A bird strike test piece

Abstract

The application 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. The composite flat plate (5) has a plate surface for bearing bird impact. The inner pressing plate (4) and the outer pressing plate (6) are frame structures and are respectively pressed on both sides of the plate surface of the composite flat plate (5). The inner pressing plate (4) is connected with a test fixture. Each composite partition plate comprises a composite partition plate web (1), a lower edge strip and a side edge strip (2). The plate surface of the composite partition plate web (1) is perpendicular to the plate surface of the composite flat plate (5). The composite partition plate web (1) is connected with the composite flat plate (5) through the lower edge strip (3) at the bottom. The composite partition plate web (1) is connected with the test fixture through the side edge strips (2) at both sides. The application simplifies the bird impact test structure of the aircraft with the composite partition plates and improves the test reliability.

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 bird strike test specimens with composite bulkhead structures require the inclusion of all components connected to the bulkheads. If bird strike resistance studies are conducted solely on factors such as bulkhead spacing, thickness, and connection methods, the large size of conventional test specimens can lead to numerous uncontrollable factors during bird strike testing, potentially interfering with 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 panel with a bird strike-resistant surface;

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

[0006] Multiple composite partitions, each composite partition includes 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 pressed 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 through 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 adjacent webs of the composite bulkheads is set to be the same as the spacing between bulkheads on the aircraft box section beams.

[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, thereby improving the reliability 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 the 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 embodiment shown.

[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 solutions and advantages of the implementation of this application clearer, the technical solutions in the implementation of this application will be described in more detail below in conjunction with the drawings in the implementation of this application. In the drawings, the same or similar numbers 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 should not 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 conjunction with the drawings.

[0018] This 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] This application uses multiple composite bulkheads to simulate bulkheads on the plane of the aircraft's box section and tail wing box beam. Side edge strips on the composite bulkheads are connected to a test fixture to simulate the connection between the bulkheads and other aircraft structures. Furthermore, an internal pressure plate (4) is connected to the test fixture to simulate the connection between the perimeter of the bird strike panel and the aircraft structure. This application solves the problem of simplifying the simulation of aircraft structures with composite bulkheads 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 pressed 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, and the inner pressure plate 4, the composite flat plate 5 and the outer pressure plate 6 are connected as a whole by through 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 plate 5, and the outer pressure plate 6 are further connected to the test fixture, thereby transmitting the force on the composite plate 5 to the test fixture through the inner and outer pressure plates and the screws, thereby preventing premature failure of the connection between the inner and outer pressure plates and the composite plate.

[0026] In some optional embodiments, the composite material partitions include at least two, which evenly divide the composite material flat plate 5 into three sections along the length direction of the composite material flat plate 5. Figure 1 The two composite partitions evenly distributed on the composite flat plate 5 can provide better reinforcement and support for the composite 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 further 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 transmit the force acting 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 and the test fixture.

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

Claims

1. A bird strike test piece, characterized in that: include: A composite flat plate (5) having a surface for bearing bird strikes; The inner pressure plate (4) and the outer pressure plate (6) are frame structures and are respectively pressed onto both sides of the plate surface of the composite flat plate (5). The inner pressure plate (4) is connected to the test fixture. A plurality of composite partitions, each composite partition comprising a composite partition web (1), a lower edge strip and side edge strips (2), the surface of the composite partition web (1) being perpendicular to the surface of the composite flat plate (5), the composite partition web (1) being connected to the composite flat plate (5) via the lower edge strip (3) at the bottom, and the composite partition web (1) being connected to the test fixture via the side edge strips (2) on both sides; The composite partitions include at least two, and the composite flat plate (5) is evenly divided into three sections along the length direction of the composite flat plate (5). The spacing between adjacent composite partition webs (1) is set to be the same as the spacing between partitions on the aircraft box section beam.

2. The bird strike test piece according to claim 1, wherein: The inner pressure plate (4) and the outer pressure plate (6) have through holes. After the composite flat plate (5) is pressed 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 through bolts.

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

4. The bird strike test piece according to claim 1, wherein: The lower edge strip (3) of the composite material partition is connected to the composite material flat plate (5) via bolts.

5. The bird strike test piece according to claim 1, wherein: 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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