CN213163614U - Domestic civil aircraft titanium alloy skin laser cutting anchor clamps - Google Patents
Domestic civil aircraft titanium alloy skin laser cutting anchor clamps Download PDFInfo
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- CN213163614U CN213163614U CN202020752516.2U CN202020752516U CN213163614U CN 213163614 U CN213163614 U CN 213163614U CN 202020752516 U CN202020752516 U CN 202020752516U CN 213163614 U CN213163614 U CN 213163614U
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Abstract
The utility model relates to a domestic civil aircraft titanium alloy covering laser cutting anchor clamps, include the bottom plate and adorn the location base on the bottom plate admittedly, location type piece is installed to the front end of location base, the front end of location type piece connects supporting shoe, well supporting shoe and lower shoe admittedly, the front end of going up the supporting shoe connects the locating pin admittedly, the front end of lower shoe connects down the locating pin admittedly, the surface mounting of well supporting shoe front end has the elasticity clamp, electromagnet assembly is all installed to the both sides of location base, upper and middle, lower three supporting shoe, electromagnet assembly comprises the electro-magnet and the piece of inhaling that adsorbs on the electro-magnet. The utility model discloses an electro-magnet suction is as the clamp force, and the piece is inhaled in the cooperation use for exert the clamp force on covering surface soft relatively, and can change the size of clamp force through the power adjustment of electro-magnet, better protection aircraft covering surface guarantees that the machining precision of covering meets the demands.
Description
Technical Field
The utility model relates to a laser beam machining equipment technical field specifically indicates, a domestic civil aircraft titanium alloy covering laser cutting anchor clamps.
Background
The laser cutting is to irradiate workpiece with focused high-power-density laser beam to melt, vaporize and ablate the irradiated material quickly or reach burning point, and to blow off the molten material with the help of high-speed airflow coaxial with the beam, so as to cut the material along with the movement of the beam. The laser cutting has the advantages of high precision, narrow cutting seam, smooth surface, high cutting speed, high efficiency, non-contact cutting and the like, and can realize the cutting of planes, space curved surfaces and complex figures of various materials.
The aircraft skin belongs to thin-wall component, and current skin cutting anchor clamps from the clamping mode, mainly utilize cylinder thrust to press from both sides tightly. The covering is clamped from the front and the two side surfaces respectively through the three cylinders, the cylinders are generally fixed on the base, the pressing block is installed at the head part of the ejector rod of each cylinder, and the pressing block is pressed against the covering through the air pressure of each cylinder. The cylinder is limited by the structure of the cylinder when pressing the skin, and the pressing block can generate certain impact force on the skin when contacting the skin, so that the skin can deform to a certain degree. Cylinder clamping can also damage the skin surface profile. Typically, aircraft skins are of a fully curved configuration and are of a thin sheet construction, typically a titanium alloy (Ti-6Al-4V) having a thickness of only 0.8 or 0.5 mm. If the cylinder is clamped by the traditional cylinder top, the surface roughness and the profile tolerance of the skin are adversely affected, the surface of the skin is not favorably protected, and the cylinder is high in manufacturing cost, too large in size and weight and inconvenient to process.
SUMMERY OF THE UTILITY MODEL
For overcoming the defect of prior art, the utility model provides a domestic civil aircraft titanium alloy covering laser cutting anchor clamps can effectively protect aircraft covering surface, carries out effectual clamp simultaneously and tightly.
In order to solve the above problem, the utility model discloses a technical scheme as follows:
a laser cutting clamp for titanium alloy skins of domestic civil aircrafts comprises a bottom plate and a positioning base fixedly arranged on the bottom plate, wherein a positioning block is arranged at the front end of the positioning base, an upper supporting block, a middle supporting block and a lower supporting block are fixedly connected with the front end of the positioning block, an upper positioning pin is fixedly connected with the front end of the upper supporting block, a lower positioning pin is fixedly connected with the front end of the lower supporting block, an elastic clamp is arranged on the outer surface of the front end of the middle supporting block,
electromagnet assemblies are arranged on two sides of the positioning base and two sides of the upper supporting block, the middle supporting block and the lower supporting block, and each electromagnet assembly consists of an electromagnet and a suction block adsorbed on the electromagnet.
Furthermore, two sides of the positioning base are respectively provided with two electromagnet assemblies, and two sides of the upper supporting block, the middle supporting block and the lower supporting block are respectively provided with one electromagnet assembly.
Furthermore, a base threaded hole and a hanging ring threaded hole are formed in the bottom plate, and the positioning base is connected with the base threaded hole through a screw.
Furthermore, the positioning base is connected with the positioning block through two keys, and the two keys are symmetrically arranged on the left side and the right side of the positioning block.
Furthermore, electromagnet mounting holes are respectively formed in two sides of the positioning base, and two sides of the upper supporting block, the middle supporting block and the lower supporting block, and the shape of each electromagnet mounting hole is matched with the shape of each electromagnet.
Compared with the prior art, the beneficial effects of the utility model reside in that:
1. the utility model discloses an electro-magnet suction is as the clamp force, and the piece is inhaled in the cooperation use for apply the clamp force on covering surface soft relatively, and can change the size of clamp force through the power adjustment of electro-magnet, better protection aircraft covering surface guarantees the hydrodynamics nature of covering, thereby more is favorable to the aircraft security.
2. The utility model discloses do not need the peripheral clamping device of cylinder class, only need adopt the electro-magnet direct mount on location base and upper and lower three supporting shoe for whole anchor clamps specific volume and weight reduce, the anchor clamps processing of being convenient for, installation and transportation.
3. The utility model discloses well location base is connected with the base screw hole through the screw, can adjust mounted position on the bottom plate according to the processing needs to satisfy covering parts machining's requirement.
Drawings
Fig. 1 is a front view of a preferred embodiment of the present invention.
Fig. 2 is a left side view of fig. 1.
Fig. 3 is a top view of fig. 1.
Fig. 4 is an axonometric view of the present invention.
Fig. 5 is an exploded view of fig. 4.
Detailed Description
The present invention will be described in further detail with reference to the following drawings and specific embodiments. The objects, aspects and advantages of the present invention will become more apparent from the following description. It should be understood that the described embodiments are presently preferred, but not all embodiments of the invention.
Referring to fig. 1 and 2, the laser cutting clamp for titanium alloy skins of domestic civil aircrafts comprises a bottom plate 1 and a positioning base 2 fixedly mounted on the bottom plate 1, wherein a positioning block 3 is mounted at the front end of the positioning base 2, the positioning base 2 is connected with the positioning block 3 through two keys 11, and the two keys 11 are symmetrically mounted on the left side and the right side of the positioning block 3. The front end of the positioning type block 3 is fixedly connected with an upper supporting block 4, a middle supporting block 5 and a lower supporting block 6, the front end of the upper supporting block 4 is fixedly connected with an upper positioning pin 9, the front end of the lower supporting block 6 is fixedly connected with a lower positioning pin 10, and an elastic clamp 7 is installed on the outer surface of the front end of the middle supporting block 5.
The two sides of the positioning base 2, the two sides of the upper supporting block, the two sides of the middle supporting block and the two sides of the lower supporting block are respectively provided with an electromagnet assembly 8, referring to fig. 5, each electromagnet assembly 8 is composed of an electromagnet 81 and an absorption block 82 absorbed on the electromagnet 81, and when laser cutting is carried out, a skin is clamped tightly through the electromagnets 81 and the absorption blocks 82. With reference to fig. 4, a total of 4 electromagnet assemblies 8 are mounted on the positioning base 2, and two are mounted on each side of two sides of the positioning base; two sides of the upper supporting block, the middle supporting block and the lower supporting block are respectively provided with an electromagnet assembly 8.
Referring to fig. 3, a base threaded hole 13 and a lifting ring threaded hole 14 are formed in the bottom plate 1, and the positioning base 2 is connected with the base threaded hole 13 through a screw, so that the mounting position can be adjusted on the bottom plate according to the processing requirement to meet the requirement of skin part processing.
Referring to fig. 5, electromagnet mounting holes 80 are respectively formed in two sides of the positioning base 2, and two sides of the upper support block, the middle support block and the lower support block, and the shape of the electromagnet mounting holes 80 is matched with the shape of an electromagnet 81.
Utilize the utility model discloses the process of carrying out laser cutting processing as follows:
loading: the skin blank is placed on the upper supporting block 4, the middle supporting block 5 and the lower supporting block 6 in the fixture, and is positioned through the upper positioning pin 9 and the lower positioning pin 10 on the upper supporting block 4 and the lower supporting block 6, and the elastic clamp 7 hoops the skin blank at the same time, so that the inner curved surface of the skin blank and the supporting block positioning surface are in a fit state.
Clamping: after the skin blank is positioned, the electromagnet 81 is electrified, and the suction block 82 is placed on the surface of the skin blank and aligned with the electromagnet 81 for suction. So that the inner surface of the blank is tightly attached to the positioning surface of the clamp.
Laser cutting: according to the technological requirements, the laser head can be used for implementing cutting operation according to the program.
The following steps: after laser cutting is completed, the electromagnet 81 is powered off, the suction block 82 falls off, the elastic hoop 7 is taken down, and the formed skin workpiece is taken down.
The above description is only for the purpose of illustration of the preferred embodiments of the present invention, and it is not intended to limit the scope of the present invention, and it is obvious that any person skilled in the art can easily conceive of alterations and modifications to obtain other embodiments based on the above embodiments, and these should be covered by the scope of the present invention.
Claims (5)
1. The utility model provides a domestic civil aircraft titanium alloy covering laser cutting anchor clamps which characterized in that:
comprises a bottom plate and a positioning base fixedly arranged on the bottom plate, wherein the front end of the positioning base is provided with a positioning block, the front end of the positioning block is fixedly connected with an upper supporting block, a middle supporting block and a lower supporting block, the front end of the upper supporting block is fixedly connected with an upper positioning pin, the front end of the lower supporting block is fixedly connected with a lower positioning pin, the outer surface of the front end of the middle supporting block is provided with an elastic hoop,
electromagnet assemblies are arranged on two sides of the positioning base and two sides of the upper supporting block, the middle supporting block and the lower supporting block, and each electromagnet assembly consists of an electromagnet and a suction block adsorbed on the electromagnet.
2. The laser cutting clamp for titanium alloy skins of domestic civil aircrafts according to claim 1, characterized in that:
two sides of the positioning base (2) are respectively provided with two electromagnet assemblies, and two sides of the upper supporting block, the middle supporting block and the lower supporting block are respectively provided with one electromagnet assembly.
3. The laser cutting clamp for titanium alloy skins of domestic civil aircrafts according to claim 1, characterized in that:
the bottom plate (1) is provided with a base threaded hole and a hanging ring threaded hole, and the positioning base is connected with the base threaded hole through a screw.
4. The laser cutting clamp for titanium alloy skins of domestic civil aircrafts according to claim 1, characterized in that:
the positioning base is connected with the positioning block through two keys, and the two keys are symmetrically arranged on the left side and the right side of the positioning block.
5. The laser cutting clamp for titanium alloy skins of domestic civil aircrafts according to claim 1, characterized in that:
electromagnet mounting holes are respectively formed in the two sides of the positioning base, the two sides of the upper supporting block, the two sides of the middle supporting block and the two sides of the lower supporting block, and the shape of each electromagnet mounting hole is matched with the shape of each electromagnet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020752516.2U CN213163614U (en) | 2020-05-09 | 2020-05-09 | Domestic civil aircraft titanium alloy skin laser cutting anchor clamps |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020752516.2U CN213163614U (en) | 2020-05-09 | 2020-05-09 | Domestic civil aircraft titanium alloy skin laser cutting anchor clamps |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213163614U true CN213163614U (en) | 2021-05-11 |
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ID=75764628
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020752516.2U Active CN213163614U (en) | 2020-05-09 | 2020-05-09 | Domestic civil aircraft titanium alloy skin laser cutting anchor clamps |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213163614U (en) |
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2020
- 2020-05-09 CN CN202020752516.2U patent/CN213163614U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 200233 No. 770, Xuhui District, Shanghai, Yishan Road Patentee after: Shanghai Laser Technology Research Institute Co.,Ltd. Address before: 200233 No. 770, Xuhui District, Shanghai, Yishan Road Patentee before: Shanghai Institute of Laser Technology |