CN205342514U - Quick positioning mechanism of aircraft part - Google Patents
Quick positioning mechanism of aircraft part Download PDFInfo
- Publication number
- CN205342514U CN205342514U CN201520967232.4U CN201520967232U CN205342514U CN 205342514 U CN205342514 U CN 205342514U CN 201520967232 U CN201520967232 U CN 201520967232U CN 205342514 U CN205342514 U CN 205342514U
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- locating shaft
- aircraft components
- base
- guide
- axle
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Abstract
The utility model creatively discloses a quick positioning mechanism of aircraft part, have guiding orientation mechanism and with the spacing seat of guiding orientation mechanism complex, guiding orientation mechanism has a location axle, location axle be cylindric, and location axle inside both ends are equipped with the connecting axle respectively, jogged joint on connecting axle and the aircraft part, fix a position the epaxial axial stopper that still is equipped with, the middle part at the location axle is established to axial stopper cover, spacing seat has the base, is equipped with the axial positioning groove on the base, axial positioning is carried out to guiding orientation mechanism to the cooperation of axial spacing groove and axial stopper. Realize the aircraft part and the putting on the shelf or when reinstallating quick location and the purpose is connected of different stations, realize the flexibility of aircraft part location and installation, the adaptation product put into production upper and lower of the different stations of on -line with circulate, shorten the production preparation cycle, reduction aircraft development cost.
Description
Technical field
The invention belongs to aircraft mounting technology field, is specifically related to a kind of aircraft components quick positioning mechanism, quickly positioning and being connected for aircraft components.
Background technology
Aircraft manufacturing process is complicated, and by part to assembly, parts until forming full machine process, its link is numerous, and product component needs multiple bearing to install, particularly the reorientation of large component, and its positioning precision and efficiency are bigger on the impact in aircraft manufacturing cycle.The shortcomings such as conventional airplane manufacture adopts simulation to coordinate, and important positioning datum such as crossing point holes, important mating surface, locating slot etc., when upstream and downstream operation circulates, exists repetitive positioning accuracy low, operating time length, govern assembling quality and the efficiency of aircraft.
Summary of the invention
The goal of the invention of the invention is the added of different station or to reinstall offer quickly location and connected mode for aircraft components, realize aircraft components location and the flexibility installed, to adapt to upper and lower frame and the circulation of product different station 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, having guide-localization mechanism and the limit base coordinated with guide-localization mechanism, described guide-localization mechanism has locating shaft, and described locating shaft is cylindric, being respectively arranged at two ends with connection axle inside locating shaft, described connection axle is connected with the hole on aircraft components；Being additionally provided with axial limiting block on described locating shaft, described axial limiting block is set in the middle part of locating shaft；
Described limit base has base, and base is provided with axial locating slot, and described axial limiting groove coordinates with axial limiting block guide-localization mechanism is axially positioned.
Described a kind of aircraft components quick positioning mechanism, described axial locating slot is arranged on the middle part of base, and the two ends of base further respectively have opening shape inverted ladder type locating piece, and described ladder type locating piece coordinates with locating shaft guide-localization mechanism is carried out guide-localization.
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 additionally provided with the retaining mechanism for fixed guide detent mechanism, described retaining mechanism includes grip base and clamping block, grip base is installed in the side of ladder type locating piece, described clamping block is L-type clamping block, one end of clamping block is connected with grip base by rotating axle, the end of ladder type locating piece opposite side is provided with screw thread shrinkage pool, the other end of clamping block is provided with clamping screw, the locating shaft that described clamping block is directed in detent mechanism by clamping screw and screw thread shrinkage pool effect is fixed in ladder type locating piece.
Described a kind of aircraft components quick positioning mechanism, the barrel at described locating shaft two ends axially has long through-hole along locating shaft respectively, described connection axle is additionally provided with operative pin, one end of described operative pin through long through-hole with to be connected axle affixed, the other end of operative pin extends to outside locating shaft, and described connection axle slides in locating shaft along the band that slides axially of the locating shaft axle that is dynamically connected in long through-hole.
Described a kind of aircraft components quick positioning mechanism, the barrel at described locating shaft two ends is additionally provided with through hole and locking pin, and described locking pin is positioned at the connection axle within locating shaft by through hole effect, is fixed in locating shaft by connection axle.
A kind of aircraft components method for rapidly positioning, comprises the steps:
1) location of aircraft components and connection, it is directed to detent mechanism be connected with aircraft components, connection axle is utilized to coordinate with the hole on aircraft components, being operated by pin makes connection axle insert in the hole on aircraft components, locking pin is utilized to be fixed connecting axle, it is prevented that to connect axle and come off from the hole aircraft components；
2) location of guide-localization mechanism, by coordinating of the guide-localization mechanism being fixed on aircraft components and limit base, first by axial limiting block and axial limiting groove coarse alignment, then aircraft components is slowly put down, enter after axial limiting groove until axial limiting block, again locating shaft is slipped in the open area of opening shape inverted ladder type locating piece, put down aircraft components, namely complete the location of aircraft components equipped with guide-localization mechanism；
3) locking of guide-localization mechanism, clamping block is connected with grip base by rotating axle, clamping block rotate moving axis rotate, clamping block is made to compress locating shaft, then clamping screw is 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 the advantages that
The invention one aircraft components quick positioning mechanism has the shortening product manufacturing cycle, reduce frock manufacturing expense, flexible frock is made to obtain the advantages such as extensive application, meet the aircraft components quickly location on different station and clamping purpose, as the aircraft components between automatic punching station, milling automatic station, intersection point polish station, measurement and detection station circulates, save the time of a large amount of upper and lower frame of aircraft components product, 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 with aircraft components by connecting axle, and the link connecting axle adopts unified interface with the hole, location on aircraft components, it is achieved being quickly connected between aircraft components with guide-localization mechanism.
Guide-localization mechanism is connected from aircraft components and in company with aircraft in different station circulations by connecting axle, aircraft components plays the effect of guide-localization, it is achieved the quick and precisely location of aircraft components.During work, guide-localization mechanism is operated by the connection that pin controls to connect axle with 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 guide-localization effect is played by ladder type locating piece by guide-localization mechanism, and limits except other degree of freedom moved axially.Axially location adopts the cooperation of axial limiting block and axial limiting groove to realize, axial limiting block is annular, it has bigger chamfering and axial limiting slot fit vertically, guide effect is played in the installation of guide-localization mechanism, during work, axial limiting block is gradually inserted in axial limiting groove, until the spacing end face of axial limiting block is completely into, in axial limiting groove, completing the axial positioning process of guide-localization mechanism.After having positioned, compressed the locating shaft of guide-localization mechanism by the clamping block at two ends, and lock with clamping screw, form firm connection.
Retaining mechanism is detachable with limit base to be connected, and meets the interchangeability requirement of different station and product.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind 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-clamps block, and 5-rotates axle, 6-base, 7-ladder type locating piece, 8-grip base, 9-axial limiting groove, 10-axial limiting block, 11-locating shaft, and 12-connects 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, there is guide-localization mechanism 2 and the limit base 1 coordinated 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, locating shaft 11 is internal is respectively arranged at two ends with connection axle 12, and described connection axle 12 is connected with the hole on aircraft components；The barrel at described locating shaft 11 two ends axially has long through-hole along locating shaft 11 respectively, described connection axle 12 is additionally provided with operative pin 13, one end of described operative pin 13 through long through-hole with to be connected axle 12 affixed, the other end of operative pin 13 extends to outside locating shaft, and described connection axle 12 slides in locating shaft 11 along the band that slides axially of locating shaft 11 axle 12 that is dynamically connected in long through-hole；Being additionally provided with through hole and locking pin 14 on the barrel at described locating shaft 11 two ends, described locking pin 14 is positioned at the connection axle 12 within locating shaft 11 by through hole effect, is fixed in locating shaft 11 by connection axle 12.Being additionally provided with axial limiting block 10 on described locating shaft 11, 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 locating slot 9, and described axial limiting groove 9 coordinates with axial limiting block 10 guide-localization mechanism 2 is axially positioned.Described axial locating slot 9 is arranged on the middle part of base 6, it is provided that the observation panel of the viewed from below positioning scenarios of operator.The two ends of base 6 further respectively have opening shape inverted ladder type locating piece 7, and described ladder type locating piece 7 coordinates with locating shaft 11 guide-localization mechanism 2 is carried out guide-localization.Described base 6 is additionally provided with the retaining mechanism for fixed guide detent mechanism 2, described retaining mechanism includes grip base 8 and clamping block 4, grip base 8 is installed in the side of ladder type locating piece 7, described clamping block 4 clamps block 4 for L-type, one end of clamping block 4 is connected with grip base 8 by rotating axle 5, the end of ladder type locating piece 7 opposite side is provided with screw thread shrinkage pool, the other end of clamping block 4 is provided with clamping screw 3, and the locating shaft 11 that described clamping block 4 is directed in detent mechanism 2 by clamping screw 3 and screw thread shrinkage pool effect is fixed in ladder type locating piece 7.
A kind of aircraft components method for rapidly positioning, comprises the steps:
1) location of aircraft components and connect and be first directed to detent mechanism 2 and be connected with aircraft components, connection axle 12 is utilized to coordinate with corresponding hole in aircraft components structure, being operated by pin 13 makes connection axle 12 insert in the hole coordinated accordingly on aircraft components, after the connection axle 12 being positioned at locating shaft 11 two ends all inserts aircraft components, locking pin 14 is installed and is fixed connecting axle 12, prevent from connecting axle 12 to come off from the hole aircraft components, it is ensured that 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 being assemblied on aircraft components and limit base 1, it is achieved the assembling of aircraft components and fixture system.Aircraft components is added or during reorientation, first coarse alignment axial limiting block 10 and axial limiting groove 9, then slowly puts down aircraft components, enters after axial limiting groove 9 until chamfered region, axial limiting block 10 two ends, 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 positioned, is connected clamping block 4 with grip base 8 by rotating axle 5, clamps block 4 moving axis 5 that can rotate and rotates.Rotate clamping block 4, so as to compress locating shaft ll, then clamping screw 3 is screwed in the bolt shrinkage pool on ladder type locating piece 7, it is achieved guide-localization mechanism 2 is connected with limit base 1, and then the reliable positioning and locking completing aircraft components connects.
Claims (6)
1. an aircraft components quick positioning mechanism, it is characterized in that, there is guide-localization mechanism and the limit base coordinated with guide-localization mechanism, described guide-localization mechanism has locating shaft, described locating shaft is cylindric, being respectively arranged at two ends with connection axle inside locating shaft, described connection axle is connected with the hole on aircraft components；Being additionally provided with axial limiting block on described locating shaft, described axial limiting block is set in the middle part of locating shaft；
Described limit base has base, and base is provided with axial locating slot, and described axial limiting groove coordinates with axial limiting block guide-localization mechanism is axially positioned.
2. a kind of aircraft components quick positioning mechanism according to claim 1, it is characterized in that, described axial locating slot is arranged on the middle part of base, and the two ends of base further respectively have opening shape inverted ladder type locating piece, and described ladder type locating piece coordinates with locating shaft guide-localization mechanism is carried out guide-localization.
3. a kind of aircraft components quick positioning mechanism according to claim 1 and 2, it is characterised 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 additionally provided with the retaining mechanism for fixed guide detent mechanism, described retaining mechanism includes grip base and clamping block, grip base is installed in the side of ladder type locating piece, described clamping block is L-type clamping block, one end of clamping block is connected with grip base by rotating axle, the end of ladder type locating piece opposite side is provided with screw thread shrinkage pool, the other end of clamping block is provided with clamping screw, the locating shaft that described clamping block is directed in detent mechanism by clamping screw and screw thread shrinkage pool effect is fixed in ladder type locating piece.
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 axially has long through-hole along locating shaft respectively, described connection axle is additionally provided with operative pin, one end of described operative pin through long through-hole with to be connected axle affixed, the other end of operative pin extends to outside locating shaft, and described connection axle slides in locating shaft along the band that slides axially of the locating shaft axle that is dynamically connected in long through-hole.
6. a kind of aircraft components quick positioning mechanism according to claim 5, it is characterized in that, being additionally provided with through hole and locking pin on the barrel at described locating shaft two ends, described locking pin is positioned at the connection axle within locating shaft by through hole effect, is fixed in locating shaft by connection axle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520967232.4U CN205342514U (en) | 2015-11-27 | 2015-11-27 | Quick positioning mechanism of aircraft part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520967232.4U CN205342514U (en) | 2015-11-27 | 2015-11-27 | Quick positioning mechanism of aircraft part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205342514U true CN205342514U (en) | 2016-06-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520967232.4U Withdrawn - After Issue CN205342514U (en) | 2015-11-27 | 2015-11-27 | Quick positioning mechanism of aircraft part |
Country Status (1)
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| CN (1) | CN205342514U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105252314A (en) * | 2015-11-27 | 2016-01-20 | 沈阳飞机工业（集团）有限公司 | Mechanism and method for quickly positioning airplane components |
| CN106181827A (en) * | 2016-08-12 | 2016-12-07 | 岳西县恒意机械有限公司 | A kind of frock clamp of high-axiality |
| CN109333095A (en) * | 2018-09-04 | 2019-02-15 | 北京北机机电工业有限责任公司 | A kind of positioning fixture fixed for revolving body and special-shaped part |
| CN110238780A (en) * | 2019-06-21 | 2019-09-17 | 芜湖市努尔航空信息科技有限公司 | A kind of positioning device for airplane parts tooling |
-
2015
- 2015-11-27 CN CN201520967232.4U patent/CN205342514U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105252314A (en) * | 2015-11-27 | 2016-01-20 | 沈阳飞机工业（集团）有限公司 | Mechanism and method for quickly positioning airplane components |
| CN105252314B (en) * | 2015-11-27 | 2018-05-01 | 沈阳飞机工业（集团）有限公司 | A kind of aircraft components quick positioning mechanism and localization method |
| CN106181827A (en) * | 2016-08-12 | 2016-12-07 | 岳西县恒意机械有限公司 | A kind of frock clamp of high-axiality |
| CN109333095A (en) * | 2018-09-04 | 2019-02-15 | 北京北机机电工业有限责任公司 | A kind of positioning fixture fixed for revolving body and special-shaped part |
| CN110238780A (en) * | 2019-06-21 | 2019-09-17 | 芜湖市努尔航空信息科技有限公司 | A kind of positioning device for airplane parts tooling |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160629 Effective date of abandoning: 20180501 |
|
| AV01 | Patent right actively abandoned |