CN221224180U - Frock is used in detection of aviation high strength bolt fatigue strength - Google Patents
Frock is used in detection of aviation high strength bolt fatigue strength Download PDFInfo
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- CN221224180U CN221224180U CN202322938633.4U CN202322938633U CN221224180U CN 221224180 U CN221224180 U CN 221224180U CN 202322938633 U CN202322938633 U CN 202322938633U CN 221224180 U CN221224180 U CN 221224180U
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- connecting rod
- threaded hole
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- detection
- aviation high
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- 238000001514 detection method Methods 0.000 title claims abstract description 30
- 238000009661 fatigue test Methods 0.000 claims abstract description 14
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 3
- 229910052721 tungsten Inorganic materials 0.000 claims description 3
- 239000010937 tungsten Substances 0.000 claims description 3
- 125000006850 spacer group Chemical group 0.000 description 5
- 238000012360 testing method Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002146 bilateral effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The application relates to the technical field of aerospace mechanical part detection, and particularly discloses a tool for detecting fatigue strength of an aviation high-strength bolt. The structure of the connecting rod comprises an upper connecting rod and a lower connecting rod, the upper connecting rod is identical to the lower connecting rod in structure, the section of the upper connecting rod is in an inverted convex shape, the protruding edge of the inverted convex shape of the upper connecting rod is a boss, the vertical part is a connecting rod, an internal threaded hole which can be connected with a fatigue testing machine is formed in the boss, a detection threaded hole which is consistent with the aperture of an aviation high-strength bolt and penetrates through the connecting rod is formed in the connecting rod, and the internal threaded hole is communicated with the detection threaded hole. The technical problems that the bolt fatigue test tool in the prior art is not suitable for detecting conventional aviation high-strength bolts and cannot measure bolts of the same specification and different lengths are solved.
Description
Technical Field
The utility model relates to the technical field of aerospace mechanical part detection, in particular to a tool for detecting fatigue strength of an aviation high-strength bolt.
Background
With the development of the aerospace field, the aerospace high-strength bolt has a plurality of demands in the aerospace field, is one of commonly used aerospace fasteners, and is mainly used for important core components such as engines. Because of the specificity of the aviation field, the high-strength bolt performance also has extremely severe standard, and meanwhile, the positioning of the high-strength bolt detection is very important, and the detection result can be directly influenced, but most of the existing tool equipment is used in the processing production process, the special detection tools are few, even if similar tools cannot be matched with the special detection equipment of aviation, most of the tools need to be combined with test equipment according to the characteristics of parts, and tools such as detection tools, clamps and the like are designed.
The utility model discloses a bolt fatigue test clamping device just discloses in the patent document that is CN104827423B in the publication, its structure is including last anchor clamps, upward is provided with the screw rod perforation that the axis extended along upper and lower direction supplies corresponding bolt to be tested's polished rod section to pass on the anchor clamps, and the perforated aperture of screw rod is greater than the diameter of polished rod section, bolt fatigue test clamping device still includes centering frock, and centering frock includes left arc spacer and right arc spacer that the axis along upper and lower direction extension is used for the cartridge between polished rod section and the perforated pore wall of screw rod, left and right arc spacer have the inside Zhou Humian that the diameter is unanimous with polished rod section external diameter and the outside Zhou Humian that the diameter is unanimous with the perforated aperture of screw rod, during the use, push left and right arc spacer in polished rod section and the perforated clearance of screw rod for the polished rod section and the perforated coaxial line setting of screw rod of bolt to be tested, after fixing the head of bolt on the anchor clamps on, take off left and right arc spacer can carry out fatigue test to the bolt.
The fatigue test to the bolt can be accomplished to above-mentioned patent, but its pertinence is too strong, is not applicable to conventional aviation high strength bolt, and when using, still need push left and right arc locating piece in polished rod section and the clearance between the screw rod perforation, the operation is complicated, can not measure the bolt of different length of same specification.
Disclosure of utility model
The utility model aims to provide a tool for detecting fatigue strength of an aviation high-strength bolt, which is used for solving the technical problems that the prior art of bolt fatigue test tools is not applicable to detection of conventional aviation high-strength bolts and can not measure bolts with the same specification and different lengths.
In order to solve the problems, the technical scheme adopted by the utility model is as follows: the utility model provides an aviation high strength bolt fatigue strength detects and uses frock, includes the upper connecting rod and the lower connecting rod that vertical stack and structure are the same, the cross-section of upper connecting rod is the convexity that falls, the protruding edge of upper connecting rod convexity is the boss, and vertical part is the connecting rod, be equipped with the internal thread hole that can be connected with fatigue testing machine on the boss, open in the connecting rod have with aviation high strength bolt aperture unanimity and run through the detection screw hole of connecting rod, internal thread hole and detection screw hole switch-on.
The beneficial effects of this embodiment lie in:
1. The application designs the upper connecting rod and the lower connecting rod, and the detection threaded holes in the upper connecting rod and the lower connecting rod are holes penetrating the connecting rod, so that the detection threaded holes can be extended when the length of the aviation high-strength bolt is too long, and the application can measure bolts with the same specification and different lengths.
2. The upper connecting rod and the lower connecting rod have the same structure, so that an operator does not need to distinguish the upper connecting rod from the lower connecting rod during testing, and compared with the prior art, the assembly efficiency is higher during detection
2. According to the application, the internal threaded hole is designed to be connected with the fatigue testing machine, and the structure of the threads enables clamping with the fatigue testing machine to be completed only by screwing the upper connecting rod and the lower connecting rod, so that the operation is simpler and more convenient.
3. According to the application, the detection threaded holes are designed in the upper connecting rod and the lower connecting rod, the detected aviation high-strength bolt is matched with the detection threaded holes, and the practical working condition of connecting the two parts by the aviation high-strength bolt is simulated in a screwing connection mode of the upper connecting rod and the lower connecting rod, so that the experimental process is closer to the application scene of the aviation high-strength bolt, and experimental data is more reliable.
Further, the boss and the connecting rod are of a cylindrical structure made of tungsten steel.
Further, the boss and the connecting rod are integrally processed into an integral part.
Further, the bore diameter of the internal threaded bore is larger than the bore diameter of the detection threaded bore.
Further, a rubber layer is arranged on the periphery of the connecting rod.
Further, the surface of the rubber layer is provided with a convex rib.
Drawings
Figure 1 is an assembled front cross-sectional view of an embodiment of the present utility model,
FIG. 2 is a cross-sectional view of a connecting rod according to an embodiment of the present utility model.
Detailed Description
The following is a further detailed description of the embodiments:
Reference numerals in the drawings of the specification include: the device comprises an upper connecting rod 1, a boss 11, an internal threaded hole 12, a connecting rod 13, a detection threaded hole 14, a lower connecting rod 2 and a bolt 3 to be detected.
Examples are shown in fig. 1-2: the utility model provides an aviation high strength bolt fatigue strength detects and uses frock, including last connecting rod 1, lower connecting rod 2, go up connecting rod 1 and lower connecting rod 2 structural identity, be tungsten steel material down, lower connecting rod 2 is just last connecting rod 1 of coming over, during the assembly, go up and down the connecting rod along the contact surface bilateral symmetry.
As shown in fig. 2, the section of the upper connecting rod 1 is in an inverted convex shape, the protruding edge of the inverted convex shape is a boss 11, the vertical part of the inverted convex shape is a connecting rod 13, the boss 11 and the connecting rod 13 are integrally processed integral parts, and are both in cylindrical structures, an internal threaded hole 12 is formed in the middle of the boss 11, internal threads in the internal threaded hole 12 are just matched with a screw rod of a clamping head of a fatigue testing machine, so that the upper connecting rod and the lower connecting rod can be connected with the fatigue testing machine by the internal threaded hole 12, the internal threaded hole 12 penetrates through the boss 11, the bottom of the internal threaded hole 12 is a connecting surface of the connecting rod 13 and the boss 11, a detection threaded hole 14 is formed in the connecting surface, the internal threads of the detection threaded hole 14 are consistent with the diameter of the detected bolt 3, but the diameter of the detection threaded hole 14 is smaller than that of the internal threaded hole 12, and the structure enables a bolt head 31 of the detected bolt 3 to be clamped in the internal threaded hole 12 when the detected bolt 3 is screwed into the detection threaded hole 14. The detection threaded hole 14 penetrates through the connecting rod 13, so that when the detected bolts 3 with the same specification and longer length are measured, the long detected bolts 3 can penetrate through the connecting rod of the lower connecting rod 2 and enter the internal threaded holes of the lower connecting rod 2, the application can measure the detected bolts 3 with the same specification and different lengths, the circumferential surface of the connecting rod 13 is adhered with a primary rubber layer, the rubber can play a role in dust prevention and protection on the connecting rod 13, an operator can not freeze hands when using a tool in winter, the tool is more artificial, the surface of the rubber layer is provided with fine ribs with the thickness of 1mm, the friction force between the hands of the operator and the tool can be increased, and the sliding of the operator is not easy to occur from the hands of the operator.
The specific implementation process is as follows:
When the tool disclosed by the application is used for fatigue test, the internal threaded hole of the lower connecting rod 2 can be screwed with the clamping screw of the fatigue tester, the upper connecting rod 1 is aligned with the lower connecting rod 2, the tested bolt 3 is screwed into the upper connecting rod 1, and the tested bolt 3 passes through the upper connecting rod 1 and is screwed into the lower connecting rod 1, so that the upper connecting rod 1 and the lower connecting rod 2 are connected into a whole by utilizing the tested bolt 3, and the internal threaded hole 12 of the upper connecting rod 1 and the clamping screw (capable of rotating independently) of the fatigue tester are screwed with a tool to complete assembly.
The mode that the upper connecting rod and the lower connecting rod are connected by the tested bolt 3 simulates the application environment of the tested bolt 3 under the actual working condition, so that the test is closer to the actual use condition of the aviation high-strength bolt, and the data is more reliable.
The foregoing is merely exemplary embodiments of the present utility model, and specific structures and features that are well known in the art are not described in detail herein. It should be noted that modifications and improvements can be made by those skilled in the art without departing from the structure of the present utility model, and these should also be considered as the scope of the present utility model, which does not affect the effect of the implementation of the present utility model and the utility of the patent. The protection scope of the present utility model is subject to the content of the claims, and the description of the specific embodiments and the like in the specification can be used for explaining the content of the claims.
Claims (6)
1. Frock is used in detection of aviation high strength bolt fatigue strength, including last connecting rod, lower connecting rod, its characterized in that: the connecting rod is identical with the lower connecting rod in structure, the section of the upper connecting rod is in an inverted convex shape, the protruding edge of the inverted convex shape of the upper connecting rod is a boss, the vertical part is a connecting rod, an internal threaded hole which can be connected with a fatigue testing machine is formed in the boss, a detection threaded hole which is consistent with the aperture of an aviation high-strength bolt and penetrates through the connecting rod is formed in the connecting rod, and the internal threaded hole is communicated with the detection threaded hole.
2. The tooling for detecting fatigue strength of aviation high-strength bolts according to claim 1, wherein: the boss and the connecting rod are of a cylindrical structure made of tungsten steel.
3. The tooling for detecting fatigue strength of aviation high-strength bolts according to claim 2, wherein: and the boss and the connecting rod are integrally processed into an integral part.
4. The tooling for detecting fatigue strength of aviation high-strength bolts according to claim 1, wherein: the aperture of the internal threaded hole is larger than that of the detection threaded hole.
5. The tooling for detecting fatigue strength of aviation high-strength bolts according to claim 1, wherein: the connecting rod periphery is equipped with the rubber layer.
6. The tooling for detecting fatigue strength of aviation high-strength bolts according to claim 5, wherein: and a convex rib is arranged on the surface of the rubber layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322938633.4U CN221224180U (en) | 2023-10-31 | 2023-10-31 | Frock is used in detection of aviation high strength bolt fatigue strength |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322938633.4U CN221224180U (en) | 2023-10-31 | 2023-10-31 | Frock is used in detection of aviation high strength bolt fatigue strength |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221224180U true CN221224180U (en) | 2024-06-25 |
Family
ID=91577695
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322938633.4U Active CN221224180U (en) | 2023-10-31 | 2023-10-31 | Frock is used in detection of aviation high strength bolt fatigue strength |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221224180U (en) |
-
2023
- 2023-10-31 CN CN202322938633.4U patent/CN221224180U/en active Active
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