CN112605924A - Positioning structure and positioning method of wing leading edge rib - Google Patents
Positioning structure and positioning method of wing leading edge rib Download PDFInfo
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- CN112605924A CN112605924A CN202011473167.1A CN202011473167A CN112605924A CN 112605924 A CN112605924 A CN 112605924A CN 202011473167 A CN202011473167 A CN 202011473167A CN 112605924 A CN112605924 A CN 112605924A
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- 238000000034 method Methods 0.000 title claims description 10
- 230000007547 defect Effects 0.000 abstract description 4
- 210000001503 joint Anatomy 0.000 description 3
- 101100334009 Caenorhabditis elegans rib-2 gene Proteins 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 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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Abstract
The positioning structure is connected to an assembling tool of the wing front edge rib, the positioning structure comprises a positioning component, an actuating cylinder and a limiter, the positioning component is connected with the front end of a telescopic rod of the actuating cylinder, a cylinder body end of the actuating cylinder is connected to the assembling tool structure, the telescopic stroke of the actuating cylinder is limited by the limiter, the telescopic actuating cylinder is used for solving the difficulty of automatic lifting, the automatic limiter is used for completing station control of lifting working conditions, the design of the positioning component completely avoids the defects that the tail end of the positioner interferes with a product and the positioner needs to be disassembled, the assembling efficiency is greatly improved, the operating strength is reduced, and potential safety hazards are avoided. In addition, due to the universality of the assembly of the front edge rib, the structure can be widely applied to the assembly of the front edge rib parts of box-type products such as outer wings, tail wings, movable wing surfaces and the like of military and civil aircraft.
Description
Technical Field
The application relates to the technical field of airplane assembly, in particular to a positioning structure and a positioning method for a front edge rib of a wing.
Background
Along with the improvement of the processing technology of airplane parts, the positioning of the leading edge rib of the existing large airplane wing box is generally realized by arranging two process holes on a rib web surface, so that an intensive leading edge rib positioning structure often appears in the assembling process of the front edge of a box section, and meanwhile, in order to ensure the convenience and safety of putting on and off a product, a larger space needs to be arranged between a leading edge area and a leading edge rib positioner, so that the leading edge rib positioner needs to complete the avoiding action of a lifting product to meet the assembling requirement of the product.
At present, internal large-scale army, civil aircraft wing box leading edge rib's location structure, adopt and set up at frock major structure and stretch a corner seat, product orientation module end is arranged in on the corner seat involution face, in order to satisfy product location and put up the demand from top to bottom, location module generally adopts detachable form or installation direction slide rail and helping hand air spring to rely on the artifical push-and-pull lift action that carries out the locator, this two kinds of schemes are though can accomplish the assembly of leading edge rib and put up the demand from top to bottom of product, but its structure has three main defect: 1) the labor intensity of workers is large: because the avoiding area between the positioner and the product is large, the weight of the positioning module is increased, and the labor intensity of workers is high in both a detachable mode and a manual power-assisted push-pull mode. 2) The potential safety hazard is big: because the height of the upper beam positioner of the tool from the ground is large, generally 3-5 m, a worker can finish the actions of detaching, pushing, pulling, lifting and inserting the limit pin on the fixed working ladder by adding a working stool, and safety accidents such as overturning of the worker, falling of heavy objects, empty stepping and the like easily occur in the execution process. 3) The assembly efficiency and the degree of automation are low: with the rapid increase of the output of the military and civil aircraft, the improvement of the assembly efficiency becomes a key research direction, the automation of the tool positioning structure is one of the best means for improving the assembly efficiency, the traditional front edge rib positioning structure completely depends on manual execution of the whole-course operation, and the efficiency is low.
Disclosure of Invention
In order to meet the requirements of aircraft production and overcome the defects of the prior art, the present application aims to provide a positioning structure and a positioning method of a wing leading edge rib.
The positioning structure of the wing leading edge rib is connected to an assembling tool of the wing leading edge rib, and is characterized in that the positioning structure comprises a positioning component, an actuating cylinder and a limiter, a body of the positioning component is of a cantilever structure, one end of a cantilever is provided with a connecting disc, the connecting disc is connected with the front end of a telescopic rod of the actuating cylinder, the other end of the cantilever is provided with a positioning surface and a positioning hole matched with the wing leading edge rib, the cylinder end of the actuating cylinder is connected to the assembling tool structure, and the telescopic stroke of the actuating cylinder is limited by the limiter.
The connecting disc is provided with a central through hole and a plurality of connecting holes, the center of the front end of the telescopic rod of the actuating cylinder is provided with a rotary positioning pin, the rotary positioning pin of the telescopic rod of the actuating cylinder is in clearance fit with the central through hole of the connecting disc, so that the cantilever structure can rotate relative to the front end of the telescopic rod of the actuating cylinder, and the connecting disc and the front end of the telescopic rod of the actuating cylinder can be pressed and fixed by a connecting bolt through the connecting holes.
The limiting device is fixed on the assembly tool structure and comprises a limiting sleeve and a limiting pin, the limiting sleeve is sleeved on the cylinder body of the actuating cylinder to limit the axial direction of the actuating cylinder, the limiting pin is of a telescopic pin structure, the telescopic direction of the limiting pin is perpendicular to the axial direction of the actuating cylinder, limiting holes matched with the limiting pin are formed in the cylinder body of the actuating cylinder and the telescopic rod, and the limiting pin limits the telescopic stroke of the actuating cylinder.
The present application also provides a method for positioning a leading edge rib of a wing, comprising: 1) using the positioning structure of the wing leading edge rib, 2) pre-installing the wing leading edge rib on a butt-joint product, 3) driving the actuator cylinder to enable a telescopic rod of the actuator cylinder to drive the positioning component to be close to the wing leading edge rib, inserting a limiting pin of a limiter into limiting holes on a cylinder body of the actuator cylinder and the telescopic rod, locking the telescopic stroke of the actuator cylinder through the limiting pin, 4) loosening a connecting bolt of a connecting plate of the positioning component and the actuator cylinder, rotating a cantilever of the positioning component to enable the cantilever to avoid the space interference of the wing leading edge rib, butt-jointing and positioning a positioning surface and a positioning hole at the other end of the positioning component with a reference surface and a reference hole of the wing leading edge rib, then compressing and fixing the connecting plate and the front end of the telescopic rod of the actuator cylinder through the connecting bolt, 5) loosening the butt-joint relation between the positioning surface and the positioning hole of the positioning component and the reference surface and the reference hole of the, and then loosening a connecting bolt of a connecting disc of the positioning assembly and the actuator cylinder, rotating a cantilever of the positioning assembly to enable the cantilever to avoid the spatial interference of the front edge rib of the wing, and 6) driving the actuator cylinder to enable a telescopic rod of the actuator cylinder to drive the positioning assembly to be far away from the front edge rib of the wing, and then locking the state of the actuator cylinder through a limiting pin of a limiter.
The beneficial effect of this application lies in: the invention solves the difficulty of automatic lifting by utilizing the telescopic actuating cylinder, adopts the limiter to complete the stroke control during lifting, and completely avoids the defects that the tail end of the positioner interferes with a product and the positioner needs to be disassembled due to the design of the positioning assembly, thereby greatly improving the assembly efficiency, reducing the operation intensity and avoiding the potential safety hazard. In addition, due to the universality of the assembly of the front edge rib, the structure can be widely applied to the assembly of the front edge rib parts of box-type products such as outer wings, tail wings, movable wing surfaces and the like of military and civil aircraft.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic illustration of a method of positioning a leading edge rib of an airfoil.
Fig. 2 is a schematic structural view of the positioning assembly.
Fig. 3 is a schematic view of the actuator cylinder.
FIG. 4 is a schematic view of a positioning structure of a leading edge rib of a wing.
The numbering in the figures illustrates: the wing assembly device comprises a wing 1 front edge rib, a 2 butt joint product, a 3 assembling tool, a 4 positioning component, a 5 actuator cylinder, a 6 limiter, a 7 connecting disc, an 8 plate, a 9 sleeve, a 10 positioning surface, a 11 positioning hole, a 12 central through hole, a 13 connecting hole, a 14 rotating positioning pin, a 15 limiting hole, a 16 disc, a 17 limiting sleeve and a 18 limiting pin.
Detailed Description
Referring to the accompanying drawings, the positioning structure of the wing leading edge rib of the present application is shown in fig. 1 and 4, the positioning structure is connected to an assembly fixture 3 of the wing leading edge rib 1, the positioning structure includes a positioning component 4, an actuating cylinder 5 and a limiter 6, the positioning component 4 is shown in fig. 2, a body of the positioning component 4 is a cantilever structure, one end of the cantilever is provided with a connecting disc 7, the connecting disc 7 is connected with the front end of a telescopic rod of the actuating cylinder 5, the other end of the cantilever is a plate 8, the plate 8 is provided with two sleeves 9, the front end of the sleeve 9 is a positioning surface 10, the center of the sleeve is provided with a positioning hole 11, the positioning surface 10 and the positioning hole 11 are matched with the positioning surface and the positioning hole of the wing leading edge rib 2, a cylinder end of the actuating cylinder 5 is connected to the assembly fixture 3, and the telescopic stroke of the actuating cylinder is limited by the.
In the embodiment, a connecting disc 7 at one end of a positioning assembly 4 is provided with a central through hole 12 and a plurality of connecting holes, the front end of an actuating cylinder telescopic rod is provided with a disc 16 matched with the connecting disc, the center of the disc is provided with a rotary positioning pin 14, the rotary positioning pin 14 is in clearance fit with the central through hole 12 of the connecting disc 7, so that a cantilever structure of the positioning assembly 4 can rotate relative to the circular disc 16 at the front end of the telescopic rod of the actuating cylinder 5, and a connecting bolt can connect and fix the connecting disc 7 and the circular disc 16 at the front end of the actuating cylinder telescopic rod through the.
The limiting device 6 is fixed on the structure of the assembly tool 3, the limiting device 6 comprises a limiting sleeve 17 and a limiting pin 18, the limiting sleeve 17 is sleeved on the cylinder body of the actuating cylinder 5 to limit the axial direction of the actuating cylinder 5, the limiting pin 18 is of a telescopic pin structure, the telescopic direction of the limiting pin 18 is perpendicular to the axial direction of the actuating cylinder 5, limiting holes 15 matched with the limiting pin 18 are formed in the cylinder body and the telescopic rod of the actuating cylinder 5, and the limiting pin 18 is matched with the limiting holes 15 to limit the telescopic stroke of the actuating cylinder 5.
When the wing positioning device is used, a wing leading edge rib 1 is preassembled on a butt-joint product 2, a positioning structure of the wing leading edge rib 1 is connected to a proper position of an assembly tool of the wing leading edge rib 1, the actuator cylinder 5 is driven, a telescopic rod of the actuator cylinder 5 drives the positioning component 4 to be close to the wing leading edge rib 1, when the actuator cylinder moves in place, a limiting pin 18 of a control limiter 6 is inserted into a limiting hole in the upper part of a cylinder body and the telescopic rod of the actuator cylinder 5, the telescopic stroke of the actuator cylinder in a working state is locked through the limiting pin 18, when the actuator cylinder is in the working state, a connecting bolt between a connecting disc 7 of the positioning component 4 and a circular disc 16 at the front end of the actuator cylinder is loosened, the connecting disc and the circular disc 16 at the front end of the actuator cylinder are in clearance connection only through rotating the positioning pin, a cantilever of the positioning component 4 is rotated, the cantilever of the positioning component 4 is enabled to avoid space interference of the wing leading edge rib 1, and a positioning surface 10 and a positioning hole, then the connecting disc 7 and the front end circular disc 16 of the telescopic rod of the actuating cylinder are pressed and fixed through the connecting bolt, after the assembly of the wing front edge rib 1 and the butt joint product 2 is completed, loosening the butt joint relation between a positioning surface 10 and a positioning hole 11 of the positioning component and a reference surface and a reference hole of the wing leading edge rib 1, loosening a connecting bolt of a connecting disc 7 of the positioning component and a circular disc 16 at the front end of the actuating cylinder, rotating a cantilever of the positioning component 4 to enable the cantilever to avoid the space interference of the wing leading edge rib 1, retracting a limiting pin 18 of a limiting stopper 6, releasing the locking state of the limiting pin 18 on the actuating cylinder 5, reversely driving the actuating cylinder 5, enabling a telescopic rod of the actuating cylinder 5 to drive the positioning component 4 to be far away from the wing leading edge rib 1, and when the actuating cylinder is in a non-working state, and a limiting pin 18 of the control limiter 6 is inserted into a barrel body of the actuating cylinder 5 and a limiting hole 15 at the lower part of the telescopic rod, and the telescopic stroke of the actuating cylinder in a non-working state is locked through the limiting pin 18.
Claims (4)
1. The positioning structure of the wing leading edge rib is connected to an assembling tool of the wing leading edge rib, and is characterized in that the positioning structure comprises a positioning component, an actuating cylinder and a limiter, a body of the positioning component is of a cantilever structure, one end of a cantilever is provided with a connecting disc, the connecting disc is connected with the front end of a telescopic rod of the actuating cylinder, the other end of the cantilever is provided with a positioning surface and a positioning hole matched with the wing leading edge rib, the cylinder end of the actuating cylinder is connected to the assembling tool structure, and the telescopic stroke of the actuating cylinder is limited by the limiter.
2. The wing leading edge rib positioning structure of claim 1, wherein the connecting plate is provided with a central through hole and a plurality of connecting holes, the center of the front end of the telescopic rod of the actuator cylinder is provided with a rotation positioning pin, the rotation positioning pin of the telescopic rod of the actuator cylinder is in clearance fit with the central through hole of the connecting plate, so that the cantilever structure can rotate relative to the front end of the telescopic rod of the actuator cylinder, and the connecting bolt can press and fix the connecting plate and the front end of the telescopic rod of the actuator cylinder through the connecting holes.
3. The wing leading edge rib positioning structure of claim 1, wherein the limiter is fixed to the assembly fixture structure, the limiter comprises a limiting sleeve and a limiting pin, the limiting sleeve is sleeved on the cylinder body of the actuator cylinder to limit the axial direction of the actuator cylinder, the limiting pin is of a telescopic pin structure, the telescopic direction of the limiting pin is perpendicular to the axial direction of the actuator cylinder, limiting holes matched with the limiting pin are formed in the cylinder body of the actuator cylinder and the telescopic rod, and the limiting pin limits the telescopic stroke of the actuator cylinder.
4. A method of positioning a leading edge rib of a wing, comprising: 1) the positioning structure of the leading edge rib of the wing as claimed in claim 1, 2 or 3 is used, 2) the leading edge rib of the wing is pre-installed on a butted product, 3) the actuator cylinder is driven, the telescopic rod of the actuator cylinder drives the positioning component to approach the leading edge rib of the wing, the limiting pin of the limiter is inserted into the limiting holes on the cylinder body of the actuator cylinder and the telescopic rod, the telescopic stroke of the actuator cylinder is locked through the limiting pin, 4) the connecting bolt of the connecting disc of the positioning component and the actuator cylinder is loosened, the cantilever of the positioning component is rotated, the cantilever avoids the spatial interference of the leading edge rib of the wing, the positioning surface and the positioning hole at the other end of the positioning component are butted and positioned with the reference surface and the reference hole of the leading edge rib of the wing, the connecting disc and the front end of the telescopic rod of the actuator cylinder are pressed and fixed through the connecting bolt, 5) after the leading edge rib of the wing and the product are assembled, the positioning surface and the positioning, and then loosening a connecting bolt of a connecting disc of the positioning assembly and the actuator cylinder, rotating a cantilever of the positioning assembly to enable the cantilever to avoid the spatial interference of the front edge rib of the wing, and 6) driving the actuator cylinder to enable a telescopic rod of the actuator cylinder to drive the positioning assembly to be far away from the front edge rib of the wing, and then locking the state of the actuator cylinder through a limiting pin of a limiter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011473167.1A CN112605924A (en) | 2020-12-15 | 2020-12-15 | Positioning structure and positioning method of wing leading edge rib |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011473167.1A CN112605924A (en) | 2020-12-15 | 2020-12-15 | Positioning structure and positioning method of wing leading edge rib |
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| Publication Number | Publication Date |
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| CN112605924A true CN112605924A (en) | 2021-04-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011473167.1A Pending CN112605924A (en) | 2020-12-15 | 2020-12-15 | Positioning structure and positioning method of wing leading edge rib |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114772429A (en) * | 2022-05-09 | 2022-07-22 | 常州市新创智能科技有限公司 | Web demolding and hoisting tool and demolding and hoisting method |
| CN115648105A (en) * | 2022-11-16 | 2023-01-31 | 中航沈飞民用飞机有限责任公司 | Assembly tool for vertical tail wing of airplane |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2554189A1 (en) * | 1996-03-22 | 1997-09-25 | The Boeing Company | Determinant wing assembly |
| CN201147919Y (en) * | 2007-11-29 | 2008-11-12 | 昌河飞机工业（集团）有限责任公司 | Flexible locater for assembling landing gear joint |
| CN202572193U (en) * | 2011-12-28 | 2012-12-05 | 西北工业大学 | External front flap positioner |
| CN202572212U (en) * | 2011-12-28 | 2012-12-05 | 西北工业大学 | Wing rib assembly positioning device |
| CN105619292A (en) * | 2015-11-23 | 2016-06-01 | 浙江吉利控股集团有限公司 | Vehicle door hinge positioning device |
| CN106976032A (en) * | 2017-04-27 | 2017-07-25 | 浙江大学 | A kind of assembly tooling system of large aircraft outer wing wing box |
| CN107628267A (en) * | 2017-07-31 | 2018-01-26 | 成都飞机工业（集团）有限责任公司 | A kind of deep camber airframe assembles double track locator unit |
| US20190100334A1 (en) * | 2017-10-04 | 2019-04-04 | Airbus Operations Limited | Aircraft assembly locating tool |
| CN110026926A (en) * | 2019-05-16 | 2019-07-19 | 沈阳飞机工业（集团）有限公司 | A kind of Movable telescopic positioning device for the assembly of tooling upper product |
| CN111532447A (en) * | 2020-05-15 | 2020-08-14 | 沈阳飞机工业（集团）有限公司 | Large-scale integral positioner |
-
2020
- 2020-12-15 CN CN202011473167.1A patent/CN112605924A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2554189A1 (en) * | 1996-03-22 | 1997-09-25 | The Boeing Company | Determinant wing assembly |
| CN201147919Y (en) * | 2007-11-29 | 2008-11-12 | 昌河飞机工业（集团）有限责任公司 | Flexible locater for assembling landing gear joint |
| CN202572193U (en) * | 2011-12-28 | 2012-12-05 | 西北工业大学 | External front flap positioner |
| CN202572212U (en) * | 2011-12-28 | 2012-12-05 | 西北工业大学 | Wing rib assembly positioning device |
| CN105619292A (en) * | 2015-11-23 | 2016-06-01 | 浙江吉利控股集团有限公司 | Vehicle door hinge positioning device |
| CN106976032A (en) * | 2017-04-27 | 2017-07-25 | 浙江大学 | A kind of assembly tooling system of large aircraft outer wing wing box |
| CN107628267A (en) * | 2017-07-31 | 2018-01-26 | 成都飞机工业（集团）有限责任公司 | A kind of deep camber airframe assembles double track locator unit |
| US20190100334A1 (en) * | 2017-10-04 | 2019-04-04 | Airbus Operations Limited | Aircraft assembly locating tool |
| CN110026926A (en) * | 2019-05-16 | 2019-07-19 | 沈阳飞机工业（集团）有限公司 | A kind of Movable telescopic positioning device for the assembly of tooling upper product |
| CN111532447A (en) * | 2020-05-15 | 2020-08-14 | 沈阳飞机工业（集团）有限公司 | Large-scale integral positioner |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114772429A (en) * | 2022-05-09 | 2022-07-22 | 常州市新创智能科技有限公司 | Web demolding and hoisting tool and demolding and hoisting method |
| CN115648105A (en) * | 2022-11-16 | 2023-01-31 | 中航沈飞民用飞机有限责任公司 | Assembly tool for vertical tail wing of airplane |
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