CN206502048U - Clamp and aircraft assembly fixture - Google Patents
Clamp and aircraft assembly fixture Download PDFInfo
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- CN206502048U CN206502048U CN201720157668.6U CN201720157668U CN206502048U CN 206502048 U CN206502048 U CN 206502048U CN 201720157668 U CN201720157668 U CN 201720157668U CN 206502048 U CN206502048 U CN 206502048U
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- clamp
- rod member
- aircraft
- assembly fixture
- utility
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Abstract
A kind of clamp and aircraft assembly fixture, belong to aircraft assembling field, and clamp includes rod member and determine part clamp, described to determine part clamp and be connected to the rod member, described to determine part clamp for positioning aircraft components.Aircraft assembly fixture includes type frame body and above-mentioned clamp, and the clamp is fixedly installed in the type frame body.This clamp can effectively mitigate the weight of itself relative to existing pure plate structure, reduce processing cost, while convenient transport, installs and debug, effectively compensate for the defect of existing clamp.This aircraft assembly fixture can effectively reduce the rigid requirement of the crossbeam to installing clamp, so as to reduce the volume and weight of itself, to transport and to install, compensate for the defect of existing aircraft assembly fixture.
Description
Technical field
The utility model is related to aircraft assembling field, in particular to a kind of clamp and aircraft assembly fixture.
Background technology
Aircraft assembly fixture is essential technological equipment during aircraft manufacturing, and it manufactures and designs cycle and precision pole
Earth effect aircraft manufacturing cycle and product quality.In aircraft assembly fixture, clamp is ensured outside aircraft components aerodynamic force
The setting element of the shape degree of accuracy, its working surface and airplane aerodynamic profile are closely bound up.Existing clamp design is general to be used
Aluminium clamp, aluminium clamp coefficient of dilatation is relatively small, lighter in weight, and easily, material is easily purchased for digital control processing after the completion of design
Buy, adjust and being accurately positioned for aircraft installation is can guarantee that after the completion of filling.
But,, will to the crossbeam rigidity for installing clamp if processing clamp using aluminium sheet for large-scale assembly jig
Ask very high, the cross section of crossbeam can only be increased, this necessarily causes the integrally-built increasing of aircraft assembly fixture, correspondingly cost
It can increase, and very big inconvenience is caused to installing and transporting.
Utility model content
The purpose of this utility model is to provide a kind of clamp, and it can effectively mitigate the weight of itself, reduces processing cost,
Convenient transport simultaneously, installs and debugs.
Another object of the present utility model is to provide a kind of aircraft assembly fixture, and it can be effectively reduced to installing clamp
Crossbeam is rigid to be required, so as to reduce the volume and weight of itself, to transport and to install.
What embodiment of the present utility model was realized in：
A kind of clamp, it includes rod member and determines part clamp, described to determine part clamp and be connected to the rod member, described to determine part clamp
For positioning aircraft components.
Further, in the utility model preferred embodiment, the rod member is metal tube.
Further, in the utility model preferred embodiment, the rod member is aluminium square tube.
Further, in the utility model preferred embodiment, the two ends of the rod member are respectively arranged with angled seat, two
The angled seat is provided with mounting hole.
Further, in the utility model preferred embodiment, the two ends of the rod member are respectively arranged with joint, two
The joint is respectively arranged with threaded portion.
Further, it is described to determine part clamp two alignment pins of setting in the utility model preferred embodiment.
Further, in the utility model preferred embodiment, two alignment pins are hollow structure.
Further, in the utility model preferred embodiment, the rod member is provided with the first pin-and-hole, described to determine part card
Plate is provided with the second pin-and-hole, and first pin-and-hole and second pin-and-hole, which are interconnected, forms positioning hole, and clamp also includes and institute
State the pin of positioning hole cooperation.
Further, in the utility model preferred embodiment, the rod member is provided with handle.
A kind of aircraft assembly fixture, it includes type frame body and above-mentioned clamp, and the clamp is fixedly installed in the type
Frame body.
The utility model embodiment achieves following technique effect：
This clamp includes rod member and determines part clamp, determines part clamp and is connected to rod member, and determining part clamp is used to position aircraft components.
This clamp uses the structure type that rod member and plate be combined with each other, relative to existing pure plate structure, can effectively mitigate certainly
The weight of body, reduces processing cost, while convenient transport, installs and debug, effectively compensate for the defect of existing clamp.
This aircraft assembly fixture includes type frame body and above-mentioned clamp, and clamp is fixedly installed in type frame body.This aircraft
Assembly jig can effectively reduce the rigid requirement of the crossbeam to installing clamp due to using above-mentioned clamp, so that
Reduce the volume and weight of itself, to transport and to install, compensate for the defect of existing aircraft assembly fixture.
Brief description of the drawings
In order to illustrate more clearly of the technical scheme of the utility model embodiment, it will use below required in embodiment
Accompanying drawing be briefly described, it will be appreciated that the following drawings illustrate only some embodiments of the present utility model, therefore should not be by
Regard the restriction to scope as, for those of ordinary skill in the art, on the premise of not paying creative work, may be used also
To obtain other related accompanying drawings according to these accompanying drawings.
The structural representation for the clamp that Fig. 1 provides for the utility model first embodiment；
The structural representation at another visual angle for the clamp that Fig. 2 provides for the utility model first embodiment；
Fig. 3 is Fig. 2 II enlarged drawing；
The structural representation for the clamp that Fig. 4 provides for the utility model second embodiment.
Icon：100- clamps；110- rod members；120- determines part clamp；122- alignment pins；124- cylindrical holes；130-
First angled seat；The angled seats of 140- second；150- handles；The joints of 160- first；The joints of 170- second.
Embodiment
It is new below in conjunction with this practicality to make the purpose, technical scheme and advantage of the utility model embodiment clearer
Accompanying drawing in type embodiment, the technical scheme in the utility model embodiment is clearly and completely described, it is clear that retouched
The embodiment stated is a part of embodiment of the utility model, rather than whole embodiments.Generally here described in accompanying drawing and
The component of the utility model embodiment shown can be arranged and designed with a variety of configurations.
Therefore, the detailed description of embodiment of the present utility model below to providing in the accompanying drawings is not intended to limit requirement
The scope of the present utility model of protection, but it is merely representative of selected embodiment of the present utility model.Based in the utility model
Embodiment, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made, all
Belong to the scope of the utility model protection.
It should be noted that：Similar label and letter represents similar terms in following accompanying drawing, therefore, once a certain Xiang Yi
It is defined in individual accompanying drawing, then it further need not be defined and explained in subsequent accompanying drawing.
, it is necessary to explanation in description of the present utility model, term " " center ", " on ", " under ", it is "left", "right", " perpendicular
Directly ", the orientation or position relationship of the instruction such as " level ", " interior ", " outer " be based on orientation shown in the drawings or position relationship, or
It is the orientation or position relationship usually put when the utility model product is used, is for only for ease of description the utility model and letter
Change description, rather than indicate or imply signified device or element must have specific orientation, with specific azimuth configuration and
Operation, therefore it is not intended that to limitation of the present utility model.In addition, term " first ", " second ", " the 3rd " etc. are only used for area
Divide description, and it is not intended that indicating or implying relative importance.
In addition, the term such as term " level ", " vertical " is not offered as requiring part abswolute level or pendency, but can be slightly
Low dip.It is not that the expression structure must be complete as " level " only refers to its direction with respect to more level for " vertical "
Full level, but can be slightly tilted.
In description of the present utility model, in addition it is also necessary to which explanation, unless otherwise clearly defined and limited, term " are set
Put ", " installation ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected,
Or be integrally connected；Can be mechanical connection or electrical connection；Can be joined directly together, intermediary can also be passed through
It is indirectly connected to, can is the connection of two element internals.For the ordinary skill in the art, it can be managed with concrete condition
Solve concrete meaning of the above-mentioned term in the utility model.
First embodiment：
Fig. 1 is refer to, a kind of clamp 100 is present embodiments provided, aircraft assembly fixture can be installed on, for aircraft
Part is positioned.This clamp 100 includes rod member 110 and determines part clamp 120.
Wherein, rod member 110 can be used in various structures and form, the present embodiment, and rod member 110 selects metal tube.Metal
Tubular construction while the mechanical property requirements of rod member 110 are met, can reduce the volume and weight of rod member 110 as far as possible.
Metal tube can have a variety of materials and shape, it is contemplated that in processing characteristics and use requirement, the present embodiment, metal
Pipe aluminium square tube.
Certainly, it is necessary to which explanation, in other embodiments, rod member 110 can also be non-metallic material, such as engineering plastic
Material；Shape can also be shape, such as cylindrical, be determined with specific reference to actual demand.
In reference picture 2, for convenience installation of the clamp 100 on aircraft assembly fixture, the present embodiment, the two of rod member 110
End is respectively arranged with the first angled seat 130 and the second angled seat 140.
Four mounting holes are provided with first angled seat 130 and the second angled seat 140, it is virtual that four mounting holes are located at one respectively
On rectangular four angles, four mounting holes two-by-two one group and respectively be located at the length direction of rod member 110 both sides, to ensure stress
Uniformity.
The movement and installation of clamp 100 for convenience, so that in the operation of personnel convenient for assembly, the present embodiment, rod member 110
It is provided with handle 150.Handle 150 has four and is arranged at intervals along the length direction of rod member 110, and two of which is located at rod member 110
Away from the side surface for determining part clamp 120, remaining two are located at rod member 110 close to two surfaces for determining part clamp 120 respectively.
Determine part clamp 120 and be connected to rod member 110 and for positioning aircraft components.Various knots can be used by determining part clamp 120
Structure and form are connected in rod member 110, the present embodiment, determine part clamp 120 and rod member 110 is bolted.
Positioning when part clamp 120 and the connection of rod member 110 is determined for convenience, it is ensured that the relative position after both connect is consolidated
Fixed, in the present embodiment, clamp 100 also includes the pin of cylinder, and rod member 110 is provided with the first pin-and-hole, determines part clamp 120 and set
There is the second pin-and-hole, the first pin-and-hole and the second pin-and-hole, which are interconnected, forms the positioning hole of cylinder, positioning hole and pin interference fits.
It can be realized in the positioning to aircraft components, the present embodiment to determine part clamp 120, determine part clamp 120 detachable
Two cylindrical alignment pins 122 are connected with, length direction of two alignment pins 122 along rod member 110 sets and be respectively perpendicular to
Determine the plane where part clamp 120.
In order to mitigate the weight of alignment pin 122, so that further mitigate the weight of whole clamp 100, reference picture 3, this
In embodiment, two alignment pins 122 are hollow structure, i.e., the inside of two straight pins is provided with the cylindrical hole of one end open
124。
The application method of this clamp 100 is such：When assembling aircraft, by bolt and mounting hole by the first angled seat 130
It is fixed with aircraft assembly fixture, being assembled so that clamp 100 to be reliablely and stablely fixedly mounted to aircraft respectively with the second angled seat 140
In type frame, when installing clamp 100, two alignment pins 122 determined on part clamp 120 of clamp 100 insert aircraft portion to be assembled
In two default positioning holes of part, the position of corresponding aircraft components so can be effectively fixed, so as to ensure aircraft components
The profile degree of accuracy.
To sum up, the existing clamp 100 for aircraft assembly fixture is mostly pure plate structure, because clamp 100 is necessary
With certain length and intensity, causing it to exist, volume is big, and weight is big, the problem of cost is high, and this clamp 100 is by rod member
110 and determine part clamp 120 and constitute, determine part clamp 120 and be connected to rod member 110.Rod member 110 constitutes the agent structure of clamp 100, full
While the foot length and intensity requirement of clamp 100, the volume and weight of clamp 100 is reduced again, determining part clamp 120 is used for
Aircraft components are positioned, because rod member 110 is agent structure, therefore part clamp 120 are determined relative to existing clamp 100, Ke Yi great
Reduce the volume and weight of itself greatly, so, by rod member 110 and the combination for determining part clamp 120, be just effectively reduced certainly
The weight of body, reduces processing cost, while convenient transport, installs and debug, effectively compensate for the defect of prior art.
The present embodiment additionally provides a kind of aircraft assembly fixture, and it includes type frame body and above-mentioned clamp 100, clamp
100 the first angled seat 130 and the second angled seat 140 are fixedly installed in type frame body respectively by bolt and mounting hole.
This aircraft assembly fixture includes type frame body and above-mentioned clamp 100, and clamp 100 is fixedly installed in type frame body.
This aircraft assembly fixture can effectively reduce the rigidity of the crossbeam to installing clamp 100 due to using above-mentioned clamp 100
Requirement, so as to reduce the volume and weight of itself, to transport and to install, compensate for lacking for existing aircraft assembly fixture
Fall into.
Second embodiment：
It refer to Fig. 4, the present embodiment provides a kind of clamp 100, its unitary construction, the technique effect of application method and acquirement
The clamp 100 provided with first embodiment is essentially identical, and difference is the connection knot at the two ends of the rod member 110 of clamp 100
Structure.
In the present embodiment, the two ends of rod member 110 no longer set angled seat, but are replaced by setting joint, specifically, bar
The two ends of part 110 are respectively arranged with the first joint 160 and the second joint 170, and the first joint 160 and the second joint 170 are set respectively
It is equipped with threaded portion.When this clamp 100 are installed, the first joint 160 and the second joint 170 are connected to aircraft by threaded portion
Assembly jig.
Preferred embodiment of the present utility model is these are only, the utility model is not limited to, for this area
Technical staff for, the utility model can have various modifications and variations.It is all it is of the present utility model spirit and principle within,
Any modification, equivalent substitution and improvements made etc., should be included within protection domain of the present utility model.
Claims (10)
- It is described to determine part clamp and be connected to the rod member 1. a kind of clamp, it is characterised in that including rod member and determine part clamp, it is described Determining part clamp is used to position aircraft components.
- 2. clamp according to claim 1, it is characterised in that the rod member is metal tube.
- 3. clamp according to claim 2, it is characterised in that the rod member is aluminium square tube.
- 4. the clamp according to claim 1-3 any one, it is characterised in that the two ends of the rod member are respectively arranged with Angled seat, two angled seats are provided with mounting hole.
- 5. the clamp according to claim 1-3 any one, it is characterised in that the two ends of the rod member are respectively arranged with Joint, two joints are respectively arranged with threaded portion.
- 6. clamp according to claim 1, it is characterised in that described to determine part clamp and be provided with two alignment pins.
- 7. clamp according to claim 6, it is characterised in that two alignment pins are hollow structure.
- 8. clamp according to claim 1, it is characterised in that the rod member is provided with the first pin-and-hole, described to determine part clamp Be provided with the second pin-and-hole, first pin-and-hole and second pin-and-hole are interconnected and form positioning hole, clamp also include with it is described The pin that positioning hole coordinates.
- 9. clamp according to claim 1, it is characterised in that the rod member is provided with handle.
- 10. a kind of aircraft assembly fixture, it is characterised in that including the card described in type frame body and claim 1-9 any one Plate, the clamp is fixedly installed in the type frame body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720157668.6U CN206502048U (en) | 2017-02-21 | 2017-02-21 | Clamp and aircraft assembly fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720157668.6U CN206502048U (en) | 2017-02-21 | 2017-02-21 | Clamp and aircraft assembly fixture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206502048U true CN206502048U (en) | 2017-09-19 |
Family
ID=59833740
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720157668.6U Active CN206502048U (en) | 2017-02-21 | 2017-02-21 | Clamp and aircraft assembly fixture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206502048U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115519344A (en) * | 2022-09-28 | 2022-12-27 | 陕西飞机工业有限责任公司 | Rapid posture adjusting device and method for inner clamping plate and outer clamping plate of fixture |
-
2017
- 2017-02-21 CN CN201720157668.6U patent/CN206502048U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115519344A (en) * | 2022-09-28 | 2022-12-27 | 陕西飞机工业有限责任公司 | Rapid posture adjusting device and method for inner clamping plate and outer clamping plate of fixture |
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