CN114056595B - Numerical control locator stress release device and docking attitude adjustment system - Google Patents
Numerical control locator stress release device and docking attitude adjustment system Download PDFInfo
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- CN114056595B CN114056595B CN202010772552.XA CN202010772552A CN114056595B CN 114056595 B CN114056595 B CN 114056595B CN 202010772552 A CN202010772552 A CN 202010772552A CN 114056595 B CN114056595 B CN 114056595B
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- 238000003032 molecular docking Methods 0.000 title claims description 11
- 210000001503 joint Anatomy 0.000 abstract description 12
- 238000000034 method Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 7
- 230000009286 beneficial effect Effects 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000006872 improvement Effects 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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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
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- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Control Devices (AREA)
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Abstract
The invention discloses a stress release device of a numerical control positioner and a butt joint attitude adjustment system, wherein the stress release device of the numerical control positioner comprises: the positioning device comprises a supporting plate, a guide rail, a sliding block, an adapter plate and a positioning piece, wherein the guide rail is arranged on the supporting plate, the sliding block is in sliding connection with the guide rail, the adapter plate is connected with the sliding block, and the positioning piece is configured to be detachably connected with the supporting plate through the adapter plate or is configured to be detachably connected with the adapter plate through the supporting plate; when the positioning piece is connected with the supporting plate or the adapter plate, the sliding block is in a locking state, and the sliding block cannot slide on the guide rail; when the locating piece is not connected with the supporting plate or the adapter plate, the sliding block is in a release state, and the sliding block can slide on the guide rail. The stress release device and the butt joint gesture adjusting system of the numerical control locator have the advantages of being high in gesture adjusting and positioning precision, improving the overall assembly efficiency of the aircraft body and saving the assembly cost.
Description
Technical Field
The invention relates to the field of aircraft manufacturing, in particular to a stress release device of a numerical control positioner and a docking and posture adjustment system.
Background
Along with the rapid development of the domestic aviation industry, the numerical control positioner is widely applied to the butt joint and posture adjustment of large parts of an airplane. Generally, a plurality of numerical control positioners form a butt joint attitude adjusting system, and a traditional butt joint attitude adjusting system generally adopts a full-active spherical hinge fixed system, and the system can actively control the movement of all the numerical control positioners, so as to realize automatic position finding and aircraft part space positioning in the process of mounting aircraft parts on a frame. However, the system adopts full active positioning, is over-constraint positioning, and can generate certain reaction force in the gesture adjusting process to cause positioning tolerance and thermal expansion problem (taking a 10 m aluminum alloy wallboard component as an example, the temperature change is 10 ℃ for thermal expansion of the component by 3 mm), so that gesture adjusting positioning precision is influenced, and even large parts of the aircraft can be damaged by pulling, and the whole assembly cost and the assembly efficiency of the aircraft body are influenced.
Disclosure of Invention
The invention aims to provide a stress release device of a numerical control positioner and a butt joint attitude adjustment system, which can be used for over-restricting the attitude adjustment positioning accuracy of the positioning system, improving the overall assembly efficiency of an aircraft body and saving the assembly cost.
In order to achieve the purpose, on one hand, the invention adopts the following technical scheme:
a numerical control positioner stress relief device comprising: the positioning device comprises a supporting plate, a guide rail, a sliding block, an adapter plate and a positioning piece, wherein the guide rail is arranged on the supporting plate, the sliding block is in sliding connection with the guide rail, the adapter plate is connected with the sliding block, the positioning piece is configured to be detachably connected with the supporting plate through the adapter plate, or the positioning piece is configured to be detachably connected with the adapter plate through the supporting plate; the sliding block is in a locking state when the positioning piece is connected with the supporting plate or the adapter plate, and the sliding block cannot slide on the guide rail; when the locating piece is not connected with the supporting plate or the adapter plate, the sliding block is in a release state, and the sliding block can slide on the guide rail.
In one embodiment, the numerical control positioner stress relief device further comprises a force sensor, the force sensor being connected with the adapter plate.
In one embodiment, the stress relief device of the numerical control positioner further comprises a driving member, and the driving member is connected with the positioning member.
In one embodiment, the positioning member is a cylinder.
In one embodiment, the numerical control positioner stress relief device further comprises a controller, the controller being connected to the force sensor and the driving member, respectively.
In one embodiment, the supporting plate or the adapter plate is provided with a positioning part, and the positioning piece is detachably connected with the positioning part.
In one embodiment, the positioning portion is a positioning hole formed on the supporting plate or the adapter plate.
In one embodiment, the positioning portion is a positioning column arranged on the supporting plate or the adapter plate, and the positioning column is provided with an insertion hole.
In one embodiment, the positioning member is a latch.
On the other hand, the invention also provides a docking and attitude adjusting system, which comprises the numerical control locator stress releasing device.
The stress release device of the numerical control positioner is matched with a ball socket structure (connected with a large part of an airplane) and the numerical control positioner of the docking and posture adjustment system, and is connected with the numerical control positioner through a supporting plate when in use, and the adapter plate is connected with the ball socket structure. Taking the attitude adjustment positioning of the side wall plate of the machine body as an example, the installation direction of the stress release device of the numerical control positioner is the aircraft heading, when the side wall plate is positioned and adjusted, the positioning piece of the stress release device of the numerical control positioner is connected with the supporting plate, the sliding block is in a locking state, and the sliding block cannot slide on the guide rail; after the gesture adjustment of the side wall plate is finished, the positioning piece is adjusted, the positioning piece is not connected with the supporting plate, the sliding block is in a release state and slides on the guide rail, so that the course thermal expansion stress of the side wall plate of the airplane body along the setting direction of the guide rail can be released, the accurate gesture adjustment positioning of the large part of the airplane is realized, the assembly precision of the large part of the airplane can be improved, the pulling damage to the large part of the airplane can be avoided, the overall assembly efficiency of the airplane body is improved, and the assembly cost is saved. In addition, the stress release device of the numerical control positioner has the advantages of simple structure, low manufacturing cost and short manufacturing period, and is beneficial to further saving the whole assembly cost of the airplane body.
The butt joint gesture adjusting system has the beneficial effects of high gesture adjusting and positioning precision, improvement of the integral assembly efficiency of the aircraft body and assembly cost saving by applying the numerical control positioner stress release device, and can be widely applied to butt joint gesture adjustment of large parts of the aircraft body.
Drawings
FIG. 1 is a schematic view of a portion of a docking and posture adjustment system in one embodiment;
FIG. 2 is a schematic view of a portion of a docking and posture adjustment system in another embodiment;
FIG. 3 is a schematic diagram of a configuration of a numerical control positioner stress relief device in one embodiment;
FIG. 4 is a side view of a numerical control positioner stress relief device in one embodiment;
FIG. 5 is a schematic view of a structure of a slider of a stress relief device of a numerical positioner in a locked state according to another embodiment;
fig. 6 is a schematic structural view of a slider of the stress relief device of the numerical positioner in a released state according to another embodiment.
Reference numerals illustrate:
the device comprises a 10-numerical control positioner stress releasing device, a 11-supporting plate, a 111-positioning part, a 12-guide rail, a 13-sliding block, a 14-adapter plate, a 15-positioning piece, a 16-force sensor, a 17-driving piece, a 20-numerical control positioner and a 30-ball socket structure.
Detailed Description
The technical scheme of the invention is further described below by the specific embodiments with reference to the accompanying drawings.
In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
The invention provides a docking attitude adjustment system which is used for accurately adjusting and positioning the attitude of a large part of an airplane. Referring to fig. 1, a docking and posture adjustment system of an embodiment includes a numerical control positioner stress release device 10 and a numerical control positioner 20, where the numerical control positioner stress release device 10 is connected with the numerical control positioner 20. In this embodiment, the numerical control positioner 20 adopts a lateral numerical control positioner, and in another embodiment, as shown in fig. 2, the numerical control positioner 20 may also adopt a vertical numerical control positioner, which is not limited in particular.
As shown in fig. 3 and 4, the stress relief device 10 of the numerical control positioner according to an embodiment includes a pallet 11, a guide rail 12, a slider 13, an adapter plate 14, and a positioning member 15. The guide rail 12 is arranged on the supporting plate 11, the sliding block 13 is in sliding connection with the guide rail 12, the adapter plate 14 is connected with the sliding block 13, the positioning piece 15 is configured to be detachably connected with the supporting plate 11 through the adapter plate 14, the sliding block 13 is in a locking state when the positioning piece 15 is connected with the supporting plate 11, and the sliding block 13 cannot slide on the guide rail 12; when the positioning member 15 is not connected to the pallet 11, the slider 13 is in a released state, and the slider 1 can slide on the guide rail 12.
The stress release device of the numerical control positioner is matched with the ball socket structure 30 (connected with a large part of an airplane) and the numerical control positioner of the docking and posture adjustment system, and is connected with the numerical control positioner through the supporting plate 11 when in use, and the adapter plate is connected with the ball socket structure 30. Taking the attitude adjustment positioning of the side wall plate of the machine body as an example, the installation direction of the stress release device 10 of the numerical control positioner is the aircraft heading, when the side wall plate is positioned and adjusted, the positioning piece 15 of the stress release device 10 of the numerical control positioner is connected with the supporting plate 11, the sliding block 13 is in a locking state, and the sliding block 13 cannot slide on the guide rail 12; after the posture adjustment of the side wall plate is finished, the positioning piece 15 is adjusted, the positioning piece 15 is not connected with the supporting plate 11, the sliding block 13 is in a release state, the sliding block 13 slides on the guide rail 12, the course thermal expansion stress of the side wall plate of the airplane body along the setting direction of the guide rail 12 can be released, the accurate posture adjustment positioning of the large part of the airplane is realized, the assembly precision of the large part of the airplane can be improved, the large part of the airplane can be prevented from being pulled and damaged, the integral assembly efficiency of the airplane body is improved, and the assembly cost is saved. In addition, the numerical control positioner stress release device 10 has simple structure, low manufacturing cost and short manufacturing period, and is beneficial to further saving the whole assembly cost of the airplane body.
The butt joint attitude adjusting system has the beneficial effects of high attitude adjusting and positioning precision, improvement of the integral assembly efficiency of the aircraft body and assembly cost saving by applying the numerical control positioner stress release device 10, and can be widely applied to the butt joint attitude adjustment of large components of the aircraft body.
In one embodiment, the numerical control positioner stress relief device 10 further includes a force sensor 16, the force sensor 16 being coupled to the adapter plate 14. Specifically, when the numerical control positioner stress release device is used, the force sensor 16 is arranged between the adapter plate 14 and the ball socket structure 30 (as shown in fig. 1 and 2), the force sensor 16 is used for detecting thermal expansion stress of a large part (such as a side wall plate) of the aircraft in real time, the force sensor 16 has an alarm function that the stress exceeds a preset thermal expansion stress threshold, if the thermal expansion stress exceeds the preset thermal expansion stress threshold in the process of positioning and posture adjustment of the large part of the aircraft, the force sensor 16 sends alarm information to remind an operator to disconnect the positioning piece 15 from the supporting plate 11 in time, and the thermal expansion stress of the large part of the aircraft is released. The embodiment can release thermal expansion stress in time in the attitude adjustment process by arranging the force sensor 16, and is beneficial to further improving the attitude adjustment positioning accuracy of the large part of the airplane.
In one embodiment, the supporting plate 11 is provided with a positioning portion 111, and the positioning member 15 is detachably connected to the positioning portion 111. As shown in fig. 4, in this embodiment, the positioning portion 111 is a positioning column disposed on the supporting plate 11, a jack is formed on the positioning column, the positioning member 15 is connected with the positioning column in a plugging manner through the jack, and when the sliding block 13 needs to be locked, the positioning member 15 is inserted into the jack; when the slide block 13 is required to be released, the positioning piece 15 is pulled out of the jack, and the operation is simple and convenient. In another embodiment, the positioning portion may be a positioning hole formed on the supporting plate 11, and the positioning member 15 is directly connected with the supporting plate 11 in a plugging manner through the positioning hole. Further, in other embodiments, the positioning member 15 may directly abut against the supporting plate 11 to tightly lock the slider 13, which is not limited in the above embodiments. Still further, in one embodiment, the positioning member 15 may be, but is not limited to, a latch.
In the above embodiment, the positioning member 15 is configured to be detachably connected with the pallet 11 through the adapter plate 14. In another embodiment, as shown in fig. 5 and 6, the positioning member 15 may be further configured to detachably connect with the adapter plate 14 through the pallet 11. The sliding block 13 is in a locking state when the positioning piece 15 is connected with the adapter plate 14, and the sliding block 13 cannot slide on the guide rail 12; when the positioning piece 15 is not connected with the adapter plate 14, the sliding block 13 is in a release state, and the sliding block 13 can slide on the guide rail 12. Specifically, in this embodiment, the adapter plate 14 is provided with a positioning hole to form a positioning portion 111, and the positioning member 15 is connected with the adapter plate 14 in an inserting manner through the positioning hole. When the sliding block 13 needs to be locked, the positioning piece 15 is inserted into the positioning hole; when the slide 13 needs to be released, the positioning piece 15 is pulled out of the positioning hole. In other embodiments, the adapter plate 14 is provided with a positioning column forming positioning part 111, the positioning column is provided with a jack, the positioning piece 15 is connected with the positioning column in a plugging manner through the jack, and when the sliding block 13 needs to be locked, the positioning piece 15 is inserted into the jack; when it is desired to release the slider 13, the positioning member 15 is pulled out of the insertion hole. Of course, in other embodiments, the positioning member 15 may directly abut against the adapter plate 14 to tightly lock the slider 13. The numerical control positioner stress release device 10 of the present embodiment is different from the numerical control positioner stress release device 10 of the foregoing embodiment only in that the positioning member 15 passes through the supporting plate 11 and is detachably connected with the adapter plate 14 to lock or release the sliding block 13, and other structures and components are the same, and are not described herein.
Further, in one embodiment, the stress relief device of the numerical control positioner further comprises a driving member 17, and the driving member 17 is connected with the positioning member 15. Specifically, the positioning member 15 may be, but is not limited to, a cylinder. The driving piece 17 is arranged on the supporting plate 11, the driving piece 17 is used for providing driving force for the positioning piece 15 so that the positioning piece 15 can be inserted into the positioning hole or pulled out of the positioning hole, when the sliding block 13 is in a locking state, the air cylinder is ejected, and the positioning piece 15 is inserted into the positioning hole; when the slide block 13 needs to be switched to the release state, the cylinder is retracted, the positioning piece 15 is pulled out of the positioning hole, and the slide block 13 is released. Generally, the operation height of the numerical control positioner is higher, the manual plugging and unplugging of the positioning piece 15 is inconvenient and has potential safety hazards, in this embodiment, the cylinder is adopted to drive the positioning piece 15 to be plugged and unplugged automatically, so that the working efficiency and the safety of the stress release device 10 of the numerical control positioner can be improved. Further, as shown in fig. 5 and 6, in the present embodiment, the driving member 17 is disposed on the supporting plate 11, and when the positioning member 15 is configured to be detachably connected to the supporting plate 11 through the adapter plate 14, the driving member 17 is disposed on the adapter plate 14 correspondingly.
In one embodiment, the numerical control positioner stress relief 10 further includes a controller (not shown) coupled to the force sensor 16 and the driver 17, respectively. The controller is used for controlling the working state of the driving piece 17 and controlling the working state of the driving piece 17 in real time according to the detection result of the force sensor 16. Specifically, in this embodiment, when the large part of the aircraft is positioned and adjusted, the controller controls the air cylinder to extend, and the air cylinder drives the positioning piece 15 to be inserted into the positioning hole so that the sliding block 13 is in a locking state; after the gesture adjustment is finished, the controller controls the air cylinder to retract, the air cylinder drives the positioning piece 15 to move, the positioning piece 15 is pulled out of the positioning hole, the sliding block 13 is in a release state, the sliding block 13 slides on the guide rail 12, and the heading thermal expansion stress of the side wall plate of the machine body along the setting direction of the guide rail 12 can be released. Further, in the posture adjustment process, the force sensor 16 detects that the thermal expansion stress exceeds a preset thermal expansion stress threshold value and sends an alarm signal to the controller, the controller receives the alarm signal and then controls the cylinder to retract, the positioning piece 15 is pulled out of the positioning hole, the sliding block 13 is in a release state, after the thermal expansion stress release is completed, the controller controls the cylinder to extend out, the positioning piece 15 is inserted into the positioning hole to lock the sliding block 13, and the posture adjustment operation is continued. The numerical control locator stress release device 10 of the embodiment can realize automatic plug control of the locating piece 15, and can meet development requirements of automatic assembly and intelligent assembly of aircraft parts.
The numerical control positioner stress release device 10 can be matched with a full-active positioning system for use, is simple in structure and convenient to use, can select the locking slide block 13 or the release slide block 13 according to different use conditions (thermal expansion stress overrun during position and posture adjustment, after posture adjustment or in the posture adjustment process), can ensure the product precision requirement, can effectively consider the problems of process equipment cost and working efficiency, and can be widely applied to the butt joint and posture adjustment of large parts of an airplane body. The butt joint attitude adjusting system has the beneficial effects of high attitude adjusting and positioning precision, improving the overall assembly efficiency of the aircraft fuselage and saving the assembly cost by applying the numerical control positioner stress release device 10.
The technical features of the above-described embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above-described embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.
The above examples illustrate only a few embodiments of the invention, which are described in detail and are not to be construed as limiting the scope of the invention. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention. Accordingly, the scope of protection of the present invention is to be determined by the appended claims.
Claims (9)
1. A numerical control positioner stress relief device, comprising: a supporting plate (11), a guide rail (12), a sliding block (13), an adapter plate (14) and a positioning piece (15), wherein the guide rail (12) is arranged on the supporting plate (11), the sliding block (13) is in sliding connection with the guide rail (12), the adapter plate (14) is connected with the sliding block (13), the positioning piece (15) is configured to be detachably connected with the supporting plate (11) through the adapter plate (14), or the positioning piece (15) is configured to be detachably connected with the adapter plate (14) through the supporting plate (11); the sliding block (13) is in a locking state when the positioning piece (15) is connected with the supporting plate (11) or the adapter plate (14), and the sliding block (13) cannot slide on the guide rail (12); when the positioning piece (15) is not connected with the supporting plate (11) or the adapter plate (14), the sliding block (13) is in a release state, and the sliding block (13) can slide on the guide rail (12);
the numerical control locator stress release device further comprises a force sensor (16), and the force sensor (16) is connected with the adapter plate (14); the force sensor (16) is used for detecting thermal expansion stress of large parts of the aircraft in real time.
2. The numerical control positioner stress relief device according to claim 1, further comprising a driving member (17), the driving member (17) being connected with the positioning member (15).
3. The numerical control positioner stress relief device according to claim 2, wherein the positioner (15) is a cylinder.
4. A digitally controlled positioner stress relief device according to claim 3 characterised in that the digitally controlled positioner stress relief device further comprises a controller connected to the force sensor (16) and the drive member (17), respectively.
5. The numerical control positioner stress relief device according to any of claims 1 to 4, wherein a positioning portion (111) is provided on the pallet (11) or the adapter plate (14), and the positioning member (15) is detachably connected to the positioning portion (111).
6. The numerical control positioner stress relief device according to claim 5, wherein the positioning portion (111) is a positioning hole provided in the pallet (11) or the adapter plate (14).
7. The numerical control positioner stress relief device according to claim 5, wherein the positioning portion (111) is a positioning column provided on the supporting plate (11) or the adapter plate (14), and the positioning column is provided with a jack.
8. The numerical control positioner stress relief device according to any of claims 1 to 4 wherein the positioning member (15) is a pin.
9. Docking attitude adjustment system, characterized by comprising a numerical control positioner stress relief device (10) according to any of claims 1 to 8.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010772552.XA CN114056595B (en) | 2020-08-04 | 2020-08-04 | Numerical control locator stress release device and docking attitude adjustment system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010772552.XA CN114056595B (en) | 2020-08-04 | 2020-08-04 | Numerical control locator stress release device and docking attitude adjustment system |
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| CN114056595A CN114056595A (en) | 2022-02-18 |
| CN114056595B true CN114056595B (en) | 2024-01-23 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1063166A1 (en) * | 1999-06-26 | 2000-12-27 | EADS Airbus GmbH | Method and apparatus for the manufacture of a three-dimensional large sized structure |
| CN103274055A (en) * | 2013-06-14 | 2013-09-04 | 沈阳飞机工业（集团）有限公司 | Indoor-GPS-based (indoor global positioning system-based) stress-free assembly system for large-size airplane parts, and application thereof |
| CN206598071U (en) * | 2017-03-15 | 2017-10-31 | 成都飞机工业（集团）有限责任公司 | A kind of many intersection point assembling positioning units |
| CN107471171A (en) * | 2017-08-28 | 2017-12-15 | 浙江大学 | The posture adjustment alignment system and its numerical control posture adjustment positioner of large aircraft wing wallboard |
| CN108871253A (en) * | 2018-06-27 | 2018-11-23 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft intersection point connector rigging error and stress detection device and detection method |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102018210507A1 (en) * | 2018-06-27 | 2020-01-02 | Airbus Operations Gmbh | Assembly system for automated interior assembly of an aircraft fuselage |
| US11072439B2 (en) * | 2018-09-07 | 2021-07-27 | The Boeing Company | Mobile fixture apparatuses and methods |
-
2020
- 2020-08-04 CN CN202010772552.XA patent/CN114056595B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1063166A1 (en) * | 1999-06-26 | 2000-12-27 | EADS Airbus GmbH | Method and apparatus for the manufacture of a three-dimensional large sized structure |
| CN103274055A (en) * | 2013-06-14 | 2013-09-04 | 沈阳飞机工业（集团）有限公司 | Indoor-GPS-based (indoor global positioning system-based) stress-free assembly system for large-size airplane parts, and application thereof |
| CN206598071U (en) * | 2017-03-15 | 2017-10-31 | 成都飞机工业（集团）有限责任公司 | A kind of many intersection point assembling positioning units |
| CN107471171A (en) * | 2017-08-28 | 2017-12-15 | 浙江大学 | The posture adjustment alignment system and its numerical control posture adjustment positioner of large aircraft wing wallboard |
| CN108871253A (en) * | 2018-06-27 | 2018-11-23 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft intersection point connector rigging error and stress detection device and detection method |
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| CN114056595A (en) | 2022-02-18 |
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