CN107985627B - Assembly parallel docking system for aircraft - Google Patents
Assembly parallel docking system for aircraft Download PDFInfo
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- CN107985627B CN107985627B CN201711331675.4A CN201711331675A CN107985627B CN 107985627 B CN107985627 B CN 107985627B CN 201711331675 A CN201711331675 A CN 201711331675A CN 107985627 B CN107985627 B CN 107985627B
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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
Abstract
The invention provides an assembly parallel docking system, which comprises a docking system base station, a parallel six-degree-of-freedom floating platform, a docking reference station and a trigger type detection system, wherein the docking system base station is connected with the docking system base station through a connecting device; the parallel six-degree-of-freedom floating platform, the docking reference platform and the trigger type detection system are all arranged on the docking system base station; the trigger type detection system adopts a three-coordinate type trigger mechanism, moves and touches any position point for detecting each product, and calculates the assembly base standard coordinate system of the product through the point position. The system is mainly used for automatic assembly of certain aviation products. Compared with the traditional process, the project not only realizes one-button type full-automatic assembly of a certain aviation product, but also improves the consistency of product assembly and improves the comprehensive assembly performance of the product.
Description
Technical Field
The invention belongs to the technical field of automatic assembly, and particularly relates to an assembly parallel butt joint system for an airplane.
Background
The aviation industry is the strategic production industry of national economy and national defense construction, the aircraft manufacturing has the characteristics of large structural size, complex and various part shapes, high pneumatic appearance and machining precision and the like, and a large number of assembly type frames are required to be used for ensuring the assembly quality. The final quality of the aircraft product depends to a large extent on the quality of the assembly, which is the most significant feature of aircraft manufacture in distinction from general machine manufacture. In the aircraft manufacturing process, assembly and installation work plays an extremely important role in aircraft manufacturing, and the labor amount of the assembly and installation work accounts for (50-60)% of the total labor amount of the whole aircraft manufacturing; and the mechanization and automation degree of the assembly and installation work is relatively low, the manual swimming specific gravity is large, and the productivity is low. Meanwhile, the aircraft assembly is a complex system project, the cooperation range is wide, and the management is difficult. In a word, the assembly and installation work of the airplane is large in labor amount, difficult to cooperate, high in quality requirement and large in technical difficulty, and is the most critical link in the airplane process. Therefore, the technical level of airplane assembly and installation is improved, the manufacturing method has very important effects on shortening the manufacturing period of products and improving the quality of the products, and has great significance in the airplane development and production process.
At present, the overall design and manufacturing level of the airplane assembly in China is backward, the airplane assembly still adopts manual operation or manual control, and the precision and the efficiency are lower. The low-efficiency traditional airplane assembly technology becomes a great obstacle for restricting the rapid development of airplanes in China, and becomes a problem to be solved urgently in the aviation manufacturing industry in China.
Disclosure of Invention
In order to overcome the technical problems, the purpose is to develop an automatic docking system integrating automatic detection and automatic docking, and the technical scheme adopted for realizing the purpose is as follows: the assembly parallel docking system for the airplane comprises a docking system base station, a parallel type six-degree-of-freedom floating platform, a docking reference station and a trigger type detection system; the parallel six-degree-of-freedom floating platform, the butt joint reference platform and the trigger type detection system are all arranged on a butt joint system base platform and move smoothly by adopting an air-floating guide rail; the trigger type detection system adopts a three-coordinate type trigger mechanism, moves and touches any position point for detecting each product, and calculates the assembly base standard coordinate system of the product through the point position.
Furthermore, the parallel type six-degree-of-freedom floating platform adopts a standard Stewart parallel type adjusting mechanism. The six-freedom-degree arbitrary position adjustment of the product can be realized, so that the automatic posture adjustment and automatic butt joint of the product are realized.
Respectively clamping products to be butted on the parallel six-degree-of-freedom floating platform and the butting reference platform; an operator selects an assembly mode through the control system; the trigger type detection system detects products on each platform according to programs, and the system calculates assembly references of the products according to the detected position information of each product; after detection is finished, the trigger type detection system returns to the initial position, and each parallel type six-freedom-degree floating platform carries a product to perform attitude adjustment, so that the assembly reference of each product is ensured to be on the same axis; feeding each parallel type six-freedom-degree floating platform to the position of the butt joint reference platform to complete the butt joint of the product; and after the butt joint is finished, taking down the product, and returning each parallel type six-freedom-degree floating platform to the initial position.
Compared with the prior art, the invention has the beneficial effects that: the assembly parallel connection butt joint system is high in integration, one-key automatic detection of the assembly reference of the product is realized, and the automatic posture adjustment and butt joint of the product are completed in one key; the detection precision is high, and the precision of each shaft can reach 5 mu m by adopting an air floating type guide rail; a standard stewart structure is adopted, so that the overall stability and positioning accuracy are effectively improved; the multi-axis parallel control is adopted, so that the accumulation and amplification of joint errors are reduced; and a plurality of sets of modes are arranged, so that the device is suitable for various products. The system is mainly used for automatic assembly of certain aviation products. Compared with the traditional process, the project not only realizes one-button type full-automatic assembly of a certain aviation product, but also improves the consistency of product assembly and improves the comprehensive assembly performance of the product.
Drawings
Fig. 1 is a schematic structural view of the present invention.
In the figure: the system comprises a butt joint system base station 1, a parallel type six-degree-of-freedom floating platform 2, a butt joint reference station 3 and a trigger type detection system 4.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, the present invention provides a technical solution: an assembly parallel docking system for an airplane comprises a docking system base station 1, a parallel six-degree-of-freedom floating platform 2, a docking reference station 3 and a trigger type detection system 4; the parallel six-degree-of-freedom floating platform 2, the butt joint reference platform 3 and the trigger type detection system 4 are all arranged on the butt joint system base platform 1 and move smoothly by adopting an air-floating guide rail; trigger formula detecting system 4 adopts three-dimensional formula trigger mechanism, removes and the arbitrary position point of touching each product of detection, calculates the dress base standard coordinate system of product through the point location.
Further, the parallel type six-degree-of-freedom floating platform 2 adopts a standard Stewart parallel type adjusting mechanism. The six-freedom-degree arbitrary position adjustment of the product can be realized, so that the automatic posture adjustment and automatic butt joint of the product are realized.
Respectively clamping products to be butted on the parallel six-degree-of-freedom floating platform 2 and the butting reference platform 3; an operator selects an assembly mode through the control system; the trigger type detection system 4 detects products on each platform according to programs, and the system calculates assembly reference of the products according to the detected position information of each product; after detection is finished, the trigger type detection system 4 returns to the initial position, and the parallel type six-degree-of-freedom floating platform 2 carries products to adjust the postures, so that the assembly references of the products are ensured to be on the same axis; feeding each parallel type six-degree-of-freedom floating platform 2 to the position of the butt-joint reference platform 3 to finish the butt joint of the product; after the butt joint is completed, the product is taken down, and each parallel type six-freedom-degree floating platform 2 returns to the initial position.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (2)
1. An assembled parallel docking system for an aircraft, characterized by: the assembly parallel docking system comprises a docking system base station, a parallel six-degree-of-freedom floating platform, a docking reference station and a trigger type detection system; the parallel six-degree-of-freedom floating platform, the butt joint reference platform and the trigger type detection system are all arranged on a butt joint system base platform and move smoothly by adopting an air-floating guide rail; the trigger type detection system adopts a three-coordinate type trigger mechanism, any position point of each product is moved and touched and detected, an assembly base quasi-coordinate system of the product is calculated through the point position, and the assembly butt joint method of the assembly parallel butt joint system for the airplane is as follows: respectively clamping products to be butted on the parallel six-degree-of-freedom floating platform and the butting reference platform; an operator selects an assembly mode through the control system; the trigger type detection system detects products on each platform according to a program, and the system calculates the assembly reference of the products according to the detected position information of each product; after detection is finished, the trigger type detection system returns to the initial position, and each parallel type six-freedom-degree floating platform carries a product to perform attitude adjustment, so that the assembly reference of each product is ensured to be on the same axis; feeding each parallel type six-freedom-degree floating platform to the position of the butt joint reference platform to complete the butt joint of the product; and after the butt joint is finished, taking down the product, and returning each parallel type six-freedom-degree floating platform to the initial position.
2. The set-up parallel docking system for an aircraft according to claim 1, wherein: the parallel type six-degree-of-freedom floating platform adopts a standard Stewart parallel type adjusting mechanism.
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| CN201711331675.4A CN107985627B (en) | 2017-12-13 | 2017-12-13 | Assembly parallel docking system for aircraft |
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| CN201711331675.4A CN107985627B (en) | 2017-12-13 | 2017-12-13 | Assembly parallel docking system for aircraft |
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| CN107985627A CN107985627A (en) | 2018-05-04 |
| CN107985627B true CN107985627B (en) | 2021-06-15 |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109318183B (en) * | 2018-11-22 | 2024-03-12 | 浙江虹湾通用航空工程技术有限公司 | CESSNA172 series aircraft repair frame |
| CN109318210B (en) * | 2018-11-26 | 2020-11-06 | 燕山大学 | Active and passive compliant attitude-adjusting docking platform with thirteen degrees of freedom and flexible docking method thereof |
| CN109909979B (en) * | 2019-04-16 | 2022-01-07 | 上海交通大学 | Ship propeller shaft hole flexible assembly parallel robot |
| CN110844117A (en) * | 2019-11-14 | 2020-02-28 | 沈阳航空航天大学 | Generalized butt joint test system based on multi-degree-of-freedom parallel mechanism |
| CN110877752A (en) * | 2019-12-05 | 2020-03-13 | 江西洪都航空工业集团有限责任公司 | Multifunctional butt-joint platform |
| CN111746819B (en) * | 2020-07-10 | 2022-02-15 | 中国航空制造技术研究院 | Automatic assembly equipment for helicopter hub |
| CN112570987B (en) * | 2020-10-27 | 2022-06-14 | 成都飞机工业（集团）有限责任公司 | Flexible posture-adjusting and involuting tool and assembling method thereof |
| CN112873103A (en) * | 2021-01-05 | 2021-06-01 | 航天科工空间工程发展有限公司 | Method and system for assembling satellite deck and satellite main body frame and adjusting device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105619049A (en) * | 2016-04-08 | 2016-06-01 | 哈尔滨工业大学 | Air-floating type flexible assembly butt-joint system |
| CN106862908A (en) * | 2017-04-01 | 2017-06-20 | 哈尔滨工业大学 | A kind of full-automatic assembling docking calculation based on air flotation technology |
| CN206567965U (en) * | 2017-02-28 | 2017-10-20 | 梅木精密工业(珠海)有限公司 | Digital-controlled internal lathe contact automatic contraposition device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US9682788B2 (en) * | 2014-09-17 | 2017-06-20 | The Boeing Company | Fuselage manufacturing system |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105619049A (en) * | 2016-04-08 | 2016-06-01 | 哈尔滨工业大学 | Air-floating type flexible assembly butt-joint system |
| CN206567965U (en) * | 2017-02-28 | 2017-10-20 | 梅木精密工业(珠海)有限公司 | Digital-controlled internal lathe contact automatic contraposition device |
| CN106862908A (en) * | 2017-04-01 | 2017-06-20 | 哈尔滨工业大学 | A kind of full-automatic assembling docking calculation based on air flotation technology |
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