CN100534724C - Clamping device and clamping method - Google Patents
Clamping device and clamping method Download PDFInfo
- Publication number
- CN100534724C CN100534724C CNB2006100786861A CN200610078686A CN100534724C CN 100534724 C CN100534724 C CN 100534724C CN B2006100786861 A CNB2006100786861 A CN B2006100786861A CN 200610078686 A CN200610078686 A CN 200610078686A CN 100534724 C CN100534724 C CN 100534724C
- Authority
- CN
- China
- Prior art keywords
- machined surface
- connecting elements
- fixed component
- vacuum
- fastening
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Abstract
The invention relates to the clamping method for a flying machine connecting structure. The said connecting structure is clamped on the first support surface through the first fixing component. The said connecting structure is clamped on the first support surface through the first fixing component. The said third machining surface of the connecting component is clamped through the clamping equipment vacuum fixing structure, and the said vacuum fixed component applying a vacuum filed to fix the said the third machining surface.
Description
Technical field
[1] the present invention relates to a kind of clamping means and apparatus for fastening that is used to clamp the aircraft connecting elements.
Background technology
[2] in present commercial aircraft, the connection between aircraft fuselage and the aircraft wing must be in the extreme accurately with firm.In addition, be very important being connected at the interface wing being regulated very accurately of fuselage, because the length of wing, several millimeters closed tolerance can cause at place, wing end several centimetres high tolerance.For example, if the aligning between starboard wing and the fuselage is different with the aligning between port wing and the fuselage, then can cause adverse influence to the flight characteristics of aircraft.
[3] therefore, the connecting elements that wing is connected to aircraft must very accurately and exactly be made.Connecting elements can for example be the angle counterpart, and one face is connected to aircraft fuselage and another face is connected to aircraft wing.Because the size of aircraft wing is very big, the impossible accurate and single wing of manufacturing dimension, thus each wing has different tolerances.Must come these tolerances are regulated and compensated by connecting elements, obtain same aligning and adjusting, to guarantee best flight characteristics with the wing of guaranteeing aircraft.Therefore, connecting counterpart must be adaptive respectively with each wing by the milling joint face, so that the alignment error between the aircraft wing minimizes.
[4] each connection counterpart must be made individually to regulate wing with respect to fuselage.Therefore, the counterpart face that is connected with wing or fuselage in angle is by specification and the tolerance of milling (mill) to expectation.Normally, connecting elements is clamped on the apparatus for fastening like this, wherein, each face, is that each machined surface of connecting elements all mechanically is clamped on the seating surface of described apparatus for fastening.Therefore, each machined surface all must be clamped on the apparatus for fastening by for example several screw clamps, with clamping engagement part accurately and stably.
[5] by mechanically clamping all fixed component machined surfaces, clamping is an overdetermination.When the Milling Process face, for example temperature and other physical parameter have been changed, and make the material of fixed component expand.Because the formed overdetermination of mechanical grip has produced tension force---it causes injustice, the distortion in the machined surface and curls.This has caused for wing being connected to the flagrant tolerance of fuselage.Therefore, must carry out several milling steps to guarantee the expectation precision and the closed tolerance of machined surface.
Summary of the invention
[6] an object of the present invention is to provide a kind of clamping means that alleviate stress for the angle counterpart.
[7] this can realize by a kind of clamping means and apparatus for fastening that is used to clamp the aircraft connecting elements.
[8] according to first example embodiment of the present invention, a kind of clamping means that are used to clamp the aircraft connecting elements are provided.Described clamping means may further comprise the steps.First machined surface of connecting elements is clamped to first seating surface of apparatus for fastening by first fixed component.Second machined surface of connecting elements is clamped to second seating surface of apparatus for fastening by second fixed component, and the vacuum fixed component of the 3rd machined surface of connecting elements by apparatus for fastening clamps.Described vacuum fixed component is fixed the 3rd machined surface by applying a vacuum field.
[9], provide a kind of apparatus for fastening that is used to clamp the aircraft connecting elements according to another example embodiment.Described apparatus for fastening comprises first seating surface, second seating surface and vacuum fixed component.Described first seating surface is suitable for clamping by first machined surface of first fixed component to connecting elements.Described second seating surface is suitable for clamping by second machined surface of second fixed component to connecting elements.Described vacuum fixed component is suitable for clamping the 3rd machined surface of connecting elements, and wherein said vacuum fixed component is suitable for coming the 3rd machined surface is fixed by applying a vacuum field.
[10] connecting elements can have or comprise an angle counterpart, and it comprises for example first machined surface, second machined surface and the 3rd machined surface.Each described machined surface all comprises an independently plane, wherein the normal on each plane all have different towards.Connecting elements can for example be a carriage with vertical machined surface.
[11] vacuum field can be by having low pressure or for example almost being the area limiting of zero pressure, and especially, low pressure can be to be lower than the pressure that ambient atmosphere is pressed, and promptly in this application, a lower pressure that is lower than the ambient atmosphere pressure is called as " vacuum ".For example, vacuum field can be zone or the space of a pressure between 0 millibar to 100 millibars or 0 millibar to 50 millibars.Described vacuum field can be arranged between the machined surface of vacuum fixed component and connecting elements.Machined surface according to this application can be zone or face to be processed, as to act on or handle, for example connecting elements face.
[12], connecting elements can be clamped on the apparatus for fastening and can not cause tension force and distortion in the connecting elements by using example embodiment of the present invention.By clamp at least one machined surface of connecting elements by vacuum field, can the tension force in fixed component and/or the connecting elements be compensated.By applying a vacuum field, can rigidly fix towards the direction of apparatus for fastening machined surface to connecting elements.On the other hand,, still have one degree of freedom, make and can the tension force in the machined surface material be compensated along the machined surface of fixed component.
[13] Yi Qian method mechanically clamps each machined surface, makes that clamped member is an overdetermination, does not promptly provide the free degree so that the tension force in the material is compensated.By mechanically clamping the machined surface of connecting elements, must use a plurality of mechanical cooperating equipments, wherein, can need fewer purpose fixed component and/or vacuum fixed component by using a vacuum field to come the machined surface of connecting elements is clamped.Thereby the contact area between machined surface and the apparatus for fastening also can reduce, thereby can reduce the distortion in the material that is caused by fixed component.Reduced by tension force and stretching and/or by the specification of stress in the machined surface and/or the connecting elements that strain caused and/or the change of size, thereby, can no longer need machined surface is carried out repeatedly milling and provide desired tolerance for machined surface.Opposite with the mechanical fixation member, the vacuum fixed component is clamping surface more entirely, thereby can prevent the distortion on surface.
[14] according to another example embodiment, the vacuum field of vacuum fixed component is provided with flexibly.Therefore, can use identical vacuum field to clamp the connecting elements of difformity or specification, promptly clamp difform the 3rd machined surface.Thereby vacuum field can be suitable with the machined surface of difformity or design flexibly.
[15] according to another example embodiment, the 3rd machined surface of connecting elements clamps by a plurality of vacuum fixed components of apparatus for fastening.Therefore, a plurality of vacuum fields can provide the even clamping to the 3rd machined surface, simultaneously, still can the tension force in the material be compensated.
[16] according to another example embodiment, described vacuum fixed component is provided by vacuum cylinder.Described vacuum cylinder can be designed to tubulose, and an end of wherein said pipe can be connected to a vavuum pump and the other end of pipe can be suitable for clamping the 3rd machined surface of connecting elements.
[17] according to another example embodiment, the vacuum fixed component of described apparatus for fastening moves towards the 3rd machined surface of connecting elements.Therefore, the vacuum fixed component can be with the connecting elements of difformity and different designs, promptly the 3rd machined surface is suitable.Can also make the vacuum fixed component along one towards the 3rd machined surface or also can be along with the direction of the 3rd machined surface---promptly along---moves towards the perpendicular direction of the direction of connecting elements machined surface.The vacuum fixed component can pass through a cardan joints support.
[18] according to another example embodiment, at least one in first fixed component and second fixed component clamps in first machined surface and second machined surface at least one by mechanical grip equipment.Described mechanical grip equipment can be chosen from the combination of being made up of anchor clamps, clip, securing member, compactor and binding clasp (tightspot).
[19] according to another example embodiment, at least one in first fixed component and second fixed component clamps in first machined surface and second machined surface at least one by applying a vacuum field.Thereby connecting elements is more entirely clamped, thereby can clamp sensitive material and can not damage the machined surface of connecting elements.
[20] according to another example embodiment of the present invention, at least one in the 3rd machined surface of first machined surface of connecting elements, second machined surface of connecting elements and connecting elements is suitable for being installed on the wing of aircraft.Because used the method for present embodiment, machined surface can very accurately be made, thereby can the manufacturing tolerance of wing be compensated.In addition, can carry out more accurate adjusting to the port wing and the starboard wing of aircraft, thereby can improve the flight characteristics of aircraft.
[21] according to another example embodiment, at least one in the 3rd machined surface of first machined surface of connecting elements, second machined surface of connecting elements and connecting elements is suitable for being installed on the fuselage of aircraft.
[22] at this, must be pointed out: for a technical staff, the example embodiment of the described clamping means that are used to clamp the aircraft connecting elements is also applicable to the apparatus for fastening that clamps the aircraft connecting elements.
[23] according to another example embodiment of apparatus for fastening, fixed component can be provided with vacuum field, especially intensity and/or form and/or shape flexibly.
[24] according to another example embodiment of apparatus for fastening, apparatus for fastening further comprises a plurality of vacuum fixed components.
[25] according to another example embodiment of the present invention, the vacuum fixed component has vacuum cylinder.
[26] according to another example embodiment of apparatus for fastening, the vacuum fixed component is suitable for moving towards the 3rd machined surface of connecting elements.
Description of drawings
[27] hereinafter, with reference to the accompanying drawings example embodiment of the present invention is described in detail, to explain further and to understand better:
[28] Fig. 1 shows the schematic diagram of the example embodiment of a foundation apparatus for fastening of the present invention, wherein can use clamping means;
[29] Fig. 2 shows the schematic diagram of the illustrative embodiments of a connecting elements; And
[30] Fig. 3 a shows the schematic diagram of other illustrative embodiments of apparatus for fastening to 3d.
[31] in several figure, similar or related parts are marked with identical reference number.View among the figure is schematic rather than full-scale.
The specific embodiment
[32] Fig. 1 shows an exemplary apparatus for fastening 5, and it is used to clamp an aircraft connecting elements.First machined surface 1 (being shown among Fig. 2) of connecting elements can be clamped on first seating surface 11 of apparatus for fastening 5 by first fixed component 21.Second machined surface 2 of connecting elements can be clamped on second seating surface 12 of apparatus for fastening 5 by second fixed component.The 3rd machined surface 3 of connecting elements clamps by the vacuum fixed component 23 of apparatus for fastening 5.Vacuum fixed component 23 is fixed the 3rd machined surface 3 by applying a vacuum field.
[33] after connecting elements being clamped on the apparatus for fastening 5, can carrying out milling to the 3rd machined surface and can not cause tension force or the stress or the distortion of material.Thereby, only need a milling step, alteration of form takes place because can prevent the 3rd machined surface 3.
[34] vacuum field of vacuum fixed component 23 also can be provided with flexibly.As shown in Figure 1, vacuum fixed component 23 can have and/or comprise vacuum cylinder, and described vacuum cylinder can have for example shape of tubulose.These vacuum cylinders can move towards the 3rd machined surface 3 of connecting elements.Thereby the connecting elements of difformity or different size and specification can be by flexible vacuum fixed component 23, promptly by each movably vacuum cylinder clamp.Also can pass through a cardan joints support vacuum fixed component 23, thereby make the 3rd machined surface 3 to clamp by identical apparatus for fastening 5 with difformity and/or different angles.
[35] vacuum fixed component 23 is connected to vavuum pump to produce vacuum field.As shown in Figure 1, the mechanical grip member 21 that is positioned on first seating surface 12 includes anchor clamps or jack.
[36] Fig. 2 shows an exemplary connecting elements, and it comprises first machined surface 1, second machined surface 2 and the 3rd machined surface 3.In the machined surface 1,2,3 each all can be clamped on the apparatus for fastening 5.
[37] by clamping at least one machined surface 1,2,3, can prevent from the material of connecting elements, tension force to occur by vacuum fixed component 23.For to connecting elements, promptly provide the more freedom degree to first machined surface 1 and second machined surface 2, the first and/or second mechanical fixation member 21,22 also can have or comprise the vacuum fixed component.
[38] Fig. 3 a shows other example embodiment of apparatus for fastening to 3d, and wherein first seating surface 11 and second seating surface 12 are suitable for cooperating with first and second machined surfaces 21,22 of connecting elements.The 3rd seating surface---for example vacuum field---can be adaptive flexibly.
[39] thereby, the connecting elements that is used for aircraft wing is connected to aircraft fuselage can be made according to effective clamping means of embodiment of the present invention exactly by one.Can not re-use and/or reduce complicated method for milling or a plurality of milling step.
[40] should be noted that term " comprises " member or the step of not getting rid of other, and " one " or " one " does not get rid of a plurality of situations.And the member of describing with reference to different embodiments can combine.Shall also be noted that reference signs in the claim is not to be understood that the restriction of paired claim protection domain.
Claims (10)
1. clamping means that are used to clamp the aircraft connecting elements, wherein said method comprises:
By using first fixed component (21) first machined surface (1) of described connecting elements is clamped on first seating surface (11) of apparatus for fastening (5);
By using second fixed component (22) second machined surface (2) of described connecting elements is clamped on second seating surface (12) of described apparatus for fastening (5);
Clamp the 3rd machined surface (3) of described connecting elements by the vacuum fixed component (23) that uses apparatus for fastening (5);
Wherein said vacuum fixed component (23) clamps described the 3rd machined surface (3) by applying a vacuum field.
2. clamping means as claimed in claim 1 further comprise:
The vacuum field of described vacuum fixed component (23) is set flexibly.
3. clamping means as claimed in claim 1, wherein,
The 3rd machined surface (3) of described connecting elements clamps by a plurality of vacuum fixed components (23) of described apparatus for fastening (5).
4. clamping means as claimed in claim 1, wherein, described vacuum fixed component (23) is provided by the vacuum cylinder of described apparatus for fastening (5).
5. clamping means as claimed in claim 4 further comprise:
Move the vacuum fixed component (23) of described apparatus for fastening (5) towards the 3rd machined surface (3) of described connecting elements.
6. clamping means as claimed in claim 1, wherein, at least one in described first fixed component (21) and second fixed component (22) is mechanical grip equipment.
7. clamping means as claimed in claim 1, wherein, at least one in described first fixed component (21) and second fixed component (22) clamps in described first machined surface (1) and second machined surface (2) at least one by applying a vacuum field.
8. clamping means as claimed in claim 1, wherein, at least one in the 3rd machined surface (3) of second machined surface (2) of first machined surface (1) of described connecting elements, described connecting elements and described connecting elements is suitable for being installed on the wing of aircraft.
9. clamping means as claimed in claim 1, wherein, at least one in the 3rd machined surface (3) of second machined surface (2) of first machined surface (1) of described connecting elements, described connecting elements and described connecting elements is suitable for being installed on the fuselage of aircraft.
10. apparatus for fastening that is used to clamp the aircraft connecting elements, wherein, described apparatus for fastening (5) comprising:
First seating surface (11);
Second seating surface (12); And
Vacuum fixed component (23);
Wherein, described first seating surface (11) is suitable for clamping by first fixed component (21) first machined surface (1) of described connecting elements;
Described second seating surface (12) is suitable for clamping by second fixed component (22) second machined surface (2) of described connecting elements; Described vacuum fixed component (23) is suitable for clamping the 3rd machined surface (3) of described connecting elements;
And described vacuum fixed component (23) is suitable for fixing described the 3rd machined surface (3) by applying a vacuum field.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100786861A CN100534724C (en) | 2006-04-30 | 2006-04-30 | Clamping device and clamping method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100786861A CN100534724C (en) | 2006-04-30 | 2006-04-30 | Clamping device and clamping method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101062551A CN101062551A (en) | 2007-10-31 |
| CN100534724C true CN100534724C (en) | 2009-09-02 |
Family
ID=38963949
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2006100786861A Expired - Fee Related CN100534724C (en) | 2006-04-30 | 2006-04-30 | Clamping device and clamping method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100534724C (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008043490A1 (en) * | 2008-11-05 | 2010-05-12 | Airbus Deutschland Gmbh | Device for the temporary fixation of two fuselage sections to be joined together |
| US20140042682A1 (en) * | 2012-08-08 | 2014-02-13 | Yixing Bao | Universal fixture for machining a flat substrate |
| CN108581534B (en) * | 2018-05-31 | 2019-08-13 | 厦门宏发精密机械有限公司 | A kind of part positioning device |
| CN110906809B (en) * | 2019-11-22 | 2020-09-29 | 大连理工大学 | Large-size cylinder model clamping and throwing system and method |
-
2006
- 2006-04-30 CN CNB2006100786861A patent/CN100534724C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN101062551A (en) | 2007-10-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100534724C (en) | Clamping device and clamping method | |
| TWI719197B (en) | Clamping device, clamping system and clamping arrangement | |
| CN103471843B (en) | A kind of stretch bending multiaxle fatigue experimental mechanism | |
| US9302394B2 (en) | Positioning device | |
| KR102584319B1 (en) | Adhesive testing systems and methods | |
| US20120006236A1 (en) | Adhesive holder for holding objects and kit, as well as method for making an adhesive holder | |
| US20140325813A1 (en) | System and method of assembling components | |
| US20200070234A1 (en) | Adapter, stretcher-leveller and method for operating a stretcher-leveller | |
| CN104637859A (en) | WIRE clamp, method and apparatus for applying a preload force to a piezoelectric actuator | |
| US8950270B2 (en) | Short beam shear test fixture | |
| AT520028B1 (en) | System and associated techniques for handling aligned pairs of substrates | |
| CN104406853B (en) | It is applied to the assay device of the uniaxial tensile test of viscoelastic material | |
| CN209095004U (en) | Flexible clamping positioning device | |
| US20190247983A1 (en) | Apparatus and method for holding a workpiece | |
| KR101723445B1 (en) | An apparatus for testing of laminated material | |
| US20210323652A1 (en) | Pressure Bulkhead Assembly Support Tool | |
| CN107414708A (en) | For small space clamping and accurate positioning device | |
| US8393062B2 (en) | Systems and methods for positioning fairing sheaths of gas turbine engines | |
| US20110037488A1 (en) | Flexural mechanism for passive angle alignment and locking | |
| CN107699890A (en) | Plated film machine clamp and coating machine | |
| ES2898091T3 (en) | Production of aircraft frame components | |
| CN107419240A (en) | A kind of graphite boat fast fixture | |
| CN113654983A (en) | Device and method for testing adhesive property of T-shaped surface of paper honeycomb and rigid structure | |
| CN107884266B (en) | Clamp for testing pull-out performance of composite material omega-shaped component and testing method | |
| US20200406430A1 (en) | Attachment jig and attachment method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee |
Owner name: AIRBUS OPERATIONS GMBH Free format text: FORMER NAME: AIRBUS GMBH |
|
| CP01 | Change in the name or title of a patent holder |
Address after: hamburg Patentee after: Airbus Operations GmbH Address before: hamburg Patentee before: Airbus GmbH |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090902 Termination date: 20170430 |