CN110239741A - A kind of aircraft components assemble integrated tooling and its application method - Google Patents
A kind of aircraft components assemble integrated tooling and its application method Download PDFInfo
- Publication number
- CN110239741A CN110239741A CN201910479967.5A CN201910479967A CN110239741A CN 110239741 A CN110239741 A CN 110239741A CN 201910479967 A CN201910479967 A CN 201910479967A CN 110239741 A CN110239741 A CN 110239741A
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- product
- tooling
- aircraft components
- conformal
- connector
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/50—Handling or transporting aircraft components
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automatic Assembly (AREA)
- Connection Of Plates (AREA)
Abstract
This application discloses a kind of aircraft components to assemble integrated tooling and its application method, including conformal frame, conformal frame roof is equipped with the hanging ring structure matched with hanging, conformal base of frame, which is equipped with, can be equipped with the ball head structure cooperated with pose_adjuster along the connector of conformal frame movement in vertical direction, quadrangle with what product cooperated.Integrated tooling is lifted to the assembly erect-position of aircraft components product to be transported by hanging ring, and integrated tooling is positioned by the ball head structure in the cup-and-cone system and integrated tooling on assembly erect-position；Integrated tooling is connect by connector with product；It again by integrated tooling by product lifting transport to adjustment erect-position, and carries out being pre-positioned integrated tooling, while realizing that product is pre-positioned；By posture adjusting system, the spatial position of integrated tooling is adjusted, realizes the posture adjustment positioning of product.
Description
Technical field
This application involves aircraft mounting technology field, especially a kind of aircraft components assemble integrated tooling and its user
Method.
Background technique
In aircraft components assembling process, mostly use the process connection on product that hanging is cooperated to be lifted by crane and transported, portion
Part posture adjustment is also used to after the process connection progress four-point supporting on product, carries out posture adjustment to product by pose_adjuster, but right
The component product poor and more structural openings in integral rigidity, when carrying out allocation and transportation and posture adjustment using the above method, component product
It can generate severely deformed, in order to avoid the deformation of product, to increase conformal device at the poor structure of component product rigidity.Portion
There are various structures for part product, need different conformal devices to carry out it conformal, cause conformal device excessive and conformal process
It is complicated.Therefore need to design a kind of integrated form tooling, while meeting product lifting transport and posture adjustment function, component product is carried out
It is conformal.
Summary of the invention
To solve the above-mentioned problems, this application provides it is a kind of collect it is conformal, lifting, transport, posture adjustment be positioned at integrated work
Dress realizes the lifting transport of component after the assembly is completed in aircraft assembling process, and realizes product in next assembly using the frame
The posture adjustment of erect-position positions.
A kind of aircraft components assemble integrated tooling, including conformal frame, and conformal frame roof is equipped with to be matched with hanging
Hanging ring structure, conformal base of frame be equipped with product cooperate can be along the connector of conformal frame movement in vertical direction, quadrangle is equipped with
With the ball head structure of pose_adjuster cooperation.Wherein conformal frame is I-shaped symmetrical structure, and conformal framework upper is by crossbeam, tiltedly
The fenestral fabric that fine strain of millet and stringer are constituted, lower part are equipped with more vertical support columns.It is symmetrical that hanging ring structure is mounted on conformal frame
Axis two sides equidistant.Support post is equipped with rail structure.Connector is connected on rail structure, and can vertically be transported along sliding rail
It is dynamic.Connector bottom surface is the type face being bonded with product shape, and type face is equipped with consistent with hole site at the beginning of the fastener made on product
, and diameter is greater than the connection through-hole of first bore dia, and cooperates with solid bolt.Connector is by drilling pilot hole on solid bolt
It is connect with the appended claims on product.The process of pilot hole are as follows: solid bolt is installed to connector connection through-hole, connector edge is made
Sliding rail moves up and down until its type face is bonded with product, and lock-on connection and product pass through hole Xiang Shixin at the beginning of the fastener on product
Bolt pilot hole, then produced on solid bolt with first hole mounting hole of the same size, by the service bolt cooperated with first hole,
Connector and aircraft product are linked together.
The application method of integrated tooling, includes the following steps:
1 is lifted to integrated tooling with hanging by the hanging ring on conformal frame the assembly of aircraft components product to be transported
Erect-position, and integrated tooling is positioned by the ball head structure in the cup-and-cone system and integrated tooling on assembly erect-position；
2 connect integrated tooling by connector with product；
Product is lifted by crane transport extremely adjustment erect-position by integrated tooling by 3, and is carried out in advance by adjusting the cup-and-cone system of erect-position
Integrated tooling is positioned, while realizing that product is pre-positioned；
4 by adjusting erect-position posture adjusting system, adjust the spatial position of integrated tooling, realize the posture adjustment positioning of product.
Present application addresses the rigid poor problems of product lifting, transport, posture adjustment in aircraft components assembling process, and will be more
Function is integrated in a tooling, and between tooling and product by replaceable solid service bolt drilling connect,
The accurate positioning for avoiding tooling simplifies the drilling type of attachment of tooling and product, has general applicability.
Using being described in further detail with reference to the accompanying drawings and embodiments to the application.
Detailed description of the invention
Fig. 1 integrates tooling overall structure figure；
Fig. 2 joint structure；
Fig. 3 posture adjustment schematic diagram；
Explanation: 1, conformal frame is numbered in figure；2, hanging ring structure；3, connector；4, ball head structure；5, solid bolt；6, work
Skill bolt；7, product；8, cup-and-cone system；9, posture adjusting system, 10, rail structure
Specific embodiment
As shown in Figure 1-3, a kind of aircraft components assemble integrated tooling, including conformal frame 1, it is equipped at the top of conformal frame 1
The hanging ring structure 2 matched with hanging, conformal 1 bottom of frame are equipped with and can transport along conformal 1 vertical direction of frame with what product cooperated
Dynamic connector 3, quadrangle are equipped with the ball head structure 4 cooperated with pose_adjuster 9.Wherein conformal frame 1 is I-shaped symmetrical structure, is protected
1 top of shape frame is the fenestral fabric being made of crossbeam, oblique fine strain of millet and stringer, and lower part is equipped with more vertical support columns.Hanging ring
Structure 2 is mounted on conformal 1 axis of symmetry two sides equidistant of frame.Support post is equipped with rail structure 10.Connector 3 is connected to cunning
In rail structure 10, and it can move vertically along sliding rail.3 bottom surface of connector is the type face with 7 topographies of product, and type face is equipped with and production
Just hole site is consistent for the fastener made on product 7, and diameter is greater than the connection through-hole of first bore dia, and matches with solid bolt 5
It closes.Connector 3 is connect by drilling pilot hole on solid bolt 5 with the appended claims on product 7.The process of pilot hole are as follows: will be real
The installation of heart bolt 5 to connector 3 connects on through-hole, moves up and down connector 3 along sliding rail and is bonded up to its type face with product 7, locks
Connector 3 and product 7, by hole at the beginning of the fastener on product 7 to solid 5 pilot hole of bolt, then produced on solid bolt 5 with just
Hole mounting hole of the same size is linked together connector 3 and aircraft product 7 by the service bolt 6 cooperated with first hole.
The application method of integrated tooling, includes the following steps:
1 is lifted to integrated tooling aircraft components product to be transported with hanging by the hanging ring structure 2 on conformal frame 1
7 assembly erect-position, and integrated tooling is positioned by the ball head structure 4 in the cup-and-cone system 8 and integrated tooling on assembly erect-position；
2 connect integrated tooling by connector 3 with product 7；
The lifting transport of product 7 is extremely adjusted erect-position by integrated tooling by 3, and by adjusting the progress of the cup-and-cone system 8 of erect-position
It is pre-positioned integrated tooling, while realizing that product 7 is pre-positioned；
4 by adjusting erect-position posture adjusting system 9, adjust the spatial position of integrated tooling, realize the posture adjustment positioning of product 7.
Claims (9)
1. a kind of aircraft components assemble integrated tooling, including conformal frame, it is characterised in that the conformal frame roof be equipped with
Hang the hanging ring structure that matches, conformal base of frame be equipped with product cooperate can connecing along conformal frame movement in vertical direction
Head, quadrangle are equipped with the ball head structure cooperated with pose_adjuster.
2. a kind of aircraft components according to claim 1 integrate tooling, it is characterised in that the conformal frame is I-shaped
Type symmetrical structure, conformal framework upper are the fenestral fabric being made of crossbeam, oblique fine strain of millet and stringer, and lower part is equipped with more vertical branch
Support column.
3. a kind of aircraft components according to claim 2 integrate tooling, it is characterised in that the support post is equipped with
Rail structure.
4. a kind of aircraft components according to claim 1 integrate tooling, it is characterised in that the hanging ring structure is mounted on
Conformal frame axis of symmetry two sides equidistant.
5. a kind of aircraft components according to claim 1 integrate tooling, it is characterised in that the connector is connected to sliding rail
In structure, and it can move vertically along sliding rail.
6. a kind of aircraft components according to claim 5 integrate tooling, it is characterised in that the connector bottom surface is and production
The type face of product topographies, it is consistent that type face is equipped with hole site at the beginning of with the fastener made on product, and diameter is greater than first hole
The connection through-hole of diameter, and cooperate with solid bolt.
7. a kind of aircraft components according to claim 5 integrate tooling, it is characterised in that the connector passes through solid
Pilot hole is drilled on bolt to connect with the appended claims on product.
8. a kind of aircraft components according to claim 5 integrate tooling, it is characterised in that the process for drilling pilot hole
Are as follows: solid bolt is installed to connector connection through-hole, connector is moved up and down along sliding rail and is bonded up to its type face with product, locked
Then tight coupling and product are produced and first hole by hole at the beginning of the fastener on product to solid bolt pilot hole on solid bolt
Mounting hole of the same size is linked together connector and aircraft product by the service bolt cooperated with first hole.
9. the application method that a kind of aircraft components integrate tooling, it is characterised in that include the following steps:
Integrated tooling is lifted to the assembly of aircraft components product to be transported by the hanging ring on conformal frame by 9-1 with hanging
Erect-position, and integrated tooling is positioned by the ball head structure in the cup-and-cone system and integrated tooling on assembly erect-position；
Integrated tooling is connect by connector with product by 9-2；
Product lifting transport is extremely adjusted erect-position by integrated tooling by 9-3, and is made a reservation for by adjusting the cup-and-cone system of erect-position
The integrated tooling in position, while realizing that product is pre-positioned；
9-4 adjusts the spatial position of integrated tooling by adjusting the posture adjusting system of erect-position, realizes the posture adjustment positioning of product.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910479967.5A CN110239741A (en) | 2019-06-03 | 2019-06-03 | A kind of aircraft components assemble integrated tooling and its application method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910479967.5A CN110239741A (en) | 2019-06-03 | 2019-06-03 | A kind of aircraft components assemble integrated tooling and its application method |
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| CN110239741A true CN110239741A (en) | 2019-09-17 |
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| CN201910479967.5A Pending CN110239741A (en) | 2019-06-03 | 2019-06-03 | A kind of aircraft components assemble integrated tooling and its application method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113173256A (en) * | 2021-05-11 | 2021-07-27 | 上海交通大学 | Ultra-large type tensioning integral keel structure integration tool and method thereof |
| CN113734459A (en) * | 2021-05-19 | 2021-12-03 | 中航西安飞机工业集团股份有限公司 | Attitude adjusting and positioning method for wall plate on lower surface of airplane body |
| EP4177171A1 (en) * | 2021-11-03 | 2023-05-10 | The Boeing Company | Method and system for transporting a workpiece in a manufacturing environment |
| EP4177170A1 (en) * | 2021-11-03 | 2023-05-10 | The Boeing Company | Systems and methods for supporting a workpiece in a manufacturing environment |
| NL2029839B1 (en) * | 2021-11-19 | 2023-06-13 | Boeing Co | Method and system for transporting a workpiece in a manufacturing environment |
| NL2029840B1 (en) * | 2021-11-19 | 2023-06-13 | Boeing Co | Systems and methods for supporting a workpiece in a manufacturing environment |
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| DE102008062026A1 (en) * | 2008-12-12 | 2010-06-17 | Dürr Systems GmbH | Assembly device for structural assembly i.e. lining or wing assembly, of airplane, has positioning units including joints indirectly connected with sections of main part, where one of sections is connected with rail through one of joints |
| CN102730199A (en) * | 2012-07-05 | 2012-10-17 | 浙江大学 | Large-opening shape-preserving device used for large-scale airplane assembly |
| CN204197308U (en) * | 2014-06-13 | 2015-03-11 | 沈阳飞机工业（集团）有限公司 | A kind of flexible apparatus to the assembling of aircraft housing |
| CN105729420A (en) * | 2016-04-01 | 2016-07-06 | 中航飞机股份有限公司西安飞机分公司 | Movable supporting and locating method and device for aircraft component assembly |
| CN108372935A (en) * | 2016-12-21 | 2018-08-07 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of the posture adjustment docking system and method for a wide range of movement and self-navigation |
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2019
- 2019-06-03 CN CN201910479967.5A patent/CN110239741A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008062026A1 (en) * | 2008-12-12 | 2010-06-17 | Dürr Systems GmbH | Assembly device for structural assembly i.e. lining or wing assembly, of airplane, has positioning units including joints indirectly connected with sections of main part, where one of sections is connected with rail through one of joints |
| CN102730199A (en) * | 2012-07-05 | 2012-10-17 | 浙江大学 | Large-opening shape-preserving device used for large-scale airplane assembly |
| CN204197308U (en) * | 2014-06-13 | 2015-03-11 | 沈阳飞机工业（集团）有限公司 | A kind of flexible apparatus to the assembling of aircraft housing |
| CN105729420A (en) * | 2016-04-01 | 2016-07-06 | 中航飞机股份有限公司西安飞机分公司 | Movable supporting and locating method and device for aircraft component assembly |
| CN108372935A (en) * | 2016-12-21 | 2018-08-07 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of the posture adjustment docking system and method for a wide range of movement and self-navigation |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113173256A (en) * | 2021-05-11 | 2021-07-27 | 上海交通大学 | Ultra-large type tensioning integral keel structure integration tool and method thereof |
| CN113734459A (en) * | 2021-05-19 | 2021-12-03 | 中航西安飞机工业集团股份有限公司 | Attitude adjusting and positioning method for wall plate on lower surface of airplane body |
| EP4177171A1 (en) * | 2021-11-03 | 2023-05-10 | The Boeing Company | Method and system for transporting a workpiece in a manufacturing environment |
| EP4177170A1 (en) * | 2021-11-03 | 2023-05-10 | The Boeing Company | Systems and methods for supporting a workpiece in a manufacturing environment |
| NL2029839B1 (en) * | 2021-11-19 | 2023-06-13 | Boeing Co | Method and system for transporting a workpiece in a manufacturing environment |
| NL2029840B1 (en) * | 2021-11-19 | 2023-06-13 | Boeing Co | Systems and methods for supporting a workpiece in a manufacturing environment |
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Application publication date: 20190917 |
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