CN109264020A - Docking system above and below the big Component Intelligent of fuselage - Google Patents
Docking system above and below the big Component Intelligent of fuselage Download PDFInfo
- Publication number
- CN109264020A CN109264020A CN201811370637.4A CN201811370637A CN109264020A CN 109264020 A CN109264020 A CN 109264020A CN 201811370637 A CN201811370637 A CN 201811370637A CN 109264020 A CN109264020 A CN 109264020A
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- CN
- China
- Prior art keywords
- component
- locator
- fuselage
- locators
- big component
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- 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.)
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Classifications
-
- 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
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automatic Assembly (AREA)
Abstract
The invention discloses docking systems above and below the big Component Intelligent of fuselage, it is characterized by: system includes four upper-part locators and four lower component locators, X, Y, Z three-axis moving may be implemented in every locator, four groups of locator association linkages can form six degree of freedom posture adjustment, realize the positioning and support of big component.Compared with prior art, the beneficial effects of the present invention are: application of the invention will greatly improve merging precision and speed, Improving The Quality of Products stability reduces person works' intensity, is to promote output to improve must equipping for yield.
Description
Technical field
The invention belongs to aircraft manufacturing technical fields, and in particular to a kind of upper and lower docking system of the big Component Intelligent of fuselage.
Background technique
Traditional large component docks up and down mostly uses the more people of manual hand manipulation's mechanical lifting gear simultaneously operating simultaneously
Lifting part adjustment position is docked, and this mode docks low efficiency, and joint quality is unstable, and operation number is more, and labour is strong
Degree is high, and asynchronous operation such as occur will result in damage parts, therefore is highly desirable to research and develop a can be realized or more component
Component automatic butt system above and below the digitlization of automatic butt.
Summary of the invention
For above-mentioned the technical problems existing in the prior art, present invention technical solution used for the above purpose
It is:
Docking system, system include four upper-part locators and four lower component locators to the big Component Intelligent of fuselage up and down, often
X, Y, Z three-axis moving may be implemented in platform locator, and four groups of locator association linkages can form six degree of freedom posture adjustment, realize big component
Positioning and support.
Further, the upper-part locator and lower component locator are all made of laser tracker measurement land marking point
With by component identification point, import system is calculated component alternate position spike value, upper and lower component up and down automatically by software algorithm and adjusted respectively
Docking is completed after whole posture.
Further, be additionally provided with integrated control platform, four upper-part locators and four lower component locators with
The connection of integrated control platform.
Compared with prior art, the beneficial effects of the present invention are: application of the invention will greatly improve merging precision and speed
Degree, Improving The Quality of Products stability reduce person works' intensity, are to promote output to improve must equipping for yield.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of top locator of the present invention.
Fig. 2 is the structural schematic diagram of lower part locator of the present invention.
Fig. 3 is overall structure diagram of the invention.
Wherein: 1 top locator, 2 lower part locators, 3 integrated control platforms.
Specific embodiment
Below in conjunction with the embodiment of the present invention and attached drawing, technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
Docking system, system include four upper-part locators 1 and four lower component positioning to the big Component Intelligent of fuselage up and down
X, Y, Z three-axis moving may be implemented in device 2, every locator, and four groups of locator association linkages can form six degree of freedom posture adjustment, realize
The positioning and support of big component.Lower component is positioned and is supported by lower part locator 2 when upper and lower component docking, and upper-part is determined by top
The position positioning of device 1 and support.
Further, the upper-part locator and lower component locator are all made of laser tracker measurement land marking point
With by component identification point, import system is calculated component alternate position spike value, upper and lower component up and down automatically by software algorithm and adjusted respectively
Docking is completed after whole posture.
Further, be additionally provided with integrated control platform, four upper-part locators and four lower component locators with
Integrated control platform 3 connects, and upper and lower component locator is uniformly controlled by integrated control platform 3.
The course of work: coordinate system is established using laser tracker measurement ground TB point and theoretical value fitting first, is made later
The workpiece coordinate system for establishing component up and down respectively with the measurement point on laser tracker measurement lock ball point and component, after being measured
Component position and attitude difference up and down is calculated by system automatic Fitting, aligner carries out six-freedom motion, in drive
Lower component carries out position and attitude adjustment respectively, adjusts supreme lower component coordinate system and is completely coincident, and completes docking.
It although an embodiment of the present invention has been shown and described, for the ordinary skill in the art, can be with
A variety of variations, modification, replacement can be carried out to these embodiments without departing from the principles and spirit of the present invention by understanding
And modification, the scope of the present invention is defined by the appended.
Claims (3)
1. docking system above and below the big Component Intelligent of fuselage, it is characterised in that: system includes under four upper-part locators and four platforms
X, Y, Z three-axis moving may be implemented in positioning parts device, every locator, and four groups of locator association linkages can form six degree of freedom tune
Appearance realizes the positioning and support of big component.
2. docking system above and below the big Component Intelligent of fuselage as described in claim 1, it is characterised in that: the upper-part locator
Laser tracker measurement land marking point is all made of with by component identification point with lower component locator, and import system is calculated by software
Method calculates component alternate position spike value up and down automatically, and upper and lower component completes docking after adjusting separately posture.
3. docking system above and below the big Component Intelligent of fuselage as described in claim 1, it is characterised in that: be additionally provided with integrated control
Platform, four upper-part locators and four lower component locators are connect with integrated control platform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811370637.4A CN109264020A (en) | 2018-11-17 | 2018-11-17 | Docking system above and below the big Component Intelligent of fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811370637.4A CN109264020A (en) | 2018-11-17 | 2018-11-17 | Docking system above and below the big Component Intelligent of fuselage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109264020A true CN109264020A (en) | 2019-01-25 |
Family
ID=65189193
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811370637.4A Withdrawn CN109264020A (en) | 2018-11-17 | 2018-11-17 | Docking system above and below the big Component Intelligent of fuselage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109264020A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113247298A (en) * | 2021-06-30 | 2021-08-13 | 成都飞机工业（集团）有限责任公司 | Coordinate transformation method for multiple control localizer physical space arbitrary axis |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2318702C2 (en) * | 2006-01-25 | 2008-03-10 | Открытое акционерное общество "Комсомольское-на-Амуре авиационное производственное объединение имени Ю.А. Гагарина" | Method of mounting assembling devices for compartments and sets of aircraft |
| CN102249006A (en) * | 2011-05-11 | 2011-11-23 | 西安飞机工业（集团）有限责任公司 | Movement butt joint device for large body part of airplane general assembly |
| KR20160081314A (en) * | 2014-12-31 | 2016-07-08 | 한국항공우주산업 주식회사 | Fuselage Automatic Splice System for Rotor-Craft |
| CN106275501A (en) * | 2016-08-30 | 2017-01-04 | 深圳市劲拓自动化设备股份有限公司 | The control system of a kind of six degree of freedom posture adjustment platform and control method |
| CN108080910A (en) * | 2017-12-12 | 2018-05-29 | 大连四达高技术发展有限公司 | A kind of packaged type digitizes docking system |
-
2018
- 2018-11-17 CN CN201811370637.4A patent/CN109264020A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2318702C2 (en) * | 2006-01-25 | 2008-03-10 | Открытое акционерное общество "Комсомольское-на-Амуре авиационное производственное объединение имени Ю.А. Гагарина" | Method of mounting assembling devices for compartments and sets of aircraft |
| CN102249006A (en) * | 2011-05-11 | 2011-11-23 | 西安飞机工业（集团）有限责任公司 | Movement butt joint device for large body part of airplane general assembly |
| KR20160081314A (en) * | 2014-12-31 | 2016-07-08 | 한국항공우주산업 주식회사 | Fuselage Automatic Splice System for Rotor-Craft |
| CN106275501A (en) * | 2016-08-30 | 2017-01-04 | 深圳市劲拓自动化设备股份有限公司 | The control system of a kind of six degree of freedom posture adjustment platform and control method |
| CN108080910A (en) * | 2017-12-12 | 2018-05-29 | 大连四达高技术发展有限公司 | A kind of packaged type digitizes docking system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113247298A (en) * | 2021-06-30 | 2021-08-13 | 成都飞机工业（集团）有限责任公司 | Coordinate transformation method for multiple control localizer physical space arbitrary axis |
| CN113247298B (en) * | 2021-06-30 | 2021-11-19 | 成都飞机工业（集团）有限责任公司 | Coordinate transformation method for multiple control localizer physical space arbitrary axis |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190125 |
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| WW01 | Invention patent application withdrawn after publication |