Non-standard fastener for space flight and aviation

Abstract

The utility model relates to the technical field of fasteners, in particular to a non-standard fastener for aerospace, which comprises a threaded rod and is characterized in that a first locking part is arranged at one end of the threaded rod, the threaded rod and the first locking part are integrally formed, an annular groove is formed in one side, close to the first locking part, of the threaded rod, and the first locking part is arranged in the annular groove. The threaded rod is sleeved with a spring washer, the spring washer is partially and fixedly connected with the threaded rod, a cylindrical connecting part is arranged on the face, away from the threaded rod, of the first locking part, the connecting part and the first locking part are integrally formed, and a locking structure is arranged on the connecting part. Through the spring washer, the first locking part, the connecting part and the locking structure which are arranged on the threaded rod, the threaded rod is effectively prevented from loosening, the problem that the threaded rod is loosened due to vibration and other reasons when the threaded rod is used for a long time is solved, and therefore the stability and safety of the device are guaranteed.

Description

Technical Field

[0001] The present application relates to the technical field of fasteners, and in particular to a non-standard fastener for aerospace. Background Art

[0002] Fasteners, as the basic components for connecting structural parts, are a type of mechanical parts with extremely wide applications. Fasteners are used in a wide range of industries, including electrical appliances, electronics, machinery, vehicles, railways, bridges, tools and instruments. Various fasteners can be seen on them, which are characterized by diverse types and specifications, different performances and uses.

[0003] The reliable installation of non-standard fasteners currently used in the aerospace industry is directly related to the stability and safety of the device. While many of these fasteners offer flexibility in design and manufacturing, meeting specific application requirements, they can easily loosen during use. Common approaches include adding washers and applying loosening coatings to prevent loosening. However, over time, this loosening issue remains difficult to resolve. Utility Model Content

[0004] In view of the shortcomings of the existing technology, the purpose of this application is to provide a non-standard fastener for aerospace, which is used to solve the problem of the stability and safety of the device caused by the loosening of the non-standard fasteners mentioned in the background art after long-term use.

[0005] The above-mentioned purpose of the present application is achieved through the following technical solutions: A non-standard fastener for aerospace, comprising a threaded rod, a first locking portion is provided at one end of the threaded rod, the threaded rod and the first locking portion are integrally formed, an annular groove is provided on the threaded rod close to the first locking portion, a spring washer is sleeved on the threaded rod, the spring washer is provided on the annular groove, the spring washer portion is fixedly connected to the threaded rod, a cylindrical connecting portion is provided on the side of the first locking portion away from the threaded rod, the connecting portion and the first locking portion are integrally formed, and a locking structure is provided on the connecting portion.

[0006] According to a further optimization solution, arc portions are provided on the edges of the upper and lower sides of the outer ring of the spring washer.

[0007] A further optimized solution is that the locking structure includes a circular locking sleeve, a second locking portion is provided at one end of the locking sleeve, the second locking portion and the locking sleeve are integrally formed, an external thread is provided on the outer side of the locking sleeve away from the second locking portion, and the thread direction of the external thread is set opposite to the thread direction of the threaded rod.

[0008] A further optimized solution is that an annular groove is opened on the side wall of the locking sleeve away from the second locking part, and the opening direction of the annular groove is set toward the second locker. A first spring is fixedly installed in the annular groove, and an annular limiter is fixedly installed on the other end of the first spring, and the annular limiter is partially exposed outside the groove.

[0009] According to a further optimized solution, a plurality of first springs are provided.

[0010] According to a further optimization solution, a spiral guide rail is provided on the connecting portion, the direction of the spiral guide rail is the same as the direction of the external thread, the end point of the spiral guide rail is connected to a termination groove, and a termination rod is connected to the inner cavity of the locking sleeve.

[0011] According to a further optimization solution, a receiving groove facing the connecting part is provided in the locking sleeve, the terminating rod is arranged in the accommodating groove and is slidingly connected to the locking sleeve, a second spring is fixedly installed in the accommodating groove, and the other end of the second spring is fixedly connected to the terminating rod.

[0012] According to a further optimized solution, an arc portion is provided on the terminating rod, and when the terminating rod is clamped in the terminating groove, the connecting portion abuts against the second locking portion.

[0013] In summary, this application has at least the following beneficial technical effects:

[0014] The present application uses a spring washer installed on a threaded rod. When the first locking part is screwed using an installation tool to install the threaded rod and the internal thread on the workpiece together, the spring washer also enters the installation area of ​​the threaded washer opened on the workpiece. The spring washer is stuck in the installation area of ​​the workpiece due to its elasticity. Then the locking structure covers the connection part, and the second locking part is screwed using an installation tool to lock the external thread of the locking sleeve of the locking structure with the internal thread opened on the workpiece. Since the thread direction of the locking sleeve is opposite to the thread direction of the threaded rod, when the threaded rod is loose, the loosening direction is the same as the locking direction of the locking sleeve. Therefore, when the threaded rod is loose and rotated, the locking sleeve can effectively prevent the threaded rod from loosening, thereby solving the problem of loosening of the threaded rod due to vibration and other reasons during long-term use, thereby ensuring the stability and safety of the device. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is an exploded schematic diagram of the overall structure in the embodiment;

[0016] Figure 2 2. It is a cross-sectional view of the locking structure of the embodiment.

[0017] Figure markings: 1. threaded rod; 2. first locking part; 3. spring washer; 4. connecting part; 40. spiral guide rail; 41. end groove; 5. locking sleeve; 50. external thread; 6. second locking part; 7. first spring; 8. annular limiter; 9. second spring; 10. end rod. DETAILED DESCRIPTION

[0018] The present application is further described in detail below with reference to the accompanying drawings.

[0019] Example, see Figure 1 and Figure 2 A non-standard fastener for aerospace, comprising a threaded rod 1, a first locking portion 2 being provided at one end of the threaded rod 1, the threaded rod 1 and the first locking portion 2 being integrally formed, an annular groove being provided on the threaded rod 1 close to the side of the first locking portion 2, a spring washer 3 being sleeved on the threaded rod 1, the spring washer 3 being arranged in the annular groove, and a portion of the spring washer 3 being fixedly connected to the threaded rod 1, a cylindrical connecting portion 4 being provided on the side of the first locking portion 2 away from the threaded rod 1, the connecting portion 4 being integrally formed with the first locking portion 2, and a locking structure being provided on the connecting portion 4.

[0020] Specifically, arc portions are formed on the upper and lower edges of the outer ring of the spring washer 3 .

[0021] Specifically, the locking structure includes a circular locking sleeve 5, a second locking portion 6 is provided at one end of the locking sleeve 5, the second locking portion 6 and the locking sleeve 5 are integrally formed, and an external thread 50 is provided on the outer side of the locking sleeve 5 away from the second locking portion 6, and the thread direction of the external thread 50 is set opposite to the thread direction of the threaded rod 1.

[0022] When the first locker is rotated using the installation tool to install the threaded rod 1 and the internal thread on the workpiece together, the spring washer 3 also enters the installation area of ​​the spring washer 3 opened on the workpiece. The spring washer 3 will be stuck in the installation area of ​​the workpiece due to its elasticity, and then the locking structure covers the connecting part 4. The second locking part 6 is rotated using the installation tool to lock the external thread 50 of the locking sleeve 5 of the locking structure with the internal thread opened on the workpiece. Since the thread direction of the locking sleeve 5 in the locking structure is opposite to the thread direction of the threaded rod 1, when the threaded rod 1 is loosened, the loosening direction is the same as the locking direction of the locking sleeve 5. Therefore, when the threaded rod 1 is loosened and rotated, the locking sleeve 5 can limit the loosening of the threaded rod 1, which solves the problem of loosening of the threaded rod 1 due to vibration and other reasons during long-term use, thereby ensuring the stability and safety of the device.

[0023] In the embodiment of the present disclosure, when the locking sleeve 5 is installed on the workpiece, an annular groove is formed on the side wall of the locking sleeve 5 away from the second locking portion 6 to prevent the locking sleeve 5 from loosening. The opening direction of the annular groove is set toward the second locker. A first spring 7 is fixedly installed in the annular groove. An annular limiter 8 is fixedly installed at the other end of the first spring 7, and the annular limiter 8 is partially exposed outside the groove. The first spring 7 will press the limiter against the surface of the workpiece due to the reaction force of the spring. At the same time, the locking sleeve 5 will be pulled outward from the workpiece due to the elastic force of the spring, thereby preventing the locking sleeve 5 from loosening itself.

[0024] Specifically, a plurality of first springs 7 are provided.

[0025] In the embodiment of the present disclosure, the connecting portion 4 is provided with a spiral guide rail 40, which is oriented in the same direction as the external thread 50. The end point of the spiral guide rail 40 is connected to a termination groove 41. A termination rod 10 is connected to the inner cavity of the locking sleeve 5. When the locking sleeve 5 is installed on the workpiece, the termination rod 10 slides within the spiral guide rail 40 and ultimately engages in the termination groove 41, further preventing the threaded rod 1 from loosening.

[0026] In the embodiment of the present disclosure, a receiving groove is defined in the locking sleeve 5, facing the connecting portion 4. The terminating rod 10 is disposed in the terminating groove and is slidably connected to the locking sleeve 5. A second spring 9 is fixedly mounted in the terminating groove, and the other end of the second spring 9 is fixedly connected to the terminating rod 10. When the locking rod enters the terminating groove 41 from the spiral guide rail 40, the second spring 9 can push the terminating rod 10 into the terminating groove 41.

[0027] In the embodiment of the present disclosure, an arc portion is provided on the terminating rod 10, which facilitates the terminating rod 10 to disengage from the terminating groove 41 when the locking sleeve 5 is disassembled. When the terminating rod 10 is clamped in the terminating groove 41, the connecting portion 4 abuts against the second locking portion, which can effectively prevent the threaded rod 1 from loosening.

[0028] In the specific implementation process, when the first locking part 2 is rotated using the installation tool to install the threaded rod 1 and the internal thread on the workpiece together, the spring washer 3 also enters the installation area of ​​the threaded washer opened on the workpiece. The spring washer 3 will be stuck in the installation area of ​​the workpiece due to its elasticity, and then the locking structure covers the connecting part 4. The second locking part 6 is rotated using the installation tool to lock the external thread 50 of the locking sleeve 5 of the locking structure with the internal thread opened on the workpiece. At the same time, the second spring 9 installed in the locking sleeve 5 is clamped in the termination groove 41, and the connecting part 4 and the second locking part 6 are abutted together.

[0029] The embodiments of this specific implementation method are all preferred embodiments of the present application and are not intended to limit the scope of protection of the application. Therefore, any equivalent changes made based on the structure, shape, and principle of the present application should be included in the scope of protection of the present application.

Claims

1. A non-standard fastener for aerospace, comprising a threaded rod (1), characterized in that: A first locking portion (2) is provided at one end of the threaded rod (1), and the threaded rod (1) and the first locking portion (2) are designed to be integrally formed. An annular groove is provided on the threaded rod (1) on a side close to the first locking portion (2). A spring washer (3) is sleeved on the threaded rod (1), and the spring washer (3) is arranged in the annular groove. Part of the spring washer (3) is fixedly connected to the threaded rod (1). A cylindrical connecting portion (4) is provided on a side of the first locking portion (2) away from the threaded rod (1). The connecting portion (4) and the first locking portion (2) are designed to be integrally formed, and a locking structure is provided on the connecting portion (4).

2. The non-standard fastener for aerospace according to claim 1, characterized in that: The edges of the upper and lower sides of the outer ring of the spring washer (3) are both provided with arc portions.

3. The non-standard fastener for aerospace according to claim 1, characterized in that: The locking structure comprises a circular locking sleeve (5), one end of which is provided with a second locking portion (6), the second locking portion (6) and the locking sleeve (5) being integrally formed, an external thread (50) being provided on the outer side of the locking sleeve (5) away from the second locking portion (6), and the thread direction of the external thread (50) being opposite to the thread direction of the threaded rod (1).

4. The non-standard fastener for aerospace according to claim 3, characterized in that: An annular groove is provided on the side wall of the locking sleeve (5) away from the second locking portion (6), and the opening direction of the annular groove is arranged toward the second locker. A first spring (7) is fixedly installed in the annular groove, and an annular limiter (8) is fixedly installed at the other end of the first spring (7), and a portion of the annular limiter (8) is exposed outside the groove.

5. The non-standard fastener for aerospace according to claim 4, characterized in that: A plurality of the first springs (7) are provided.

6. The non-standard fastener for aerospace according to claim 3, characterized in that: The connecting portion (4) is provided with a spiral guide rail (40), the direction of the spiral guide rail (40) is the same as the direction of the external thread (50), the end point of the spiral guide rail (40) is connected to a termination groove (41), and the inner cavity of the locking sleeve (5) is connected to a termination rod (10).

7. The non-standard fastener for aerospace according to claim 6, characterized in that: The locking sleeve (5) is provided with an accommodating groove facing the connecting portion (4); the terminating rod (10) is arranged in the accommodating groove and is slidably connected to the locking sleeve (5); a second spring (9) is fixedly installed in the accommodating groove; the other end of the second spring (9) is fixedly connected to the terminating rod (10).

8. The non-standard fastener for aerospace according to claim 6, characterized in that: The terminating rod (10) is provided with an arc portion, and when the terminating rod (10) is clamped in the terminating groove (41), the connecting portion (4) abuts against the second locking portion (6).

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