CN221007111U - Aviation part fatigue strength detection device - Google Patents
Aviation part fatigue strength detection device Download PDFInfo
- Publication number
- CN221007111U CN221007111U CN202322563973.3U CN202322563973U CN221007111U CN 221007111 U CN221007111 U CN 221007111U CN 202322563973 U CN202322563973 U CN 202322563973U CN 221007111 U CN221007111 U CN 221007111U
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- fatigue strength
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- 238000001514 detection method Methods 0.000 title claims abstract description 18
- 238000004080 punching Methods 0.000 claims description 6
- 230000002457 bidirectional effect Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 241001391944 Commicarpus scandens Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model discloses an aviation component fatigue strength detection device, which comprises a support base assembly and a detection assembly, wherein the support base assembly is provided with a support base; the supporting base assembly comprises a base and pushing blocks arranged on two sides of the surface of the base; a lifting seat is arranged between the pushing blocks; the pushing block is provided with a first inclined plane, and two sides of the lifting seat are provided with second inclined planes which are attached to the first inclined plane; a driving component and an anti-skid component are arranged between the base and the pushing block; according to the utility model, the push blocks are arranged on two sides of the surface of the base, the lifting seats are arranged between the push blocks, the first inclined surfaces are arranged on the push blocks, the second inclined surfaces which are attached to the first inclined surfaces are arranged on two sides of the lifting seats, and when the push blocks on two sides squeeze towards the lifting seats, the first inclined surfaces lift the second inclined surfaces, so that the lifting seats are lifted, and the lifting mode is more stable.
Description
Technical Field
The utility model relates to the technical field of strength detection of aviation parts, in particular to a fatigue strength detection device for aviation parts.
Background
With the development of society, the application of strength detection of aviation parts is wider, parts refer to single non-detachable parts in machinery, are basic components of machinery, and are also basic units in the manufacturing process of machinery, and the manufacturing process generally does not need assembly procedures, such as shaft sleeves, bearing bushes, nuts, crankshafts, blades, gears, cams, connecting rod bodies, connecting rod heads and the like, so that the aviation parts, as the name implies, refer to parts used in the aviation field, and the requirement of an aviation part strength detection device is growing;
The application number in the prior art is: 202020437162.2 an aircraft component strength detection device; in this prior art's structure, when the hydraulic stem strikes to the backup pad, articulated connected mode supportability is poor in the above-mentioned structure, and the junction is easy to break, and simultaneously when striking, the slider takes place to skid easily between screw rod to lead to the device to use for a long time, and the degree of accuracy that detects is relatively poor.
Disclosure of Invention
The utility model aims to solve the technical problem of providing an aviation component fatigue strength detection device for solving the technical problem in the background art.
The utility model relates to an aviation component fatigue strength detection device which is realized by the following technical scheme: comprises a supporting base component and a detecting component; the supporting base assembly comprises a base and pushing blocks arranged on two sides of the surface of the base; a lifting seat is arranged between the pushing blocks;
The pushing block is provided with a first inclined plane, and two sides of the lifting seat are provided with second inclined planes which are attached to the first inclined plane; a driving component and an anti-skid component are arranged between the base and the pushing block.
As a preferred technical solution, the anti-skid assembly comprises a panel; the surface of the base is provided with a groove, and the panel is vertically movably arranged in the groove;
The surface of the panel is provided with more than one limiting block, and one side of the limiting block is provided with a third inclined plane; the lower surface of the pushing block is provided with a limit groove; the limiting block is unidirectionally movably arranged in the limiting groove.
As a preferable technical scheme, the surface of the panel is provided with a through hole, and the surface of the groove is provided with a first threaded hole; bolts are inserted and installed on the through holes;
the other end of the bolt is meshed and installed in the first threaded hole; elastic elements are arranged on the bolts, and two ends of each elastic element respectively support the corresponding groove and the corresponding panel.
As a preferable technical scheme, guide grooves are formed in two sides of the surface of the base; the driving assembly comprises a bidirectional motor arranged in the guide groove and a guide sliding block arranged at the lower end of the pushing block;
the guide sliding block is arranged in the guide groove in a sliding way; the guide sliding block is provided with a second threaded hole; a screw motor shaft on the bidirectional motor is meshed with and installed in the second threaded hole.
As the preferable technical scheme, a cushion block is arranged on the surface of the lifting seat, a positioning hole is arranged on the surface of the lifting seat, and a positioning column is arranged on the surface of the cushion block; the positioning column is fixed in the positioning hole in a limiting way.
As the preferable technical scheme, the detection component comprises a support bracket, wherein two ends of the support bracket are arranged at two sides of the base; the hydraulic telescopic component is arranged on the support bracket;
The movable end of the hydraulic telescopic component is provided with a punching block, and the punching block and the cushion block are arranged up and down oppositely.
As the preferable technical scheme, the two ends of the support bracket are provided with first bolt holes, and the two ends of the base are provided with second bolt holes;
The first bolt hole and the second bolt hole are oppositely arranged; a bolt for connecting the second bolt hole is arranged in the first bolt hole.
The beneficial effects of the utility model are as follows:
1. By arranging the pushing blocks on two sides of the surface of the base and arranging the lifting seats between the pushing blocks, arranging the first inclined planes on the pushing blocks, arranging the second inclined planes which are attached to the first inclined planes on two sides of the lifting seats, and when the pushing blocks on two sides squeeze towards the lifting seats, the first inclined planes lift the second inclined planes, so that the lifting seats are lifted, and compared with a hinged connection mode in the prior art, the lifting mode is more stable;
2. A panel capable of moving up and down is arranged in a groove on the surface of the base; and be provided with more than one stopper on the panel surface, set up the third inclined plane in stopper one side, set up the spacing groove at the ejector pad lower surface, the unidirectional activity of stopper sets up in the spacing inslot, runs through the bolt that sets up the connection recess on the panel, installs the elastic component of both ends end bottom pool recess and panel on the bolt, through elastic component to make the ejector pad can limit while the motion, guarantee the stability of ejector pad.
Drawings
In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a support base assembly;
FIG. 2 is a schematic cross-sectional view of a support base assembly;
FIG. 3 is a schematic diagram of a second support base assembly;
FIG. 4 is a schematic view of an aircraft component fatigue strength testing device according to the present utility model;
FIG. 5 is a schematic cross-sectional view of an aerospace component fatigue strength detection apparatus of the present utility model;
fig. 6 is a schematic diagram of a pad.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
1-5, The device for detecting fatigue strength of the aviation component comprises a supporting base assembly and a detecting assembly; the supporting base assembly comprises a base 2 and pushing blocks 9 arranged on two sides of the surface of the base 2; a lifting seat 4 is arranged between the pushing blocks 9;
The pushing block 9 is provided with a first inclined plane 7, and two sides of the lifting seat 4 are provided with a second inclined plane 10 which is attached to the first inclined plane 7; a driving component and an anti-skid component are arranged between the base 2 and the push block 9;
When the pushing blocks at two sides are extruded to the lifting seat, the first inclined plane lifts the second inclined plane, so that the lifting seat is lifted, and compared with a hinged connection mode in the prior art; the lifting mode of the utility model is more stable.
In this embodiment, the anti-skid assembly includes a panel 20; the surface of the base 2 is provided with a groove 19, and a panel 20 is arranged in the groove 19 in an up-and-down movable way;
More than one limiting block 15 is arranged on the surface of the panel 20, and a third inclined plane 16 is arranged on one side of the limiting block 15; the lower surface of the pushing block 9 is provided with a limit groove 27; the limiting block 15 is movably arranged in the limiting groove 27 in one direction;
the surface of the panel 20 is provided with a through hole 18, and the surface of the groove 19 is provided with a first threaded hole; the through hole 18 is inserted and provided with a bolt 17;
the other end of the bolt 17 is meshed and installed in the first threaded hole; the bolt 17 is provided with an elastic element (not shown), and two ends of the elastic element respectively support the groove 19 and the panel 20; through the elastic element, the push block can move and limit at the same time, so that the stability of the push block is ensured.
In order to realize that the pushing blocks at two sides simultaneously or simultaneously move outwards, guide grooves 1 are arranged at two sides of the surface of the base 2; the driving assembly comprises a bidirectional motor 11 arranged in the guide groove 1 and a guide sliding block 60 arranged at the lower end of the push block 9;
The guide sliding block 60 is arranged in the guide groove 1 in a sliding way; the guide sliding block 60 is provided with a second threaded hole 13; a threaded motor shaft 14 on the bi-directional motor 11 is engaged and mounted in the second threaded hole 13.
As shown in fig. 4 and 6, in order to prevent the phenomenon that the lifting seat cannot support because the volume of the tested element is large, a cushion block 26 is installed on the surface of the lifting seat 4, a positioning hole 5 is formed on the surface of the lifting seat 4, and a positioning column 25 is arranged on the surface of the cushion block 26; the positioning column 25 is fixed in the positioning hole 5 in a limiting way.
In this embodiment, the detection assembly includes a support bracket 23, and two ends of the support bracket 23 are disposed on two sides of the base 2; the hydraulic telescopic assembly 21 is arranged on the support bracket 23; the movable end of the hydraulic telescopic component 21 is provided with a punching block 22, and the punching block 22 and the cushion block 26 are arranged up and down oppositely.
In order to realize quick assembly or disassembly between the supporting base assembly and the detection assembly, the two ends of the supporting bracket 23 are provided with first bolt holes 29, and the two ends of the base 2 are provided with second bolt holes 24; the first pin hole 29 is disposed opposite to the second pin hole 24; a plug 41 for connecting the second plug hole 24 is installed in the first plug hole 29.
The foregoing is merely illustrative of specific embodiments of the present utility model, and the scope of the utility model is not limited thereto, but any changes or substitutions that do not undergo the inventive effort should be construed as falling within the scope of the present utility model. Therefore, the protection scope of the present utility model should be subject to the protection scope defined by the claims.
Claims (7)
1. An aviation component fatigue strength detection device comprises a support base assembly and a detection assembly; the method is characterized in that: the supporting base component comprises a base (2) and pushing blocks (9) arranged on two sides of the surface of the base (2); a lifting seat (4) is arranged between the pushing blocks (9);
The pushing block (9) is provided with a first inclined plane (7), and two sides of the lifting seat (4) are provided with a second inclined plane (10) which is attached to the first inclined plane (7); a driving component and an anti-skid component are arranged between the base (2) and the pushing block (9).
2. The aviation component fatigue strength testing device of claim 1, wherein: the anti-skid assembly includes a panel (20); the surface of the base (2) is provided with a groove (19), and the panel (20) is movably arranged in the groove (19) up and down;
More than one limiting block (15) is arranged on the surface of the panel (20), and a third inclined plane (16) is arranged on one side of the limiting block (15); a limit groove (27) is formed in the lower surface of the pushing block (9); the limiting block (15) is movably arranged in the limiting groove (27) in one direction.
3. The aviation component fatigue strength testing device of claim 1, wherein: the surface of the panel (20) is provided with a through hole (18), and the surface of the groove (19) is provided with a first threaded hole; bolts (17) are inserted and installed on the through holes (18);
The other end of the bolt (17) is meshed and installed in the first threaded hole; elastic elements are arranged on the bolts (17), and two ends of each elastic element respectively support the corresponding groove (19) and the corresponding panel (20).
4. The aviation component fatigue strength testing device of claim 1, wherein: guide grooves (1) are formed in two sides of the surface of the base (2); the driving assembly comprises a bidirectional motor (11) arranged in the guide groove (1) and a guide sliding block (60) arranged at the lower end of the pushing block (9);
The guide sliding block (60) is arranged in the guide groove (1) in a sliding way; the guide sliding block (60) is provided with a second threaded hole (13); a threaded motor shaft (14) on the bidirectional motor (11) is meshed and installed in the second threaded hole (13).
5. The aviation component fatigue strength testing device of claim 1, wherein: a cushion block (26) is arranged on the surface of the lifting seat (4), a positioning hole (5) is formed in the surface of the lifting seat (4), and a positioning column (25) is arranged on the surface of the cushion block (26); the positioning column (25) is fixed in the positioning hole (5) in a limiting way.
6. The aviation component fatigue strength testing device of claim 1, wherein: the detection assembly comprises a support bracket (23), and two ends of the support bracket (23) are arranged on two sides of the base (2); the hydraulic telescopic component (21) is arranged on the supporting bracket (23);
The movable end of the hydraulic telescopic component (21) is provided with a punching block (22), and the punching block (22) and the cushion block (26) are arranged up and down oppositely.
7. The aviation component fatigue strength testing device of claim 1, wherein: the two ends of the support bracket (23) are provided with first bolt holes (29), and the two ends of the base (2) are provided with second bolt holes (24);
The first bolt hole (29) is opposite to the second bolt hole (24); a plug pin (41) for connecting the second plug pin hole (24) is installed in the first plug pin hole (29).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322563973.3U CN221007111U (en) | 2023-09-21 | 2023-09-21 | Aviation part fatigue strength detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322563973.3U CN221007111U (en) | 2023-09-21 | 2023-09-21 | Aviation part fatigue strength detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221007111U true CN221007111U (en) | 2024-05-24 |
Family
ID=91111924
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322563973.3U Active CN221007111U (en) | 2023-09-21 | 2023-09-21 | Aviation part fatigue strength detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221007111U (en) |
-
2023
- 2023-09-21 CN CN202322563973.3U patent/CN221007111U/en active Active
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