CN211491147U - Aircraft cabin door processingequipment - Google Patents
Aircraft cabin door processingequipment Download PDFInfo
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- CN211491147U CN211491147U CN201921940959.8U CN201921940959U CN211491147U CN 211491147 U CN211491147 U CN 211491147U CN 201921940959 U CN201921940959 U CN 201921940959U CN 211491147 U CN211491147 U CN 211491147U
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- sealing groove
- air exhaust
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- block area
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Abstract
The utility model discloses an airplane cabin door processing device, which comprises a tool body, wherein a rectangular bulge part in the middle area of the upper surface of the tool body is a middle material block area; a rectangular outer sealing groove is formed in the periphery of the middle material block area, and a circular sealing groove and a rectangular inner sealing groove are formed in the middle material block area; sealing strips are arranged in the rectangular outer sealing groove, the circular sealing groove and the rectangular inner sealing groove; a first air exhaust hole and a second air exhaust hole are respectively formed in the middle material block area; and a third air exhaust hole communicated with the first air exhaust hole in the tool body and a fourth air exhaust hole communicated with the second air exhaust hole in the tool body are respectively arranged on two opposite side walls of the tool body. The utility model discloses a vacuum adsorption laminating, pin location, bolt clamp tightly, the clamping is simple, the location is reliable, the simple operation, has solved processing deformation and size out of tolerance problem, has shortened production clamping time, has reduced artifical volume of polishing, has improved the parts machining quality.
Description
Technical Field
The utility model belongs to the technical field of machining process equipment, concretely relates to aircraft hatch door processingequipment in aircraft spare part course of working.
Background
The aircraft manufacturing industry is currently worldwide, and with the development of science and technology and the innovation of ideas, the requirements on processing and acceptance of parts are higher and higher, so that the selection of a processing technology method and the design and application of a tool are particularly important. As for the processing of airplane cabin door parts, the parts are limited by the structural characteristics, the parts are easy to deform in the processing process, and further the processing size is not uniform, and the design required size can be ensured only by arranging a bench worker process for manual polishing treatment after a numerical control process. The self-processing quality and the processing efficiency of the part are improved, technological equipment is required to support, rapid positioning and efficient processing are realized, the mechanical manufacturing capacity is fully improved, the consumption of auxiliary materials is reduced, the workload of manual polishing and repair is reduced, and the integral processing quality of the part can be improved.
A large amount of gypsum is filled in the traditional processing method, when a processing surface is supported by stress, the part is easy to generate internal stress, the processing deformation is caused, the guarantee of processing size is influenced, the surface of the part can be corroded in different degrees, the gypsum is dissolved in cutting fluid, the surface of the part is easy to generate corrosion, the surface quality of the part is influenced in different degrees, and then the subsequent surface is polished in a large area.
Disclosure of Invention
Defect and not enough to among the prior art, the utility model provides an aircraft hatch door processingequipment solves prior art processing deformation and size out of tolerance problem, shortens the production clamping time, has removed the gypsum and has filled the requirement, reduces artifical volume of polishing by a wide margin, improves the parts machining quality.
In order to achieve the purpose, the utility model adopts the following technical proposal:
the airplane cabin door machining device comprises a tool body with a cuboid structure, wherein a rectangular convex part in the middle area of the upper surface of the tool body is a middle material block area, and the upper surface of the middle material block area is an arc-shaped concave surface so as to be attached to the large surface of an airplane cabin door to be machined in parallel;
a rectangular outer sealing groove with an upward opening is formed in the periphery of the middle material block area, and a circular sealing groove with an upward opening, which is matched with the circular part of the cabin door of the airplane to be processed, and a rectangular inner sealing groove with an upward opening, which is matched with the rectangular part of the cabin door of the airplane to be processed, are formed in the middle material block area; sealing strips are arranged in the rectangular outer sealing groove, the circular sealing groove and the rectangular inner sealing groove;
a first air exhaust hole and a second air exhaust hole are respectively formed in the two ends of the middle material block area; and a third air exhaust hole communicated with the first air exhaust hole in the tool body and a fourth air exhaust hole communicated with the second air exhaust hole in the tool body are respectively arranged on two opposite side walls of the tool body.
The utility model discloses still include following technical characteristic:
specifically, the surfaces of the middle material block regions outside the circular sealing groove and the rectangular inner sealing groove are provided with latticed air exhaust grooves which can be communicated with the first air exhaust hole and the second air exhaust hole.
Specifically, a first positioning pin hole is formed in the circle center of a circular area defined by the circular sealing groove, and two bolt holes are formed in two sides of the first positioning pin hole; a second positioning pin hole is formed in the center of a rectangular area defined by the rectangular inner sealing grooves, and two bolt holes are formed in two sides of the second positioning pin hole.
Specifically, the third air exhaust hole and the fourth air exhaust hole are both connected with a vacuum air exhaust device, and the vacuum air exhaust device comprises an air exhaust pipe, a joint and a vacuum pump; one end of the exhaust pipe is connected with the third exhaust hole and the fourth exhaust hole, and the other end of the exhaust pipe is connected with the vacuum pump through the joint.
Specifically, the upper surface of the tool body is provided with bolt holes distributed around the middle material block area in a circle.
Specifically, the number of the bolt holes distributed on the upper surface of the tool body around the middle material block area is eight, and two bolt holes are correspondingly arranged on the outer side of each edge of the middle material block area.
Specifically, the two opposite side walls of the tool body are provided with pressure plate grooves.
Compared with the prior art, the utility model, profitable technological effect is:
the utility model discloses a vacuum adsorption laminating, pin location, bolt clamp tightly, the clamping is simple, the location is reliable, the simple operation, has solved processing deformation and size out of tolerance problem, has shortened production clamping time, has removed the gypsum filling requirement, has reduced artifical volume of polishing by a wide margin, has improved the part processingquality.
Through the utility model discloses, can be to all aircraft hatches, carry out the deformation control of course of working, machining dimension control, surface quality improves etc, utilize numerical control processing technology to replace artifical the polishing, utilize the frock to support and replace a large amount of gypsum and fill, the lathe utilization ratio has fully been improved, the auxiliary material that significantly reduces consumes, the difficult processing of work piece has directly been solved in the course of working, the difficult assurance of size, the problem that surface quality is poor, surface corrosion and corrosion owing to pack the gypsum and cause have been avoided, and owing to polish the surperficial different degrees overburning that causes, new breakthrough has been had in the aspect of the processing control of this type of part.
Compared with the traditional processing method, the utility model relates to a thinking closely combines the actual processing of part, and frock structural processing is guaranteed to be leading with solution course of working deformation, machining size, and the frock uses the location high-efficient, and the clamping is simple, and the machining effect is obvious, and the steady quality directly eliminates the bench worker surface and polishes, directly eliminates the gypsum and fills, fully gives play to the manufacturing advantage of digit control machine tool.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is a top view of the present invention.
Fig. 3 is a front view of the present invention and the part mounting type.
Fig. 4 is a side view of the present invention and a part molding.
Fig. 5 is a top view of the present invention and a part mounting type.
In the figure, the reference numbers are 1-a tool body, 2-a middle material block area and 3-an airplane cabin door;
11-a third air extraction hole, 12-a fourth air extraction hole and 13-a pressure plate groove;
21-a rectangular outer sealing groove, 22-a circular sealing groove, 23-a rectangular inner sealing groove, 25-a first air extraction hole, 26-a second air extraction hole and 27-an air extraction groove;
221-first dowel hole, 231-second dowel hole.
Detailed Description
The following detailed description of the embodiments of the present invention will be made with reference to the accompanying drawings. It is to be understood that the description of the embodiments herein is for purposes of illustration and explanation only and is not intended to limit the invention.
As shown in fig. 1 to 5, the utility model provides an airplane cabin door processing device, which comprises a tool body 1 with a cuboid structure, wherein a rectangular convex part in the middle area of the upper surface of the tool body 1 is a middle material block area 2, and the upper surface of the middle material block area 2 is an arc concave surface to be attached to the large surface of an airplane cabin door 3 to be processed in parallel; a rectangular outer sealing groove 21 with an upward opening is formed in the periphery of the middle material block area 2, and a circular sealing groove 22 with an upward opening, which is matched with the circular part of the airplane door 3 to be processed, and a rectangular inner sealing groove 23 with an upward opening, which is matched with the rectangular part of the airplane door 3 to be processed, are formed in the middle material block area 2; sealing strips are arranged in the rectangular outer sealing groove 21, the circular sealing groove 22 and the rectangular inner sealing groove 23; a first air exhaust hole 25 and a second air exhaust hole 26 are respectively arranged at two ends of the middle material block area 2; and a third air exhaust hole 11 communicated with the first air exhaust hole 25 inside the tool body 1 and a fourth air exhaust hole 12 communicated with the second air exhaust hole 26 inside the tool body 1 are respectively arranged on two opposite side walls of the tool body 1. After the tool body 1 is attached to the large surface of the part, a vacuum pumping device is used for vacuumizing and adsorbing to ensure that the part is completely attached to the tool, and frame blanks are clamped through bolts and then are processed; the vacuum clamping device adopts vacuum adsorption fitting, pin positioning and bolt clamping, is simple in clamping, reliable in positioning and convenient and fast to operate, solves the problems of machining deformation and size over-tolerance, shortens the production clamping time, removes the gypsum filling requirement, greatly reduces the manual grinding amount and improves the part machining quality.
In the present embodiment, the surface of the intermediate block region 2 other than the circular seal groove 22 and the rectangular inner seal groove 23 is provided with the air extraction grooves 27 in a grid shape which can communicate with the first air extraction holes 25 and the second air extraction holes 26. The vacuum pumping device can pump vacuum between the middle material block area 2 and the part through the pumping groove 27, so that the part is tightly attached to the middle material block area 2, and the closer the part is attached to the middle material block area, the more uniform the supporting force provided when the tool body 1 clamps the part is, thereby ensuring that the part is not easy to deform in the subsequent processing process and ensuring the size precision of part processing; meanwhile, the problem of corrosion on the surface of the part caused by filling the gypsum is avoided, the step of polishing the surface of a bench worker is eliminated, and the speed of processing the part is increased.
A first positioning pin hole 221 is formed in the circle center of a circular area enclosed by the circular sealing groove 22, and two bolt holes are formed in two sides of the first positioning pin hole 221; a second positioning pin hole 231 is formed in the center of a rectangular region surrounded by the rectangular inner sealing groove 23, and two bolt holes are formed in two sides of the second positioning pin hole 231. The first positioning pin hole 221 and the second positioning pin hole 231 are used for accurately positioning a circular part and a rectangular part of a part or an airplane cabin door through being matched with positioning pins, the positioning pins can quickly position the part, the time for production clamping is shortened, and the production efficiency is improved. After positioning, the two bolt holes on two sides of the first positioning pin hole 221 and the two bolt holes on two sides of the second positioning pin hole 231 are matched with bolts to fix the part or the material block in the middle area of the airplane door in the middle material block area 2.
The third air exhaust hole 11 and the fourth air exhaust hole 12 are both connected with a vacuum air exhaust device, and the vacuum air exhaust device comprises an air exhaust pipe, a joint and a vacuum pump; one end of the air exhaust pipe is connected with the third air exhaust hole 11 and the fourth air exhaust hole 12, and the other end of the air exhaust pipe is connected with the vacuum pump through a joint. The vacuum pump is used for pumping air between the processing part and the middle material block area through the exhaust pipe, so that the processing part and the middle material block area are uniformly and tightly attached.
The bolt holes distributed around the middle material block area 2 in a circle are formed in the upper surface of the tool body 1, specifically, in the embodiment, the number of the bolt holes distributed around the middle material block area 2 in a circle is eight in the upper surface of the tool body 1, and two bolt holes are correspondingly formed in the outer side of each edge of the middle material block area 2. The tool body is used for fixing a part frame or an airplane cabin door frame on the tool body through matching with the inner hexagonal bolt.
The press plate grooves 13 are formed in the two opposite side walls of the tool body 1, so that the press plates on the working table surface of the numerical control machine tool can be clamped in the press plate grooves 13 in the subsequent machining operation of the numerical control machine tool, the tool body 1 can be fixed on the operating table surface, the consumption of auxiliary materials can be reduced, resources are saved, the weight of the tool body 1 is reduced, and the cost is reduced.
The utility model discloses an use step as follows:
1. the device is arranged on a working table as shown in figures 3 to 5 and is matched with various accessories shown in the figures;
2. sealing strips are embedded into the sealing grooves of the tool body;
3. connecting a vacuum air exhaust device, checking the air exhaust pipe to be closed and smoothly exhausting air;
4. positioning the position of the workpiece with the frame, which corresponds to the pin hole, on the tool by using a positioning pin, and ensuring that the machined molded surface of the part is attached to the large surface of the tool;
5. starting a vacuum air extractor, confirming that the sealing effect is good, and checking that the air pressure meets the adsorption requirement of the workpiece;
6. fixing the workpiece on the tool by using bolts corresponding to the tool bolt holes respectively;
7. setting a processing reference, setting a tool, inputting a numerical control program according to the technological processing requirements, starting the numerical control machine tool to process, and normally processing the workpiece according to the processing content of the technological numerical control program.
The preferred embodiments of the present invention have been described in detail with reference to the accompanying drawings, however, the present invention is not limited to the details of the above embodiments, and the technical concept of the present invention can be within the scope of the present invention to perform various simple modifications to the technical solution of the present invention, and these simple modifications all belong to the protection scope of the present invention.
It should be noted that the various features described in the above embodiments may be combined in any suitable manner without departing from the scope of the invention. In order to avoid unnecessary repetition, the present invention does not separately describe various possible individual aspects.
In addition, various embodiments of the present invention can be combined arbitrarily, and the disclosed content should be regarded as the present invention as long as it does not violate the idea of the present invention.
Claims (7)
1. The airplane cabin door machining device is characterized by comprising a tool body (1) with a cuboid structure, wherein a rectangular convex part in the middle area of the upper surface of the tool body (1) is a middle material block area (2), and the upper surface of the middle material block area (2) is an arc-shaped concave surface to be attached to the large surface of an airplane cabin door (3) to be machined in parallel;
a rectangular outer sealing groove (21) with an upward opening is formed in the periphery of the middle material block area (2), a circular sealing groove (22) with an upward opening, which is matched with the circular part of the airplane cabin door (3) to be processed, and a rectangular inner sealing groove (23) with an upward opening, which is matched with the rectangular part of the airplane cabin door (3) to be processed, are formed in the middle material block area (2); sealing strips are arranged in the rectangular outer sealing groove (21), the circular sealing groove (22) and the rectangular inner sealing groove (23);
a first air suction hole (25) and a second air suction hole (26) are respectively arranged at two ends of the middle material block area (2); and a third air exhaust hole (11) communicated with the first air exhaust hole (25) in the tool body (1) and a fourth air exhaust hole (12) communicated with the second air exhaust hole (26) in the tool body (1) are respectively arranged on two opposite side walls of the tool body (1).
2. The aircraft door machining device according to claim 1, characterized in that a latticed air suction groove (27) which can be connected with the first air suction hole (25) and the second air suction hole (26) is provided on the surface of the intermediate block region (2) outside the circular sealing groove (22) and the rectangular inner sealing groove (23).
3. The aircraft door processing device according to claim 1, wherein a first positioning pin hole (221) is formed in the center of a circular area enclosed by the circular sealing groove (22), and two bolt holes are formed in two sides of the first positioning pin hole (221); a second positioning pin hole (231) is formed in the center of a rectangular area surrounded by the rectangular inner sealing groove (23), and two bolt holes are formed in two sides of the second positioning pin hole (231).
4. The aircraft door machining device according to claim 1, characterized in that a vacuum suction device is connected to each of the third suction hole (11) and the fourth suction hole (12), the vacuum suction device comprising a suction pipe, a joint and a vacuum pump; one end of the air exhaust pipe is connected with the third air exhaust hole (11) and the fourth air exhaust hole (12), and the other end of the air exhaust pipe is connected with the vacuum pump through the joint.
5. The aircraft door machining device according to claim 1, characterized in that bolt holes arranged around the middle block area (2) are formed in the upper surface of the tool body (1).
6. The aircraft door processing device according to claim 5, characterized in that the number of the bolt holes arranged on the upper surface of the tool body (1) around the middle block area (2) is eight, and two bolt holes are correspondingly arranged on the outer side of each edge of the middle block area (2).
7. The aircraft door machining device according to claim 1, characterized in that the presser plate grooves (13) are provided on both opposite side walls of the tool body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921940959.8U CN211491147U (en) | 2019-11-11 | 2019-11-11 | Aircraft cabin door processingequipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921940959.8U CN211491147U (en) | 2019-11-11 | 2019-11-11 | Aircraft cabin door processingequipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211491147U true CN211491147U (en) | 2020-09-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921940959.8U Active CN211491147U (en) | 2019-11-11 | 2019-11-11 | Aircraft cabin door processingequipment |
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| Country | Link |
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| CN (1) | CN211491147U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114952334A (en) * | 2022-04-26 | 2022-08-30 | 成都市鸿侠科技有限责任公司 | Milling tool for aircraft wall plate |
-
2019
- 2019-11-11 CN CN201921940959.8U patent/CN211491147U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114952334A (en) * | 2022-04-26 | 2022-08-30 | 成都市鸿侠科技有限责任公司 | Milling tool for aircraft wall plate |
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