CN106314820A - Plug pin type anti-escape process connector and application method thereof - Google Patents
Plug pin type anti-escape process connector and application method thereof Download PDFInfo
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- CN106314820A CN106314820A CN201510366832.XA CN201510366832A CN106314820A CN 106314820 A CN106314820 A CN 106314820A CN 201510366832 A CN201510366832 A CN 201510366832A CN 106314820 A CN106314820 A CN 106314820A
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Abstract
The invention discloses a plug pin type anti-escape process connector and an anti-escape process connector connecting method which achieves butt joint and attitude adjusting of an aircraft process component by applying the plug pin type anti-escape process connector. The process connector comprises a ball socket, a ball head and a plug pin, wherein the ball socket is installed on the aircraft process component, and a first pin hole is formed in the ball socket; the ball head is installed on a positioner through a base and makes contact with the ball socket in a matched mode; a second pin hole is formed in the ball head; and the plug pin penetrates through the first pin hole and the second pin hole when the ball socket and the ball head are attached in place. The process connector further comprises a self-adaption adjusting device. The self-adaption adjusting device is fixedly connected with the ball head so that the ball head can be promoted to automatically adjust the position deviation in the ball socket. According to the plug pin type anti-escape process connector, the course deviation during repeated positioning of the positioner can be absorbed, the process connector is used cooperatively with a digital automatic assembling system, and thus high-efficiency and high-precision attitude adjusting and butt joint of the process component in the assembling process can be achieved.
Description
Technical field
Present invention relates generally to automatic-posture-adjustment and the docking field of aircraft digital assembling, especially relate to
And a kind of bolt-type anti-escape process connection and application process thereof.
Background technology
Along with the fast development of domestic air mail industry, aircraft digital automatic assembly technique becomes increasingly
Ripe.In high precision, high efficiency, low energy consumption make Digital assembly system generally raw by each big aircraft
Business men is favored.Process connection is the connecting points connecting aircraft product with automated arm, tradition
Process connection be usually designed with loosen, anti-escape, locking three kinds of states, need drive
Power goes to realize the switching between three kinds of states, and general type has motor driving, air cylinder driven, people
Power drives.Traditional process connection structure is complicated, with high costs, for ensureing the nothing of process components
Stress fixing and supporting, its locking part needs to be designed to three and homocentric is synchronized with the movement.Additionally,
The complexity of the frame for movement of traditional handicraft joint also brings the requirement of harshness to processing and manufacturing.
Bolt-type anti-escape joint is the one that process connection equipped automatically by digitized, it and numerical control
Locators uses, it is possible to be reliably completed the action such as posture adjustment, docking.The anti-escape of bolt-type
Process connection, compared with traditional handicraft joint, structure has the biggest simplification.Wherein, bolt-type
Anti-escape process connection abandons the locking function of traditional handicraft joint, remains to loosen and escapes with anti-
Ease function.After process connection enters position, only need to insert anti-escape latch can realize anti-escape function.
Under specific product component docking operating mode (hold, support only power by gravity direction, other
Component is ignored) disclosure satisfy that the demand of user.In component attitude adjusting, docking operation bulb,
Ball-and-socket fits tightly all the time.
But, the aircraft type of aircraft digital application gets more and more, and the technique of single form connects
Head can not meet the demand of factory.Different assembly technologies required process connection connected mode
Also different.Realizing equally in high precision, in the case of high efficiency assembles, pursue with low cost,
Operation easy to process, easy, safe and reliable process connection have become research tendency.
Summary of the invention
It is an object of the invention to the posture adjustment for aircraft large component and docking, design a kind of letter
Single bolt-type anti-escape process connection reliably, to make up high cost, difficulty in traditional handicraft joint
The deficiency of processing.Take into account simultaneously localizer repeat into time course deviation problem, make this latch
Formula anti-escape process connection can absorb localizer repeat into time course deviation, it is to avoid time-consuming take
The measurement of the localizer attitude of power and correction.
For realizing object above, according to an aspect of the present invention, it is provided that a kind of bolt-type is anti-to be escaped
Ease process connection, it is fixed on localizer the docking for aircraft process components and posture adjustment, described
Process connection includes:
Ball-and-socket, it is arranged on aircraft process components and is formed with the first pin-and-hole；
Bulb, its by floor installation on localizer and with described ball-and-socket coordinate contact, described ball
The second pin-and-hole it is formed with on Tou；
Latch, it runs through described first pin-and-hole and described the when the laminating of described ball-and-socket and bulb puts in place
Two pin-and-holes；
Wherein, described process connection also includes self-adaptive regulating, and it is fixing with described bulb even
Connect the position deviation promoting described bulb to be automatically adjusted in described ball-and-socket.
By technique scheme, by means of bolt-type anti-escape process connection, process part can be realized
Part assembling during high efficiency, high-precision posture adjustment with dock.Additionally, Automatic adjusument dress
Put can adapt to localizer repeat into time course deviation, it is ensured that it is same that latch inserts smoothly
Time, it is to avoid the repeated measure of localizer and correcting locater attitude.
According to a kind of embodiment, described self-adaptive regulating includes being installed on described base
Bearing block, the plane bearing being fixed on described bearing block and be installed on described plane bearing and
Deep groove ball bearing between described bulb.Wherein deep groove ball bearing, plane bearing ensure that bulb exists
Rotate freely around unique rotary shaft in one plane, provide convenient for inserting latch.
Preferably, described process connection also includes assisting anti-release apparatus, and it is arranged at described bulb
Interior auxiliary prevents the latch inserted from escaping.
According to a kind of embodiment, the anti-release apparatus of described auxiliary includes spring-loaded plunger, and it is arranged on
In the 3rd pin-and-hole formed in described bulb, described 3rd pin-and-hole communicates with described second pin-and-hole.
Advantageously, the anti-release apparatus of described auxiliary also includes the guiding being positioned at described spring-loaded plunger one end
Steel ball, described latch is correspondingly provided with gathering sill, and described guiding steel ball is at the work of described spring-loaded plunger
Can embed in described gathering sill under with, thus prevent latch from escaping further.
According to a kind of embodiment, described process connection also includes the power sensing being connected to described bulb
Device, thus the weight of aircraft process components during measuring posture adjustment in real time, it is to avoid process connection produces
Pitch deviation, keeps horizontal direction stable.
Advantageously, the diameter of the first pin-and-hole of described ball-and-socket is slightly larger than the diameter of described latch so that
Technique connects the ball pivot connection forming little scope.Ball pivot connection ensure that the central shaft in process connection
When line is identical with gravity direction, ball-and-socket only rotates freely around unique fixing point on bulb, makes technique
Joint is unstressed point location in change system.
According to a further aspect in the invention, additionally provide a kind of docking for aircraft process components and
The anti-escape process connection method of attachment of posture adjustment, it uses above-mentioned bolt-type anti-escape process connection
Implementing, described method includes:
Anti-for multiple bolt-types escape process connection being installed on localizer, wherein, each ball-and-socket is pacified
It is loaded on aircraft process components；
Aircraft process components is lifted into position, when ball-and-socket will contact with bulb, adjust each ball
Head the second pin-and-hole towards so that it is align with the first pin-and-hole of corresponding described ball-and-socket；
Latch is inserted along described first pin-and-hole of described ball-and-socket and described second pin-and-hole of described bulb；
Decline suspender, make described bulb support whole aircraft process components, and described bulb completely
Spherical pair is become with described ball-and-socket type；
Withdraw suspender, carry out posture adjustment and the docking of aircraft process components.
According to a kind of embodiment, described method also includes:
Use laser tracker to set up assembling coordinate system, under assembling coordinate system, calibrate aircraft technique
The center of each ball-and-socket on parts；
Adjust the locus of each bulb so that the center of each bulb and corresponding ball
The center of nest overlaps.
During the assembling of aircraft process components, laser tracker is used to be conducive to the most accurately
Characterization processes joint and the current pose of aircraft process components, and then judge that posture adjustment departure is easy to
The position of adjusting process joint, it is achieved relatively reliable accurate posture adjustment is docked.
From the general introduction of technique scheme it is known that advantages of the present invention at least that:
1, the bolt-type of the present invention anti-escape process connection can be joined with digitized automatic setup system
Close and use, process components high efficiency, high-precision posture adjustment and docking during assembling can be realized；
2, in the bolt-type of the present invention anti-escape process connection, bulb is fixed by deep groove ball bearing
On plane bearing, it is ensured that bulb in the plane of plane bearing around the axle of deep groove ball bearing
Line rotate, thus automatically adapt to localizer repeat into time course deviation, it is ensured that latch is smooth
Insert；
3, in the bolt-type of the present invention anti-escape process connection, spring-loaded plunger is set in bulb,
Make it abut against with the latch inserted, prevent latch from escaping further, it is ensured that the reliability of docking.
Accompanying drawing explanation
The further feature of the present invention and advantage are by preferred by describe in detail below in conjunction with accompanying drawing
Embodiment is more fully understood that, wherein:
Fig. 1 is the cross section of bolt-type anti-escape process connection according to the preferred embodiment of the present invention
Schematic diagram；
Fig. 2 is the side schematic view of the anti-escape process connection of bolt-type shown in Fig. 1, not shown in it
Ball-and-socket part；
Fig. 3 is the schematical top view of the anti-escape process connection of bolt-type shown in Fig. 2.
Detailed description of the invention
Enforcement and the use of embodiment are discussed further below.It will be appreciated, however, that discussed
Specific embodiment the most exemplarily illustrates to implement and use the ad hoc fashion of the present invention, it is no intended to
Limit is according to all embodiments of the present invention.Additionally, the structural design drawing of example is used merely to facilitate
Understand the present invention, rather than the architectural feature of the present invention is made concrete restriction.
See Fig. 1 and combine Fig. 2 and Fig. 3, according to the preferred embodiment of the present invention bolt-type
Anti-escape process connection includes the ball-and-socket 1 being arranged on aircraft process components and can join with ball-and-socket 1
The bulb 2 that splice grafting touches, ball-and-socket 1 is formed the first pin-and-hole 11, bulb 2 is formed the second pin
Hole 21.Latch 6 runs through the first pin-and-hole 11 and the second pin with bulb 2 laminating when ball-and-socket 1 puts in place
Hole 21 realizes the anti-escape docking of ball-and-socket 1 and bulb 2.Bulb 2 is installed on base 10, the end
Seat 10 is then installed on localizer (not shown) by connection members such as such as screws.Generally feelings
Under condition, this process connection is installed between localizer and aircraft process components in a vertical manner, passes through
Bulb accepts the weight of process components, and the spherical pair formed by means of bulb and ball-and-socket realizes technique
The docking posture adjustment of parts.Wherein, the diameter of the first pin-and-hole 11 of ball-and-socket 1 is slightly larger than latch 6
Diameter, to form ball pivot connection, makes process connection unstressed point location in change system.
According to the present invention, bulb 2 is fixedly connected with self-adaptive regulating, so that bulb and ball
When socket and spigot joint touches, bulb 2 is automatically adjusted its position deviation in ball-and-socket 1, thinks highly of absorbing location
Course deviation during reentrant position.As shown in Figure 1, this self-adaptive regulating can include being installed on
Bearing block 8, the plane bearing 7 being fixed on bearing block 8 on base 10 and be installed on flat
Deep groove ball bearing 3 between spherical bearing 7 and bulb 2, bearing cap 4 is installed on base 10 and covers
Lid self-adaptive regulating.Whereby, bulb 2 can be around deep-groove ball axle in the plane of plane bearing 7
Hold the axis rotation of 3, thus be automatically adjusted the first pin-and-hole 11 and the second pin when inserting latch 6
Deviation between hole 21, it is achieved the smooth insertion of latch 6.
Seeing Fig. 1 and combine Fig. 3, the present invention is additionally advantageously provided with the 3rd pin-and-hole in bulb 2
22, place in it and spring-loaded plunger 5 assisting anti-escape function is provided.Embodiment shown in the figure
In, the 3rd pin-and-hole 22 is formed at bulb 2 top, and extends to communicate with the second pin-and-hole 21.
It is understood, however, that the 3rd pin-and-hole may be alternatively formed to extend to from the side of bulb 2 with
Second pin-and-hole 21 communicates, as long as spring-loaded plunger 5 can be with when latch 6 inserts the second pin-and-hole 21
Latch 6 abuts against and realizes anti-escape.As a kind of preferred implementation, at the one of spring-loaded plunger 5
End can arrange a guiding steel ball 51, correspondingly, latch 6 is correspondingly provided with gathering sill 61, at bullet
Under the effect of spring plunger 5, guiding steel ball 51 can embed and realize anti-escape in gathering sill 61.
In actual use, it is generally directed to an aircraft process components and uses multiple process connection.
Thus, how to guarantee the reliable and stable particularly significant of each process connection.In order to measure tune in real time
The weight of the tested section of aircraft process components during appearance, prevents process components and process connection from bowing
Facing upward the generation of deviation, process connection also includes the force transducer 9 being connected to bulb 2.Illustrate
In embodiment, force transducer 9 is fixed on bearing block 8, as shown in Figure 1.Sense according to power
The data that device 9 records, it is possible to adjust counterweight accordingly, keep the stable support of horizontal direction.Additionally,
Each process connection can also be made to work in coordination with according to the deviations of the data judgement process connection recorded
Coordinate, each other without result in process components docking posture adjustment error involve power.
The bolt-type anti-escape process connection of illustrated embodiment is used below in conjunction with Summary of drawings
Realize the docking of aircraft process components and the anti-escape process connection method of attachment of posture adjustment, with further
Understand the present invention.
Exemplary work process is as follows:
1, anti-for multiple bolt-types escape process connection is fixed on digital control location device or the most hand
On localizer, wherein each ball-and-socket is installed on aircraft process components；
2, use laser tracker to set up assembling coordinate system, under assembling coordinate system, calibrate aircraft
The center of each ball-and-socket on process components；
3, the locus of each bulb on localizer is adjusted so that the centre bit of each bulb 2
Put the center with corresponding ball-and-socket 1 to overlap；
4, aircraft process components is lifted into position, when ball-and-socket 1 will contact with bulb 2, adjust
Second pin-and-hole 21 of each bulb 2 whole towards so that it is with the first of corresponding ball-and-socket 1 the pin
Align in hole 11；
5, latch 6 is inserted along the first pin-and-hole 11 of ball-and-socket 1 and the second pin-and-hole 21 of bulb 2；
6, decline suspender, make bulb 2 support whole aircraft process components completely, by ball-and-socket 1 He
Bulb 2 forms spherical pair；
7, withdraw suspender, carry out posture adjustment and the docking of aircraft process components.
Technology contents and the technical characterstic of the present invention have revealed that as above.It should be appreciated that accompanying drawing
The principle being only the present invention that is shown and that be been described by, there is many amendment sides in above-mentioned embodiment
Formula, these modes are clearly for various equivalent modifications.Such as, each shown in figure
The planform of parts is merely illustrative, not as a limitation of the invention, every according to the present invention's
Any simple modification, equivalent variations and the modification that above example is made by technical spirit, each falls within this
In the protection domain of inventive technique scheme.
Claims (9)
1. a bolt-type anti-escape process connection, it is fixed on localizer for aircraft technique
The docking of parts and posture adjustment, described process connection includes:
Ball-and-socket, it is arranged on aircraft process components and is formed with the first pin-and-hole；
Bulb, its by floor installation on localizer and with described ball-and-socket coordinate contact, described
The second pin-and-hole it is formed with on bulb；
Latch, it runs through described first pin-and-hole and described when the laminating of described ball-and-socket and bulb puts in place
Second pin-and-hole；
Wherein, described process connection also includes self-adaptive regulating, and it is fixed with described bulb
Connect with the position deviation promoting described bulb to be automatically adjusted in described ball-and-socket.
Bolt-type the most according to claim 1 anti-escape process connection, it is characterised in that
Described self-adaptive regulating includes the bearing block being installed on described base, is fixed on described axle
Plane bearing in bearing and be installed on the zanjon between described plane bearing and described bulb
Ball bearing.
Bolt-type the most according to claim 1 and 2 anti-escape process connection, its feature exists
In, described process connection also includes assisting anti-release apparatus, and it prevents in being arranged at described bulb
The latch inserted is escaped.
Bolt-type the most according to claim 3 anti-escape process connection, it is characterised in that
The anti-release apparatus of described auxiliary includes spring-loaded plunger, and it is arranged on the 3rd of the interior formation of described bulb the
In pin-and-hole, described 3rd pin-and-hole communicates with described second pin-and-hole.
Bolt-type the most according to claim 4 anti-escape process connection, it is characterised in that
The anti-release apparatus of described auxiliary also includes the guiding steel ball being positioned at described spring-loaded plunger one end, described
Being correspondingly provided with gathering sill on latch, described guiding steel ball can under the effect of described spring-loaded plunger
Embed in described gathering sill.
Bolt-type the most according to claim 1 anti-escape process connection, it is characterised in that
Described process connection also includes the force transducer being connected to described bulb.
Bolt-type the most according to claim 1 anti-escape process connection, it is characterised in that
The diameter of described first pin-and-hole of described ball-and-socket is slightly larger than the diameter of described latch.
8. the docking for aircraft process components and the anti-escape process connection connection side of posture adjustment
Method, uses bolt-type according to any one of claim 1 to 7 anti-escape process connection,
Described method includes:
Anti-for multiple bolt-types escape process connection is installed on localizer, wherein, each ball-and-socket
It is installed on aircraft process components；
Aircraft process components is lifted into position, when ball-and-socket will contact with bulb, adjust each
Second pin-and-hole of bulb towards so that it is align with the first pin-and-hole of corresponding described ball-and-socket；
Insert insert along described first pin-and-hole of described ball-and-socket and described second pin-and-hole of described bulb
Pin；
Decline suspender, make described bulb support whole aircraft process components, and described ball completely
Head becomes spherical pair with described ball-and-socket type；
Withdraw suspender, carry out posture adjustment and the docking of aircraft process components.
Anti-escape process connection method of attachment the most according to claim 8, it is characterised in that
Before described ball-and-socket contacts with described bulb, described method also includes:
Use laser tracker to set up assembling coordinate system, under assembling coordinate system, calibrate aircraft work
The center of each ball-and-socket on skill parts；
Adjust the locus of each bulb so that the center of each bulb is with corresponding
The center of ball-and-socket overlaps.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510366832.XA CN106314820B (en) | 2015-06-29 | 2015-06-29 | Bolt type anti-escape process connector and application method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510366832.XA CN106314820B (en) | 2015-06-29 | 2015-06-29 | Bolt type anti-escape process connector and application method thereof |
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| Publication Number | Publication Date |
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| CN106314820A true CN106314820A (en) | 2017-01-11 |
| CN106314820B CN106314820B (en) | 2021-05-07 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107263351A (en) * | 2017-05-09 | 2017-10-20 | 浙江大学 | A kind of mechanical ball head locking device of locator |
| CN109420880A (en) * | 2017-08-24 | 2019-03-05 | 中航贵州飞机有限责任公司 | A kind of accurate installation method of aircraft joint part |
| CN110239736A (en) * | 2019-05-17 | 2019-09-17 | 陕西飞机工业（集团）有限公司 | One kind changes the outfit tooling and costume changing method |
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| CN103887219A (en) * | 2012-12-20 | 2014-06-25 | 英飞凌科技股份有限公司 | Self-aligning pick-up head and method for manufacturing a device with the self-aligning pick-up head |
| CN203294080U (en) * | 2013-05-10 | 2013-11-20 | 三一汽车制造有限公司 | Supporting leg seat, supporting leg and engineering machinery |
| CN203371431U (en) * | 2013-07-12 | 2014-01-01 | 沈阳航空航天大学 | Multi-point array self-adaptive vacuum suction plate type flexible assembling tool equipment |
| CN204378633U (en) * | 2014-01-24 | 2015-06-10 | 苹果公司 | For showing the display system of product and the fixator for fixed product |
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| CN107263351A (en) * | 2017-05-09 | 2017-10-20 | 浙江大学 | A kind of mechanical ball head locking device of locator |
| CN107263351B (en) * | 2017-05-09 | 2019-01-29 | 浙江大学 | A kind of mechanical ball head locking device of locator |
| CN109420880A (en) * | 2017-08-24 | 2019-03-05 | 中航贵州飞机有限责任公司 | A kind of accurate installation method of aircraft joint part |
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