CN216126399U - Aircraft skin stretcher jaw - Google Patents
Aircraft skin stretcher jaw Download PDFInfo
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- CN216126399U CN216126399U CN202120204936.1U CN202120204936U CN216126399U CN 216126399 U CN216126399 U CN 216126399U CN 202120204936 U CN202120204936 U CN 202120204936U CN 216126399 U CN216126399 U CN 216126399U
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- jaw
- connecting seat
- jaws
- aircraft skin
- hydraulic cylinder
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Abstract
The utility model belongs to the technical field of aircraft manufacturing, and particularly relates to a jaw of an aircraft skin stretcher. The clamping device comprises a connecting seat, a lower jaw, an upper jaw, a hydraulic cylinder and a ox nose, wherein the lower jaw is arranged at the bottom of the inner side of the connecting seat, the upper jaw is arranged at the upper part of the inner side of the connecting seat, and the hydraulic cylinder penetrates through the upper end face of the connecting seat and then is connected with the upper jaw; the ox nose is arranged on the side surface of the upper part of the jaw part of the connecting seat; the upper jaws and the lower jaws are arranged in a blocking and alternating mode, the number of the upper jaws is at least 3, and the number of the lower jaws is at least 2; each upper jaw is connected with the output end of the hydraulic cylinder; the bottom and the outer side surface of the ox nose are designed in an arc shape. The centre gripping is more fastened, effectively prevents to tear, and skin spare is higher with aircraft skin part goodness of fit, effectively places the formation of fold.
Description
Technical Field
The utility model belongs to the technical field of aircraft manufacturing, and particularly relates to a novel jaw of an aircraft skin stretcher.
Background
At present, each jaw for the aircraft skin stretcher is clamped by a hydraulic control jaw, and the contact part of the front end of the jaw and an aluminum plate is a right-angle transfer block.
Ubiquitous: 1. the poor clamping results in the aluminum sheet slipping off the jaws during the stretching process and easily causes the aluminum sheet to tear from the clamping position. 2. The aluminum plate is directly clamped, so that the aluminum plate is easy to wrinkle at a joint, and the aluminum plate forms a dead fold at the joint and the wrinkling position during stretching, so that a product cannot reach the standard within the specified stretching times; 3. the front end of the jaw is provided with a right-angle transfer block, so that the aluminum plate can not be completely matched with the hyperbolic or saddle-shaped profile of the die during stretching, the stretching forming is not in place, and the product is out of tolerance or scrapped; 4. in the stretching process, materials are taken and loaded again at every time, the space is insufficient, the operation of workers is inconvenient, and the working efficiency is influenced.
SUMMERY OF THE UTILITY MODEL
The utility model aims to: the utility model provides a novel aircraft skin stretcher keeps silent, solves among the prior art the not tight technical problem who drops easily of centre gripping of keeping silent, and corrugate easily at the clamping process.
In order to achieve the aim, the jaw of the aircraft skin stretcher comprises a connecting seat, a lower jaw, an upper jaw, a hydraulic cylinder and a ox nose, wherein the lower jaw is arranged at the bottom of the inner side of the connecting seat, the upper jaw is arranged at the upper part of the inner side of the connecting seat, and the hydraulic cylinder penetrates through the upper end face of the connecting seat and then is connected with the upper jaw; the ox nose is arranged on the side surface of the upper part of the jaw part of the connecting seat; the method is characterized in that: the upper jaws and the lower jaws are arranged in a blocking and alternating mode, the number of the upper jaws is at least 3, and the number of the lower jaws is at least 2; each upper jaw is connected with the output end of the hydraulic cylinder; the bottom and the outer side surface of the ox nose are designed in an arc shape.
Furthermore, the upper jaw is sequentially clamped from the middle to two sides under the control of the hydraulic cylinder.
Furthermore, two sides of the connecting seat are connected with the force bearing seat through connecting shafts.
Furthermore, the bearing seat is fixed on the supporting plate through screws.
Furthermore, the ends of the upper jaw and the lower jaw are in a trapezoidal or conical structure.
Furthermore, the end faces of the upper jaw and the lower jaw are provided with 35-degree twills.
Furthermore, the upper jaw is 9 groups and the lower jaw is 8 groups, and the end of the lower jaw is just opposite to the gap between the upper jaws.
Further, the lower bottom surface of the jaw part of the connecting seat is bent downwards from inside to outside.
Compared with the prior art, the utility model has the beneficial effects that: the upper jaws are designed in a partitioning mode, a hydraulic cylinder which is controlled independently is arranged on each upper jaw, and then the clamping sequence of the jaws is controlled by controlling the extension and contraction of a hydraulic rod; the upper and lower jaws are alternately arranged, so that the clamping force is remarkably improved, and the tearing is prevented; the bottom surface of the ox nose is kept parallel to the bottom surface of the upper part of the jaw of the connecting seat, and then the outer side surface of the ox nose and the bottom surface form an arc shape, so that the aluminum plate is completely inosculated with the hyperbolic or saddle-shaped molded surface of the die, and the stretching forming is ensured to be accurate and in place.
Drawings
Fig. 1 is a schematic perspective view of the present invention.
Fig. 2 is a schematic end view of the present invention.
Description of reference numerals: 1. a support plate; 2. a force bearing seat; 3. a connecting shaft; 4. a connecting seat; 5. A lower jaw mounting base; 6. a lower jaw; 7. an upper jaw; 8. an upper jaw mounting base; 9. a hydraulic cylinder; 10. a bovine nose; 11. a skin member.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Thereby effectively solving the technical problems that the jaw is not tightly clamped and is easy to fall off and easy to wrinkle in the clamping process in the prior art. The upper jaws are designed in a partitioning mode, a hydraulic cylinder which is controlled independently is arranged on each upper jaw, and then the clamping sequence of the jaws is controlled by controlling the extension and contraction of a hydraulic rod; the upper and lower jaws are alternately arranged, so that the clamping force is remarkably improved, and the tearing is prevented; the bottom surface of the ox nose is kept parallel to the bottom surface of the upper part of the jaw of the connecting seat, and then the outer side surface of the ox nose and the bottom surface form an arc shape, so that the aluminum plate is completely inosculated with the hyperbolic or saddle-shaped molded surface of the die, and the stretching forming is ensured to be accurate and in place.
In order to effectively reduce the wrinkle formation of the jaws of the aircraft skin stretching machine in the clamping process, the jaws of the aircraft skin stretching machine are further clamped from the middle to two sides in sequence in the clamping process under the control of the hydraulic cylinder 9 by the upper jaw 7.
In order to make the skin covering machine 10 easier to install and disassemble, the two sides of the connecting seat 4 are movably connected with the bearing seat 2 through the connecting shaft 3, the inner connecting shaft 3 can be pulled out in the installation process, the skin covering machine can be inserted and connected after being assembled and disassembled, and in addition, the equipment maintenance can be more convenient and faster.
In order to make the transportation and maintenance of the whole equipment more convenient and reduce the maintenance cost of the equipment, further, the force bearing seat 2 is fixed on the supporting plate 1 through screws, and the supporting plate 1 is connected with the stretching mechanism, so that the stretching of the skin is realized through stretching the supporting plate 1 in the skin process.
In order to enable the jaws to clamp more firmly and effectively prevent tearing or clamping falling, the ends of the upper jaw 7 and the lower jaw 6 are in a trapezoidal or conical structure.
In order to enable the clamping of the jaws to be firmer and effectively prevent tearing or clamping falling, the end faces of the upper jaw 7 and the lower jaw 6 are further provided with 35-degree twills.
In one embodiment of the utility model, the upper jaws 7 are 9 sets and the lower jaws 6 are 8 sets, and the ends of the lower jaws 6 face the gaps between the upper jaws 7.
In one embodiment of the utility model, the upper jaws 7 are 7 groups and the lower jaws 6 are 8 groups, and the ends of the lower jaws 6 are opposite to the gap between the upper jaws 7.
In another embodiment of the utility model, the upper jaws 7 are set to 11 and the lower jaws 6 are set to 10, and the ends of the lower jaws 6 are opposite to the gap between the upper jaws 7.
The lower bottom surface of the jaw part of the preferable connecting seat 4 is of an arc structure which is bent downwards, so that the inside of the jaw has a larger operation space, and the installation convenience of the skin piece 11 is improved.
The working principle and the working process are as follows: in the working process, the skin piece 11 is fixed to the jaws of the aircraft skin stretching machine symmetrically arranged, the jaw part of the specific connecting seat 4 extends into the space between the upper jaw 7 and the lower jaw 6, then the hydraulic cylinder is controlled to move from the middle to two sides and clamp by controlling the electromagnetic valve and further controlling the oil supply of the hydraulic cylinder, and then the upper jaw 7 fixed to the bottom of the hydraulic cylinder is driven to move downwards, so that the upper jaw 7 is sequentially clamped from the middle to two sides, then the stretching mechanism arranged at the bottom of the jaws of the aircraft skin stretching machine is started, the skin piece control mechanism in the middle of the skin machine is also started, so that the stretching skin piece is realized, and the skin piece 11 is in dislocation occlusion of the upper jaw 7 and the lower jaw 6 and is firmer and effectively prevented from falling. And after covering is finished, controlling the hydraulic cylinders to simultaneously loosen to finish covering.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. The jaw of the aircraft skin stretcher comprises a connecting seat (4), a lower jaw (6), an upper jaw (7), a hydraulic cylinder (9) and a ox nose (10), wherein the lower jaw (6) is arranged at the bottom of the inner side of the connecting seat (4), the upper jaw (7) is arranged at the upper part of the inner side of the connecting seat (4), and the hydraulic cylinder (9) penetrates through the upper end face of the connecting seat (4) and then is connected with the upper jaw (7); the ox nose (10) is arranged on the side surface of the upper part of the jaw part of the connecting seat (4); the method is characterized in that: the upper jaws (7) and the lower jaws (6) are arranged in a blocking and alternating mode, the number of the upper jaws (7) is at least 3, and the number of the lower jaws (6) is at least 2; each upper jaw (7) is connected with the output end of the hydraulic cylinder (9); the bottom and the outer side surface of the ox nose (10) are designed into an arc shape.
2. The aircraft skin stretcher jaw of claim 1, wherein: the upper jaw (7) is sequentially clamped from the middle to two sides under the control of the hydraulic cylinder (9).
3. The aircraft skin stretcher jaw of claim 1, wherein: two sides of the connecting seat (4) are connected with the bearing seat (2) through the connecting shaft (3).
4. The aircraft skin stretcher jaw of claim 1, wherein: the bearing seat (2) is fixed on the support plate (1) through screws.
5. The aircraft skin stretcher jaw according to any one of claims 1 to 4, wherein: the ends of the upper jaw (7) and the lower jaw (6) are in a trapezoidal or conical structure.
6. The aircraft skin stretcher jaw of claim 5, wherein: the end faces of the upper jaw (7) and the lower jaw (6) are provided with 35-degree twills.
7. The aircraft skin stretcher jaw of claim 6, wherein: the upper jaw (7) is 9 groups and the lower jaw (6) is 8 groups, and the end of the lower jaw (6) is just opposite to the gap between the upper jaws (7).
8. The aircraft skin stretcher jaw of claim 1, wherein: the lower bottom surface of the jaw part of the connecting seat (4) is bent downwards from inside to outside.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120204936.1U CN216126399U (en) | 2021-01-26 | 2021-01-26 | Aircraft skin stretcher jaw |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120204936.1U CN216126399U (en) | 2021-01-26 | 2021-01-26 | Aircraft skin stretcher jaw |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216126399U true CN216126399U (en) | 2022-03-25 |
Family
ID=80764623
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120204936.1U Active CN216126399U (en) | 2021-01-26 | 2021-01-26 | Aircraft skin stretcher jaw |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216126399U (en) |
-
2021
- 2021-01-26 CN CN202120204936.1U patent/CN216126399U/en active Active
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