CN113125131A - Aviation wire experiment workbench - Google Patents
Aviation wire experiment workbench Download PDFInfo
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- CN113125131A CN113125131A CN202110259942.1A CN202110259942A CN113125131A CN 113125131 A CN113125131 A CN 113125131A CN 202110259942 A CN202110259942 A CN 202110259942A CN 113125131 A CN113125131 A CN 113125131A
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- 239000011248 coating agent Substances 0.000 claims description 9
- 238000000576 coating method Methods 0.000 claims description 9
- 230000003750 conditioning effect Effects 0.000 claims 1
- 238000000034 method Methods 0.000 description 2
- 241000256602 Isoptera Species 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 239000003513 alkali Substances 0.000 description 1
- 239000003153 chemical reaction reagent Substances 0.000 description 1
- 239000011247 coating layer Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 231100000053 low toxicity Toxicity 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses an aviation wire experiment workbench, wherein an output shaft of a servo motor is driven to rotate to drive an eccentric roller to axially rotate, the eccentric wheel is arranged between an inner ring and an outer ring of an eccentric guide ring, so that the eccentric roller slides between the eccentric guide ring, a steering connecting block is driven to rotate by taking the axis of the eccentric roller as a circular point, a connecting sliding rod is driven to slide up and down in a guide cylinder body, and a back plate is driven to vibrate up and down.
Description
Technical Field
The invention relates to the technical field of aviation equipment, in particular to an aviation wire experiment workbench.
Background
The aerospace industry is currently in constant demand for cables that are highly reliable, lightweight, clean, flexible and low toxicity in harsh environments. The special cable is a cable which has special purposes and can be used in special occasions, such as high temperature resistance, acid and alkali resistance, termite resistance, and electric wires and cables used in occasions such as ship, airplane, nuclear power station and the like. In terms of classification, it is not in the same classification method as the categories of power, control, computer cables, etc., i.e., the above-listed cables also include special cables. Generally, special cables need to establish enterprise internal control standards. The special cable is a series of products with unique performance and special structure, and has the characteristics of higher technical content, stricter use conditions, smaller batch and higher added value compared with the common electric wires and cables with large quantity and wide range.
After the aviation wire is actually assembled on the aircraft, the protective layer of the aviation wire is easily lost through the long-time use of the aircraft, but no experiment workbench can simulate the actual working condition of the aircraft in the flight process under a good condition at present, so that the simulation experiment result of the aviation wire cannot be accurately obtained.
Disclosure of Invention
The invention aims to provide an aviation wire experiment workbench, and aims to solve the technical problems in the prior art.
In order to achieve the purpose, the aviation wire experiment workbench adopted by the invention comprises a workbench body, a wire and a supporting device; the lead is connected with the table body through the supporting device and is positioned on one side of the table body; the supporting device comprises a supporting plate, a back plate, a skin and a vibration assembly, the supporting plate is fixedly connected with the table body and is positioned on one side of the table body close to the lead, the back plate is slidably connected with the supporting plate and is fixedly connected with the lead and is positioned on one side of the supporting plate far away from the table body, and the skin is fixedly connected with the back plate and is positioned on one side of the back plate far away from the lead; the vibration subassembly includes the direction barrel, connects slide bar, servo motor and eccentric component, the direction barrel with backup pad fixed connection, and run through the backup pad, and be located the stage body with between the backplate, the one end of connecting the slide bar with backplate fixed connection, and the other end runs through the direction barrel, and the part stretches into in the stage body, servo motor with stage body fixed connection, and the output shaft with it passes through to connect the slide bar eccentric component rotates to be connected, and is located the stage body is close to connect one side of slide bar.
Wherein, eccentric component includes eccentric guide ring and eccentric running roller, eccentric guide ring with connect slide bar fixed connection, and be located it is close to connect the slide bar one side of servo motor, eccentric running roller with eccentric guide ring rotates to be connected, and with servo motor's output fixed connection, and be located eccentric guide ring is close to one side of servo motor.
The eccentric component further comprises a steering connecting block, the steering connecting block is rotatably connected with the connecting sliding rod, fixedly connected with the eccentric guide ring and located on one side, close to the eccentric guide ring, of the connecting sliding rod.
The eccentric component further comprises a connecting rotating shaft, the connecting rotating shaft is fixedly connected with the steering connecting block, the connecting rotating shaft is rotatably connected with the connecting sliding rod, and the connecting rotating shaft is located on one side, close to the connecting sliding rod, of the steering connecting block.
The eccentric component further comprises a connecting bearing, the connecting bearing is fixedly connected with the connecting sliding rod, is rotatably connected with the connecting rotating shaft, and is located on one side, close to the connecting rotating shaft, of the connecting sliding rod.
The vibration component further comprises a hydraulic cylinder and a telescopic rod, the hydraulic cylinder is fixedly connected with the supporting plate and is positioned on one side, close to the back plate, of the supporting plate; one end of the telescopic rod is fixedly connected with the output end of the hydraulic cylinder, and the other end of the telescopic rod is rotatably connected with the supporting plate and is positioned between the hydraulic cylinder and the back plate.
The vibration assembly further comprises a steering bearing, the steering bearing is fixedly connected with the back plate, is rotatably connected with the telescopic rod and is positioned on one side, close to the telescopic rod, of the back plate.
The supporting device further comprises a wire clamp, wherein the wire clamp is fixedly connected with the back plate, abutted against the lead and located on one side, close to the lead, of the back plate.
The supporting device further comprises a backboard coating, and the backboard coating is fixedly connected with the skin and is positioned on one side of the skin, which is far away from the backboard.
According to the aviation wire experiment workbench, the output shaft of the servo motor is driven to rotate, the eccentric roller is driven to rotate axially, the eccentric wheel is installed between the inner ring and the outer ring of the eccentric guide ring, so that the eccentric roller slides between the eccentric guide rings, the steering connecting block is driven to rotate by taking the axis of the eccentric roller as a circular point, the connecting sliding rod is driven to slide up and down in the guide cylinder body, the back plate is driven to vibrate up and down, the wire is installed on the inner side of the back plate, and the skin is installed on the outer side of the back plate, so that the reagent working condition of the wire in the aircraft is simulated, and the experiment result of the wire is more reliable.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic view of the structure of the vibration assembly of the present invention.
Fig. 2 is a schematic view of the internal structure of the stage of the present invention.
Fig. 3 is a schematic view of the structure of the eccentric member of the present invention.
Fig. 4 is a schematic structural view of the supporting device of the present invention.
In the figure: 1-platform body, 2-wire, 3-supporting device, 31-supporting plate, 32-back plate, 33-skin, 34-vibration component, 35-wire clamp, 36-back plate coating, 100-aviation wire experiment workbench, 341-guiding cylinder, 342-connecting sliding rod, 343-servo motor, 344-eccentric component, 345-hydraulic cylinder, 346-telescopic rod, 347-steering bearing, 3441-eccentric guiding ring, 3442-eccentric roller, 3443-steering connecting block, 3444-connecting rotating shaft and 3445-connecting bearing.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
Referring to fig. 1 to 4, the present invention provides an aviation wire experiment workbench 100, which includes a workbench body 1, a wire 2 and a supporting device 3; the lead 2 is connected with the table body 1 through the supporting device 3 and is positioned on one side of the table body 1; the supporting device 3 comprises a supporting plate 31, a back plate 32, a skin 33 and a vibrating assembly 34, the supporting plate 31 is fixedly connected with the table body 1 and is positioned on one side of the table body 1 close to the lead 2, the back plate 32 is slidably connected with the supporting plate 31 and is fixedly connected with the lead 2 and is positioned on one side of the supporting plate 31 far away from the table body 1, and the skin 33 is fixedly connected with the back plate 32 and is positioned on one side of the back plate 32 far away from the lead 2; the vibration assembly 34 includes a guide cylinder 341, a connecting slide rod 342, a servo motor 343, and an eccentric member 344, the guide cylinder 341 is fixedly connected to the support plate 31, and penetrates through the support plate 31, and is located between the table 1 and the back plate 32, one end of the connecting slide rod 342 is fixedly connected to the back plate 32, and the other end penetrates through the guide cylinder 341, and partially extends into the table 1, the servo motor 343 is fixedly connected to the table 1, and an output shaft is rotatably connected to the connecting slide rod 342 through the eccentric member 344, and is located on one side of the table 1 close to the connecting slide rod 342.
Further, referring to fig. 3, the eccentric member 344 includes an eccentric guide ring 3441 and an eccentric roller 3442, the eccentric guide ring 3441 is fixedly connected to the connecting slide bar 342 and is located at a side of the connecting slide bar 342 close to the servo motor 343, and the eccentric roller 3442 is rotatably connected to the eccentric guide ring 3441 and is fixedly connected to an output end of the servo motor 343 and is located at a side of the eccentric guide ring 3441 close to the servo motor 343.
Further, referring to fig. 3 and 4, the eccentric member 344 further includes a turning connecting block 3443, wherein the turning connecting block 3443 is rotatably connected to the connecting slide bar 342, fixedly connected to the eccentric guide ring 3441, and located on one side of the connecting slide bar 342 close to the eccentric guide ring 3441.
In this embodiment, the table body 1 is placed on the ground, the table body 1 is hollow, the top of the table body 1 has an opening, the support plate 31 is threadedly mounted at the top opening of the table body 1, the support plate 31 has a through hole, the guide cylinder 341 is mounted in the through hole of the support plate 31 and penetrates through the through hole of the support plate 31, the guide cylinder 341 is hollow, the connecting slide rod 342 is slidably mounted in the guide cylinder 341, the top of the connecting slide rod is rotatably connected with the support plate 31, the bottom of the connecting slide rod is rotatably connected with the steering connecting block 3443, the steering connecting block 3443 is swung left and right with the bottom of the connecting slide rod 342 through a rotating shaft, the eccentric guide ring 3441 is threadedly mounted on the surface of the steering connecting block 3443, the eccentric guide ring 3441 comprises an inner ring and an outer ring, and the eccentric roller 3442 is rotatably mounted in the eccentric guide ring 3441, one side of the eccentric roller 3442 is fixed with the output shaft of the servo motor 343 by a thread, and the other side has a thread, the eccentric roller 3442 is rotatably connected with the inner and outer rings of the eccentric guide ring 3441 by a thread, the inner and outer rings of the eccentric guide ring 3441 perform sliding position limitation on the outer side of the eccentric roller 3442, so that the eccentric roller 3442 can only slide between the inner and outer rings of the eccentric guide ring 3441, thus driving the output shaft of the servo motor 343 to rotate and drive the eccentric roller 3442 to rotate axially, the eccentric wheel is installed between the inner and outer rings of the eccentric guide ring 3441, and thus the eccentric roller 3442 slides between the eccentric guide ring 3441, driving the steering connecting block 3443 to rotate with the axis of the eccentric roller 3442 as a circular point 342, driving the connecting slide rod to slide up and down in the guide cylinder 341, and driving the back plate 32 to vibrate up and down, because the lead 2 is arranged on the inner side of the back plate 32, and the skin 33 is arranged on the outer side of the back plate 32, the actual working condition of the lead 2 in the aircraft is simulated, and the experimental result of the lead 2 is more credible.
Further, referring to fig. 2, the eccentric member 344 further includes a connecting rotating shaft 3444, wherein the connecting rotating shaft 3444 is fixedly connected to the steering connecting block 3443, is rotatably connected to the connecting slide bar 342, and is located at a side of the steering connecting block 3443 close to the connecting slide bar 342.
In this embodiment, the connecting rotating shaft 3444 is fixed to the turning connecting block 3443 by a screw thread, and rotates axially with the connecting slide bar 342 to drive the turning connecting block 3443 and the connecting slide bar 342 to rotate, the servo motor 343 drives the eccentric roller 3442 to swing when sliding in the eccentric guide ring 3441, and the connecting rotating shaft 3444 enables the turning connecting block 3443 and the connecting slide bar 342 to rotate.
Further, referring to fig. 3, the eccentric member 344 further includes a connecting bearing 3445, wherein the connecting bearing 3445 is fixedly connected to the connecting sliding rod 342, rotatably connected to the connecting rotating shaft 3444, and located on one side of the connecting sliding rod 342 close to the connecting rotating shaft 3444.
In this embodiment, the outer ring of the connecting bearing 3445 is fixed on the connecting sliding rod 342 by a thread, and is connected to the connecting rotating shaft 3444 by an inner ring, and is driven to rotate by the balls between the outer ring and the inner ring, and the number of the connecting bearings 3445 is two, and the two connecting bearings 3445 are respectively installed at two ends of the connecting rotating shaft 3444, so that the rotation of the connecting rotating shaft 3444 and the connecting sliding rod 342 is more stable.
Further, referring to fig. 1, the vibration assembly 34 further includes a hydraulic cylinder 345 and a telescopic rod 346, wherein the hydraulic cylinder 345 is fixedly connected to the supporting plate 31 and is located at a side of the supporting plate 31 close to the back plate 32; one end of the telescopic rod 346 is fixedly connected with the output end of the hydraulic cylinder 345, and the other end is rotatably connected with the supporting plate 31 and is positioned between the hydraulic cylinder 345 and the back plate 32.
In the present embodiment, the hydraulic cylinder 345 is screwed to the top of the support plate 31, the telescopic rod 346 is mounted to the top of the hydraulic cylinder 345, the telescopic rod 346 supports the end of the back plate 32, and the telescopic rod 346 is matched with the telescopic action of the telescopic rod 346 to slide up and down the connecting slide bar 342, so that the back plate 32 is swung back and forth, thereby simulating the situation that the aircraft bumps.
Further, referring to fig. 1, the vibration assembly 34 further includes a steering bearing 347, and the steering bearing 347 is fixedly connected to the back plate 32, rotatably connected to the telescopic rod 346, and located at a side of the back plate 32 close to the telescopic rod 346.
In this embodiment, a transverse rod is installed at the end of the telescopic rod 346, and the steering bearing 347 is screwed on the back plate 32 and is rotatably connected with the transverse rod at the end of the telescopic rod 346, so that the back plate 32 and the telescopic rod 346 rotate, and the back plate 32 shakes.
Further, referring to fig. 4, the supporting device 3 further includes a wire clamp 35, and the wire clamp 35 is fixedly connected to the back plate 32, abuts against the conducting wire 2, and is located on one side of the back plate 32 close to the conducting wire 2.
In this embodiment, the clip 35 is screwed on the inner side of the back plate 32, and clamps and fixes the wire 2 by a limit clip, so that the installation of the wire 2 is more stable.
Further, referring to fig. 4, the supporting device 3 further includes a back plate coating 36, and the back plate coating 36 is fixedly connected to the skin 33 and is located on a side of the skin 33 away from the back plate 32.
In the present embodiment, the backing plate coating 36 is a coating of the skin 33 of the aircraft, and is applied to the surface of the skin 33 to simulate a coating layer on the outer surface of the aircraft.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (9)
1. An aviation wire experiment workbench is characterized by comprising a workbench body, a wire and a supporting device;
the lead is connected with the table body through the supporting device and is positioned on one side of the table body;
the supporting device comprises a supporting plate, a back plate, a skin and a vibration assembly, the supporting plate is fixedly connected with the table body and is positioned on one side of the table body close to the lead, the back plate is slidably connected with the supporting plate and is fixedly connected with the lead and is positioned on one side of the supporting plate far away from the table body, and the skin is fixedly connected with the back plate and is positioned on one side of the back plate far away from the lead;
the vibration subassembly includes the direction barrel, connects slide bar, servo motor and eccentric component, the direction barrel with backup pad fixed connection, and run through the backup pad, and be located the stage body with between the backplate, the one end of connecting the slide bar with backplate fixed connection, and the other end runs through the direction barrel, and the part stretches into in the stage body, servo motor with stage body fixed connection, and the output shaft with it passes through to connect the slide bar eccentric component rotates to be connected, and is located the stage body is close to connect one side of slide bar.
2. The airborne wire test stand of claim 1,
the eccentric component comprises an eccentric guide ring and an eccentric roller wheel, the eccentric guide ring is fixedly connected with the connecting slide rod and is positioned on one side of the servo motor, the eccentric roller wheel is rotatably connected with the eccentric guide ring and is fixedly connected with the output end of the servo motor and is positioned on one side of the servo motor, and the eccentric guide ring is close to the servo motor.
3. The airborne wire test stand of claim 2,
the eccentric component further comprises a steering connecting block, the steering connecting block is rotatably connected with the connecting sliding rod, fixedly connected with the eccentric guide ring and located on one side, close to the eccentric guide ring, of the connecting sliding rod.
4. The airborne wire test stand of claim 3,
the eccentric component further comprises a connecting rotating shaft, the connecting rotating shaft is fixedly connected with the steering connecting block, the connecting rotating shaft is rotatably connected with the connecting sliding rod, and the connecting rotating shaft is located on one side, close to the connecting sliding rod, of the steering connecting block.
5. The airborne wire test stand of claim 4,
the eccentric component further comprises a connecting bearing, the connecting bearing is fixedly connected with the connecting sliding rod, is rotatably connected with the connecting rotating shaft, and is located on one side, close to the connecting rotating shaft, of the connecting sliding rod.
6. The airborne wire test stand of claim 1,
the vibration assembly further comprises a hydraulic cylinder and a telescopic rod, the hydraulic cylinder is fixedly connected with the supporting plate and is positioned on one side, close to the back plate, of the supporting plate; one end of the telescopic rod is fixedly connected with the output end of the hydraulic cylinder, and the other end of the telescopic rod is rotatably connected with the supporting plate and is positioned between the hydraulic cylinder and the back plate.
7. The airborne wire conditioning station of claim 6,
the vibration assembly further comprises a steering bearing, the steering bearing is fixedly connected with the back plate, is rotatably connected with the telescopic rod and is positioned on one side, close to the telescopic rod, of the back plate.
8. The airborne wire test stand of claim 1,
the supporting device further comprises a wire clamp, wherein the wire clamp is fixedly connected with the back plate, abutted against the lead and positioned on one side, close to the lead, of the back plate.
9. The airborne wire test stand of claim 1,
the supporting device further comprises a backboard coating, and the backboard coating is fixedly connected with the skin and is positioned on one side of the skin, which is far away from the backboard.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110259942.1A CN113125131A (en) | 2021-03-10 | 2021-03-10 | Aviation wire experiment workbench |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110259942.1A CN113125131A (en) | 2021-03-10 | 2021-03-10 | Aviation wire experiment workbench |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113125131A true CN113125131A (en) | 2021-07-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110259942.1A Pending CN113125131A (en) | 2021-03-10 | 2021-03-10 | Aviation wire experiment workbench |
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| Country | Link |
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| CN (1) | CN113125131A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204269326U (en) * | 2014-11-21 | 2015-04-15 | 武汉安凯电缆有限公司 | A kind of radio frequency co-axial cable subassembly vibration testing device |
| CN110426300A (en) * | 2019-07-30 | 2019-11-08 | 南京兆能节能科技有限公司 | A kind of spring fatigue test device and method |
| CN110441041A (en) * | 2019-08-07 | 2019-11-12 | 烟台中宇航空液压有限公司 | Aerial hydraulic attachments linear displacement loading test device |
| CN209691488U (en) * | 2019-05-31 | 2019-11-26 | 无锡市中鼎电工机械有限公司 | A kind of unwrapping wire wire installation of longitudinal wrap machine |
| CN111208017A (en) * | 2020-01-19 | 2020-05-29 | 宝鸡市韦思特电气有限公司 | Fatigue tolerance loading test device for spacer |
| WO2020164186A1 (en) * | 2019-02-13 | 2020-08-20 | 安徽理工大学 | Six-degree-of-freedom series-parallel electromagnetic vibration test stand |
| CN212134014U (en) * | 2020-05-28 | 2020-12-11 | 固力发电气有限公司 | Vibration simulation detection device for overhead line |
| CN112453275A (en) * | 2020-10-20 | 2021-03-09 | 陈小梅 | Peeling and cutting device for cable recovery |
| CN214471701U (en) * | 2021-03-10 | 2021-10-22 | 中国人民解放军海军航空大学青岛校区 | Aviation wire experiment workbench |
-
2021
- 2021-03-10 CN CN202110259942.1A patent/CN113125131A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204269326U (en) * | 2014-11-21 | 2015-04-15 | 武汉安凯电缆有限公司 | A kind of radio frequency co-axial cable subassembly vibration testing device |
| WO2020164186A1 (en) * | 2019-02-13 | 2020-08-20 | 安徽理工大学 | Six-degree-of-freedom series-parallel electromagnetic vibration test stand |
| CN209691488U (en) * | 2019-05-31 | 2019-11-26 | 无锡市中鼎电工机械有限公司 | A kind of unwrapping wire wire installation of longitudinal wrap machine |
| CN110426300A (en) * | 2019-07-30 | 2019-11-08 | 南京兆能节能科技有限公司 | A kind of spring fatigue test device and method |
| CN110441041A (en) * | 2019-08-07 | 2019-11-12 | 烟台中宇航空液压有限公司 | Aerial hydraulic attachments linear displacement loading test device |
| CN111208017A (en) * | 2020-01-19 | 2020-05-29 | 宝鸡市韦思特电气有限公司 | Fatigue tolerance loading test device for spacer |
| CN212134014U (en) * | 2020-05-28 | 2020-12-11 | 固力发电气有限公司 | Vibration simulation detection device for overhead line |
| CN112453275A (en) * | 2020-10-20 | 2021-03-09 | 陈小梅 | Peeling and cutting device for cable recovery |
| CN214471701U (en) * | 2021-03-10 | 2021-10-22 | 中国人民解放军海军航空大学青岛校区 | Aviation wire experiment workbench |
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