Lightning protection test piece for movable control surface of airplane

Abstract

An airplane movable control surface lightning protection test piece comprises an upper wall plate, a lower wall plate and a supporting beam. The portion, close to the wingtip, of the outer side of the upper wall plate is a first area, the other portions of the upper wall plate are second areas, flame spraying aluminum is sprayed to the first area, and flame spraying aluminum is sprayed to rib occupying and beam occupying portions of the second area; the part, close to the wing tip, of the outer side of the lower wall plate is a third area, the part, close to the wing root, of the outer side of the lower wall plate is a fourth area, the part, close to the wing root, of the outer side of the lower wall plate is a sixth area, the other parts are fifth areas, flame spraying aluminum is sprayed to the third area, flame spraying aluminum is sprayed to the fourth area, and copper nets are laid on rib occupying and beam occupying parts of the fifth area; and copper meshes are laid at rib occupation and beam occupation positions in the sixth area.

Description

Technical Field

[0001] The present application belongs to the technical field of design of lightning protection test pieces for movable control surfaces of aircraft, and specifically relates to a lightning protection test piece for movable control surfaces of aircraft. Background Art

[0002] The lightning protection test of aircraft movable control surfaces is used to verify the lightning protection effect of lightning protection measures. Currently, multiple movable control surface lightning protection test pieces are mostly designed. Each movable control surface lightning protection test piece verifies the lightning protection effect of a single lightning protection measure respectively, and the test cycle and cost are relatively high.

[0003] This application is proposed in view of the above-mentioned technical defects. Utility Model Content

[0004] The purpose of the present application is to provide an aircraft movable control surface lightning protection test piece to overcome or alleviate at least one of the known technical defects.

[0005] The technical solution of this application is:

[0006] An aircraft movable control surface lightning protection test piece includes: an upper wall plate, a lower wall plate, and a support beam;

[0007] The upper wall panels, lower wall panels and support beams are made of composite materials;

[0008] The front of the upper wall panel is connected to the front of the lower wall panel, and the support beam is supported between the rear of the upper wall panel and the rear of the lower wall panel. A plurality of support ribs are formed on the inner side of the upper wall panel, and each support rib is connected to the lower wall panel and the support beam;

[0009] The outer side of the upper wall panel near the wing tip is area 1, and the rest is area 2. Area 1 is sprayed with flame-sprayed aluminum with a thickness of 0.254 to 0.305 mm or a maximum resistance of 0.5 mΩ. Area 2 is sprayed with flame-sprayed aluminum with a thickness of 0.102 to 0.175 mm or a maximum resistance of 1.3 mΩ at the rib and beam positions.

[0010] The outer side of the lower wall panel near the wing tip is area No. 3, behind area No. 3 is area No. 4, the part near the wing root is area No. 6, and the rest is area No. 5. Among them, area No. 3 is sprayed with flame-sprayed aluminum with a thickness of 0.254 to 0.305 mm or a maximum resistance of 0.5 mΩ, area No. 4 is sprayed with flame-sprayed aluminum with a thickness of 0.102 to 0.175 mm or a maximum resistance of 1.3 mΩ, area No. 5 is covered with a copper mesh with a nominal unit area mass of 73 g / m2 at the rib and beam occupying parts, and area No. 6 is covered with a copper mesh with a nominal unit area mass of 142 g / m2 at the rib and beam occupying parts.

[0011] According to at least one embodiment of the present application, the upper wall panel, the lower wall panel, and the support beam in the above-mentioned aircraft movable control surface lightning protection test piece are respectively integrally formed using a VARI liquid molding process.

[0012] According to at least one embodiment of the present application, the upper wall panel, the lower wall panel, and the support beam in the above-mentioned aircraft movable control surface lightning protection test piece are connected by fasteners.

[0013] According to at least one embodiment of the present application, the No. 1 area on the upper wall panel of the above-mentioned aircraft movable control surface lightning protection test piece is an area within a range of 500 mm along the extension.

[0014] According to at least one embodiment of the present application, in the above-mentioned aircraft movable control surface lightning protection test piece, area No. 3 on the lower wall panel is the area within the range of 250 mm along the extension, and area No. 4 is the area within the range of 250 to 500 mm along the extension. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 Schematic diagram of an aircraft movable control surface lightning protection test piece provided in an embodiment of the present application;

[0016] Figure 2 This is a transverse cross-sectional view of an aircraft movable control surface lightning protection test piece provided in an embodiment of the present application;

[0017] Figure 3 This is a schematic diagram of the distribution of area No. 1 and area No. 2 on the upper wall plate provided in an embodiment of the present application;

[0018] Figure 4 This is a schematic diagram of the distribution of area No. 3, area No. 4, and area No. 5 on the lower wall panel provided in an embodiment of the present application;

[0019] in:

[0020] 1-Upper wall panel; 2-Lower wall panel; 3-Support beam.

[0021] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0022] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0023] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application means that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0024] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0025] An aircraft movable control surface lightning protection test piece includes an upper wall plate 1, a lower wall plate 2, and a support beam 3. Figure 1-Figure 2 shown.

[0026] The upper wall panel 1, the lower wall panel 2 and the support beam 3 are made of composite materials and can be integrally formed using a VARI liquid molding process.

[0027] The front of the upper wall panel 1 is connected to the front of the lower wall panel 2, and the support beam 3 is supported between the rear of the upper wall panel 1 and the rear of the lower wall panel 2. Multiple support ribs can be formed on the inner side of the upper wall panel 1, and each support rib is connected to the lower wall panel 2 and the support beam 3.

[0028] The upper wall panel 1, the lower wall panel 2 and the support beam 3 form the shape of the movable control surface of the aircraft as a whole, and can be connected by fasteners.

[0029] In the movable control surfaces of an aircraft, the upper and lower wall panels near the wingtips are mostly lightning attachment areas, which are severely struck by lightning and require stronger lightning protection measures. The rest are lightning swept areas and require lightning protection measures to maintain electrical continuity of the entire control surface.

[0030] The outer side of the upper wall panel 1 near the wing tip is area 1, and the rest is area 2. Area 1 is sprayed with flame-sprayed aluminum with a thickness of 0.254 to 0.305 mm or a maximum resistance of 0.5 mΩ. Area 2 is sprayed with flame-sprayed aluminum with a thickness of 0.102 to 0.175 mm or a maximum resistance of 1.3 mΩ at the rib and beam positions. Figure 3 shown.

[0031] Area No. 1 on the upper wall panel 1 is the area within 500 mm along the extension.

[0032] The outer side of the lower wall panel 2 near the wing tip is area No. 3, behind area No. 3 is area No. 4, the part near the wing root is area No. 6, and the rest is area No. 5. Among them, area No. 3 is sprayed with flame-sprayed aluminum with a thickness of 0.254-0.305 mm or a maximum resistance of 0.5 mΩ, area No. 4 is sprayed with flame-sprayed aluminum with a thickness of 0.102-0.175 mm or a maximum resistance of 1.3 mΩ, area No. 5 is covered with a copper mesh with a nominal unit area mass of 73 g / m2 at the rib and beam positions, and area No. 6 is covered with a copper mesh with a nominal unit area mass of 142 g / m2 at the rib and beam positions. Figure 4 shown.

[0033] The third area on the lower wall panel 2 is an area within a range of 250 mm along the extension, and the fourth area is an area within a range of 250 to 500 mm along the extension.

[0034] In the aircraft movable control surface lightning protection test piece disclosed in the above embodiment, taking into account the actual different lightning strikes on different components and different areas of the test piece, lightning protection measures are set up in different areas, and multiple lightning protection measures are integrated on the same test piece, which can shorten the test cycle, save test costs, and compare the effects of different lightning protection measures for improvement. For example, the effect of the lightning protection measures in area No. 1 on the upper wall panel 1 can be compared with the effects of the lightning protection measures in areas No. 3 and No. 4 on the lower wall panel 2 as a control group, and the effects of the lightning protection measures in areas No. 3 and No. 4 on the lower wall panel 2 themselves can also be used as a control group for comparison.

[0035] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A lightning protection test piece for an aircraft movable control surface, characterized in that: include: Upper wall plate (1), lower wall plate (2), support beam (3); The upper wall plate (1), the lower wall plate (2) and the support beam (3) are made of composite materials; The front portion of the upper wall panel (1) is connected to the front portion of the lower wall panel (2), the support beam (3) is supported between the rear portion of the upper wall panel (1) and the rear portion of the lower wall panel (2), a plurality of support ribs are formed on the inner side of the upper wall panel (1), and each support rib is connected to the lower wall panel (2) and the support beam (3); The outer side of the upper wall plate (1) near the wing tip is area No. 1, and the rest of the area is area No. 2, wherein area No. 1 is sprayed with flame-sprayed aluminum with a thickness of 0.254 to 0.305 mm or a maximum resistance of 0.5 mΩ, and area No. 2 is sprayed with flame-sprayed aluminum with a thickness of 0.102 to 0.175 mm or a maximum resistance of 1.3 mΩ at the rib and beam positions; The outer side of the lower wall plate (2) near the wing tip is area No. 3, behind area No. 3 is area No. 4, the part near the wing root is area No. 6, and the rest is area No.

5. Among them, area No. 3 is sprayed with flame-sprayed aluminum with a thickness of 0.254-0.305 mm or a maximum resistance of 0.5 mΩ, area No. 4 is sprayed with flame-sprayed aluminum with a thickness of 0.102-0.175 mm or a maximum resistance of 1.3 mΩ, area No. 5 is covered with a copper mesh with a nominal unit area mass of 73 g / m2 at the rib and beam positions, and area No. 6 is covered with a copper mesh with a nominal unit area mass of 142 g / m2 at the rib and beam positions.

2. The aircraft movable control surface lightning protection test piece according to claim 1, characterized in that: The upper wall plate (1), the lower wall plate (2) and the support beam (3) are respectively integrally formed using a VARI liquid forming process.

3. The aircraft movable control surface lightning protection test piece according to claim 1, characterized in that: The upper wall plate (1), the lower wall plate (2) and the support beam (3) are connected by fasteners.

4. The aircraft movable control surface lightning protection test piece according to claim 1, characterized in that: The first area on the upper wall plate (1) is an area within a range of 500 mm along the extension.

5. The aircraft movable control surface lightning protection test piece according to claim 1, characterized in that: The third area on the lower wall plate (2) is an area within a range of 250 mm along the extension, and the fourth area is an area within a range of 250 to 500 mm along the extension.

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