CN103921070B - The working method of helicopter fuselage top half frame and vacuum suck fixture - Google Patents
The working method of helicopter fuselage top half frame and vacuum suck fixture Download PDFInfo
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- CN103921070B CN103921070B CN201410142768.2A CN201410142768A CN103921070B CN 103921070 B CN103921070 B CN 103921070B CN 201410142768 A CN201410142768 A CN 201410142768A CN 103921070 B CN103921070 B CN 103921070B
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
- B23Q3/08—Work-clamping means other than mechanically-actuated
- B23Q3/088—Work-clamping means other than mechanically-actuated using vacuum means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Jigs For Machine Tools (AREA)
Abstract
The invention belongs to Machining Technology, it relates to improvement and the vacuum suck fixture of helicopter fuselage top half frame working method. The procedure of processing of the present invention is: the blank of maker body half frame; The lower surface (5) of processing machine body half frame; The upper surface (2) of processing machine body half frame; The side (1) of processing machine body half frame. The vacuum suck fixture of the present invention, it is characterised in that: it is made up of with the clamp body (9) of vacuum adsorption mechanism, left steady brace (12), right steady brace (13) and push bolt an inside. The invention solves the difficult problem that the profile tolerance, wall thickness and the web size that add big, the part of part deformation amount in man-hour are difficult to ensure card, it is to increase passing rate of processing and working (machining) efficiency.
Description
Technical field
The invention belongs to Machining Technology, it relates to improvement and the vacuum suck fixture of helicopter fuselage top half frame working method.
Background technology
The structure of certain a kind of fuselage top half of type vertiplane frame is see Fig. 1 and Fig. 2, the outline shape of overlooking of this fuselage top half frame is arch, the side 1 of this fuselage top half frame connects to form complex profile for plane and curved surface, with the frame being made up of stiffening web anyhow on the upper surface 2 of this fuselage top half frame, the bottom surface of frame is web, the upper surface 2 of fuselage top half frame has left pilot hole 3 and right pilot hole 4, boss structure and the through-hole structure also having other, the lower surface 5 of this fuselage top half frame is plane. Current processing scheme is: adopt 5-shaft linkage numerical control lathe to process, the first step, blanking; The lower surface 5 of the 2nd step, processing machine body half frame: add and man-hour the upper surface 2 of fuselage top half frame is placed on the worktable of 5-shaft linkage numerical control lathe, with the lower surface 5 of pressing plate compacting machine body half frame, the then lower surface 5 of processing machine body half frame; The upper surface 2 of the 3rd step, processing machine body half frame: blank is overturn 180 degree, the lower surface 5 of fuselage top half frame is placed on the worktable of 5-shaft linkage numerical control lathe, with the upper surface 2 of pressing plate compacting machine body half frame, the then upper surface 2 of processing machine body half frame; The side 1 of the 4th step, processing machine body half frame. Its shortcoming is: part deformation amount is big, the profile tolerance of part, wall thickness and web size are difficult to ensure card, and qualification rate and working (machining) efficiency are low.
Summary of the invention
It is an object of the invention to: working method and the vacuum suck fixture proposing helicopter fuselage top half frame of a kind of improvement, to solve the difficult problem that the profile tolerance, wall thickness and the web size that add big, the part of part deformation amount in man-hour are difficult to ensure card, it is to increase passing rate of processing and working (machining) efficiency.
The technical scheme of the present invention is: the working method of helicopter fuselage top half frame, the outline shape of overlooking of this fuselage top half frame is arch, the side 1 of this fuselage top half frame connects to form complex profile for plane and curved surface, with the frame being made up of stiffening web anyhow on the upper surface 2 of this fuselage top half frame, the bottom surface of frame is web, the upper surface 2 of fuselage top half frame has left pilot hole 3 and right pilot hole 4, also have other boss structure and through-hole structure, the lower surface 5 of this fuselage top half frame is plane, it is characterized in that, adopt 5-shaft linkage numerical control machine tooling fuselage top half frame, the step of processing is:
1, the blank of maker body half frame: adopt plate blanking to form rectangular stock, left pilot hole 3 and right pilot hole 4 is processed at the two ends of woollen length direction, set up three-dimensional system of coordinate, taking the central point of right pilot hole 4 as initial point, taking the straight line of left pilot hole 3 and right pilot hole 4 central point excessively as X-axis, positive dirction is towards left pilot hole 3, and backward, the positive dirction of Z axle is upwards for the positive dirction of Y-axis; The profile that contour machining goes out blank side 8 is overlooked according to fuselage top half frame, the profile of blank side 8 is according to the theoretical profile extension 60mm��100mm of fuselage top half frame, then contour machining along blank side 8 goes out the bolt through-hole 7 compressed, bolt through-hole 7 is positioned on the epitaxial part of blank 6, along blank 6 to overlook profile uniform;
2, the lower surface 5 of processing machine body half frame: on the adsorption plane of the vacuum suck fixture upper surface of blank 6 being placed on 5-shaft linkage numerical control worktable downwards, left steady brace 12 is inserted left pilot hole 3 inner position, right steady brace 13 is inserted right pilot hole 4 inner position, the bolt through-hole 7 that push bolt passes on blank 6 is screwed in the threaded hole on vacuum suck fixture boss 10, the edge of blank 6 is fixed on the boss 10 of vacuum suck fixture, now, the upper surface of blank 6 and the adsorption plane laminating of vacuum suck fixture, open vacuum pump the upper surface vacuum suck of blank 6 to be clamped, require that the lower surface to blank carries out roughing and precision work according to drawing, make it to become the lower surface 5 of fuselage top half frame,
3, the upper surface 2 of processing machine body half frame: unload blank 6 and overturn 180 degree, on the adsorption plane of the vacuum suck fixture lower surface of blank 6 being placed on 5-shaft linkage numerical control worktable downwards, left steady brace 12 is inserted left pilot hole 3 inner position, right steady brace 13 is inserted right pilot hole 4 inner position, the bolt through-hole 7 that push bolt passes on blank 6 is screwed in the threaded hole on vacuum suck fixture boss 10, the edge of blank 6 is fixed on the boss 10 of vacuum suck fixture, now, the lower surface of blank 6 and the adsorption plane laminating of vacuum suck fixture, open vacuum pump the upper surface vacuum suck of blank 6 to be clamped, require that the upper surface to blank carries out roughing and precision work according to drawing, make it to become the upper surface 2 of fuselage top half frame,
4, the side 1 of processing machine body half frame: the side 1 requiring processing machine body half frame according to drawing, cutter cuts through between the side 1 and push bolt of fuselage top half frame, until being excised by the epitaxial part of blank 6, forms fuselage top half frame.
For the vacuum suck fixture of processing machine body half frame, it is characterized in that: it is by the clamp body 9 of an inside with vacuum adsorption mechanism, left steady brace 12, right steady brace 13 and push bolt composition, clamp body 9 upper surface has a boss 10, the profile of the side 11 of boss 10 is identical with the profile of blank 6 side 8, the upper surface of boss 10 is plane, the upper surface of boss 10 has two the fixture pilot holes in left and right, the position of the left pilot hole of fixture with the position of the left pilot hole of fuselage top half frame is corresponding and aperture is identical, the position of the right pilot hole of fixture with the position of the right pilot hole of fuselage top half frame is corresponding and aperture is identical, along overlooking the right uniform threaded hole 15 of profile on boss 10, the quantity of threaded hole 15 is identical with the quantity of bolt through-hole 7 on blank 6 and position is corresponding, each threaded hole 15 has a push bolt, when blank 6 is located on clamp body 9, left steady brace 12 is inserted in the left pilot hole of fixture after pilot hole 3 and keeps running fit, right steady brace 13 is inserted in the right pilot hole of fixture after pilot hole 4 and keeps running fit, and the adsorption plane of the part that on blank 6, fuselage top half frame is corresponding and vacuum adsorption mechanism on boss 10 is fitted.
It is an advantage of the invention that: working method and the vacuum suck fixture proposing helicopter fuselage top half frame of a kind of improvement, solve the difficult problem that the profile tolerance, wall thickness and the web size that add big, the part of part deformation amount in man-hour are difficult to ensure card, it is to increase passing rate of processing and working (machining) efficiency. Proving through test, the passing rate of processing of the present invention improves more than 90%, and working (machining) efficiency improves more than 50%.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of fuselage top half of type vertiplane frame.
Fig. 2 is the rear view of Fig. 1.
Fig. 3 is the structural representation of the blank of fuselage top half frame.
Fig. 4 is the structural representation of vacuum suck fixture.
Embodiment
Below the present invention is described in further details. see Fig. 1 to Fig. 4, the working method of helicopter fuselage top half frame, the outline shape of overlooking of this fuselage top half frame is arch, the side 1 of this fuselage top half frame connects to form complex profile for plane and curved surface, with the frame being made up of stiffening web anyhow on the upper surface 2 of this fuselage top half frame, the bottom surface of frame is web, the upper surface 2 of fuselage top half frame has left pilot hole 3 and right pilot hole 4, also have other boss structure and through-hole structure, the lower surface 5 of this fuselage top half frame is plane, it is characterized in that, adopt 5-shaft linkage numerical control machine tooling fuselage top half frame, the step of processing is:
1, the blank of maker body half frame: adopt plate blanking to form rectangular stock, left pilot hole 3 and right pilot hole 4 is processed at the two ends of woollen length direction, set up three-dimensional system of coordinate, taking the central point of right pilot hole 4 as initial point, taking the straight line of left pilot hole 3 and right pilot hole 4 central point excessively as X-axis, positive dirction is towards left pilot hole 3, and backward, the positive dirction of Z axle is upwards for the positive dirction of Y-axis; The profile that contour machining goes out blank side 8 is overlooked according to fuselage top half frame, the profile of blank side 8 is according to the theoretical profile extension 60mm��100mm of fuselage top half frame, then contour machining along blank side 8 goes out the bolt through-hole 7 compressed, bolt through-hole 7 is positioned on the epitaxial part of blank 6, along blank 6 to overlook profile uniform;
2, the lower surface 5 of processing machine body half frame: on the adsorption plane of the vacuum suck fixture upper surface of blank 6 being placed on 5-shaft linkage numerical control worktable downwards, left steady brace 12 is inserted left pilot hole 3 inner position, right steady brace 13 is inserted right pilot hole 4 inner position, the bolt through-hole 7 that push bolt passes on blank 6 is screwed in the threaded hole on vacuum suck fixture boss 10, the edge of blank 6 is fixed on the boss 10 of vacuum suck fixture, now, the upper surface of blank 6 and the adsorption plane laminating of vacuum suck fixture, open vacuum pump the upper surface vacuum suck of blank 6 to be clamped, require that the lower surface to blank carries out roughing and precision work according to drawing, make it to become the lower surface 5 of fuselage top half frame,
3, the upper surface 2 of processing machine body half frame: unload blank 6 and overturn 180 degree, on the adsorption plane of the vacuum suck fixture lower surface of blank 6 being placed on 5-shaft linkage numerical control worktable downwards, left steady brace 12 is inserted left pilot hole 3 inner position, right steady brace 13 is inserted right pilot hole 4 inner position, the bolt through-hole 7 that push bolt passes on blank 6 is screwed in the threaded hole on vacuum suck fixture boss 10, the edge of blank 6 is fixed on the boss 10 of vacuum suck fixture, now, the lower surface of blank 6 and the adsorption plane laminating of vacuum suck fixture, open vacuum pump the upper surface vacuum suck of blank 6 to be clamped, require that the upper surface to blank carries out roughing and precision work according to drawing, make it to become the upper surface 2 of fuselage top half frame,
4, the side 1 of processing machine body half frame: the side 1 requiring processing machine body half frame according to drawing, cutter cuts through between the side 1 and push bolt of fuselage top half frame, until being excised by the epitaxial part of blank 6, forms fuselage top half frame.
For the vacuum suck fixture of processing machine body half frame, it is characterized in that: it is by the clamp body 9 of an inside with vacuum adsorption mechanism, left steady brace 12, right steady brace 13 and push bolt composition, clamp body 9 upper surface has a boss 10, the profile of the side 11 of boss 10 is identical with the profile of blank 6 side 8, the upper surface of boss 10 is plane, the upper surface of boss 10 has two the fixture pilot holes in left and right, the position of the left pilot hole of fixture with the position of the left pilot hole of fuselage top half frame is corresponding and aperture is identical, the position of the right pilot hole of fixture with the position of the right pilot hole of fuselage top half frame is corresponding and aperture is identical, along overlooking the right uniform threaded hole 15 of profile on boss 10, the quantity of threaded hole 15 is identical with the quantity of bolt through-hole 7 on blank 6 and position is corresponding, each threaded hole 15 has a push bolt, when blank 6 is located on clamp body 9, left steady brace 12 is inserted in the left pilot hole of fixture after pilot hole 3 and keeps running fit, right steady brace 13 is inserted in the right pilot hole of fixture after pilot hole 4 and keeps running fit, and the adsorption plane of the part that on blank 6, fuselage top half frame is corresponding and vacuum adsorption mechanism on boss 10 is fitted.
The structure of the vacuum adsorption mechanism of vacuum suck fixture inside is known features. The using method of vacuum suck fixture is: be connected with vacuum pump by the air exhaust nozzle of vacuum adsorption mechanism, after blank 6 is located on vacuum suck fixture, tightness system is had between the binding face of vacuum adsorption mechanism and blank 6, after starting vacuum pump, form negative pressure between blank 6 and the adsorption plane of vacuum adsorption mechanism, blank 6 is sucked on the adsorption plane of vacuum adsorption mechanism.
Embodiment 1
The working method of certain type helicopter fuselage top half frame, the step of processing is:
1, the blank of maker body half frame: adopt plate blanking to form rectangular stock, left pilot hole 3 and right pilot hole 4 is processed at the two ends of woollen length direction, set up three-dimensional system of coordinate, taking the central point of right pilot hole 4 as initial point, taking the straight line of left pilot hole 3 and right pilot hole 4 central point excessively as X-axis, positive dirction is towards left pilot hole 3, and backward, the positive dirction of Z axle is upwards for the positive dirction of Y-axis; The profile that contour machining goes out blank side 8 is overlooked according to fuselage top half frame, the profile of blank side 8 is according to the theoretical profile extension 70mm of fuselage top half frame, then contour machining along blank side 8 goes out the bolt through-hole 7 compressed, bolt through-hole 7 is positioned on the epitaxial part of blank 6, along blank 6 to overlook profile uniform;
2, the lower surface 5 of processing machine body half frame: on the adsorption plane of the vacuum suck fixture upper surface of blank 6 being placed on 5-shaft linkage numerical control worktable downwards, left steady brace 12 is inserted left pilot hole 3 inner position, right steady brace 13 is inserted right pilot hole 4 inner position, the bolt through-hole 7 that push bolt passes on blank 6 is screwed in the threaded hole on vacuum suck fixture boss 10, the edge of blank 6 is fixed on the boss 10 of vacuum suck fixture, now, the upper surface of blank 6 and the adsorption plane laminating of vacuum suck fixture, open vacuum pump the upper surface vacuum suck of blank 6 to be clamped, require that the lower surface to blank carries out roughing and precision work according to drawing, make it to become the lower surface 5 of fuselage top half frame,
3, the upper surface 2 of processing machine body half frame: unload blank 6 and overturn 180 degree, on the adsorption plane of the vacuum suck fixture lower surface of blank 6 being placed on 5-shaft linkage numerical control worktable downwards, left steady brace 12 is inserted left pilot hole 3 inner position, right steady brace 13 is inserted right pilot hole 4 inner position, the bolt through-hole 7 that push bolt passes on blank 6 is screwed in the threaded hole on vacuum suck fixture boss 10, the edge of blank 6 is fixed on the boss 10 of vacuum suck fixture, now, the lower surface of blank 6 and the adsorption plane laminating of vacuum suck fixture, open vacuum pump the upper surface vacuum suck of blank 6 to be clamped, require that the upper surface to blank carries out roughing and precision work according to drawing, make it to become the upper surface 2 of fuselage top half frame,
4, the side 1 of processing machine body half frame: the side 1 requiring processing machine body half frame according to drawing, cutter cuts through between the side 1 and push bolt of fuselage top half frame, until being excised by the epitaxial part of blank 6, forms fuselage top half frame.
Claims (2)
1. the working method of helicopter fuselage top half frame, the outline shape of overlooking of this fuselage top half frame is arch, the side (1) of this fuselage top half frame connects to form complex profile for plane and curved surface, with the frame being made up of stiffening web anyhow on the upper surface (2) of this fuselage top half frame, the bottom surface of frame is web, the upper surface (2) of fuselage top half frame has left pilot hole (3) and right pilot hole (4), also have other boss structure and through-hole structure, the lower surface (5) of this fuselage top half frame is plane, it is characterized in that, adopt 5-shaft linkage numerical control machine tooling fuselage top half frame, the step of processing is:
1.1, the blank of maker body half frame: adopt plate blanking to form rectangular stock, left pilot hole (3) and right pilot hole (4) is processed at the two ends of woollen length direction, set up three-dimensional system of coordinate, taking the central point of right pilot hole (4) as initial point, taking the straight line of left pilot hole (3) and right pilot hole (4) central point excessively as X-axis, positive dirction is towards left pilot hole (3), the positive dirction of Y-axis is backward, and point to back of a bow direction, the positive dirction of Z axle is upwards; The profile that contour machining goes out blank side (8) is overlooked according to fuselage top half frame, the profile of blank side (8) is according to the theoretical profile extension 60mm��100mm of fuselage top half frame, then contour machining along blank side (8) goes out the bolt through-hole (7) compressed, bolt through-hole (7) is positioned on the epitaxial part of blank (6), along blank (6) to overlook profile uniform;
1.2, the lower surface (5) of processing machine body half frame: on the adsorption plane of the vacuum suck fixture that the upper surface of blank (6) is placed on 5-shaft linkage numerical control worktable downwards, left steady brace (12) is inserted left pilot hole (3) inner position, right steady brace (13) is inserted right pilot hole (4) inner position, the bolt through-hole (7) that push bolt passes on blank (6) is screwed in the threaded hole in vacuum suck fixture boss (10), the edge of blank (6) is fixed on the boss (10) of vacuum suck fixture, now, the upper surface of blank (6) and the adsorption plane laminating of vacuum suck fixture, open vacuum pump the upper surface vacuum suck of blank (6) to be clamped, require that the lower surface to blank carries out roughing and precision work according to drawing, make it to become the lower surface (5) of fuselage top half frame,
1.3, the upper surface (2) of processing machine body half frame: unload blank (6) and overturn 180 degree, on the adsorption plane of the vacuum suck fixture that the lower surface of blank (6) is placed on 5-shaft linkage numerical control worktable downwards, left steady brace (12) is inserted left pilot hole (3) inner position, right steady brace (13) is inserted right pilot hole (4) inner position, the bolt through-hole (7) that push bolt passes on blank (6) is screwed in the threaded hole in vacuum suck fixture boss (10), the edge of blank (6) is fixed on the boss (10) of vacuum suck fixture, now, the lower surface of blank (6) and the adsorption plane laminating of vacuum suck fixture, open vacuum pump the upper surface vacuum suck of blank (6) to be clamped, require that the upper surface to blank carries out roughing and precision work according to drawing, make it to become the upper surface (2) of fuselage top half frame,
1.4, the side (1) of processing machine body half frame: the side (1) requiring processing machine body half frame according to drawing, cutter cuts through between the side (1) of fuselage top half frame and push bolt, until being excised by the epitaxial part of blank (6), form fuselage top half frame.
2. for the vacuum suck fixture of processing machine body half frame, it is characterized in that: it is by the clamp body (9) of an inside with vacuum adsorption mechanism, left steady brace (12), right steady brace (13) and push bolt composition, clamp body (9) upper surface has a boss (10), the profile of the side (11) of boss (10) is identical with the profile of blank (6) side (8), the upper surface of boss (10) is plane, the upper surface of boss (10) has two the fixture pilot holes in left and right, the position of the left pilot hole of fixture with the position of the left pilot hole of fuselage top half frame is corresponding and aperture is identical, the position of the right pilot hole of fixture with the position of the right pilot hole of fuselage top half frame is corresponding and aperture is identical, overlook profile on the upper edge of boss (10) and have uniform threaded hole (15), the quantity of the quantity of threaded hole (15) bolt through-hole (7) upper with blank (6) is identical and position is corresponding, each threaded hole (15) has a push bolt, when blank (6) is located on clamp body (9), left steady brace (12) is inserted in the left pilot hole of fixture after left pilot hole (3) and keeps running fit, right steady brace (13) is inserted in the right pilot hole of fixture after right pilot hole (4) and keeps running fit, and part and the adsorption plane of the upper vacuum adsorption mechanism of boss (10) that on blank (6), fuselage top half frame is corresponding are fitted.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410142768.2A CN103921070B (en) | 2014-04-10 | 2014-04-10 | The working method of helicopter fuselage top half frame and vacuum suck fixture |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410142768.2A CN103921070B (en) | 2014-04-10 | 2014-04-10 | The working method of helicopter fuselage top half frame and vacuum suck fixture |
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| CN103921070B true CN103921070B (en) | 2016-06-01 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106181228A (en) * | 2015-05-07 | 2016-12-07 | 哈尔滨飞机工业集团有限责任公司 | A kind of mechanical process technique of one side complex-shaped surface mould large-scale part |
| CN106695409A (en) * | 2017-02-15 | 2017-05-24 | 珠海格力智能装备有限公司 | Chuck clamp and display screen edge frame processing equipment |
| CN108942327B (en) * | 2017-05-26 | 2021-12-03 | 中国商用飞机有限责任公司 | Clamp for machining composite material beam of airplane |
| EP3646985A4 (en) | 2017-11-07 | 2020-11-18 | Mitsubishi Heavy Industries, Ltd. | Processing apparatus and processing method |
| CN109108578B (en) * | 2018-08-28 | 2020-05-19 | 科瑞自动化技术（苏州）有限公司 | Method for processing core part on semiconductor packaging equipment |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN201015850Y (en) * | 2007-02-16 | 2008-02-06 | 沈永才 | Vacuum adsorption type working table structure |
| CN101733651B (en) * | 2008-11-11 | 2012-05-30 | 苏州春兴精工股份有限公司 | Vacuum clamp for machining porous sheet and using method thereof |
| CN201371374Y (en) * | 2009-03-12 | 2009-12-30 | 嘉兴市峰佳吉晨实业有限公司 | Vacuum sucker cup device of numerical control machine tool |
| CN102029508B (en) * | 2010-11-04 | 2012-09-05 | 广东省韶铸集团有限公司 | Processing method of positioning holes and data holes at side surface of C-shaped frame |
| CN202070933U (en) * | 2011-04-29 | 2011-12-14 | 滁州兴达机电有限公司 | Processing fixture of engine body |
| FR2988317B1 (en) * | 2012-03-23 | 2014-05-09 | Airbus Operations Sas | MACHINING TOOLS FOR AIRCRAFT FUSELAGE FRAME |
| CN103252623A (en) * | 2013-05-14 | 2013-08-21 | 湖南湖大艾盛汽车技术开发有限公司 | Machining method using vacuum sucker to clamp thin-walled piece with variable wall thicknesses |
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