CN219455705U - Bending fatigue clamp for aerospace equipment - Google Patents
Bending fatigue clamp for aerospace equipment Download PDFInfo
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- CN219455705U CN219455705U CN202222507453.6U CN202222507453U CN219455705U CN 219455705 U CN219455705 U CN 219455705U CN 202222507453 U CN202222507453 U CN 202222507453U CN 219455705 U CN219455705 U CN 219455705U
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- clamp
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Abstract
The utility model discloses a bending fatigue clamp for aerospace equipment, which belongs to the technical field of fatigue clamps and comprises a bottom plate and further comprises: the utility model solves the problem that the existing fatigue clamp can only clamp and fix one plate shape for manufacturing the aerospace equipment, thereby avoiding the phenomenon that the clamp needs to be replaced when the other shape is required to be clamped and fixed, reducing the investment of cost and saving time.
Description
Technical Field
The utility model relates to the technical field of fatigue clamps, in particular to a bending fatigue clamp for aerospace equipment.
Background
The fatigue testing machine is mainly used for testing the fatigue performance of metal and alloy materials thereof under the conditions of stretching, compressing or alternating load of stretching and compressing at room temperature, and is widely applied to the fields of testing and evaluating the fatigue performance of materials. The fatigue testing machine is equipped with various fatigue clamps for fatigue experiments of samples of different structures. The fatigue clamp mainly plays a role in fixing, restraining and limiting the fatigue test sample. Depending on the type of fatigue, this typically includes tension compression fatigue, bending fatigue, and the like. The fatigue conditions are generally classified into normal temperature fatigue, low temperature fatigue, high temperature fatigue, and the like. Wherein, fatigue fixture is the clamping on fatigue testing machine.
Because the aerospace equipment needs to enter the space, the performance requirements of the plates for manufacturing the aerospace equipment are high at present, the plates need to be subjected to performance detection before being put into use, wherein the performance detection comprises bending fatigue performance detection, and the bending fatigue performance detection is usually carried out through a fatigue experiment machine.
Disclosure of Invention
The present utility model has been made in view of the above and/or problems occurring in the prior art bending fatigue clamps for aerospace devices.
Accordingly, an object of the present utility model is to provide a bending fatigue clamp for an aerospace device, which can solve the above-mentioned problems.
In order to solve the technical problems, according to one aspect of the present utility model, the following technical solutions are provided:
a bending fatigue clamp for an aerospace device, comprising a base plate, further comprising:
two groups of placing components for placing square plates or round plates for manufacturing aerospace equipment;
the moving assembly is used for enabling the two groups of placing assemblies to move in opposite directions so as to clamp and fix square plates or round plates for manufacturing the aerospace equipment.
As a preferable mode of the bending fatigue clamp for aerospace equipment, the utility model is characterized in that: the moving assembly includes:
the two ends of the top of the bottom plate are fixedly provided with the supporting plates;
the screw rod is rotationally connected between the two groups of support plates through the bearing, and the two ends of the screw rod are provided with placing components.
As a preferable mode of the bending fatigue clamp for aerospace equipment, the utility model is characterized in that: the mobile assembly further comprises:
the guide rod is used for preventing the placing component from rotating and is fixedly arranged between the two groups of support plates;
the servo motor is fixedly arranged on a group of supporting plates, and an output shaft of the servo motor is fixedly connected with the screw rod.
As a preferable mode of the bending fatigue clamp for aerospace equipment, the utility model is characterized in that: the placement assembly includes:
the two ends of the screw rod are connected with the placing plates in a threaded manner, the threaded directions of the two placing plates are opposite, the inner walls of the bottom ends of the two placing plates are connected with a group of guide rods in a sliding manner, and one side of each placing plate is provided with a limiting assembly for limiting the square plate or the round plate;
the first placing groove is used for placing and manufacturing square plates of the aerospace equipment and is formed in the inner wall of the top end of the placing plate;
the second placing groove is used for placing and manufacturing the round plate of the aerospace equipment and is formed in the inner wall of the middle end of the placing plate, and the second placing groove is communicated with the first placing groove.
As a preferable mode of the bending fatigue clamp for aerospace equipment, the utility model is characterized in that: the shape of the first placing groove is square, and the shape of the second placing groove is semicircular.
As a preferable mode of the bending fatigue clamp for aerospace equipment, the utility model is characterized in that: the limiting component is as follows:
the opposite ends of the two groups of placing plates are fixedly provided with first fixing plates;
the cylinder is fixedly arranged on one side of the first fixed plate;
the output end of the cylinder is fixedly provided with the first extrusion plate through a piston rod.
As a preferable mode of the bending fatigue clamp for aerospace equipment, the utility model is characterized in that: the limiting component is as follows:
the opposite ends of the two groups of placing plates are fixedly provided with second fixing plates;
the telescopic rod is fixedly arranged on one side of the second fixing plate.
As a preferable mode of the bending fatigue clamp for aerospace equipment, the utility model is characterized in that: the limiting assembly is also:
the spring is sleeved on the telescopic rod;
the second extrusion plate is fixedly arranged at one end of the telescopic rod.
Compared with the prior art:
1. the first placing groove for placing and manufacturing the square plate of the aerospace equipment and the second placing groove for placing and manufacturing the round plate of the aerospace equipment are formed in the placing plate, so that the problem that the existing fatigue clamp can only clamp and fix one plate shape for manufacturing the aerospace equipment is solved, the phenomenon that the clamp needs to be replaced when the other plate shape needs to be clamped and fixed is avoided, the investment of cost is reduced, and time is saved;
2. the movable assembly drives the two groups of placing assemblies to perform opposite movement, and the limiting assembly is arranged to limit the plates for manufacturing the aerospace equipment, so that the plate clamping device has the effect of clamping and fixing the plates with small size differences.
Drawings
FIG. 1 is a schematic front view of the structure of embodiment 1 of the present utility model;
FIG. 2 is a schematic side view of a placement module according to embodiment 1 of the present utility model;
FIG. 3 is a schematic top view of a placement module according to embodiment 1 of the present utility model;
fig. 4 is a schematic side view of the placement module according to embodiment 2 of the present utility model.
In the figure: the base plate 10, the moving assembly 20, the supporting plate 21, the screw 22, the guide rod 23, the servo motor 24, the placement assembly 30, the placement plate 31, the first placement groove 32, the second placement groove 33, the limiting assembly 40, the first fixing plate 41, the air cylinder 42, the first pressing plate 43, the second fixing plate 46, the telescopic rod 47, the spring 48, and the second pressing plate 49.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present utility model more apparent, embodiments of the present utility model will be described in further detail below with reference to the accompanying drawings.
Example 1:
the utility model provides a bending fatigue clamp for aerospace equipment, referring to fig. 1-3, comprising a bottom plate 10;
further comprises: two groups of placing components 30 for placing square plates or round plates for manufacturing the aerospace equipment and a moving component 20 for enabling the two groups of placing components 30 to move towards each other so as to clamp and fix the square plates or round plates for manufacturing the aerospace equipment.
The placement assembly 30 includes: a placement plate 31, a first placement groove 32 for placing square plates for manufacturing aerospace equipment, and a second placement groove 33 for placing round plates for manufacturing aerospace equipment;
the two ends of the screw rod 22 are both in threaded connection with the placing plates 31, the thread directions of the two placing plates 31 are opposite, the inner walls of the bottom ends of the two placing plates 31 are in sliding connection with one group of guide rods 23, one side of each placing plate 31 is provided with a limiting component 40 for limiting square plates or round plates, a first placing groove 32 is formed in the inner wall of the top end of the placing plate 31, a second placing groove 33 is formed in the inner wall of the middle end of the placing plate 31, the second placing groove 33 is communicated with the first placing groove 32, the shape of the first placing groove 32 is square, and the shape of the second placing groove 33 is semicircular;
step one: the square sheet for manufacturing the aerospace device is placed in the first placing groove 32, or the round sheet for manufacturing the aerospace device is placed in the second placing groove 33, before which the distance of the two sets of placing components 30 is adjusted by the moving component 20 until the distance of the two sets of placing boards 31 reaches a suitable value.
The limiting assembly 40 is: a first fixing plate 41, an air cylinder 42, a first pressing plate 43;
the opposite ends of the two groups of placing plates 31 are fixedly provided with a first fixing plate 41, an air cylinder 42 is fixedly provided on one side of the first fixing plate 41, and the output end of the air cylinder 42 is fixedly provided with a first extrusion plate 43 through a piston rod;
step two: after the square plate for manufacturing the aerospace device is placed in the first placing groove 32 or after the round plate for manufacturing the aerospace device is placed in the second placing groove 33, the first extruding plate 43 is moved by the air cylinder 42 until one side of the first extruding plate 43 slightly extrudes the square plate or the round plate, so that the square plate or the round plate is limited, and the square plate or the round plate is prevented from being in a skew state.
The moving assembly 20 includes: a support plate 21, a screw 22, a guide rod 23 for preventing the placement module 30 from rotating, and a servo motor 24;
the two ends of the top of the bottom plate 10 are fixedly provided with support plates 21, a screw 22 is rotatably connected between the two groups of support plates 21 through bearings, two ends of the screw 22 are provided with placing components 30, a guide rod 23 is fixedly arranged between the two groups of support plates 21, a servo motor 24 is fixedly arranged on one group of support plates 21, and an output shaft of the servo motor 24 is fixedly connected with the screw 22;
step three: after the square plate or the round plate is limited, the screw 22 is rotated by the servo motor 24, and when the screw 22 rotates, the two groups of placing plates 31 are relatively moved until the two sides of the square plate or the round plate are pressurized by the placing plates 31, so that the square plate or the round plate is clamped and fixed.
Example 2:
the present utility model provides a bending fatigue clamp for aerospace equipment, referring to fig. 4, a limiting assembly 40 is: a second fixing plate 46, a telescopic rod 47, a spring 48, a second pressing plate 49;
the opposite ends of the two groups of placing plates 31 are fixedly provided with a second fixing plate 46, a telescopic rod 47 is fixedly provided on one side of the second fixing plate 46, a spring 48 is sleeved on the telescopic rod 47, and one end of the telescopic rod 47 is fixedly provided with a second extruding plate 49;
working principle: the telescopic rod 47 is contracted through the second extrusion plate 49, at this time, the spring 48 is in a deformed state until the second extrusion plate 49 is positioned at one side of the first placing groove 32 and the second placing groove 33, after that, the square plate for manufacturing the aerospace equipment is placed in the first placing groove 32, or the round plate for manufacturing the aerospace equipment is placed in the second placing groove 33, after the placement, the external force is removed, and after the external force is removed, the square plate or the round plate is extruded at one side of the second extrusion plate 49 under the action of the spring 48, so that the square plate or the round plate is limited, and the square plate or the round plate is prevented from being in a skew state.
Although the utility model has been described hereinabove with reference to embodiments, various modifications thereof may be made and equivalents may be substituted for elements thereof without departing from the scope of the utility model. In particular, the features of the disclosed embodiments may be combined with each other in any manner as long as there is no structural conflict, and the exhaustive description of these combinations is not given in this specification merely for the sake of omitting the descriptions and saving resources. Therefore, it is intended that the utility model not be limited to the particular embodiment disclosed, but that the utility model will include all embodiments falling within the scope of the appended claims.
Claims (8)
1. Bending fatigue clamp for aerospace equipment, comprising a base plate (10), characterized in that it further comprises:
two sets of placement assemblies (30) for placing square or round panels for making aerospace devices;
and the moving assembly (20) is used for enabling the two groups of placing assemblies (30) to move towards each other so as to clamp and fix square plates or round plates for manufacturing the aerospace equipment.
2. The bending fatigue clamp for an aerospace device according to claim 1, wherein the moving assembly (20) comprises:
the support plates (21) are fixedly arranged at the two ends of the top of the bottom plate (10);
the screw rod (22), screw rod (22) are connected between two sets of backup pads (21) through the bearing rotation, and the both ends of screw rod (22) all are equipped with and place subassembly (30).
3. The bending fatigue clamp for an aerospace device according to claim 2, wherein the moving assembly (20) further comprises:
a guide bar (23) for preventing the placement module (30) from rotating, the guide bar (23) being fixedly installed between the two sets of support plates (21);
and the servo motor (24) is fixedly arranged on the group of support plates (21), and an output shaft of the servo motor (24) is fixedly connected with the screw rod (22).
4. A bending fatigue clamp for aerospace equipment according to claim 3, wherein the placement assembly (30) comprises:
the two ends of the screw rod (22) are in threaded connection with the placing plates (31), the threaded directions of the two groups of placing plates (31) are opposite, the inner walls of the bottom ends of the two groups of placing plates (31) are in sliding connection with one group of guide rods (23), and one side of each group of placing plates (31) is provided with a limiting assembly (40) for limiting square plates or round plates;
the first placing groove (32) is used for placing square plates for manufacturing aerospace equipment, and the first placing groove (32) is formed in the inner wall of the top end of the placing plate (31);
the second placing groove (33) is used for placing and manufacturing the round plate of the aerospace equipment, the second placing groove (33) is formed in the inner wall of the middle end of the placing plate (31), and the second placing groove (33) is communicated with the first placing groove (32).
5. The bending fatigue clamp for aerospace equipment according to claim 4, wherein the first placement groove (32) is square in shape and the second placement groove (33) is semicircular in shape.
6. The bending fatigue clamp for an aerospace device according to claim 4, wherein the limiting assembly (40) is:
the first fixing plates (41) are fixedly arranged at the opposite ends of the two groups of placing plates (31);
a cylinder (42), the cylinder (42) being fixedly installed on one side of the first fixing plate (41);
the output end of the air cylinder (42) is fixedly provided with the first extrusion plate (43) through a piston rod.
7. The bending fatigue clamp for an aerospace device according to claim 4, wherein the limiting assembly (40) is:
the second fixing plates (46), the opposite ends of the two groups of placing plates (31) are fixedly provided with the second fixing plates (46);
and a telescopic rod (47), wherein the telescopic rod (47) is fixedly arranged on one side of the second fixing plate (46).
8. The bending fatigue clamp for an aerospace device according to claim 7, wherein the limit assembly (40) is further:
a spring (48), wherein the spring (48) is sleeved on the telescopic rod (47);
and a second extrusion plate (49), wherein one end of the telescopic rod (47) is fixedly provided with the second extrusion plate (49).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222507453.6U CN219455705U (en) | 2022-09-21 | 2022-09-21 | Bending fatigue clamp for aerospace equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222507453.6U CN219455705U (en) | 2022-09-21 | 2022-09-21 | Bending fatigue clamp for aerospace equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219455705U true CN219455705U (en) | 2023-08-01 |
Family
ID=87421486
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222507453.6U Active CN219455705U (en) | 2022-09-21 | 2022-09-21 | Bending fatigue clamp for aerospace equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219455705U (en) |
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2022
- 2022-09-21 CN CN202222507453.6U patent/CN219455705U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
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| TR01 | Transfer of patent right |
Effective date of registration: 20230818 Address after: 710000 Building A2, No. 1, Qinling 9th Road, Caotang Town, High-tech Zone, Xi'an City, Shaanxi Province Patentee after: Xi'an Hangfeng Testing Technology Co.,Ltd. Address before: Plant 9A, Modern Industrial Square, No. 333 Xingpu Road, Suzhou Industrial Park, Suzhou Area, China (Jiangsu) Pilot Free Trade Zone, Suzhou City, Jiangsu Province, 215000 Patentee before: Suzhou Industrial Park Invex Aviation Equipment Co.,Ltd. |