Bird impact test piece

Abstract

The invention belongs to the technical field of aircraft structure design, and particularly relates to a bird impact test piece. The test piece comprises a composite flat plate (5), an inner pressing plate (4), an outer pressing plate (6) and a plurality of composite partition plates, wherein the composite flat plate (5) is provided with a plate surface for bearing bird impact; the inner pressing plate (4) and the outer pressing plate (6) are of frame structures and are connected to the two sides of the plate face of the composite flat plate (5) in a pressed mode respectively, and the inner pressing plate (4) is connected with a test clamp. Each composite partition plate comprises a composite partition plate web plate (1), a lower edge strip and side edge strips (2), the plate surface of the composite partition plate web plate (1) is perpendicular to the plate surface of the composite flat plate (5), the composite partition plate web plate (1) is connected with the composite flat plate (5) through the lower edge strip (3) at the bottom, and the composite partition plate web plate (1) is connected with the test fixture through the side edge strips (2) on the two sides. The bird impact test structure of the airplane with the composite partition plate is simplified, and the test reliability is improved.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft structure design, and in particular relates to a bird strike test piece. Background Art

[0002] Conventional aircraft with composite partition structure bird strike test pieces need to carry all the parts connected to the partition. If the anti-bird strike performance is only studied for the partition spacing, partition thickness, partition connection method, etc., due to the large scale of conventional test pieces, there are many uncontrollable factors in the bird strike test process, which will interfere with the test results. Summary of the invention

[0003] In order to solve the above problems, the present application provides a bird strike test piece, which mainly includes:

[0004] Composite flat plate with a board surface that bears bird strikes;

[0005] The inner pressure plate and the outer pressure plate are frame structures, respectively pressed on both sides of the plate surface of the composite plate, and the inner pressure plate is connected to the test fixture;

[0006] A plurality of composite partitions, each of which comprises a composite partition web, a lower edge strip and a side edge strip, the plate surface of the composite partition web is perpendicular to the plate surface of the composite flat plate, the composite partition web is connected to the composite flat plate through the lower edge strip at the bottom, and the composite partition web is connected to the test fixture through the side edge strips on both sides.

[0007] Preferably, the inner pressure plate and the outer pressure plate have through holes. After the composite flat plate is crimped between the inner pressure plate and the outer pressure plate, the through holes of the inner pressure plate and the outer pressure plate are opposite to each other, and the inner pressure plate, the composite flat plate and the outer pressure plate are connected as a whole by penetrating bolts.

[0008] Preferably, the through bolt is further connected to the test fixture.

[0009] Preferably, the composite material partitions include at least two, and the composite material flat plate is evenly divided into three sections along the length direction of the composite material flat plate.

[0010] Preferably, the spacing between the webs of adjacent composite bulkheads is set to be the same as the spacing between bulkheads on the aircraft box section beam.

[0011] Preferably, the lower edge strip of the composite partition is connected to the composite flat plate by bolts.

[0012] Preferably, each side edge strip of the composite partition is connected to the test fixture via two rows of bolts.

[0013] The present application simplifies the bird strike test structure of an aircraft with a composite partition and improves the credibility of the test. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is an axial view of a test piece of a preferred embodiment of a bird strike test piece of the present application.

[0015] Figure 2 This application Figure 1 Schematic diagram of the positional relationship between the inner and outer pressure plates and the composite flat plate of the illustrated embodiment.

[0016] Among them, 1-front edge outer panel, 2-side edge strip, 3-lower edge strip, 4-inner pressure plate, 5-composite flat plate, 6-outer pressure plate. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0018] The present application provides a bird strike test piece, such as Figure 1-Figure 2 As shown, it mainly includes:

[0019] The composite plate 5 has a plate surface for bearing bird strikes;

[0020] The inner pressure plate 4 and the outer pressure plate 6 are frame structures, respectively pressed on both sides of the plate surface of the composite flat plate 5, and the inner pressure plate 4 is connected to the test fixture;

[0021] Multiple composite partitions, each composite partition includes a composite partition web 1, a lower edge strip and a side edge strip 2, the plate surface of the composite partition web 1 is perpendicular to the plate surface of the composite flat plate 5, the composite partition web 1 is connected to the composite flat plate 5 through the lower edge strip 3 at the bottom, and the composite partition web 1 is connected to the test fixture through the side edge strips 2 on both sides.

[0022] The present application simulates the partitions on the plane of the aircraft box section tail wing box section beam through multiple composite partitions, connects the side edge strips on the composite partitions to the test fixture to simulate the connection between the partitions and other aircraft structures, and connects the inner pressure plate 4 to the test fixture to simulate the connection between the bird strike plate surface and the aircraft structure. The present application solves the problem of simplified simulation of aircraft with composite partition structures in bird strike tests.

[0023] In some optional embodiments, the inner pressure plate 4 and the outer pressure plate 6 have through holes. After the composite flat plate 5 is crimped between the inner pressure plate 4 and the outer pressure plate 6, the through holes of the inner pressure plate 4 and the outer pressure plate 6 are opposite to each other, and the inner pressure plate 4, the composite flat plate 5 and the outer pressure plate 6 are connected as a whole by penetrating bolts.

[0024] In this embodiment, the inner pressure plate 4, the composite flat plate 5 and the outer pressure plate 6 are crimped together by multiple rows of screws, which can not only protect the composite flat plate through the inner and outer pressure plates, but also further enhance the overall structural strength and facilitate connection with the test fixture.

[0025] In some optional embodiments, the through bolts are further connected to the test fixture. In this embodiment, the bolts that penetrate the inner pressure plate 4, the composite flat plate 5 and the outer pressure plate 6 are further connected to the test fixture, so that the force on the composite flat plate 5 is transmitted to the test fixture through the inner and outer pressure plates and the screws, preventing the connection between the inner and outer pressure plates and the composite flat plate from failing prematurely.

[0026] In some optional embodiments, the composite material partitions include at least two, and the composite material flat plate 5 is evenly divided into three sections along the length direction of the composite material flat plate 5. Figure 1 The two composite material partitions evenly distributed on the composite material flat plate 5 can provide a better strengthening and supporting effect on the composite material flat plate 5 .

[0027] In some optional embodiments, the spacing between adjacent composite bulkhead webs 1 is set to be the same as the spacing between bulkheads on the aircraft box beam. This embodiment can more accurately simulate the aircraft structure, and thus accurately assess whether the existing aircraft bulkhead spacing design meets the bird strike resistance requirements.

[0028] In some optional embodiments, the lower edge strip 3 of the composite partition is connected to the composite flat plate 5 by bolts. This embodiment can strengthen the connection strength between the composite partition and the composite flat plate 5, and transfer the force on the composite flat plate 5 to the composite partition.

[0029] In some optional embodiments, each side edge strip 2 of the composite partition is connected to the test fixture via two rows of bolts.

[0030] This embodiment can enhance the connection strength between the composite partition plate and the test fixture.

[0031] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A bird strike test piece, characterized in that: include: A composite flat plate (5) having a plate surface for bearing bird strikes; The inner pressure plate (4) and the outer pressure plate (6) are frame structures, respectively pressed on both sides of the plate surface of the composite flat plate (5), and the inner pressure plate (4) is connected to the test fixture; A plurality of composite partitions, each of which comprises a composite partition web (1), a lower edge strip and side edge strips (2); the surface of the composite partition web (1) is perpendicular to the surface of the composite flat plate (5); the composite partition web (1) is connected to the composite flat plate (5) via the lower edge strip (3) at the bottom; and the composite partition web (1) is connected to a test fixture via the side edge strips (2) on both sides.

2. The bird strike test piece according to claim 1, characterized in that: The inner pressure plate (4) and the outer pressure plate (6) are provided with through holes. After the composite flat plate (5) is crimped between the inner pressure plate (4) and the outer pressure plate (6), the through holes of the inner pressure plate (4) and the outer pressure plate (6) are opposite to each other, and the inner pressure plate (4), the composite flat plate (5) and the outer pressure plate (6) are connected as a whole by penetrating bolts.

3. The bird strike test piece according to claim 2, characterized in that: The through bolts further connect the test fixture.

4. The bird strike test piece according to claim 1, characterized in that: The composite material partitions include at least two, and the composite material flat plate (5) is evenly divided into three sections along the length direction of the composite material flat plate (5).

5. The bird strike test piece according to claim 1, characterized in that: The spacing between adjacent composite bulkhead webs (1) is set to be the same as the spacing between bulkheads on the aircraft box section beam.

6. The bird strike test piece according to claim 5, characterized in that: The lower edge strip (3) of the composite material partition plate is connected to the composite material flat plate (5) via bolts.

7. The bird strike test piece according to claim 1, characterized in that: Each side edge strip (2) of the composite material partition is connected to the test fixture via two rows of bolts.

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