Self-locking check bolt assembly for airplane

Abstract

The utility model belongs to the technical field of aeronautical manufacturing, and relates to a self-locking check bolt assembly for an airplane, which comprises a bolt, a fastening nut and a check nut, the fastening nut comprises a nut end and a conical sleeve arranged at one end of the nut end, the nut end of the fastening nut is in threaded connection with the bolt, a plurality of axial expansion joints are uniformly distributed on the conical sleeve, and the expansion joints are connected with the check nut. Fastening teeth are arranged on the inner surface of the conical sleeve, an inner hole of the locknut is an inner conical hole, the locknut is connected outside the conical sleeve of the fastening nut in a sleeved mode, and the fastening teeth on the inner surface of the conical sleeve of the fastening nut are tightly attached to the outer surface of the bolt. The problems of nut loosening, bolt falling and the like caused by vibration, impact and the like of aviation equipment in the working process are solved.

Description

Technical Field

[0001] The utility model belongs to the technical field of aviation manufacturing and relates to a self-locking anti-loosening bolt assembly used for connecting and fastening aircraft parts. Background Art

[0002] In the manufacturing and use of aviation equipment, bolt anti-loosening has always been one of the focus issues of users. However, most of the self-locking anti-loosening bolts currently available on the market are easily affected by strong vibrations and impacts during work, which can easily cause problems such as bolt loosening, nut falling off, and connection failure. The remaining self-locking anti-loosening bolts also have their own advantages and disadvantages. It is basically difficult to find a bolt assembly with good anti-loosening effect, easy operation, and low cost. It can be seen that it is very necessary to design an anti-loosening bolt with good anti-loosening effect and stable operation under various working conditions. Utility Model Content

[0003] Technical problem solved by the utility model: The utility model provides a self-locking anti-loosening bolt assembly with good anti-loosening effect, easy operation and low cost for use in the manufacturing process of aviation equipment. The assembly can withstand complex working conditions such as strong vibration and impact, and solves the problems of nut loosening and bolt falling off caused by vibration and impact of aviation equipment during work.

[0004] Technical Solution

[0005] A self-locking anti-loosening bolt assembly for an aircraft comprises a bolt, a fastening nut and an anti-loosening nut. The fastening nut comprises a nut end and a tapered sleeve arranged at one end of the nut end. The nut end of the fastening nut is threadedly connected to the bolt. The tapered sleeve is evenly distributed with a plurality of expansion joints along the axial direction. The inner surface of the tapered sleeve is provided with fastening teeth. The inner hole of the anti-loosening nut is an inner tapered hole. The anti-loosening nut is sleeved on the outside of the tapered sleeve of the fastening nut so that the fastening teeth on the inner surface of the tapered sleeve of the fastening nut are closely fitted with the outer surface of the bolt.

[0006] Furthermore, the fastening nut is a hexagonal nut, and a safety hole is arranged on the edge of two adjacent planes of the hexagonal nut; the anti-loosening nut is a hexagonal nut, and a safety hole is arranged on the edge of two adjacent planes of the hexagonal nut.

[0007] Furthermore, it also includes a safety, and both ends of the safety are respectively connected to the safety holes on the fastening nut and the anti-loosening nut.

[0008] Furthermore, the fuse is a Φ0.8mm fuse.

[0009] Furthermore, the length of the expansion joint is smaller than the length of the tapered sleeve.

[0010] Furthermore, the diameter of the safety holes on the fastening nut and the anti-loosening nut is 1.2 mm.

[0011] Furthermore, the fastening teeth are perpendicular to the end surface of the tapered sleeve.

[0012] Beneficial Effects

[0013] The utility model provides a self-locking anti-loosening bolt assembly with good self-locking effect and simple operation in the manufacturing process of aviation equipment. Due to the adoption of the above technical scheme, a conical sleeve integrated with the fastening nut is arranged on the end face of the fastening nut, and the conical sleeve is provided with a shrinkage seam. The conical sleeve is squeezed through the inner conical hole on the anti-loosening nut, so that the conical sleeve is tightly pressed on the bolt rod after shrinking. When the tightening torque of the anti-loosening nut is greater, the serrations inside the conical sleeve are more deeply sunk into the threaded part on the screw rod, and the anti-loosening effect is better. Finally, by insuring and lead sealing the fastening nut and the anti-loosening nut, a permanent fastening effect can be achieved. Even if subjected to strong vibration and severe impact, there will be no loosening at all, and the operation is simple. The utility model can be widely used in aviation, aerospace, engineering machinery and other fields. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of a self-locking anti-loosening bolt assembly;

[0015] Figure 2 It is a partial cross-sectional view of a self-locking anti-loosening bolt assembly;

[0016] Figure 3 It is the front view of the fastening nut;

[0017] Figure 4 It is a side view of the fastening nut;

[0018] Figure 5 This is the axial side view of the anti-loosening nut;

[0019] Figure 6 It is the side view of the locking nut;

[0020] Among them: 1. bolt, 2. fastening nut, 2-1. tapered sleeve, 2-2 fastening teeth, 3. anti-loosening nut, 3-1. inner tapered hole. DETAILED DESCRIPTION

[0021] The utility model is further described below in conjunction with the accompanying drawings. Figure 1 As shown, a self-locking anti-loosening bolt assembly for connecting and fastening aircraft parts is provided, comprising a bolt 1, a fastening nut 2, an anti-loosening nut 3, and a safety 4; wherein the bolt 1 is an ordinary bolt, using an ordinary standard bolt; the shape of the fastening nut 2 is as shown Figure 3 , 4As shown, a conical sleeve 2-1 connected to the fastening nut 2 as a whole is arranged on the end face of the ordinary hexagonal nut, and the internal thread on the fastening nut 2 is only between the two end faces of the hexagonal nut, and the inside of the conical sleeve 2-1 has uniformly distributed fastening teeth 2-2 perpendicular to the end face of the conical sleeve, distributed between the two end faces of the conical sleeve 2-1, used to increase the friction force during fastening, and an external thread is arranged on the outer surface of the conical sleeve 2-1, and expansion joints are uniformly distributed on the conical sleeve 2-1, and the length of the expansion joints is less than the length of the conical sleeve 2-1; the anti-loosening nut 3 is as shown Figure 5 , 6 As shown, the outer surface is an ordinary hexagonal nut, and an inner tapered hole matching the outer surface of the tapered sleeve 2-1 is arranged on the inner surface. The pitch is consistent with the outer surface of the tapered sleeve 2-1, and the aperture adopts a tapered hole, which changes evenly from large to small; the insurance 4 uses a Φ0.8mm insurance wire to insure the fastening nut 2 and the anti-loosening nut 3 and seal them with lead. The hexagonal nut of the fastening nut 2 has a safety hole on the edge of two adjacent planes, and 3 Φ1.2mm safety holes are evenly distributed. The anti-loosening nut 3 has a safety hole on the edge of two adjacent planes on the outside, and a total of 3 Φ1.2mm safety holes are evenly distributed.

[0022] When in use, first screw the fastening nut 2 into the rod of the bolt 1 and tighten it, and then screw the anti-loosening nut 3 into the tapered sleeve 2-1 of the fastening nut 2 until the end face of the anti-loosening nut 3 fits with the end face of the fastening nut 2 or the anti-loosening nut 3 is tightened until it cannot rotate. At this time, the inner tapered hole 3-1 of the anti-loosening nut 3 squeezes the tapered sleeve 2-1 of the fastening nut 2, so that the tapered sleeve shrinks and tightly squeezes on the bolt rod, and the fastening teeth 2-2 of the fastening nut 2 are embedded in the threads of the bolt 1, criss-crossing and very secure. Finally, the fastening nut 2 and the anti-loosening nut 3 are insulated by a fuse, so that the anti-loosening nut 3 is connected to the fastening nut 2, and the anti-loosening nut 3 will not loosen even if it is subjected to external forces such as impact and vibration.

Claims

1. A self-locking anti-loosening bolt assembly for an aircraft, characterized in that: It includes a bolt, a fastening nut and an anti-loosening nut. The fastening nut includes a nut end and a tapered sleeve arranged at one end of the nut end. The nut end of the fastening nut is threadedly connected to the bolt. A number of expansion joints along the axial direction are evenly distributed on the tapered sleeve. The inner surface of the tapered sleeve is provided with fastening teeth. The inner hole of the anti-loosening nut is an inner tapered hole. The anti-loosening nut is sleeved on the outside of the tapered sleeve of the fastening nut so that the fastening teeth on the inner surface of the tapered sleeve of the fastening nut are tightly fitted with the outer surface of the bolt; the fastening nut is a hexagonal nut, and a safety hole is arranged on the edge of two adjacent planes of the hexagonal nut; the anti-loosening nut is a hexagonal nut, and a safety hole is arranged on the edge of two adjacent planes of the hexagonal nut; the self-locking anti-loosening bolt assembly also includes a safety, and the two ends of the safety are respectively connected to the safety holes on the fastening nut and the anti-loosening nut.

2. A self-locking anti-loosening bolt assembly for an aircraft according to claim 1, characterized in that: The fuse is a Φ0.8mm fuse.

3. A self-locking anti-loosening bolt assembly for an aircraft according to claim 1, characterized in that: The length of the expansion joint is smaller than the length of the tapered sleeve.

4. A self-locking anti-loosening bolt assembly for an aircraft according to claim 1, characterized in that: The diameter of the safety holes on the fastening nut and the anti-loosening nut is 1.2 mm.

5. A self-locking anti-loosening bolt assembly for an aircraft according to claim 1, characterized in that: The fastening teeth are perpendicular to the end surface of the tapered sleeve.

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