CN108942327A - It is a kind of for processing the fixture of technique for aircraft composite beam - Google Patents
It is a kind of for processing the fixture of technique for aircraft composite beam Download PDFInfo
- Publication number
- CN108942327A CN108942327A CN201710387427.5A CN201710387427A CN108942327A CN 108942327 A CN108942327 A CN 108942327A CN 201710387427 A CN201710387427 A CN 201710387427A CN 108942327 A CN108942327 A CN 108942327A
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- China
- Prior art keywords
- vacuum
- technique
- support
- fixture
- composite beam
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Classifications
-
- 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
- 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
- B23Q3/062—Work-clamping means adapted for holding workpieces having a special form or being made from a special material
- B23Q3/064—Work-clamping means adapted for holding workpieces having a special form or being made from a special material for holding elongated workpieces, e.g. pipes, bars or profiles
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Jigs For Machine Tools (AREA)
Abstract
The present invention provides a kind of for processing the fixture of technique for aircraft composite beam, comprising: the positioning of web vacuum clamps platform assembly, and the web of technique for aircraft composite beam is clamped in the upper surface that the web vacuum positioning clamps platform assembly by way of vacuum suction；And multiple edge strip support components, it includes two edge strip supporting members of base support with the two sides for being respectively installed to base support, wherein base support is used to support the positioning of web vacuum and clamps platform assembly, and edge strip supporting member includes the link mechanism being installed on base support and the rubber block that is installed on link mechanism；Wherein, the lateral position of rubber block is adjusted by adjusting link mechanism, to realize the support to the two sides edge strip of technique for aircraft composite beam.
Description
Technical field
The invention belongs to technical fields of mechanical processing, and in particular to a kind of for processing the fixture of technique for aircraft composite beam.
The fixture may be mounted on numerically controlled processing equipment, the machining for technique for aircraft composite girder construction.
Background technique
Beam is the important component in aircraft body structure as load-carrying construction part typical on aircraft.In aircraft development
In production, there are a large amount of composite material beam parts to be processed, these design of part shapes are similar, are broadly divided into " work " type
Two kinds of " C " type, but size is different.Composite material beam constitutional detail mainly uses carbon fibre composite curing molding, in order to
Meet matching requirements, other than it need to carry out trim process to beam edge strip, also needs to carry out surface to the sacrificial layer that edge strip surface is laid with
Milling Process.
The processing of Domestic Aircraft composite material beam is mainly completed on large-scale five-axis NC machine center at present, and use adds
Clamping apparatus mainly has traditional presser type fixture and conventional vacuum suction jig.Presser type fixture mainly uses all multi-platens to beam
Web is clamped to realize being loaded for entire beam, and this mode that is loaded only simply is loaded to web, without right
Beam edge strip is effectively supported, and is difficult to ensure machining accuracy when processing to beam edge strip sacrificial layer.
Conventional vacuum adsorption fixture needs to manufacture a tooling by the shape of beam, is furnished with vacuum hole in tooling, adopts when being loaded
Web and edge strip are clamped with mode is vacuumized, this vacuum adsorption fixture is bigger compared with presser type fixture adsorption capacity, folder
It is tight more reliable, but because composite material beam edge strip has rebound, it is frequently encountered beam workpiece when being loaded and is difficult to be mounted on fixture
On.Simultaneously in the development and production of aircraft, there are a large amount of various sizes of composite material beam parts to need to process, and it is each at present
The different beam of root is equipped with individual a set of vacuum fixture, and cost is very high.
Therefore, for technique for aircraft composite beam design of part the characteristics of, designs a kind of flexible high, high reliablity processed clip
Tool is the key that guarantee technique for aircraft composite beam processing quality, reduce production cost.
Summary of the invention
The present invention for poor reliability existing for existing technique for aircraft composite beam clamp for machining, it is at high cost the problems such as, provide
A kind of transformation being suitable for technique for aircraft composite girder construction geometry is realized and is pressed from both sides to technique for aircraft composite girder construction reliable location
Tight fixture.
According to the technique and scheme of the present invention, the fixture for processing technique for aircraft composite beam includes:
The positioning of web vacuum clamps platform assembly, is pressed from both sides the web of technique for aircraft composite beam by way of vacuum suction
The upper surface of clamping platform assembly is tightly positioned in the web vacuum；And
Multiple edge strip support components comprising two edge of base support and the two sides for being respectively installed to the base support
Supporting member, wherein the base support, which is used to support the web vacuum positioning, clamps platform assembly, the edge strip support
Component includes the link mechanism being installed on the base support and the rubber block that is installed on the link mechanism；
Wherein, the lateral position of the rubber block is adjusted by adjusting the link mechanism, to realize to aircraft
The support of the two sides edge strip of composite material beam.
Wherein, the link mechanism includes:
Bolt is adjusted, the base support is fixed to；
Connecting rod, one end are flexibly connected with the adjusting bolt, and the other end installs the rubber block, the connecting rod
Middle section is equipped with elongated hole；And
Support rod, one end are flexibly connected with the base support, and the other end is connected to the elongated hole and can be along institute
It is mobile to state elongated hole；
Wherein, the lateral position of the rubber block is adjusted by screwing the adjusting bolt, to realize to aircraft
The support of the two sides edge strip of composite material beam.
Wherein, the support rod is hinged to the base support.
Wherein, it includes vacuum platform that the web vacuum positioning, which clamps platform assembly, and the vacuum platform is equipped with multiple
Vacuum hole.
Wherein, it further includes the positioning pin being mounted on the vacuum platform that the web vacuum positioning, which clamps platform assembly,.
Wherein, it includes at least two vacuum platforms that web vacuum positioning, which clamps platform assembly, under each vacuum platform
Side is equipped at least two edge strip support components.
Wherein, the base support is connect by bolt with the vacuum platform.
Wherein, the rubber block is pivotally mounted to the connecting rod.
Fixture according to the present invention has the technical effect that
Since the fixture uses the edge strip support component of position adjustable, it can be achieved that both side edges to different in width beam workpiece
The secure support of item；Simultaneously according to the structure and length dimension of beam workpiece, vacuum platform quantity and the position in the fixture are adjusted
The web positioning to the beam workpiece of different structure and length can be realized and be loaded.
Entire grip device has the characteristics that high flexibility and high reliability, while easy to operate, high-efficient, at low cost.
Detailed description of the invention
Other feature and advantage of the invention will be more preferable by the preferred embodiment being described in detail below in conjunction with attached drawing
Ground understands, in which:
Fig. 1 is the schematic diagram of fixture clamping beam workpiece according to the present invention；
Fig. 2 is the structural schematic diagram of fixture according to the present invention；
Fig. 3 is the state cross-sectional view of fixture clamping beam workpiece according to the present invention (before edge strip support)；And
Fig. 4 is the state cross-sectional view of fixture clamping beam workpiece according to the present invention (after edge strip support).
Specific embodiment
In the following detailed description of the preferred embodiment, reference is constituted to the appended attached drawing of present invention a part.Institute
Attached attached drawing, which has been illustrated by way of example, can be realized specific embodiment.Exemplary embodiment is not intended to
Exhaustive all embodiments according to the present invention.It is appreciated that without departing from the scope of the present invention, can use other
Embodiment can also carry out the modification of structure or logic.
As shown in Fig. 1 to Fig. 4, show according to the present invention for processing the preferred of the fixture of technique for aircraft composite beam
Embodiment.
Fixture according to the present invention includes that the positioning of web vacuum clamps platform assembly 10 and multiple identical edge strip support groups
Part 20 is used to clamp technique for aircraft composite beam 30.It includes vacuum platform 11, vacuum that the positioning of web vacuum, which clamps platform assembly 10,
Platform 11 is equipped with multiple vacuum holes 111, and the web of technique for aircraft composite beam 30 is adsorbed folder using the mode that vacuumizes when being loaded
Tightly in the upper surface of vacuum platform 11.Preferably, it further includes being mounted on vacuum platform that the positioning of web vacuum, which clamps platform assembly 10,
Positioning pin 12 on 11.For example, positioning reference holes are arranged on vacuum platform 11, positioning pin 12 passes through the positioning reference holes, and
Location hole on the web of technique for aircraft composite beam 30 carries out cooperation positioning.
In the embodiment shown in Fig. 1-2, it includes 3 vacuum platforms 11 that the positioning of web vacuum, which clamps platform assembly 10,
It is equipped at least two edge strip support components 20 below each vacuum platform 11, is installed on the vacuum platform 11 of the leftmost side and the rightmost side
There is positioning pin 12.
Edge strip support component 20 includes two edge strip branch of base support 21 with the two sides for being respectively installed to base support 21
Component is supportted, wherein the top of base support 21 is for example connect by bolt 40 with vacuum platform 11, and it is fixed to be used to support web vacuum
Position clamping platform component 10, the bottom of base support 21 is mounted on machine tool.
Each edge strip supporting member includes the link mechanism being installed on base support 21 and is installed on link mechanism
Rubber block 22.Link mechanism includes adjusting bolt 23, connecting rod 24 and support rod 25.It adjusts bolt 23 and is fixed to base support
21, one end of connecting rod 24 is for example flexibly connected by pin shaft with bolt 23 is adjusted, and the other end installs rubber block 22, connecting rod 24
Middle section be equipped with elongated hole 241, one end of support rod 25 is for example flexibly connected by hinge with base support 21, the other end
Such as elongated hole 241 is connected to by pin shaft and can be moved along elongated hole 241.As shown in Fig. 3-Fig. 4, in use, passing through
It screws and adjusts bolt 23 to drive connecting rod 24 to move, so that the lateral position of rubber block 22 is adjusted, it is multiple to aircraft to realize
The support of the two sides edge strip of condensation material beam.
In order to be preferably bonded rubber block 22 and support the two sides edge strip of technique for aircraft composite beam 30, rubber
Block 22 is for example pivotally mounted to connecting rod 24 by bolt, and is fixed by binding nut.
Since the fixture uses the edge strip support component of position adjustable, it can be achieved that both side edges to different in width beam workpiece
The secure support of item；Simultaneously according to the structure and length dimension of beam workpiece, vacuum platform quantity and the position in the fixture are adjusted
The web positioning to the beam workpiece of different structure and length can be realized and be loaded.Entire grip device has high flexibility and Gao Ke
By property feature, at the same it is easy to operate, high-efficient, at low cost.
The technology contents and technical characterstic of specific embodiments of the present invention are had revealed that above, it being understood, however, that in this hair
Under bright creative ideas, those skilled in the art can be to various features disclosed above and the feature not being explicitly illustrated herein
Combination make various changes and improve, but belong to protection scope of the present invention.The description of above-described embodiment be exemplary and
It is not limiting, protection scope of the present invention is determined by claim.
Claims (8)
1. a kind of for processing the fixture of technique for aircraft composite beam characterized by comprising
The positioning of web vacuum clamps platform assembly (10), by the abdomen of technique for aircraft composite beam (30) by way of vacuum suction
Board clamping positions the upper surface for clamping platform assembly (10) in the web vacuum；And
Multiple edge strip support components (20) comprising base support (21) and the two sides for being respectively installed to the base support (21)
Two edge strip supporting members, wherein the base support (21), which is used to support web vacuum positioning, clamps platform assembly
(10), the edge strip supporting member includes the link mechanism being installed on the base support (21) and is installed to the connecting rod machine
Rubber block (22) on structure；
Wherein, the lateral position of the rubber block (22) is adjusted by adjusting the link mechanism, to realize to aircraft
The support of the two sides edge strip of composite material beam (30).
2. according to claim 1 for processing the fixture of technique for aircraft composite beam, which is characterized in that the link mechanism
Include:
It adjusts bolt (23), is fixed to the base support (21)；
Connecting rod (24), one end are flexibly connected with the adjusting bolt (23), and the other end installs the rubber block (22), institute
The middle section for stating connecting rod (24) is equipped with elongated hole (241)；And
Support rod (25), one end are flexibly connected with the base support (21), and the other end is connected to the elongated hole (241) simultaneously
It can be mobile along the elongated hole (241)；
Wherein, the lateral position of the rubber block (22) is adjusted by screwing adjusting bolt (23), with realization pair
The support of the two sides edge strip of technique for aircraft composite beam.
3. according to claim 2 for processing the fixture of technique for aircraft composite beam, which is characterized in that the support rod
(25) base support (21) are hinged to.
4. according to claim 1 to the fixture for being used to process technique for aircraft composite beam described in any one of 3, which is characterized in that
It includes vacuum platform (11) that the web vacuum positioning, which clamps platform assembly (10), and the vacuum platform (11) is equipped with multiple true
Emptying aperture (111).
5. according to claim 4 for processing the fixture of technique for aircraft composite beam, which is characterized in that the web vacuum
It further includes the positioning pin (12) being mounted on the vacuum platform (11) that positioning, which clamps platform assembly (10),.
6. according to claim 4 for processing the fixture of technique for aircraft composite beam, which is characterized in that the web vacuum
It includes at least two vacuum platforms (11) that positioning, which clamps platform assembly (10), is equipped at least two below each vacuum platform (11)
The edge strip support component (20).
7. according to claim 4 for processing the fixture of technique for aircraft composite beam, which is characterized in that the base support
(21) it is connect by bolt (40) with the vacuum platform (11).
8. according to claim 4 for processing the fixture of technique for aircraft composite beam, which is characterized in that the rubber
Block (22) is pivotally mounted to the connecting rod (24).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710387427.5A CN108942327B (en) | 2017-05-26 | 2017-05-26 | Clamp for machining composite material beam of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710387427.5A CN108942327B (en) | 2017-05-26 | 2017-05-26 | Clamp for machining composite material beam of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108942327A true CN108942327A (en) | 2018-12-07 |
| CN108942327B CN108942327B (en) | 2021-12-03 |
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ID=64494804
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710387427.5A Active CN108942327B (en) | 2017-05-26 | 2017-05-26 | Clamp for machining composite material beam of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108942327B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109520801A (en) * | 2018-12-04 | 2019-03-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of impact test metal and composite material interchange structure |
| CN109605072A (en) * | 2018-12-12 | 2019-04-12 | 成都飞机工业（集团）有限责任公司 | A kind of mobile assembled tool and its application method based on magnetic force base |
| CN110370137A (en) * | 2019-08-05 | 2019-10-25 | 朱科技 | A kind of aluminium shape surface automatic processing is mechanical |
| CN110893590A (en) * | 2019-12-10 | 2020-03-20 | 中航沈飞民用飞机有限责任公司 | Symmetrical positioning tool and positioning method for composite material structural part of airplane |
| CN112405051A (en) * | 2020-11-06 | 2021-02-26 | 中国航空制造技术研究院 | Composite material opening structure machining tool and machining method |
| US20210292105A1 (en) * | 2020-03-18 | 2021-09-23 | The Boeing Company | Adaptive tooling assembly |
| CN117161795A (en) * | 2023-10-31 | 2023-12-05 | 西安驰达飞机零部件制造股份有限公司 | Hydraulic clamping mechanism and clamp for machining aircraft composite beam |
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| CN105690158A (en) * | 2016-04-25 | 2016-06-22 | 湖南航天环宇通信科技股份有限公司 | Milling fixture tooling |
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| EP2380694A1 (en) * | 2010-04-20 | 2011-10-26 | Philippe Ponthoreau | Assembling table for I-beams |
| CN203185352U (en) * | 2013-03-22 | 2013-09-11 | 深圳职业技术学院 | Pneumatic centering inside-supporting clamping device |
| CN203611029U (en) * | 2013-12-09 | 2014-05-28 | 陕西飞机工业（集团）有限公司 | Combined fixture for machining large thin-wall part |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109520801A (en) * | 2018-12-04 | 2019-03-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of impact test metal and composite material interchange structure |
| CN109520801B (en) * | 2018-12-04 | 2022-02-11 | 中国航空工业集团公司西安飞机设计研究所 | Impact test metal and composite material interchange structure |
| CN109605072A (en) * | 2018-12-12 | 2019-04-12 | 成都飞机工业（集团）有限责任公司 | A kind of mobile assembled tool and its application method based on magnetic force base |
| CN109605072B (en) * | 2018-12-12 | 2021-01-05 | 成都飞机工业（集团）有限责任公司 | Mobile combined tool based on magnetic base and use method thereof |
| CN110370137A (en) * | 2019-08-05 | 2019-10-25 | 朱科技 | A kind of aluminium shape surface automatic processing is mechanical |
| CN110893590A (en) * | 2019-12-10 | 2020-03-20 | 中航沈飞民用飞机有限责任公司 | Symmetrical positioning tool and positioning method for composite material structural part of airplane |
| US20210292105A1 (en) * | 2020-03-18 | 2021-09-23 | The Boeing Company | Adaptive tooling assembly |
| US11738425B2 (en) * | 2020-03-18 | 2023-08-29 | The Boeing Company | Adaptive tooling assembly |
| US20230356367A1 (en) * | 2020-03-18 | 2023-11-09 | The Boeing Company | Adaptive tooling assembly |
| CN112405051A (en) * | 2020-11-06 | 2021-02-26 | 中国航空制造技术研究院 | Composite material opening structure machining tool and machining method |
| CN117161795A (en) * | 2023-10-31 | 2023-12-05 | 西安驰达飞机零部件制造股份有限公司 | Hydraulic clamping mechanism and clamp for machining aircraft composite beam |
| CN117161795B (en) * | 2023-10-31 | 2024-02-06 | 西安驰达飞机零部件制造股份有限公司 | Hydraulic clamping mechanism and clamp for machining aircraft composite beam |
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| CN108942327B (en) | 2021-12-03 |
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