strips 30 of the first beam 11, second beam 12, third beam 13, and fourth beam 14 are each distributed with a plurality of bolts, one end of which passes through the connecting hole, and the other end of which is connected to the test wall, thereby achieving a fixed connection between the bottom support structure 1 and the test wall. For example, the bolts connected to the rear edge strips 30 of the first beam 11, second beam 12, third beam 13, and fourth beam 14 are evenly distributed, and the number of bolts is not less than two-thirds of the number of connecting holes, to ensure a stable and reliable connection between the bottom support structure 1 and the test wall.

[0042] In this embodiment, please refer to Figure 3 The bottom support structure 1 also includes several connecting plates 15, which are spaced apart between the web 20 of the first beam 11 and the web 20 of the second beam 12. Several ribs 102 of the test piece 100 are attached to the several connecting plates 15 one by one. Preferably, several through holes are evenly provided on the connecting plates 15. The connection between each connecting plate 15 and its corresponding rib 102 is achieved by multiple bolts being screwed into the multiple through holes one by one. On the other hand, the several through holes evenly provided on the connecting plates 15 can be used as positioning references to position the test piece 100.

[0043] Optionally, to further improve the support strength of the test specimen 100, the first beam 11, the second beam 12, the third beam 13, and the fourth beam 14 each include a plurality of reinforcing ribs 40. For example, the plurality of reinforcing ribs 40 on the first beam 11, the second beam 12, the third beam 13, and the fourth beam 14 are spaced apart. The reinforcing ribs 40 are connected to the web plate 20, and the two ends of the reinforcing ribs 40 are respectively connected to the front edge strip 10 and the rear edge strip 30, so as to strengthen the connection strength of the first beam 11, the second beam 12, the third beam 13, and the fourth beam 14, thereby improving the support strength of the test specimen 100 and preventing the first beam 11, the second beam 12, the third beam 13, and the fourth beam 14 from being damaged under bird strike conditions, thereby affecting the accuracy of the test results.

[0044] In this embodiment, please refer to Figure 2 and Figure 5 Two side support structures 3 are provided, and the two side support structures 3 are respectively connected to the two cut ends of the test specimen 100 to constrain and support the cut ends of the test specimen 100. The side support structure 3 includes a bottom plate 31, a top plate 32 and two support plates 33, wherein the two support plates 33 are arranged opposite to each other and are both connected between the bottom plate 31 and the top plate 32. Preferably, one end of the support plate 33 is welded to the bottom plate 31 and the other end is welded to the top plate 32, and the connection strength is relatively large.

[0045] Optionally, the side support structure 3 further includes a reinforcing plate 34, which is connected between the two support plates 33 to improve the support strength of the side support structure 3. Preferably, the two ends of the reinforcing plate 34 are welded to the two support plates 33 respectively, resulting in a greater connection strength.

[0046] Furthermore, the base plate 31 is connected to the leading edge strip 10 of the first beam 11 and the leading edge strip 10 of the second beam 12, and the connection position between the base plate 31 and the leading edge strip 10 of the first beam 11 and the leading edge strip 10 of the second beam 12 is adjustable. For example, the base plate 31 is bolted to the leading edge strip 10 of the first beam 11 and the leading edge strip 10 of the second beam 12, thereby allowing adjustment of the spacing between the two side support structures 3 according to the size of the test piece 100, improving the versatility of the bird strike test support structure at the leading edge of the aircraft wing.

[0047] Furthermore, the top plate 32 is provided with a connecting component, which extends between the partition 103 of the test piece 100 and the front edge rib 104 of the test piece 100. Both the partition 103 and the front edge rib 104 are connected to the connecting component. By providing the connecting component, the side support structure 3 supports the test piece 100.

[0048] For example, see Figure 4 and Figure 5 The connecting assembly includes a steel plate 35 and a T-shaped corner piece 36. The steel plate 35 is connected to the top plate 32 and extends between the partition 103 and the leading edge rib 104 of the test piece 100. The bottom of the T-shaped corner piece 36 is connected to the steel plate 35, and the extended end of the T-shaped corner piece 36 is connected to the leading edge rib 104. In this embodiment, the extended end of the T-shaped corner piece 36 is connected to the inner wall of the leading edge rib 104.

[0049] Preferably, the steel plate 35 and the T-shaped corner piece 36, as well as the T-shaped corner piece 36 and the partition plate 103 and the leading edge rib 104, are all bolted together, facilitating disassembly for bird strike testing of the next test piece 100. More preferably, the steel plate 35 has a plurality of through holes evenly distributed on it, and the connection between the bottom of the steel plate 35 and the T-shaped corner piece 36 is achieved by bolts screwed into the through holes. On the other hand, the plurality of through holes evenly distributed on the steel plate 35 can be used as positioning references to position the test piece 100.

[0050] In this embodiment, one end of the two leading edge panels 101 of the test specimen 100 is spaced apart from the adjacent side support structure 3, with a gap range of 5-10mm. The other end of the two leading edge panels 101 of the test specimen 100 is also spaced apart from the adjacent side support structure 3, with a gap range of 5-10mm. This avoids the leading edge panels 101 from deforming and contacting the side support structure 3 under bird strike conditions, making the test process closer to the real situation, thereby obtaining a more accurate bird strike resistance capability of the test specimen 100.

[0051] The bird strike test support structure for the leading edge of an aircraft wing provided in this embodiment has two aspects. Firstly, the bottom support structure 1 supports two leading edge panels 101, and the side support structure 3 supports the bulkhead 103. The bottom support structure 1 provides support for the test piece 100, while the side support structures 3 constrain the cut-off boundary of the test piece 100, making the boundary conditions more similar to the actual structure. This ensures that the deformation of the test piece 100 during the bird strike test is closer to the deformation of the actual structure under the same working conditions, making the test process closer to reality. This results in a more accurate assessment of the bird strike resistance of the test piece 100. Furthermore, the spacing between the two side support structures 3 can be adjusted, making it suitable for bird strike tests on test pieces 100 of different sizes. It is reusable, saving costs. Secondly, the bird strike test support structure for the leading edge of an aircraft wing provided in this embodiment can also be used as a positioning fixture for assembling the test piece 100. It can be used to position the various parts of the test piece 100, facilitating assembly, reducing assembly tooling, and saving development costs.

[0052] Example 2

[0053] This embodiment provides a bird strike test support structure for the leading edge of an aircraft wing, which is suitable for cases where one end of the test piece 100 in the spanwise direction is a free end and the other end is a cut-off end.

[0054] The bird strike test support structure provided in this embodiment differs structurally from that in Embodiment 1. Specifically, this embodiment includes a bottom support structure 1 and a side support structure 3. The bottom support structure 1 provides support for the test piece 100, and the side support structure 3 provides constraint support for the cut-off boundary of the test piece 100, making the boundary conditions more similar to the real structure. This ensures that the deformation of the test piece 100 during the bird strike test is closer to the deformation of the actual structure under the same working conditions, and the test process is closer to the real situation, thereby obtaining a more accurate bird strike resistance capability of the test piece 100.

[0055] Example 3

[0056] This embodiment provides a bird strike test support structure for the leading edge of an aircraft wing, which is suitable for cases where both ends of the test piece 100 in the spanwise direction are free ends.

[0057] The bird strike test support structure provided in this embodiment differs structurally from that in Embodiments 1 and 2. Specifically, this embodiment only provides a bottom support structure 1, which provides support for the test piece 100, making the boundary conditions more similar to the real structure. This ensures that the deformation of the test piece 100 during the bird strike test is closer to the deformation of the actual structure under the same working conditions, making the test process closer to the real situation, and thus obtaining a more accurate bird strike resistance capability of the test piece 100.

[0058] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A bird strike test support structure for the leading edge of an aircraft wing, characterized in that, include: The bottom support structure (1) includes a first beam (11), a second beam (12), a third beam (13) and a fourth beam (14) connected end to end. The rear edge strips (30) of the first beam (11), the second beam (12), the third beam (13) and the fourth beam (14) are fixed to the test wall. The first beam (11) and the second beam (12) are arranged opposite to each other along the width direction of the bottom support structure (1). The two front edge wall panels (101) of the test piece (100) are respectively connected to the front edge strip (10) of the first beam (11) and the front edge strip (10) of the second beam (12). A side support structure (3) is provided with a bottom plate (31) connected to the front edge strip (10) of the first beam (11) and the front edge strip (10) of the second beam (12). The top plate (32) of the side support structure (3) is provided with a connecting component. The connecting component extends between the partition plate (103) of the test piece (100) and the front edge rib (104) of the test piece (100). The partition plate (103) and the front edge rib (104) are both connected to the connecting component. The connecting assembly includes a steel plate (35) and a T-shaped corner piece (36). The steel plate (35) is connected to the top plate (32) and extends between the partition (103) of the test piece (100) and the leading edge rib (104) of the test piece (100). The bottom of the T-shaped corner piece (36) is connected to the steel plate (35), and the extended end of the T-shaped corner piece (36) is connected to the leading edge rib (104).

2. The bird strike test support structure for the leading edge of an aircraft wing according to claim 1, characterized in that, There are two side support structures (3), and the two side support structures (3) are respectively connected to the two cut ends of the test piece (100), and the distance between the two side support structures (3) is adjustable.

3. The bird strike test support structure for the leading edge of an aircraft wing according to claim 1, characterized in that, The first beam (11), the second beam (12), the third beam (13) and the fourth beam (14) are all C-shaped beams. The first beam (11), the second beam (12), the third beam (13) and the fourth beam (14) all include the front edge strip (10), the web plate (20) and the rear edge strip (30). The front edge strip (10) and the rear edge strip (30) are arranged opposite to each other and connected by the web plate (20).

4. The bird strike test support structure for the leading edge of an aircraft wing according to claim 3, characterized in that, The bottom support structure (1) further includes a plurality of connecting plates (15), which are spaced apart between the web (20) of the first beam (11) and the web (20) of the second beam (12), and the plurality of ribs (102) of the test piece (100) are connected one-to-one to the plurality of connecting plates (15).

5. The bird strike test support structure for the leading edge of an aircraft wing according to claim 3, characterized in that, The first beam (11), the second beam (12), the third beam (13) and the fourth beam (14) each include a plurality of reinforcing ribs (40). The plurality of reinforcing ribs (40) are spaced apart between the front edge strip (10) and the rear edge strip (30), and the reinforcing ribs (40) are connected to the web plate (20). The two ends of the reinforcing ribs (40) are respectively connected to the front edge strip (10) and the rear edge strip (30).

6. The bird strike test support structure for the leading edge of an aircraft wing according to any one of claims 1-5, characterized in that, The bird strike test support structure at the leading edge of the aircraft wing also includes L-shaped corner pieces (2). Several L-shaped corner pieces (2) are provided. One side of some of the L-shaped corner pieces (2) is sequentially connected to one of the leading edge panels (101) of the test piece (100), and the other side is sequentially connected to the leading edge strip (10) of the first beam (11). One side of the remaining L-shaped corner pieces (2) is sequentially connected to the other leading edge panel (101) of the test piece (100), and the other side is sequentially connected to the leading edge strip (10) of the second beam (12).

7. The bird strike test support structure for the leading edge of an aircraft wing according to any one of claims 1-5, characterized in that, One of the leading edge panels (101) of the test piece (100) is spaced apart from the leading edge strip (10) of the first beam (11), and the other leading edge panel (101) of the test piece (100) is spaced apart from the leading edge strip (10) of the second beam (12).

8. The bird strike test support structure for the leading edge of an aircraft wing according to any one of claims 1-5, characterized in that, The side support structure (3) includes the bottom plate (31), the top plate (32) and two support plates (33). The two support plates (33) are arranged opposite to each other and are connected between the bottom plate (31) and the top plate (32). The bottom plate (31) is tunably connected to the front edge strip (10) of the first beam (11) and the front edge strip (10) of the second beam (12).

9. The bird strike test support structure for the leading edge of an aircraft wing according to claim 8, characterized in that, The side support structure (3) also includes a reinforcing plate (34), which is connected between the two support plates (33).

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