Aircraft clamping piece type self-locking nut

Abstract

The utility model relates to the technical field of fasteners, and discloses an aircraft clamping piece type self-locking nut and clamping pieces, the aircraft clamping piece type self-locking nut comprises a first clamping piece, and a first mounting hole is formed in the center of the first clamping piece; one end of the first clamping piece is connected with a second clamping piece, and a second mounting hole is formed in the center of the second clamping piece; one end of the second clamping piece is connected with a third clamping piece, a fixing groove is formed in the center of the third clamping piece, a self-locking flange nut is installed in the fixing groove, the self-locking nut on an airplane is limited by the use environment, the installation condition is complex, the self-locking nut needs to be installed on an object to be fixed or an airplane panel through welding or pressing riveting, and the self-locking nut cannot be detached. The clamping piece type self-locking nut is additionally arranged, so that an airplane or an object to be fixed does not need to be modified, and time and production cost can be saved; in addition, the most easily damaged part is usually the nut part, in the past, an object needs to be disassembled and repaired after the nut is damaged, the process is complex, the clamping piece type nut can be quickly replaced, the object does not need to be disassembled, and operation is easy.

Description

Technical Field

[0001] The utility model relates to the technical field of fasteners, in particular to a clip-type self-locking nut for aircraft. Background Technique

[0002] The self-locking nuts on the aircraft are restricted by the use environment, and the installation conditions are complex. They need to be installed by welding or riveting on the object to be fixed or the aircraft panel, and they cannot be disassembled. For this reason, we have proposed a clip-type self-locking nut for aircraft. Content of the Utility Model

[0003] (1) Technical Problems to be Solved

[0004] Aiming at the deficiencies of the prior art, the utility model provides a clip-type self-locking nut for aircraft, which solves the above problems.

[0005] (2) Technical Solutions

[0006] To achieve the above object, the utility model provides the following technical solutions: A clip-type self-locking nut for aircraft, including clips, which includes a first clip, and a first mounting hole is provided at the center of the first clip; one end of the first clip is connected to a second clip, and a second mounting hole is provided at the center of the second clip; one end of the second clip is connected to a third clip, and a fixing groove is provided at the center of the third clip, and a self-locking flange nut is installed inside the fixing groove.

[0007] Preferably, a flange disc is provided at one end of the self-locking flange nut, and a spherical surface is provided at the other end of the self-locking flange nut, and a hexagonal column is installed between the flange disc and the spherical surface.

[0008] Preferably, an internal thread is provided at the center of the hexagonal column, and the internal thread and the third clip are limited so that it cannot be separated from the inside of the clip.

[0009] Preferably, the hexagonal column is installed inside the third clip, and when the hexagonal column is installed inside the fixing groove, the spherical surface on the surface of the self-locking flange nut is installed facing outward.

[0010] Preferably, a neck closing is provided at one end of the self-locking flange nut to achieve self-locking of the screw.

[0011] (3) Beneficial Effects

[0012] Compared with the prior art, the utility model provides a clip-type self-locking nut for aircraft, which has the following beneficial effects:

[0013] 1. The self-locking nuts on the aircraft are restricted by the use environment, and the installation conditions are complex. They need to be installed on the object to be fixed or the aircraft wall panel by welding or press riveting, and cannot be disassembled. Therefore, adding clip-type self-locking nuts does not require modification of the aircraft or the object to be fixed, which is conducive to saving time and production costs. In addition, the most easily damaged part is often the nut. In the past, when the nut was damaged, the object needed to be disassembled and repaired, and the process was complex. This clip-type nut can be quickly replaced without disassembling the object, and the operation is simple. Brief Description of the Drawings

[0014] Figure 1 It is a schematic structural diagram of a clip-type self-locking nut for an aircraft of the present invention;

[0015] Figure 2 It is a schematic structural diagram of the clip and the self-locking flange nut;

[0016] Figure 3 It is an exploded schematic diagram of the clip-type self-locking nut.

[0017] In the figure: 100, self-locking flange nut; 200, clip; 110, spherical surface; 120, flange plate; 130, internal thread; 140, hexagonal column; 210, first clip; 211, first mounting hole; 220, second clip; 221, second mounting hole; 230, third clip; 231, fixing groove. Detailed Embodiment

[0018] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0019] Please refer to Figures 1-3, an aircraft clip-type self-locking nut, comprising a clip 200, which includes a first clip 210, a first mounting hole 211 being provided at the center of the first clip 210; a second clip 220 being connected to one end of the first clip 210, a second mounting hole 221 being provided at the center of the second clip 220; a third clip 230 being connected to one end of the second clip 220, a fixing groove 231 being provided at the center of the third clip 230, and a self-locking flange nut 100 being installed inside the fixing groove 231, the first clip 210, the second clip 220 and the third clip 230 being connected in sequence to form a complete clip structure, the hexagonal column 140 of the self-locking flange nut 100 being installed in the fixing groove 231 of the third clip 230, ensuring that the spherical surface 110 is installed facing outward, so as to facilitate subsequent cooperation with fasteners (such as screws), and the clip structure is fixed to the components to be connected through the first mounting hole 211 and the second mounting hole 221.

[0020] Preferably, a flange 120 is provided at one end of the self-locking flange nut 100, and a spherical surface 110 is provided at the other end of the self-locking flange nut 100, and a hexagonal column 140 is installed between the flange 120 and the spherical surface 110, the hexagonal column 140 connects the spherical surface 110 and the flange 120, and the hexagonal column 140, the spherical surface 110 and the flange 120 constitute the self-locking flange nut 100.

[0021] Preferably, an internal thread 130 is provided at the center of the hexagonal column 140, and the internal thread 130 and the third clip 230 are limited and cannot be detached from the inside of the clip 200. The internal thread 130 is provided at the center of the hexagonal column 140 for cooperating with fasteners such as screws.

[0022] Preferably, a hexagonal column 140 is installed inside the third clip 230, and when the hexagonal column 140 is installed inside the fixing groove 231, the spherical surface 110 on the surface of the self-locking flange nut 100 is installed facing outward. The spherical surface 110 is located at one end of the nut and is designed to be a spherical shape, which helps to provide a larger contact area and a better sealing effect during installation.

[0023] Preferably, one end of the self-locking flange nut 100 is provided with a neck to achieve self-locking of the screw. The neck is designed at one end of the self-locking flange nut to achieve the self-locking function of the screw and prevent loosening.

[0024] Working principle: the hexagonal column is embedded in the positioning groove, so that the self-locking flange nut cannot rotate; the spherical surface of the self-locking flange nut faces outward, and the flange plate is limited by the second clip and the third clip, so that the self-locking flange nut cannot be detached from the clip.

[0025] In other words, the clip-type self-locking nut is used to fix objects; when the clip-type self-locking nut is used on an aircraft, the nut can be installed without disassembling the object to be fixed, which is beneficial to saving time and production costs; in addition, the most easily damaged part is often the nut part, and in the past, when the nut was damaged, the object needed to be disassembled and repaired, which was a complicated process. The clip-type nut can be quickly replaced without disassembling the object, and the operation is simple.

[0026] In some specific embodiments, since the aircraft may encounter air turbulence during flight, in order to ensure the reliability of the clip-on nut, reference is made to Figure 1 , Figure 2 and Figure 3 A first mounting hole is provided at the center of the first clip, and a second mounting hole is provided at the center of the second clip; the first clip and the second clip can be used to clamp the object to be fixed, and screws are passed through the first mounting hole and the second mounting hole, and fastened with the self-locking flange nut to fix the object.

[0027] In addition, an internal thread is provided at the center of the hexagonal column, and a neck is provided at one end of the internal thread to achieve self-locking; even if bumps are encountered, the screw will not easily fall off the self-locking flange nut.

[0028] In this way, when the clip nut needs to be fixed on the aircraft, the first clip and the second clip clamp the object to be fixed, and screws are used to pass through the first clip and the second clip clamp and connect with the self-locking flange nut, so that the first clip and the second clip clamp are tightly pressed against the object to be fixed by the tightening force of the screws; even if it encounters bumps, the clip nut will not fall off easily.

[0029] In the above scheme, in order to ensure the reliability of the connection between the clip and the self-locking flange nut, a flange plate is provided at one end of the self-locking flange nut; one end of the flange plate is connected to the hexagonal column, and the hexagonal column is embedded in the positioning groove, so that the self-locking flange nut cannot rotate; the flange plate is limited by the second clip and the third clip, so that the self-locking flange nut cannot be detached from the clip, which is more reliable.

[0030] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft clip-type self-locking nut, characterized in that: The invention comprises a clip (200), which comprises a first clip (210), wherein a first mounting hole (211) is provided at the center of the first clip (210); one end of the first clip (210) is connected to a second clip (220), wherein a second mounting hole (221) is provided at the center of the second clip (220); one end of the second clip (220) is connected to a third clip (230), wherein a fixing groove (231) is provided at the center of the third clip (230), and a self-locking flange nut (100) is installed inside the fixing groove (231).

2. The aircraft clip-type self-locking nut according to claim 1, characterized in that: A flange plate (120) is arranged at one end of the self-locking flange nut (100), and a spherical surface (110) is arranged at the other end of the self-locking flange nut (100), and a hexagonal column (140) is installed between the flange plate (120) and the spherical surface (110).

3. The aircraft clip-type self-locking nut according to claim 2, characterized in that: An internal thread (130) is arranged at the center of the hexagonal column (140), and the internal thread (130) and the third clamping piece (230) are limited in position and cannot be separated from the inside of the clamping piece (200).

4. The aircraft clip-type self-locking nut according to claim 3, characterized in that: The hexagonal column (140) is installed inside the third clamping piece (230), and when the hexagonal column (140) is installed inside the fixing groove (231), the spherical surface (110) of the self-locking flange nut (100) is installed facing outward.

5. The aircraft clip-type self-locking nut according to claim 1, characterized in that: One end of the self-locking flange nut (100) is provided with a neck to achieve self-locking of the screw.

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