CN205977951U - A interim fastener for airplane assembling - Google Patents
A interim fastener for airplane assembling Download PDFInfo
- Publication number
- CN205977951U CN205977951U CN201620893015.XU CN201620893015U CN205977951U CN 205977951 U CN205977951 U CN 205977951U CN 201620893015 U CN201620893015 U CN 201620893015U CN 205977951 U CN205977951 U CN 205977951U
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- CN
- China
- Prior art keywords
- temporary fastener
- aircraft
- refined
- head cap
- cap screw
- 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
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Abstract
The utility model discloses an interim fastener for airplane assembling. It is including refined soket head cap screw, interim fastener body, protective sheath, retaining ring, the tight jack catch of clamp, through handheld tool or the refined soket head cap screw clockwise rotation of automatic device driver unit drive, drive and press from both sides tight jack catch along axial displacement, four claws or six or the four claw structures of pressing from both sides tight jack catch area tapering barb shape are opened in axial displacement to with aircraft structure contact, apply the torque value pretension of settlement simultaneously, reach the purpose that two aircraft structures are connected to interim fastener, the size of interim fastener clamp force, equipment control system passes through the torque sensor closed loop feedback, realizes accurate control, automatic installation is convenient for realize by this interim fastener, shows the assembly quality and the efficiency that land and improved the aircraft.
Description
Technical field
This utility model is related to a kind of temporary fastener for aircraft assembling, belongs to the assembling of Aero-Space manufacturing based on digital
Field.
Background technology
In aircraft assembling process, either assembly class assembling, such as aircraft fuselage wallboard and stringer etc. are connected, or part
Assembling, the such as connection of aircraft wing skins and rib, are all two or more parts of tool locating, the then lamination systems of first adopting
Pre-connection hole adopts temporary fastener to connect, and finally dismantles the positioning tool in large quantities of impact drilling spaces, carries out high-volume drilling
Connect.So temporary fastener aircraft assembling process usage amount big, require positioning precision high, to temporary fastener clamping force be
No can accurately control, follow-up aircraft is assembled with quality it is critical that link, life-span of aircraft is had very important
Effect.
The pre-connection fastening method of traditional aircraft assembling, using the interim fastening of punching folder or plain bolt fastening, adopts
Both pre-connection part methods, it is poor to have a positioning precision, and clamping force cannot be precisely controlled by artificial judgment it is difficult to ensure to clamp
The concordance of power, it is impossible to realize Automated assembly, largely have impact on Aircraft Quality and efficiency of assembling.For airplane digital
The trend development changing mounting technology relevant device is next supporting.Study a kind of temporary fastener correlation technique for aircraft assembling to come
Cooperation Domestic Aircraft numeric terminal technology is imperative.
This utility model is directed to above demand it is proposed that a kind of temporary fastener for aircraft assembling, can manually adopt
Installed with handheld tool or be integrated on automatic equipment and realize automatization's installation two ways, effectively solve above two pre-
The deficiency of connector, installs positioning precision height, efficiency of assembling height, clamping force by torque sensing using being integrated on automatic equipment
Device closed loop feedback is realized being precisely controlled；Hand labor intensity reduces, and aircraft assembling bolt or rivet stress assemble quality conformance
Good.In aircraft digital assembling field, there is wide application prospect.
Description
The purpose of this utility model is to overcome the deficiencies in the prior art, provides positioning precision height, efficiency of assembling height, clamping force
Realize a kind of temporary fastener for aircraft assembling being precisely controlled by torque sensor closed loop feedback.
The concrete technical scheme of the present invention is：
A kind of temporary fastener for aircraft assembling, including refined soket head cap screw, temporary fastener body, protection
Set, back-up ring, gripping dogs；One end of gripping dogs is outer square and female thread structure, and the other end falls for contract band taper
Four claws of hook shape or six or four claw structures, are matched with square in temporary fastener body interior by outer square,
It is connected with refined soket head cap screw by female thread；Originally being provided with back-up ring in vivo in temporary fastener prevents refined soket head cap screw from taking off
Fall；Temporary fastener body one end is outer-hexagonal shape, and the other end is provided with protective case；By changing protective case part aberration vision
Distinguish temporary fastener specification.
Further, four claws with taper barb shape for the contract of described gripping dogs or six or four claw structures, be
There is elastic deformation expansion and shrink and enter aperture guide function.
A kind of installation method of temporary fastener for aircraft assembling of the present utility model, is by changing interim fastening
The lengthwise dimension size of part body and gripping dogs, can increase or shorten the clamping stroke range of temporary fastener, full
The assembling demand of sufficient aircraft target ship and wallboard or wallboard and the different aircraft structure laminated thickness materials such as stringer class.
This utility model is used for comprising the following steps that of the temporary fastener installation method of aircraft assembling：
1) on the aircraft structure A and aircraft structure B being accurately positioned, using hand-held drilling instrument or automatization's system
Hole equipment system just hole, the just generally less than whole bore dia 1mm in hole aperture；
2）By manual mode or automatization's drilling DeviceMode, the interim fastening of dimension is automatically inserted on first hole
Part, on position makes protective case contact aircraft structure A；
3）On hand-held pneumatic instrument or automatization's drilling equipment, setting outer-hexagonal and inner hexagon spanner, are pulled by outer-hexagonal
Handss are matched with the outer-hexagonal shape of temporary fastener body 2, make temporary fastener integral position keep constant, simultaneously drive interior six
Angle spanner, realizes refined soket head cap screw 1 and turns clockwise, make gripping dogs 5 pass through outer square and temporary fastener body
In inside, square matches guiding, realizes being axially moveable；
4）Continue to drive refined soket head cap screw to turn clockwise, gripping dogs are axially moveable, refined soket head cap screw
External diameter starts to back down four claws with taper barb shape for the gripping dogs or six or four claw structures, and after making to open, band taper is barb-shaped
The tapered portion diameter of four claws of shape or six or four claw structures with etc. straight section diameter consistent；
5）Continue to drive refined soket head cap screw to turn clockwise, gripping dogs are axially moveable, using gripping dogs band
Barb contact aircraft structure B on four claws of taper barb shape or six or four claws；Turned round by setting in driving instrument
The size of square threshold values or torque sensor monitoring clamping force makes aircraft structure A and aircraft structure B clamping；
6）The temporary fastener completing on aircraft structure A and aircraft structure B is installed, multiple temporary fastener peaces
Dress process repeat the above steps 1) ~ step 5)；
7）Dismounting temporary fastener, refines soket head cap screw rotate counterclockwise, clamping card using hand-held pneumatic tool drives
Pawl moves backward vertically, and the barb on four claws with taper barb shape for the gripping dogs or six or four claws is away from aircaft configuration
Part B；
8）Continue to drive refined soket head cap screw rotate counterclockwise, refined soket head cap screw external diameter departs from gripping dogs band cone
Four claws of degree barb shape or six or four claw structures, four claws with taper barb shape or six or four claw structure both shrinks return to
Original state；
9）Continue to drive refined soket head cap screw rotate counterclockwise, the original state that gripping dogs move to stroke is next time
Install and prepare；
10）Multiple temporary fastener unloading process repeat the above steps 7) ~ step 9）.
This utility model compared with prior art has the advantage that
1）Temporary fastener of the present utility model, can adopt handheld tool manually installed or be integrated on automatic equipment real
Two ways is installed by existing automatization, and adaptability is good；
2）The just hole cooperation of the gripping dogs of temporary fastener and airplane parts structure, using the cooperation of diameter small-gap suture, positioning
High precision；
3）By being integrated on automatic equipment, realize automatization and install, efficiency of assembling is high；
4）Installed by being integrated on automatic equipment, clamping force is realized closed loop feedback using torque sensor and is precisely controlled；
5）Hand labor intensity reduces, and aircraft assembling bolt or rivet stress assembling quality conformance are good.In airplane digital
Disguise to join and there is in field wide application prospect.
Brief description
Fig. 1 is temporary fastener structural representation；
Fig. 2 is aircraft structure A and aircraft structure B temporary fastener connection diagram；
Fig. 3 is temporary fastener installation steps schematic diagram；
In figure：Fastener body, 3- protective case, the special back-up ring of 4-, 5- clamping card when 1- refines soket head cap screw, 2-
Solid aircraft structure A, 7- aircraft structure B of pawl, 6-.
Specific embodiment
As shown in Figure 1, 2, for the temporary fastener of aircraft assembling, including refined soket head cap screw 1, temporary fastener originally
Body 2, protective case 3, special back-up ring 4, gripping dogs 5 form；One end of gripping dogs 5 is outer square and female thread structure, separately
One end is four claws with taper barb shape for the contract or six or four claw structures, by outer square and temporary fastener body
In 2 inside, square matches, and is connected with refined soket head cap screw 1 by female thread；It is provided with temporary fastener body 2 specially
Prevent refined soket head cap screw 1 from coming off with back-up ring 4；Temporary fastener body 2 one end is outer-hexagonal shape, and the other end is provided with protection
Set 3；Distinguish temporary fastener specification by changing protective case 3 part aberration vision；
For the temporary fastener of aircraft assembling, four claws or six or four with taper barb shape for gripping dogs 5 contract
Claw structure, has elastic deformation expansion and shrinks and enter aperture guide function；
For the temporary fastener of aircraft assembling, by changing the length direction of temporary fastener body 2 and gripping dogs 5
Size, can increase or shorten the clamping stroke range of temporary fastener, meet aircraft target ship and wallboard or wallboard and length
The assembling demand of the difference aircraft structure laminated thickness material such as purlin class；
As indicated at 3, for the temporary fastener installation method of aircraft assembling, its method and step is as follows：
1) on the aircraft structure A 6 and aircraft structure B 7 being accurately positioned, using hand-held drilling instrument or automatically
Change drilling equipment system just hole（Just hole aperture is generally less than whole bore dia 1mm）；
2）By manual mode or automatization's drilling DeviceMode, the interim fastening of dimension is automatically inserted on first hole
Part, on position makes protective case 3 contact aircraft structure A 6；
3）Setting outer-hexagonal and inner hexagon spanner on hand-held pneumatic instrument or automatization's drilling equipment, by outer-hexagonal
Spanner is matched with the outer-hexagonal shape of temporary fastener body 2, makes temporary fastener integral position keep constant, simultaneously drives interior
Die nut is realized refined soket head cap screw 1 and is turned clockwise, and makes gripping dogs 5 pass through outer square and temporary fastener body
In inside, square matches guiding, realizes being axially moveable；
4）Continue to drive refined soket head cap screw 1 to turn clockwise, gripping dogs 5 are axially moveable, and refine interior hexagonal spiral shell
Follow closely 1 external diameter to start to back down four claws with taper barb shape for the gripping dogs 5 or six or four claw structures, after making to open, band taper falls
The tapered portion diameter of four claws of hook shape or six or four claw structures with etc. straight section diameter consistent；
5）Continue to drive refined soket head cap screw 1 to turn clockwise, gripping dogs 5 are axially moveable, using gripping dogs）
Barb contact aircraft structure B 7 on four claws with taper barb shape or six or four claws；By setting in driving instrument
Put moment of torsion threshold values or the size of torque sensor monitoring clamping force makes aircraft structure A 6 and aircraft structure B 7 clamp；
6）The temporary fastener completing on aircraft structure A 6 and aircraft structure B 7 is installed, multiple interim fastenings
Part installation process repeat the above steps 1) ~ step 5)；
7）Dismounting temporary fastener, refines soket head cap screw 1 rotate counterclockwise, clamping card using hand-held pneumatic tool drives
Pawl 5 moves backward vertically, and the barb on four claws with taper barb shape for the gripping dogs 5 or six or four claws is tied away from aircraft
Component B 7；
8）Continue to drive refined soket head cap screw 1 rotate counterclockwise, refined soket head cap screw 1 external diameter departs from gripping dogs 5
Four claws with taper barb shape or six or four claw structures, four claws with taper barb shape or six or four claw structure both shrinks
Return to original state；
9）Continue to drive refined soket head cap screw 1 rotate counterclockwise, under the original state that gripping dogs 5 move to stroke is
Secondary installation prepares；
10）Multiple temporary fastener unloading process repeat the above steps 7) ~ step 9）.
Claims (2)
1. a kind of temporary fastener for aircraft assembling is it is characterised in that include refined soket head cap screw（1）, interim fasten
Part body（2）, protective case（3）, back-up ring（4）, gripping dogs（5）Composition；Gripping dogs（5）One end be outer square and interior spiral shell
Stricture of vagina structure, by outer square and temporary fastener body（2）Internal interior square matches, interior with refined by female thread
Hex screw（1）Connect, the other end is four claws with taper barb shape for the contract or six or four claw structures；Fasten interim
Part body（2）Inside it is provided with back-up ring（4）Prevent refined soket head cap screw（1）Come off；Temporary fastener body（2）One end is outer-hexagonal
Shape, the other end is provided with protective case（3）；By changing protective case（3）Part aberration area vision divides temporary fastener specification.
2. a kind of temporary fastener for aircraft assembling according to claim 1, gripping dogs（5）Contract band taper
Four claws of barb shape or six or four claw structures, have elastic deformation expansion and shrink and enter aperture guide function.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620893015.XU CN205977951U (en) | 2016-08-17 | 2016-08-17 | A interim fastener for airplane assembling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620893015.XU CN205977951U (en) | 2016-08-17 | 2016-08-17 | A interim fastener for airplane assembling |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205977951U true CN205977951U (en) | 2017-02-22 |
Family
ID=58030948
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620893015.XU Expired - Fee Related CN205977951U (en) | 2016-08-17 | 2016-08-17 | A interim fastener for airplane assembling |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205977951U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106224341A (en) * | 2016-08-17 | 2016-12-14 | 尚鳌自动化工程（上海）有限公司 | A kind of temporary fastener for aircraft assembling and installation method |
| CN113084504A (en) * | 2021-04-15 | 2021-07-09 | 李少云 | Fastening device of temporary fastening piece |
-
2016
- 2016-08-17 CN CN201620893015.XU patent/CN205977951U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106224341A (en) * | 2016-08-17 | 2016-12-14 | 尚鳌自动化工程（上海）有限公司 | A kind of temporary fastener for aircraft assembling and installation method |
| CN113084504A (en) * | 2021-04-15 | 2021-07-09 | 李少云 | Fastening device of temporary fastening piece |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170222 Termination date: 20190817 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |