CN105666133A - Parallel-connection positioner for plane parts - Google Patents
Parallel-connection positioner for plane parts Download PDFInfo
- Publication number
- CN105666133A CN105666133A CN201610193275.0A CN201610193275A CN105666133A CN 105666133 A CN105666133 A CN 105666133A CN 201610193275 A CN201610193275 A CN 201610193275A CN 105666133 A CN105666133 A CN 105666133A
- Authority
- CN
- China
- Prior art keywords
- hook hinge
- connects
- parallel
- steady arm
- aircraft components
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
Abstract
The invention relates to a parallel-connection positioner for plane parts. The parallel-connection positioner for plane parts structurally comprises a movable platform (1). The lower portion of the movable platform (1) is connected with six ball joint seats (2). Each ball joint seat (2) is connected with a ball auxiliary pressing cover (3). Each ball auxiliary pressing cover (3) is connected with a movable auxiliary shaft (4). Each movable auxiliary shaft (4) is connected with a hydraulic expansion sleeve (6). Each hydraulic expansion sleeve (6) is connected with a shaft sleeve (5). The shaft sleeves (5) are connected with hook hinge main rotary shafts (11) through hook hinge secondary rotary shafts (10). The hook hinge main rotary shafts (11) are connected with hook hinge universal joint seats (8). The hook hinge universal joint seats (8) are connected with hook hinge seats (12). The hook hinge seats (12) are connected with a fixed platform (13). The parallel-connection positioner for plane parts has the advantages that accurate positioning and adjustment of the position and posture at multiple degrees of freedom of various parts are realized; the tool cost is reduced, the requirements for tool accuracy are lowered, the assembling efficiency and assembling quality are improved, and automatic and high-accuracy assembling of plane parts are realized.
Description
Technical field
What the present invention relates to is aircraft components steady arm in parallel.
Background technology
In aircraft manufacturing process, the assembling of parts and the labor capacity of installation work account for the 50%～60% of the total labor capacity of aircraft manufacturing. During assembling, adopt flexible location technology, the change of part structure to a certain degree can be adapted to, location stress inevitable in conventional rigid locator means can be reduced simultaneously.
At present, in aircraft manufacturing process, mostly adopt based on the method for fixing tool type frame, manual setting, significantly limit the raising of the reduction of frock cost and efficiency of assembling. Traditional way pose adjusts function singleness, locates coordination relation complexity between inaccurate, parts and frock. For adapting to the long lifetime, high stealthy demand, the complex constructions such as current aircraft many employings complex profile, special-shaped framework, this just needs to adapt to complex-curved location requirement in the Design and manufacture of assembly tooling to greatest extent.
Summary of the invention
What the present invention proposed is aircraft components steady arm in parallel, and its object is intended to overcome prior art above shortcomings, it is achieved adjustment steady arm angle in parallel flexibly, adapts to complex-curved location requirement.
The technical solution of the present invention: aircraft components steady arm in parallel, its structure comprises moving platform, moving platform bottom connects 6 spherical joint seats, each spherical joint seat connects the secondary gland of 1 ball, the secondary gland of ball connects mobile countershaft, mobile countershaft connecting fluid pressure swelling cover, hydraulic expanding sleeve locking connects axle sleeve, axle sleeve connects hook hinge main shaft by hook hinge secondary shaft, hook hinge main shaft connects hook hinge cross axle bed, hook hinge cross axle bed connects hook hinge seat, and hook hinge seat connects fixed platform.
Preferably, described moving platform and fixed platform are all sexangle.
Preferably, process connection is established at described moving platform top.
Preferably, described fixed platform connects hook hinge seat by cylindrical positioning pins and diamond positioning pin.
Preferably, described axle sleeve establishes pushing pad sheet near hook hinge main shaft place.
Preferably, described hook hinge main shaft establishes adjustment pad.
The advantage of the present invention: accurate location and multiple degree of freedom position, the pose adjustment that various parts can be realized.The external measurement devices such as laser tracker auxiliary under, location platform can accurately move to target location. Can greatly reduce frock cost and the requirement to frock precision; Can combine with automatic punching system, realize the coordinated manipulation of the base part pose adjustment of rudder face and drilling, respective advantage can be played to greatest extent, and then greatly improve efficiency of assembling and assembly quality, it is achieved the automatization of the component such as aircraft wallboard, beam, rib, long purlin assembly and high precision assembling.
Accompanying drawing explanation
Fig. 1 is the structural representation of aircraft components steady arm in parallel.
Fig. 2 is the upward view of Fig. 1.
In figure 1 is moving platform, 2 to be spherical joint seat, 3 the be secondary gland, 4 of ball is mobile countershaft, 5 be axle sleeve, 6 be hydraulic expanding sleeve locking, 7 be upper pushing pad sheet, 8 be hook hinge cross axle bed, 9 be adjustment 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 is process connection.
Embodiment
Below in conjunction with embodiment and embodiment, the present invention is further detailed explanation.
As shown in Figure 1, 2, aircraft components steady arm in parallel, its structure comprises moving platform 1, moving platform 1 bottom connects 6 spherical joint seats 2, each spherical joint seat 2 connects the secondary gland 3 of 1 ball, the secondary gland 3 of ball connects mobile countershaft 4, mobile countershaft 4 connects hydraulic expanding sleeve locking 6, hydraulic expanding sleeve locking 6 connects axle sleeve 5, axle sleeve 5 connects hook hinge main shaft 11 by hook hinge secondary shaft 10, hook hinge main shaft 11 connects hook hinge cross axle bed 8, and hook hinge cross axle bed 8 connects hook hinge seat 12, and hook hinge seat 12 connects fixed platform 13.
Described moving platform 1 and fixed platform 13 are all sexangle.
Process connection 16 is established at described moving platform 1 top.
Described fixed platform 13 connects hook hinge seat 12 by cylindrical positioning pins 14 and diamond positioning pin 15.
Described axle sleeve 5 establishes pushing pad sheet 7 near hook hinge main shaft 11 place.
Described hook hinge main shaft 11 is established adjustment pad 9.
Above-described is only the preferred embodiment of the present invention, it should be noted that for the person of ordinary skill of the art, without departing from the concept of the premise of the invention, it is also possible to make some distortion and improvement, these all belong to protection scope of the present invention.
Claims (6)
1. aircraft components steady arm in parallel, its feature comprises moving platform (1), moving platform (1) bottom connects 6 spherical joint seats (2), each spherical joint seat (2) connects the secondary gland (3) of 1 ball, the secondary gland (3) of ball connects mobile countershaft (4), mobile countershaft (4) connects hydraulic expanding sleeve locking (6), hydraulic expanding sleeve locking (6) connects axle sleeve (5), axle sleeve (5) connects hook hinge main shaft (11) by hook hinge secondary shaft (10), hook hinge main shaft (11) connects hook hinge cross axle bed (8), hook hinge cross axle bed (8) connects hook hinge seat (12), hook hinge seat (12) connects fixed platform (13).
2. aircraft components as claimed in claim 1 steady arm in parallel, is characterized in that described moving platform (1) and fixed platform (13) are all sexangle.
3. aircraft components as claimed in claim 1 or 2 steady arm in parallel, is characterized in that process connection (16) is established at described moving platform (1) top.
4. aircraft components as claimed in claim 1 steady arm in parallel, is characterized in that described fixed platform (13) connects hook hinge seat (12) by cylindrical positioning pins (14) and diamond positioning pin (15).
5. aircraft components as claimed in claim 1 steady arm in parallel, is characterized in that described axle sleeve (5) is upper and establishes pushing pad sheet (7) near hook hinge main shaft (11) place.
6. aircraft components as described in claim 1 or 5 steady arm in parallel, is characterized in that establishing adjustment pad (9) on described hook hinge main shaft (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610193275.0A CN105666133A (en) | 2016-03-30 | 2016-03-30 | Parallel-connection positioner for plane parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610193275.0A CN105666133A (en) | 2016-03-30 | 2016-03-30 | Parallel-connection positioner for plane parts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105666133A true CN105666133A (en) | 2016-06-15 |
Family
ID=56225707
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610193275.0A Pending CN105666133A (en) | 2016-03-30 | 2016-03-30 | Parallel-connection positioner for plane parts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105666133A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107553468A (en) * | 2017-09-27 | 2018-01-09 | 西安电子科技大学 | A kind of restructural six-freedom parallel operating platform |
| CN108714065A (en) * | 2018-04-04 | 2018-10-30 | 邢志平 | A kind of bionical artificial limb machinery foot in parallel connection joint |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3288421A (en) * | 1965-03-29 | 1966-11-29 | Everett R Peterson | Movable and rotatable top |
| US3295224A (en) * | 1964-12-07 | 1967-01-03 | Franklin Institute | Motion simulator |
| JPH10124122A (en) * | 1996-10-07 | 1998-05-15 | Gec Alsthom Syst & Service Sa | Parallel structure-type robot |
| US20010000271A1 (en) * | 1996-03-11 | 2001-04-19 | Akeel Hadi A. | Programmable positioner for the stress-free assembly of components |
| CN102166751A (en) * | 2011-05-20 | 2011-08-31 | 汕头大学 | Branched chain-less and six-freedom degree parallel manipulator |
| CN202922582U (en) * | 2012-11-16 | 2013-05-08 | 中国航空工业集团公司北京航空制造工程研究所 | Parallel mechanism positioning platform used for aircraft assembly |
| CN205465165U (en) * | 2016-03-30 | 2016-08-17 | 宜兴市融兴铸造有限公司 | Aircraft component locator that connects in parallel |
-
2016
- 2016-03-30 CN CN201610193275.0A patent/CN105666133A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3295224A (en) * | 1964-12-07 | 1967-01-03 | Franklin Institute | Motion simulator |
| US3288421A (en) * | 1965-03-29 | 1966-11-29 | Everett R Peterson | Movable and rotatable top |
| US20010000271A1 (en) * | 1996-03-11 | 2001-04-19 | Akeel Hadi A. | Programmable positioner for the stress-free assembly of components |
| JPH10124122A (en) * | 1996-10-07 | 1998-05-15 | Gec Alsthom Syst & Service Sa | Parallel structure-type robot |
| CN102166751A (en) * | 2011-05-20 | 2011-08-31 | 汕头大学 | Branched chain-less and six-freedom degree parallel manipulator |
| CN202922582U (en) * | 2012-11-16 | 2013-05-08 | 中国航空工业集团公司北京航空制造工程研究所 | Parallel mechanism positioning platform used for aircraft assembly |
| CN205465165U (en) * | 2016-03-30 | 2016-08-17 | 宜兴市融兴铸造有限公司 | Aircraft component locator that connects in parallel |
Non-Patent Citations (2)
| Title |
|---|
| 凌武宝: "《可拆卸联接设计与应用》", 31 March 2006, 机械工业出版社 * |
| 张萌 等: "《液压与气压传动》", 31 August 2015, 华中科技大学出版社 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107553468A (en) * | 2017-09-27 | 2018-01-09 | 西安电子科技大学 | A kind of restructural six-freedom parallel operating platform |
| CN107553468B (en) * | 2017-09-27 | 2020-11-20 | 西安电子科技大学 | Reconfigurable six-degree-of-freedom parallel operation platform |
| CN108714065A (en) * | 2018-04-04 | 2018-10-30 | 邢志平 | A kind of bionical artificial limb machinery foot in parallel connection joint |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160615 |
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| WD01 | Invention patent application deemed withdrawn after publication |