CN105252314A - Mechanism and method for quickly positioning airplane components - Google Patents
Mechanism and method for quickly positioning airplane components Download PDFInfo
- Publication number
- CN105252314A CN105252314A CN201510846996.2A CN201510846996A CN105252314A CN 105252314 A CN105252314 A CN 105252314A CN 201510846996 A CN201510846996 A CN 201510846996A CN 105252314 A CN105252314 A CN 105252314A
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- China
- Prior art keywords
- aircraft components
- guide
- locating shaft
- connecting axle
- base
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- 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.)
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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
- B23Q3/062—Work-clamping means adapted for holding workpieces having a special form or being made from a special material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
- B25B11/02—Assembly jigs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Insertion Pins And Rivets (AREA)
Abstract
The invention discloses a mechanism for quickly positioning airplane components. The mechanism is provided with a guiding and positioning mechanism and a limited seat which cooperates with the guiding and positioning mechanism, wherein the guiding and positioning mechanism is provided with a positioning shaft; the positioning shaft is cylindrical; connecting shafts are respectively arranged at two ends, in the positioning shaft, and are connected with holes in the airplane components; an axial limited block is arranged on the positioning shaft, and is arranged in the middle of the positioning shaft in a sleeving manner; the limited seat is provided with a base; an axial positioning groove is formed in the base, and cooperates with the axial limited seat so as to perform axial positioning on the guiding and positioning mechanism. Through the adoption of the mechanism disclosed by the invention, the purposes that the airplane components are quickly positioned and connected when being mounted at different work positions or being remounted are realized; the positioning flexibility of the airplane components and the mounting flexibility of the airplane components are realized; products are adapted to being mounted, dismounted and transferred at different work positions on a production line; the production preparation cycle is shortened; the cost for researching and manufacturing airplanes is reduced.
Description
Technical field
The invention belongs to transporation by plane technical field, is specifically related to a kind of aircraft components quick positioning mechanism and localization method, for aircraft components quick position be connected.
Background technology
Aircraft manufacturing process is complicated, and by part to assembly, parts until form full machine process, its link is numerous, and product component needs multiple bearing to install, particularly the reorientation of large component, its positioning precision and the impact of efficiency on the aircraft manufacturing cycle larger.Conventional airplane manufacture adopts simulation to coordinate, important positioning datum, and as crossing point holes, important mating surface, the shortcomings such as locating slot etc., when upstream and downstream operation circulates, exist repetitive positioning accuracy low, and the operating time is long, govern assembly quality and the efficiency of aircraft.
Summary of the invention
The goal of the invention of the invention is for aircraft components is the added of different station or reinstall and provide location and connected mode fast, realize aircraft components location and the flexibility of installing, to adapt to the product upper and lower frame of different station and circulation on a production line, shorten the Operational preparation cycle, reduce aircraft development cost.
The technical scheme that the invention adopts is:
A kind of aircraft components quick positioning mechanism, the limit base that there is guide-localization mechanism and coordinate with guide-localization mechanism, described guide-localization mechanism has locating shaft, and described locating shaft is cylindric, the inner two ends of locating shaft are respectively equipped with connecting axle, and described connecting axle is connected with the hole on aircraft components; Described locating shaft is also provided with axial limiting block, and described axial limiting block is set in the middle part of locating shaft;
Described limit base has base, and base is provided with axial location groove, and described axial limiting groove coordinates with axial limiting block and carries out axial location to guide-localization mechanism.
Described a kind of aircraft components quick positioning mechanism, described axial location groove is arranged on the middle part of base, and the two ends of base are also respectively equipped with opening shape inverted ladder type locating piece, and described ladder type locating piece coordinates with locating shaft and carries out guide-localization to guide-localization mechanism.
Described a kind of aircraft components quick positioning mechanism, axial limiting block is ring shaped axial limited block.
Described a kind of aircraft components quick positioning mechanism, described base is also provided with the retaining mechanism for fixed guide detent mechanism, described retaining mechanism comprises grip base and clamp, grip base is installed in the side of ladder type locating piece, described clamp is L-type clamp, one end of clamp is connected with grip base by turning cylinder, the end of ladder type locating piece opposite side is provided with screw thread shrinkage pool, the other end of clamp is provided with clamping screw, locating shaft in guide-localization mechanism is fixed in ladder type locating piece by clamping screw and the effect of screw thread shrinkage pool by described clamp.
Described a kind of aircraft components quick positioning mechanism, the barrel at described locating shaft two ends has long through-hole along the axis of locating shaft respectively, described connecting axle is also provided with operative pin, one end of described operative pin through long through-hole and connecting axle affixed, the other end of operative pin extends to outside locating shaft, and described connecting axle drives connecting axle to slide in locating shaft along sliding axially of locating shaft in long through-hole.
Described a kind of aircraft components quick positioning mechanism, the barrel at described locating shaft two ends is also provided with through hole and locking pin, and described locking pin is positioned at the connecting axle of locating shaft inside by through hole effect, is fixed in locating shaft by connecting axle.
A kind of aircraft components method for rapidly positioning, comprises the steps:
1) location of aircraft components and connection, guide-localization mechanism is connected with aircraft components, connecting axle is utilized to coordinate with the hole on aircraft components, in hole connecting axle being inserted on aircraft components by operative pin, utilize locking pin to be fixed connecting axle, prevent connecting axle from coming off from the hole aircraft components;
2) location of guide-localization mechanism, by coordinating of the guide-localization mechanism be fixed on aircraft components and limit base, first by axial limiting block and axial limiting groove coarse alignment, then slowly aircraft components is put down, enter after axial limiting groove until axial limiting block, locating shaft is slipped in the open area of opening shape inverted ladder type locating piece again, put down aircraft components, namely complete the location of the aircraft components that guide-localization mechanism is housed;
3) locking of guide-localization mechanism, clamp is connected with grip base by turning cylinder, clamp rotate moving axis rotate, clamp is made to compress locating shaft, then clamping screw to be screwed on ladder type locating piece in screw thread shrinkage pool, realize being connected of guide-localization mechanism and limit base, and then complete the positioning and locking work of aircraft components.
The invention has following beneficial effect:
A kind of aircraft components quick positioning mechanism of the invention has the shortening product manufacturing cycle, reduce frock manufacturing expense, flexible frock is made to obtain the advantages such as extensive application, meet the quick position of aircraft components on different station and clamping object, as automatic punching station, milling automatic station, intersection point fine finishining station, aircraft components between measurement and detection station circulate, save the time of the upper and lower frame of a large amount of aircraft components products, improve positioning precision, meet the beat of production line.
Spacing base and retaining mechanism can be integrated in each station fixture system in advance, wherein have the geometric parameter standardization of the part of matching relationship with guide-localization mechanism, and other and each station frock connecting portion geometric parameter can be changed according to actual needs.Guide-localization mechanism is connected by connecting axle and aircraft components, and the locating hole on the link of connecting axle and aircraft components adopts unified interface, and to realize between aircraft components with guide-localization mechanism quick is connected.
Guide-localization mechanism is connected by connecting axle and aircraft components and circulates at different stations in company with aircraft, aircraft components is played to the effect of guide-localization, realizes the quick and precisely location of aircraft components.During work, guide-localization mechanism passes through the connection of operative pin control connection axle and aircraft components, and realizes being connected with locking pin.When aircraft components is added, locating shaft coordinates with the opening shape inverted ladder type locating piece on limit base, and ladder type locating piece plays guide-localization effect to guide-localization mechanism, and restriction is except other frees degree moved axially.Axial location adopts the cooperation of axial limiting block and axial limiting groove to realize, axial limiting block is annular, it has larger chamfering and axial limiting slot fit vertically, guide effect is played to the installation of guide-localization mechanism, during work, axial limiting block inserts in axial limiting groove gradually, until the spacing end face of axial limiting block enters in axial limiting groove completely, completes the axial location operation of guide-localization mechanism.After having located, compressed the locating shaft of guide-localization mechanism by the clamp at two ends, and with clamping screw locking, formed and firmly connect.
Retaining mechanism is connected with limit base is detachable, meets the interchangeability requirement of different station and product.
Accompanying drawing explanation
Fig. 1 is a kind of structural representation of aircraft components quick positioning mechanism.
Fig. 2 is the structural representation of middle guide-localization mechanism shown in Fig. 1.
Fig. 3 is the structural representation of middle limit base shown in Fig. 1.
Wherein 1-limit base, 2-guide-localization mechanism, 3-clamping screw, 4-clamp, 5-turning cylinder, 6-base, 7-ladder type locating piece, 8-grip base, 9-axial limiting groove, 10-axial limiting block, 11-locating shaft, 12-connecting axle, 13-operative pin, 14-locking pin.
Detailed description of the invention
A kind of aircraft components quick positioning mechanism as shown in Figure 1, the limit base 1 that there is guide-localization mechanism 2 and coordinate with guide-localization mechanism 2, the described mechanism of guide-localization as shown in Figure 22 has locating shaft 11, described locating shaft 11 is cylindric, the inner two ends of locating shaft 11 are respectively equipped with connecting axle 12, and described connecting axle 12 is connected with the hole on aircraft components; The barrel at described locating shaft 11 two ends has long through-hole along the axis of locating shaft 11 respectively, described connecting axle 12 is also provided with operative pin 13, one end of described operative pin 13 through long through-hole and connecting axle 12 affixed, the other end of operative pin 13 extends to outside locating shaft, and described connecting axle 12 drives connecting axle 12 to slide in locating shaft 11 along sliding axially of locating shaft 11 in long through-hole; The barrel at described locating shaft 11 two ends is also provided with through hole and locking pin 14, and described locking pin 14 is positioned at the connecting axle 12 of locating shaft 11 inside by through hole effect, is fixed in locating shaft 11 by connecting axle 12.Described locating shaft 11 is also provided with axial limiting block 10, and described axial limiting block 10 is set in the middle part of locating shaft 11.
Limit base 1 has base 6 as shown in Figure 3, and base 6 is provided with axial location groove 9, and described axial limiting groove 9 coordinates with axial limiting block 10 and carries out axial location to guide-localization mechanism 2.Described axial location groove 9 is arranged on the middle part of base 6, provides the observation panel that operating personnel observe positioning scenarios from below.The two ends of base 6 are also respectively equipped with opening shape inverted ladder type locating piece 7, and described ladder type locating piece 7 coordinates with locating shaft 11 and carries out guide-localization to guide-localization mechanism 2.Described base 6 is also provided with the retaining mechanism for fixed guide detent mechanism 2, described retaining mechanism comprises grip base 8 and clamp 4, grip base 8 is installed in the side of ladder type locating piece 7, described clamp 4 is L-type clamp 4, one end of clamp 4 is connected with grip base 8 by turning cylinder 5, the end of ladder type locating piece 7 opposite side is provided with screw thread shrinkage pool, the other end of clamp 4 is provided with clamping screw 3, and the locating shaft 11 in guide-localization mechanism 2 is fixed in ladder type locating piece 7 by clamping screw 3 and the effect of screw thread shrinkage pool by described clamp 4.
A kind of aircraft components method for rapidly positioning, comprises the steps:
1) first guide-localization mechanism 2 is connected with aircraft components with being connected by the location of aircraft components, connecting axle 12 hole corresponding in aircraft components structure is utilized to coordinate, connecting axle 12 is made to insert in the hole of corresponding cooperation on aircraft components by operative pin 13, after the connecting axle 12 being positioned at locating shaft 11 two ends all inserts aircraft components, locking pin 14 pairs of connecting axles 12 are installed be fixed, prevent connecting axle 12 from coming off from the hole aircraft components, ensure connection reliability.During work, guide-localization mechanism 2 circulates at different station in company with aircraft, until aircraft components has assembled.
2) location of guide-localization mechanism 1, all integrated limit base 1 and retaining mechanism on each station fixture system, by coordinating of the guide-localization mechanism 2 be assemblied on aircraft components and limit base 1, realize the assembling of aircraft components and fixture system.During added the or reorientation of aircraft components, first coarse alignment axial limiting block 10 and axial limiting groove 9, then slowly put down aircraft components, after chamfered region, axial limiting block 10 two ends enters axial limiting groove 9, just automatic guide can enter position.Then by locating shaft 11 coarse alignment opening shape inverted ladder type locating piece 7, axle 11 to be positioned enters in the open area of opening shape inverted ladder type locating piece 7, puts down aircraft components, can complete the six degree of freedom location of aircraft components.
3) locking of guide-localization mechanism, after aircraft components has been located, is connected clamp 4 with grip base 8 by turning cylinder 5, and clamp 4 moving axis 5 that can rotate rotates.Rotate clamp 4, make it to compress locating shaft ll, then clamping screw 3 is screwed in the bolt shrinkage pool on ladder type locating piece 7, realize being connected of guide-localization mechanism 2 and limit base 1, and then the reliable positioning and locking completing aircraft components connects.
Claims (7)
1. an aircraft components quick positioning mechanism, it is characterized in that, the limit base that there is guide-localization mechanism and coordinate with guide-localization mechanism, described guide-localization mechanism has locating shaft, described locating shaft is cylindric, the inner two ends of locating shaft are respectively equipped with connecting axle, and described connecting axle is connected with the hole on aircraft components; Described locating shaft is also provided with axial limiting block, and described axial limiting block is set in the middle part of locating shaft;
Described limit base has base, and base is provided with axial location groove, and described axial limiting groove coordinates with axial limiting block and carries out axial location to guide-localization mechanism.
2. a kind of aircraft components quick positioning mechanism according to claim 1, it is characterized in that, described axial location groove is arranged on the middle part of base, the two ends of base are also respectively equipped with opening shape inverted ladder type locating piece, and described ladder type locating piece coordinates with locating shaft and carries out guide-localization to guide-localization mechanism.
3. a kind of aircraft components quick positioning mechanism according to claim 1 and 2, is characterized in that, axial limiting block is ring shaped axial limited block.
4. a kind of aircraft components quick positioning mechanism according to claim 2, it is characterized in that, described base is also provided with the retaining mechanism for fixed guide detent mechanism, described retaining mechanism comprises grip base and clamp, grip base is installed in the side of ladder type locating piece, described clamp is L-type clamp, one end of clamp is connected with grip base by turning cylinder, the end of ladder type locating piece opposite side is provided with screw thread shrinkage pool, the other end of clamp is provided with clamping screw, locating shaft in guide-localization mechanism is fixed in ladder type locating piece by clamping screw and the effect of screw thread shrinkage pool by described clamp.
5. a kind of aircraft components quick positioning mechanism according to claim 1,2 or 4, it is characterized in that, the barrel at described locating shaft two ends has long through-hole along the axis of locating shaft respectively, described connecting axle is also provided with operative pin, one end of described operative pin through long through-hole and connecting axle affixed, the other end of operative pin extends to outside locating shaft, and described connecting axle drives connecting axle to slide in locating shaft along sliding axially of locating shaft in long through-hole.
6. a kind of aircraft components quick positioning mechanism according to claim 5, it is characterized in that, the barrel at described locating shaft two ends is also provided with through hole and locking pin, and described locking pin is positioned at the connecting axle of locating shaft inside by through hole effect, is fixed in locating shaft by connecting axle.
7. an aircraft components method for rapidly positioning, is characterized in that, comprises the steps:
1) location of aircraft components and connection, guide-localization mechanism is connected with aircraft components, connecting axle is utilized to coordinate with the hole on aircraft components, in hole connecting axle being inserted on aircraft components by operative pin, utilize locking pin to be fixed connecting axle, prevent connecting axle from coming off from the hole aircraft components;
2) location of guide-localization mechanism, by coordinating of the guide-localization mechanism be fixed on aircraft components and limit base, first by axial limiting block and axial limiting groove coarse alignment, then slowly aircraft components is put down, enter after axial limiting groove until axial limiting block, locating shaft is slipped in the open area of opening shape inverted ladder type locating piece again, put down aircraft components, namely complete the location of the aircraft components that guide-localization mechanism is housed;
3) locking of guide-localization mechanism, clamp is connected with grip base by turning cylinder, clamp rotate moving axis rotate, clamp is made to compress locating shaft, then clamping screw to be screwed on ladder type locating piece in screw thread shrinkage pool, realize being connected of guide-localization mechanism and limit base, and then complete the positioning and locking work of aircraft components.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510846996.2A CN105252314B (en) | 2015-11-27 | 2015-11-27 | A kind of aircraft components quick positioning mechanism and localization method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510846996.2A CN105252314B (en) | 2015-11-27 | 2015-11-27 | A kind of aircraft components quick positioning mechanism and localization method |
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| Publication Number | Publication Date |
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| CN105252314A true CN105252314A (en) | 2016-01-20 |
| CN105252314B CN105252314B (en) | 2018-05-01 |
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| CN201510846996.2A Active CN105252314B (en) | 2015-11-27 | 2015-11-27 | A kind of aircraft components quick positioning mechanism and localization method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106272183A (en) * | 2016-09-22 | 2017-01-04 | 无锡威孚力达催化净化器有限责任公司 | Synchronizing moving attitude reference device |
| CN107953297A (en) * | 2017-11-08 | 2018-04-24 | 江西洪都航空工业集团有限责任公司 | A kind of missile wing fast assembly and disassembly mechanism |
| CN109514466A (en) * | 2018-12-24 | 2019-03-26 | 海马汽车有限公司 | A kind of compression tooling |
| CN115070489A (en) * | 2022-06-25 | 2022-09-20 | 上海海鹰机械厂 | Rapid positioning method and positioning device for intersection point of outer circular groove and inner spiral groove |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106272183A (en) * | 2016-09-22 | 2017-01-04 | 无锡威孚力达催化净化器有限责任公司 | Synchronizing moving attitude reference device |
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| CN107953297A (en) * | 2017-11-08 | 2018-04-24 | 江西洪都航空工业集团有限责任公司 | A kind of missile wing fast assembly and disassembly mechanism |
| CN109514466A (en) * | 2018-12-24 | 2019-03-26 | 海马汽车有限公司 | A kind of compression tooling |
| CN115070489A (en) * | 2022-06-25 | 2022-09-20 | 上海海鹰机械厂 | Rapid positioning method and positioning device for intersection point of outer circular groove and inner spiral groove |
| CN115070489B (en) * | 2022-06-25 | 2024-07-12 | 上海海鹰机械厂 | Quick positioning method and device for intersection point of outer circular groove and inner spiral groove |
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|---|---|
| CN105252314B (en) | 2018-05-01 |
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