Conductive nail sleeve for lightning protection shielding layer of aircraft

Abstract

The utility model relates to a conductive nail sleeve for a lightning protection shielding layer of an aircraft, which comprises a main body arranged along the same axis, a clamping ring used for clamping a copper net and a positioning ring used for positioning a screw, and the main body comprises a main body upper part used for being connected with the clamping ring and a main body lower part used for being connected with the positioning ring. A placing hole penetrating through the upper part and the lower part of the main body is formed in the main body, the positioning ring is inserted into the placing hole, and during use, the inner wall surface of the positioning ring and the outer wall surface of the upper part of the main body clamp a copper net and then are placed in a composite material layer. According to the utility model, the conductivity of the connection point is improved, the average resistance is reduced to 1.5 omega from the previous 15 omega, and the overall qualified rate of the product is improved; the nail sleeve and the re-checking material layer are co-cured and molded, so that the connection strength is high, and the problem that the electric conductivity of the aircraft is reduced due to vibration is avoided; and the positioning ring below the screw sleeve adopts a movable mounting mode, so that mounting deviation caused by non-alignment of the screw can be avoided.

Description

Technical Field

[0001] The utility model relates to the field of lightning protection shielding, in particular to a conductive nail sleeve for an aircraft lightning protection shielding layer. Background Art

[0002] With the development of science and technology and the composite materials industry, people are constantly putting forward new demands on the functions of composite materials. Traditional composite materials are usually insulating materials. Aircraft in the cloud layer need to evacuate the accumulated charge on the surface to avoid breakdown of equipment. The existing aircraft lightning protection shielding layer is to arrange a layer of copper mesh in the composite material, and then use nail sleeves to press on the copper mesh to form an integral shape. Because the nail sleeve and copper mesh in this structure adopt a non-fixed connection method, during the composite material molding process, resin can easily enter the gap between the two, causing the connection between the copper mesh and the nail sleeve to fail, causing great harm to aircraft equipment. To this end, the utility model proposes a conductive nail sleeve for an aircraft lightning protection shielding layer. Utility Model Content

[0003] To address the problem that the connection between the conductive nail sleeve and the copper mesh in the existing aircraft lightning protection shield is prone to failure, the utility model proposes a conductive nail sleeve for the aircraft lightning protection shield. The specific technical solution is as follows:

[0004] A conductive nail sleeve for an aircraft lightning protection shielding layer includes a main body, a clamping ring and a positioning ring. The main body includes an upper part for connecting to the clamping ring and a lower part for connecting to the positioning ring. A placement hole is provided in the main body that passes through the upper and lower parts of the main body. The positioning ring is inserted into the placement hole. When in use, the inner wall surface of the positioning ring and the outer wall surface of the upper part of the main body clamp a copper mesh and are then placed in a composite material layer.

[0005] Furthermore, the inner wall surface of the positioning ring is a frustum surface, and correspondingly, the outer wall surface of the upper part of the main body is a frustum surface.

[0006] Furthermore, an interference fit is provided between the main body and the snap ring.

[0007] Furthermore, the placement hole includes a frustum section arranged in the upper part of the main body and a first cylindrical section and a second cylindrical section arranged in the lower part of the main body, the first cylindrical section connects the frustum section and the second cylindrical section, the inner diameter of the first cylindrical section is larger than the inner diameter of the positioning ring, and the inner diameter of the second cylindrical section is the same as the outer diameter of the positioning ring.

[0008] Furthermore, a groove is provided on the side wall of the second cylindrical section, and a convex ring that can cooperate with the groove is provided on the outer wall of the positioning ring. A boss is provided on the lower side of the convex ring. When the convex ring contacts the upper end face of the groove, the upper end face of the boss fits with the lower end face of the main body, and the outer diameter of the upper end face of the boss is larger than the outer diameter of the lower end face of the main body.

[0009] The beneficial effects of the present invention are:

[0010] 1. The conductivity of the connection point is improved, and the average resistance is reduced from the previous 15Ω to 1.5Ω, which improves the overall product qualification rate.

[0011] 2. The nail sleeve and the review material layer are co-cured and molded, with high connection strength, avoiding the problem of reduced conductivity caused by vibration of the aircraft.

[0012] 3. The positioning ring under the nail sleeve adopts a movable installation method, which can avoid installation deviation caused by misalignment of the screws. When the positioning ring under the nail sleeve is tightened by the bolts, the overall conductivity will be further improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0014] Figure 1 This is a schematic structural diagram of the conductive nail sleeve for the aircraft lightning protection shielding layer of the utility model;

[0015] Figure 2 This is a schematic diagram of the assembly of the clamping ring, main body and copper mesh of the utility model;

[0016] Figure 3 is a schematic diagram of a nail sleeve and a composite material layer in an embodiment;

[0017] Figure 4 It is a schematic diagram of the nail sleeve of the utility model in the aircraft protective cover.

[0018] In the figure: 1. Positioning pin; 2. Retaining ring; 3. Main body; 3.1. Upper part of main body; 3.2. Lower part of main body; 3.21. First cylindrical section; 3.22. Second cylindrical section; 3.3. Groove; 4. Positioning ring; 4.1. Protruding ring; 4.2. Boss; 5. Copper mesh; 6. Lightning shielding layer; 7. Mold. DETAILED DESCRIPTION

[0019] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0020] The utility model provides the following specific implementation scheme:

[0021] like Figure 1-4 As shown, the utility model provides a conductive nail sleeve for an aircraft lightning protection shielding layer, comprising a main body 3 placed along the same axis, a clamping ring 2 for clamping a copper mesh 5 and a positioning ring 4 for positioning screws. The main body 3 includes a main body upper part 3.1 for connecting with the clamping ring 2 and a main body lower part 3.2 for connecting with the positioning ring 4. A placement hole penetrating the main body upper part 3.1 and the main body lower part 3.2 is provided in the main body. The placement hole is used to place the screw, and the positioning ring 4 is inserted into the placement hole. When in use, the inner wall surface of the positioning ring 4 and the outer wall surface of the main body upper part 3.1 clamp the copper mesh 5 and then place it in the composite material layer.

[0022] Preferably, the inner wall surface of the positioning ring 4 is a frustum surface, and correspondingly, the outer wall surface of the upper part 3.1 of the main body is a frustum surface. The interference fit between the main body 3 and the clamping ring 2 can better clamp the copper mesh 5.

[0023] Preferably, the placement hole includes a frustum section arranged in the upper part 3.1 of the main body and a first cylindrical section 3.21 and a second cylindrical section 3.22 arranged in the lower part 3.2 of the main body, the first cylindrical section 3.21 connects the frustum section and the second cylindrical section 3.22, the inner diameter of the first cylindrical section 3.21 is larger than the inner diameter of the positioning ring 4, and the inner diameter of the second cylindrical section 3.22 is the same as the outer diameter of the positioning ring 4.

[0024] Preferably, a groove 3.3 is provided on the side wall of the second cylindrical section 3.22, and a convex ring 4.1 that can cooperate with the groove 3.3 is provided on the outer wall of the positioning ring 4. The width of the groove 3.3 in the axial direction of the positioning ring is greater than the width of the convex ring 4.1, and a boss 4.2 is provided on the lower side of the convex ring 4.1. When the convex ring 4.1 contacts the upper end surface of the groove 3.3, the upper end surface of the boss 4.2 is in contact with the lower end surface of the main body 3, and the outer diameter of the upper end surface of the boss 4.2 is greater than the outer diameter of the lower end surface of the main body 3.

[0025] Preferably, the main body 3, the clamping ring 2 and the positioning ring 4 are all made of titanium alloy.

[0026] When using the autoclave molding process and the vacuum curing furnace process to manufacture an aircraft protective cover, after laying the composite material layer in the mold 7, first use the main body 3 of the nail sleeve and the clamping ring 2 to clamp the copper mesh 5, then install the main body 3 on the preset positioning pin 1 in the composite material layer, and then lay the copper mesh 5 on the lightning protection shielding layer 6 of the composite material layer, send it into the oven for curing and molding, and finally take out the protective cover and install the positioning ring 4.

[0027] The utility model improves the conductivity of the connection point, and the average resistance is reduced from the previous 15Ω to 1.5Ω, thereby improving the overall qualified rate of the product; the nail sleeve and the review material layer are co-cured and formed, and the connection strength is high, which avoids the problem of reduced conductivity caused by vibration of the aircraft; the positioning ring 4 under the nail sleeve adopts a movable installation method, which can avoid installation deviation caused by misalignment of the screws. When the positioning ring 4 under the nail sleeve is tightened by the bolts, the overall conductivity will be further improved.

[0028] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and improvements may be made to the present invention without departing from the spirit and scope of the present invention, and such changes and improvements shall fall within the scope of the present invention as claimed.

Claims

1. A conductive nail sleeve for an aircraft lightning protection shield, characterized by: The invention comprises a main body (3), a clamping ring (2) and a positioning ring (4); the main body (3) comprises a main body upper part (3.1) for connecting with the clamping ring (2) and a main body lower part (3.2) for connecting with the positioning ring (4); a placement hole penetrating the main body upper part (3.1) and the main body lower part (3.2) is provided in the main body (3); the positioning ring (4) is inserted into the placement hole; when in use, the inner wall surface of the positioning ring (4) and the outer wall surface of the main body upper part (3.1) clamp the copper mesh (5) and then are placed in the composite material layer.

2. The conductive nail sleeve for an aircraft lightning protection shield according to claim 1, characterized in that: The inner wall surface of the positioning ring (4) is a frustum surface, and correspondingly, the outer wall surface of the upper part (3.1) of the main body is a frustum surface.

3. The conductive nail sleeve for an aircraft lightning protection shielding layer according to claim 1, characterized in that: An interference fit is provided between the main body (3) and the clamping ring (2).

4. The conductive nail sleeve for an aircraft lightning protection shielding layer according to claim 1, characterized in that: The placement hole comprises a frustum section arranged in the upper part (3.1) of the main body and a first cylindrical section (3.21) and a second cylindrical section (3.22) arranged in the lower part (3.2) of the main body. The first cylindrical section (3.21) connects the frustum section and the second cylindrical section (3.22). The inner diameter of the first cylindrical section (3.21) is larger than the inner diameter of the positioning ring (4), and the inner diameter of the second cylindrical section (3.22) is the same as the outer diameter of the positioning ring (4).

5. The conductive nail sleeve for an aircraft lightning protection shielding layer according to claim 4, characterized in that: A groove (3.3) is provided on the side wall of the second cylindrical section (3.22), a convex ring (4.1) capable of cooperating with the groove (3.3) is provided on the outer wall of the positioning ring (4), and a boss (4.2) is provided on the lower side of the convex ring (4.1). When the convex ring (4.1) contacts the upper end face of the groove (3.3), the upper end face of the boss (4.2) fits with the lower end face of the main body (3), and the outer diameter of the upper end face of the boss (4.2) is greater than the outer diameter of the lower end face of the main body (3).

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