CN205465165U - Aircraft component locator that connects in parallel - Google Patents
Aircraft component locator that connects in parallel Download PDFInfo
- Publication number
- CN205465165U CN205465165U CN201620257606.8U CN201620257606U CN205465165U CN 205465165 U CN205465165 U CN 205465165U CN 201620257606 U CN201620257606 U CN 201620257606U CN 205465165 U CN205465165 U CN 205465165U
- Authority
- CN
- China
- Prior art keywords
- connects
- hook hinge
- platform
- localizer
- hooke hinge
- Prior art date
- 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.)
- Expired - Fee Related
Links
- 210000004907 gland Anatomy 0.000 claims abstract description 9
- 238000000034 method Methods 0.000 claims description 5
- 229910003460 diamond Inorganic materials 0.000 claims description 4
- 239000010432 diamond Substances 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 241000282376 Panthera tigris Species 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000005553 drilling Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
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- Automatic Assembly (AREA)
Abstract
The utility model discloses an aircraft component locator that connects in parallel, its structure is including moving platform (1), move 6 platform (1) sub -unit connections globe joint seat (2), 1 ball vice gland (3) are connected in every globe joint seat (2), removal countershaft (4) is connected in ball vice gland (3), remove countershaft (4) and connect the bloated tight cover of hydraulic pressure (6), hydraulic pressure expands and tightly overlaps (6) connecting bushing (5), hooke hinge owner's pivot (11) is connected through hooke hinge time pivot (10) in axle sleeve (5), hooke hinge cross axle bed (8) is connected in hooke hinge owner pivot (11), hooke hinge seat (12) is connected to hooke hinge cross axle bed (8), hooke hinge seat (12) connection allocates platform (13). The utility model discloses an advantage: realize accurate positioning and multi freedom position, the posture adjustment of various parts. The frock cost is reduced and to the requirement of frock precision, improve assembly efficiency and assembly quality, realize the automation of aircraft spare part and high accuracy and assemble.
Description
Technical field
The utility model relates to aircraft components parallel connection localizer.
Background technology
During aircraft manufacturing, it is total that the assembling of parts and the amount of labour of installment work account for aircraft manufacturing
The 50%～60% of the amount of labour.During assembling, use flexible location technology, be suitable for a certain degree of part
Structure changes, and can reduce in the mode of conventional rigid location inevitably positioning stress simultaneously.
At present, during aircraft manufacturing, employing with fixing tool type frame, hand assembled is mostly
Main method, significantly limit the reduction of frock cost and the raising of efficiency of assembling.Tradition side
Formula pose adjusts function singleness, positions rapport complexity between inaccurate, parts and frock.It is suitable
Answering the long-life, high stealthy demand, current aircraft many employings complex profile, special-shaped framework etc. are multiple
Miscellaneous structure, this be accomplished by assembly tooling design and manufacture in adapt to greatest extent complex-curved
Location requirement.
Utility model content
The utility model proposes aircraft components parallel connection localizer, its purpose is intended to overcome existing skill
Art above shortcomings, it is achieved in parallel localizer angle is adjusted flexibly, adapts to complex-curved determining
Position demand.
Technical solution of the present utility model: aircraft components parallel connection localizer, its structure includes moving
Platform, moving platform bottom connects 6 spherical joint seats, and each spherical joint seat connects 1 ball pair gland,
Ball pair gland connects mobile countershaft, and mobile countershaft connects hydraulic expanding sleeve locking, hydraulic expanding sleeve locking connecting shaft
Set, axle sleeve connects hook hinge main shaft by hook hinge secondary shaft, and hook hinge main shaft is even
Connecing hook hinge cross axial base, hook hinge cross axial base connects hook hinge seat, hook hinge seat
Connect fixed platform.
Preferably, described moving platform and fixed platform are all hexagon.
Preferably, described moving platform top sets process connection.
Preferably, described fixed platform connects hook hinge by cylindrical positioning pins and diamond positioning pin
Seat.
Preferably, described axle sleeve sets pushing pad sheet at hook hinge main shaft.
Preferably, described hook hinge main shaft sets adjustment pad.
Advantage of the present utility model: can realize various parts be accurately positioned with multiple degrees of freedom position,
Pose adjustment.Under the auxiliary of the external measurement devices such as laser tracker, locating platform can be accurate
Move to target location.Frock cost and the requirement to frock precision can be greatly reduced；Can be with
Automatic punching system combines, it is achieved rudder face base part pose adjusts and the coordinated manipulation of drilling, can be
Limits ground plays respective advantage, and then is greatly improved efficiency of assembling and assembling quality, it is achieved fly
The automatization of the parts such as machine wallboard, beam, rib, stringer assembly and high accuracy assembling.
Accompanying drawing explanation
Fig. 1 is the structural representation of aircraft components parallel connection localizer.
Fig. 2 is the upward view of Fig. 1.
In figure 1 be moving platform, 2 be spherical joint seat, 3 be ball pair gland, 4 be mobile countershaft, 5
It is axle sleeve, 6 is hydraulic expanding sleeve locking, 7 is upper pushing pad sheet, 8 is hook hinge cross axial base, 9 is
Adjust pad, 10 be hook hinge secondary shaft, 11 be hook hinge main shaft, 12 be hook hinge
Seat, 13 be fixed platform, 14 be cylindrical positioning pins, 15 be diamond positioning pin, 16 be process connection.
Detailed description of the invention
Below in conjunction with embodiment and detailed description of the invention, this utility model made further details of theory
Bright.
As shown in Figure 1, 2, aircraft components parallel connection localizer, its structure includes moving platform 1, dynamic flat
Platform 1 bottom connects 6 spherical joint seats 2, and each spherical joint seat 2 connects 1 ball pair gland 3, ball
Secondary gland 3 connects mobile countershaft 4, and mobile countershaft 4 connects hydraulic expanding sleeve locking 6, hydraulic expanding sleeve locking 6
Connecting bushing 5, axle sleeve 5 connects hook hinge main shaft 11 by hook hinge secondary shaft 10, tiger
Gram hinge main shaft 11 connects hook hinge cross axial base 8, and hook hinge cross axial base 8 connects tiger
Gram hinge seat 12, hook hinge seat 12 connects fixed platform 13.
Described moving platform 1 and fixed platform 13 are all hexagon.
Described moving platform 1 top sets process connection 16.
Described fixed platform 13 connects hook hinge by cylindrical positioning pins 14 and diamond positioning pin 15
Seat 12.
At hook hinge main shaft 11, pushing pad sheet 7 is set on described axle sleeve 5.
Adjustment pad 9 is set on described hook hinge main shaft 11.
Above-described is only preferred implementation of the present utility model, it is noted that for ability
For the those of ordinary skill in territory, on the premise of creating design without departing from this utility model, also may be used
To make some deformation and improvement, these broadly fall into protection domain of the present utility model.
Claims (6)
1. aircraft components parallel connection localizer, its feature includes moving platform (1), under moving platform (1)
Portion connects 6 spherical joint seats (2), and each spherical joint seat (2) connects 1 ball pair gland (3),
Ball pair gland (3) connects mobile countershaft (4), and mobile countershaft (4) connects hydraulic expanding sleeve locking (6),
Hydraulic expanding sleeve locking (6) connecting bushing (5), axle sleeve (5) passes through hook hinge secondary shaft (10)
Connecting hook hinge main shaft (11), hook hinge main shaft (11) connects hook hinge cross
Axle bed (8), hook hinge cross axial base (8) connects hook hinge seat (12), hook hinge
Seat (12) connects fixed platform (13).
2. aircraft components parallel connection localizer as claimed in claim 1, is characterized in that described moving is put down
Platform (1) and fixed platform (13) are all hexagon.
3. aircraft components parallel connection localizer as claimed in claim 1 or 2, is characterized in that described
Moving platform (1) top sets process connection (16).
4. aircraft components parallel connection localizer as claimed in claim 1, is characterized in that described allocating
Platform (13) connects hook hinge seat (12) by cylindrical positioning pins (14) and diamond positioning pin (15).
5. aircraft components parallel connection localizer as claimed in claim 1, is characterized in that described axle sleeve
(5) upper close hook hinge main shaft (11) place sets pushing pad sheet (7).
6. the aircraft components parallel connection localizer as described in claim 1 or 5, is characterized in that described
Adjustment pad (9) is set on hook hinge main shaft (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620257606.8U CN205465165U (en) | 2016-03-30 | 2016-03-30 | Aircraft component locator that connects in parallel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620257606.8U CN205465165U (en) | 2016-03-30 | 2016-03-30 | Aircraft component locator that connects in parallel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205465165U true CN205465165U (en) | 2016-08-17 |
Family
ID=56649162
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620257606.8U Expired - Fee Related CN205465165U (en) | 2016-03-30 | 2016-03-30 | Aircraft component locator that connects in parallel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205465165U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105666133A (en) * | 2016-03-30 | 2016-06-15 | 宜兴市融兴铸造有限公司 | Parallel-connection positioner for plane parts |
-
2016
- 2016-03-30 CN CN201620257606.8U patent/CN205465165U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105666133A (en) * | 2016-03-30 | 2016-06-15 | 宜兴市融兴铸造有限公司 | Parallel-connection positioner for plane parts |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Parallel positioner for aircraft components Effective date of registration: 20200921 Granted publication date: 20160817 Pledgee: Jiangsu Yixing rural commercial bank Limited by Share Ltd. Branch Park Branch Pledgor: YIXING RONGXING CASTING Co.,Ltd. Registration number: Y2020990001143 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20210825 Granted publication date: 20160817 Pledgee: Jiangsu Yixing rural commercial bank Limited by Share Ltd. Branch Park Branch Pledgor: YIXING RONGXING CASTING Co.,Ltd. Registration number: Y2020990001143 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220516 Address after: 100000 courtyard 1, Chaoyang Road, Chaoyang District, Beijing Patentee after: AVIC BEIJING AERONAUTICAL MANUFACTURING TECHNOLOGY Research Institute Address before: 214200 Yixing Rongxing Foundry Co., Ltd., No. 15, Huixing North Road, Zhuqiao Economic Development Zone, Yixing City, Wuxi City, Jiangsu Province Patentee before: YIXING RONGXING CASTING CO.,LTD. |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160817 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |