CN109204874B - Digital final assembly system for airplane wings and application method thereof - Google Patents
Digital final assembly system for airplane wings and application method thereof Download PDFInfo
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- CN109204874B CN109204874B CN201711135624.4A CN201711135624A CN109204874B CN 109204874 B CN109204874 B CN 109204874B CN 201711135624 A CN201711135624 A CN 201711135624A CN 109204874 B CN109204874 B CN 109204874B
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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 a digital final assembly system for an airplane wing, which comprises a wing final assembly device, an integrated working platform, an integrated control device and a laser measuring device, wherein the integrated working platform is arranged on the wing final assembly device; the wing general assembly device, the integrated control device and the laser measuring device are all arranged on the integrated working platform; the wing general assembly device is used for positioning and assembling the wings of the airplane; the laser measuring device is used for measuring data of the wing general assembly device in the process of positioning and assembling the wings of the airplane; the integrated control device is used for calculating a posture adjusting path according to data measured by the laser measuring device, and then controlling the wing general assembly device to position and assemble the airplane wing through the posture adjusting path. The invention also provides a using method of the system. The invention adopts digital and automatic assembly, and improves the positioning precision.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a digital assembly system for airplane wings and a using method of the digital assembly system.
Background
At present, the wing assembly of domestic and domestic aircraft factories mainly adopts a fixed type frame and a clamping plate to position and support a front beam, a rear beam, an upper wall plate, a lower wall plate, a wing rib and the like of an aircraft wing, so as to ensure the overall appearance of the wing, and adopts the traditional tool positioning and manual assembly method. Since the 90 s of the 20 th century, aircraft manufacturers, such as boeing corporation and air passenger corporation, have adopted digitization and automation technologies to perform digitization and automation assembly of the entire aircraft wing, such as boeing 787 and a 400M.
The existing wing assembly adopts the traditional tool positioning and manual assembly method, and adopts a frame fixed on a foundation to support and position a front beam. The fixed shelf is provided with an upper wallboard and a lower wallboard of a turnover clamping plate positioning wing, the upper end of the lower wallboard turnover clamping plate is provided with a crossbeam structure which is lapped on the turnover clamping plate of the upper wallboard, a back beam of the positioning wing is provided with a fixed tool at the rib end of a wing tip, the wing tip rib is positioned in a bolt mode through a back hand rocking screw, the rib end plate of the wing root rib is positioned in place through the turnover tool at the rib end of the wing root, and the wing is lifted out of the shelf from the rib end of the wing root by utilizing the turnover tool.
The existing tool positioning and manual assembly method is not enough, and firstly, the turnover tool at the rib end of the wing root is unstable in positioning and needs to be periodically overhauled. And secondly, the back beam is positioned by utilizing the supporting beam on the turnover clamping plate, the back beam is not accurately positioned, and the clamping plate needs to be periodically overhauled. And thirdly, the whole assembly space is narrow, and in the process of lowering the wing, the wing product has the danger of collision with the fixed frame and the clamping plate.
Disclosure of Invention
In order to solve one of the technical problems, the invention provides a digital final assembly system for an airplane wing, which comprises a wing final assembly device, an integrated working platform, an integrated control device and a laser measuring device, wherein the integrated working platform is arranged on the wing final assembly device; the wing general assembly device, the integrated control device and the laser measuring device are all arranged on the integrated working platform;
the wing general assembly device is used for positioning and assembling the wings of the airplane;
the laser measuring device is used for measuring data of the wing general assembly device in the process of positioning and assembling the wings of the airplane;
the integrated control device is used for calculating a posture adjusting path according to data measured by the laser measuring device, and then controlling the wing general assembly device to position and assemble the airplane wing through the posture adjusting path.
Preferably, the wing general assembly device comprises a left wing general assembly device and a right wing general assembly device, and the left wing general assembly device and the right wing general assembly device are identical in structure and symmetrically and parallelly placed on the integrated working platform.
Preferably, the left wing general assembly device specifically includes: the front beam positioning device, the rear beam positioning device, the upper wall plate posture adjusting positioning device and the lower wall plate posture adjusting positioning device;
the front beam positioning device is used for supporting and positioning the wing front beam;
the back beam positioning device is used for supporting and positioning the wing back beam;
the upper wall plate posture adjusting and positioning device is used for positioning the upper wall plate of the wing to be attached to the front beam and the rear beam of the wing;
the lower wall plate posture adjusting and positioning device is used for positioning the lower wall plate of the wing to be attached to the front beam and the rear beam of the wing.
Preferably, the front beam positioning device comprises an upright column, a front beam cross beam and supporting positioning seats, the upright column is fixedly connected with the foundation through foundation bolts, the front beam cross beam is fixed at the top of the upright column through screws, a plurality of supporting positioning seats are arranged on the front beam cross beam side by side, and the supporting positioning seats are used for supporting and positioning the front beam of the wing.
Preferably, the back beam positioning device comprises a back beam cross beam, a back beam joint positioner, a wing root rib positioning device and a wing tip rib positioning device, the wing root rib positioning device and the wing tip rib positioning device are fixedly connected with the foundation through foundation bolts, the top of the wing root rib positioning device is connected with one end of the back beam cross beam, the top of the wing tip rib positioning device is connected with the other end of the back beam cross beam, the joints of the wing root rib positioning devices and the wing tip rib positioning devices and the back beam cross beam are provided with driving components, the driving assembly controls the back beam cross beam to do linear motion perpendicular to the length direction of the back beam cross beam on the wing root rib positioning device and the wing tip rib positioning device, a plurality of back beam joint positioners are arranged on the side wall of the back beam cross beam and used for connecting and positioning the back beam, and the external control unit controls the rear beam to do linear motion in the vertical direction on the side wall of the rear beam cross beam.
Preferably, the wing root rib positioning device comprises a first box base, a first left box upright, a first right box upright, a first longitudinal box assembly and a wing root rib positioning frame assembly;
a first left box body upright post and a first right box body upright post are arranged between the first box body base and the first longitudinal box body assembly, a gap is reserved between the first left box body upright post and the first right box body upright post, the wing root rib positioning frame assembly is arranged in the gap and used for positioning a wing root rib of a wing back beam, and horizontal sliding rails are arranged between the wing root rib positioning frame assembly and the first left box body upright post and the first right box body upright post; the wing root rib positioning frame assembly positions the wing root ribs through the forward and backward movement of the driving assembly.
One end of the back beam cross beam is arranged at the top of the first longitudinal box body assembly, and the back beam cross beam is driven by the driving assembly to move at the top of the first longitudinal box body assembly.
Preferably, the wing tip rib positioning device comprises a second box base, a second left box upright, a second right box upright, a second longitudinal box assembly and a wing tip rib positioning frame assembly;
second box base and second indulge and are provided with left box stand of second and the right box stand of second between the box subassembly, the left box stand of second with leave the space between the right box stand of second, wing tip rib positioning frame subassembly sets up in the space for the wing tip rib of location wing back-beam, just wing tip rib positioning frame subassembly with all be provided with the slide rail of horizontal direction between left box stand of second and the right box stand of second wing tip rib positioning frame subassembly passes through drive assembly seesaw positioning wing tip rib.
The other end of the back beam cross beam is arranged at the top of the second longitudinal box body assembly, and the back beam cross beam is driven by the driving assembly to move at the top of the second longitudinal box body assembly.
Preferably, the upper wall plate posture adjusting and positioning device and the lower wall plate posture adjusting and positioning device have the same structure, and the upper wall plate posture adjusting and positioning device specifically comprises: the integral shape-retaining frame of the upper wall plate, the first numerical control positioner, the second numerical control positioner, the third numerical control positioner and the fourth numerical control positioner;
the first numerical control positioner, the second numerical control positioner, the third numerical control positioner and the fourth numerical control positioner are connected with the integral shape-preserving frame of the upper wallboard and used for controlling the positioning of the integral shape-preserving frame of the upper wallboard, the integral shape-preserving frame of the upper wallboard is connected with the upper wallboard of the wing, the first numerical control positioner and the fourth numerical control positioner are positioned at the left end and the right end of the upper wallboard, two sub numerical control positioners are respectively arranged on the left end and the right end of the upper wallboard and used for adjusting the posture of the upper end and the lower end of the left end and the right end of the upper wallboard respectively, the second numerical control positioner and the third numerical control positioner are positioned in the middle of the upper wallboard and only one sub numerical control positioner is arranged and used for adjusting the posture of the middle of the upper wallboard.
Preferably, the integrated working platform is further provided with a manual operation platform for hole making, chip cleaning, gluing and/or riveting.
In order to solve one of the above technical problems, the present invention provides a method for using the digital assembly system for airplane wings, which includes:
the rear beam joint positioner of the rear beam positioning device moves to the topmost end, the rear beam positioning device moves to one side of the positioning lower wall plate, the front beam is hoisted into a position, and the front beam of the wing is supported and positioned by the supporting and positioning seat of the front beam positioning device;
the wing root rib positioning frame assembly and the wing tip rib positioning frame assembly are driven by a motor to move in place, and the end head of the front beam is positioned;
hoisting and pre-positioning the back beam, moving the back beam positioning device in place, moving the back beam joint positioner downwards in place, and connecting and positioning the back beam;
the lower wallboard integral shape-preserving frame is integrally hoisted into position with the lower wallboard, a first numerical control positioner, a second numerical control positioner, a third numerical control positioner and a fourth numerical control positioner are locked with the lower wallboard integral shape-preserving frame, a laser measuring device is used for measuring points on the lower wallboard and the lower wallboard integral shape-preserving frame and sending the measuring points to an integrated control device to obtain the current posture of the lower wallboard, and the first numerical control positioner, the second numerical control positioner, the third numerical control positioner and the fourth numerical control positioner are controlled to move in a joint adjustment mode according to the target posture of the lower wallboard, so that the lower wallboard moves along the vertical direction of the airplane, and the lower wallboard of the airplane is positioned;
carrying out hole making, chip cleaning, gluing and connecting treatment on a wing front beam, a wing rear beam, a lower wall plate, a wing root rib and a wing tip rib;
the integral shape-preserving frame of the upper wall plate is integrally hoisted into position with the upper wall plate, a first numerical control positioner, a second numerical control positioner, a third numerical control positioner and a fourth numerical control positioner are locked with the integral shape-preserving frame of the upper wall plate, a laser measuring device is used for measuring points on the integral shape-preserving frame of the upper wall plate and sending the measuring points to an integrated control device to obtain the current posture of the upper wall plate, and the first numerical control positioner, the second numerical control positioner, the third numerical control positioner and the fourth numerical control positioner are controlled to move in a joint adjustment mode according to the target posture of the upper wall plate, so that the upper wall plate moves along the vertical direction of the airplane to position the upper wall plate of;
carrying out hole making, scrap cleaning, gluing and connecting treatment on the upper wall plate;
after the wing assembly is finished, separating a back beam joint positioner of the back beam positioning device from a back beam, enabling the back beam joint positioner to move upwards, and moving the back beam positioning device to one side of the positioning lower wall plate;
bolts for separating the upper/lower wall plate shape-retaining frames from the upper and lower wall plates; the upper and lower wall plate posture adjusting positioning devices are linked to be far away from the space of the lower frame of the wing;
separating the wing root rib positioning device from the wing root rib, and separating the wing tip rib positioning device from the wing tip rib;
separating the supporting and positioning seat of the front beam positioning device from the front beam, and integrally hoisting the wing to the lower frame.
The invention has the following beneficial effects:
the invention adopts the digitization and automation technology to carry out digitization and automation assembly on the front beam, the rear beam, the upper wall plate, the lower wall plate and the wing rib of the integral wing of the wing, thereby improving the positioning precision, providing the open lower frame space of the integral wing of the airplane, simultaneously improving the manual assembly efficiency and improving the assembly quality and precision of the wing of the airplane.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
FIG. 1 is a schematic diagram of a system according to the present embodiment;
FIG. 2 is a schematic view of a wing configuration;
FIG. 3 is a schematic structural diagram of a left (right) wing final assembly apparatus according to the present embodiment;
fig. 4 is a schematic structural view of the front beam positioning device according to this embodiment;
fig. 5 is a schematic structural view of the back beam positioning device according to this embodiment;
FIG. 6 is a schematic structural view of a wing root rib positioning device according to this embodiment;
FIG. 7 is a schematic view of the tip rib positioning device of this embodiment;
fig. 8 is a schematic structural diagram of the upper wall plate posture adjusting and positioning device 10 according to the present embodiment.
Reference numerals:
1. a left wing general assembly device, a right wing general assembly device, a 3, an integrated working platform, a4, an integrated control device, a 5, a laser measuring device, a 6, a front beam positioning device, a 7, a back beam positioning device, a 8, a wing root rib positioning device, a 9, a wing tip rib positioning device, a 10, an upper wall plate posture adjusting positioning device, a 11, a lower wall plate posture adjusting positioning device, a 12, a front beam, a 13, a back beam, a 14, an upper wall plate, a 15, a lower wall plate, a 16, a wing root rib, a 17, a wing tip rib, an 18, a stand column, a 19, a front beam cross beam, a 20, a supporting positioning seat, a 21, a working step ladder, a 22, a back beam cross beam, a 23, a back beam joint positioner, a 24, a first box base, a 25, a first left box stand column, a 26, a first longitudinal box body assembly, a 27, a first right box body stand column, a 28, a wing root rib positioning frame assembly, a 30, an upper wall plate integral shape retaining, 32. the wing tip rib positioning device comprises a second numerical control positioner, 33, a third numerical control positioner, 34, a fourth numerical control positioner, 35, a lower wall plate integral shape retaining frame, 41, a second box base, 42, a second left box upright, 43, a second longitudinal box assembly, 44, a second right box upright, 45 and a wing tip rib positioning frame assembly.
Detailed Description
In order to make the technical solutions and advantages of the embodiments of the present application more apparent, the following further detailed description of the exemplary embodiments of the present application with reference to the accompanying drawings makes it clear that the described embodiments are only a part of the embodiments of the present application, and are not exhaustive of all embodiments. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.
As shown in fig. 1, the present embodiment provides a digital assembly system for an aircraft wing, which includes a wing assembly device, an integrated working platform 3, an integrated control device 4, and a laser measurement device 5; the wing general assembly device, the integrated control device 4 and the laser measuring device 5 are all arranged on the integrated working platform 3;
the wing general assembly device is used for positioning and assembling the wings of the airplane;
the laser measuring device 5 is used for measuring data of the wing general assembly device in the process of positioning and assembling the wings of the airplane;
the integrated control device 4 is used for calculating a posture adjusting path according to data measured by the laser measuring device 5, and then controlling the wing general assembly device to position and assemble the airplane wing through the posture adjusting path.
Specifically, as shown in fig. 1 and 2, the wing general assembly device further includes a left wing general assembly device 1 and a right wing general assembly device 2, and the left wing general assembly device 1 and the right wing general assembly device 2 are identical in structure and symmetrically placed on the integrated working platform 3 in parallel, so as to save assembly sites. The left wing general assembly device 1 and the right wing general assembly device 2 are used for automatically and digitally positioning and assembling a front beam 12, a rear beam 13, an upper wall plate 14, a lower wall plate 15, a wing root rib 16 and a wing tip rib 17 of an airplane wing, and after all the parts of the wing are positioned, the integrated working platform 3 provides manual operation platforms such as hole making, chip cleaning, gluing and riveting so as to perform various operations provided by the manual operation platforms on all the parts of the wing. The laser measuring device 5 is realized by adopting a laser tracker or iGPS and is used for measuring data of the wall plate in the positioning process, establishing a posture adjusting assembly coordinate system, determining the postures of the upper wall plate 14 and the lower wall plate 15, providing data for the integrated control device 4 to calculate, analyze and adjust the posture path, and the integrated control device 4 is used for controlling and operating the left wing general assembly device 1 and the right wing general assembly device 2 to automatically and digitally position and outputting result reports in various document forms after the airplane wing general assembly is finished.
Further, as shown in fig. 3, the left wing general assembly device 1 specifically includes: a front beam positioning device 6, a rear beam positioning device 7, an upper wall plate posture adjusting positioning device 10 and a lower wall plate posture adjusting positioning device 11;
the front beam positioning device 6 is used for supporting and positioning a wing front beam 12;
the back beam positioning device 7 is used for supporting and positioning a wing back beam 13;
the upper wall plate posture adjusting and positioning device 10 is used for positioning an upper wall plate 14 of the wing to be attached to a front beam 12 and a rear beam 13 of the wing;
the lower wall plate posture adjusting and positioning device 11 is used for positioning the lower wall plate 15 of the wing to be attached to the front beam 12 and the rear beam 13 of the wing.
Specifically, as shown in fig. 4, the front beam positioning device 6 includes four columns 18, a front beam cross beam 19 and supporting positioning seats 20, the columns 18 and the front beam cross beam 19 are respectively welded into a box body, the columns 18 are fixedly connected to the integrated working platform 3 through anchor bolts, the heights of the four columns 18 are sequentially increased from front to back and are arranged in a step shape, the front beam cross beam 19 is fixed at the tops of the columns 18 through screws, a plurality of supporting positioning seats 20, for example, 11 groups, are arranged on the front beam cross beam 19 side by side, and the supporting positioning seats 20 are used for supporting and positioning the wing front beam 12.
As shown in fig. 5, the back beam positioning device 7 includes a back beam cross beam 22, a back beam joint positioner 23, a wing root rib positioning device 8 and a wing tip rib positioning device 9, the wing root rib positioning device 8 and the wing tip rib positioning device 9 are fixedly connected with the integrated working platform 3 through anchor bolts, the back beam cross beam 22 is formed by welding steel plates, the top of the wing root rib positioning device 8 is connected with one end of the back beam cross beam 22, the top of the wing tip rib positioning device 9 is connected with the other end of the back beam cross beam 22, a driving assembly is arranged at the connection between the wing root rib positioning device 8 and the wing tip rib positioning device 9 and the back beam cross beam 22, the driving assembly controls the back beam cross beam 22 to make linear motion perpendicular to the length direction of the back beam cross beam 22 on the wing root rib positioning device 8 and the wing tip rib positioning device 9, a plurality of back beam joint positioners 23 are arranged on the side wall of the back beam cross beam 22, the back beam joint positioner 23 is used for connecting and positioning the back beam 13 and controlling the back beam to do linear motion in the vertical direction on the side wall of the back beam cross beam 22 through an external control unit.
The rear beam joint positioner 23 and the rear beam 13 are connected in a positioning manner through a process joint arranged on the rear beam 13, that is, the rear beam joint positioner 23 is matched with the process joint, and the rear beam 13 is positioned at a theoretical position through the matching of the rear beam joint positioner 23 and the process joint.
As shown in fig. 6, the wing root rib positioning device 8 comprises a first box base 24, a first left box upright 25, a first right box upright 27, a first longitudinal box assembly 26 and a wing root rib positioning frame assembly 28;
a first left box upright 25 and a first right box upright 27 are arranged between the first box base 24 and the first longitudinal box assembly 26, a gap is reserved between the first left box upright 25 and the first right box upright 27, the wing root rib positioning frame assembly 28 is arranged in the gap and used for positioning the wing root rib 16 of the wing back beam 13, horizontal sliding rails are arranged between the wing root rib positioning frame assembly 28 and the first left box upright 25 and the first right box upright 27, and the wing root rib positioning frame assembly 28 can be driven by a motor to move on the sliding rails in the gap so as to position the aircraft wing root rib 16;
one end of the back beam cross beam 22 is arranged on the top of the first longitudinal box body assembly 26, and the back beam cross beam 22 is driven to move on the top of the first longitudinal box body assembly 26 through a driving assembly.
Similar in structure to the wing root rib positioning device 8, as shown in fig. 7, the wing tip rib positioning device 9 includes a second box base 41, a second left box column 42, a second right box column 44, a second longitudinal box assembly 43, and a wing tip rib positioning frame assembly 45;
a second left box upright 42 and a second right box upright 44 are arranged between the second box base 41 and the second longitudinal box assembly 43, a gap is reserved between the second left box upright 42 and the second right box upright 44, the wing tip rib positioning frame assembly 45 is arranged in the gap and used for positioning a wing tip rib 17 of the wing back beam 13, horizontal sliding rails are arranged between the wing tip rib positioning frame assembly 45 and the second left box upright 42 and the second right box upright 44, and the wing tip rib positioning frame assembly 45 can be driven by a motor to move on the sliding rails in the gap so as to position the airplane wing tip rib 17;
the other end of the back beam cross beam 22 is arranged on the top of the second longitudinal box body assembly 43, and the back beam cross beam 22 is driven by the driving assembly to move on the top of the second longitudinal box body assembly 43.
As shown in fig. 8, the upper wall plate posture adjusting and positioning device 10 and the lower wall plate posture adjusting and positioning device have the same structure, and the upper wall plate 14 posture adjusting and positioning device specifically includes: the integral shape-retaining frame 30 of the upper wall plate, a first numerical control positioner 31, a second numerical control positioner 32, a third numerical control positioner 33 and a fourth numerical control positioner 34;
the first numerical control positioner 31, the second numerical control positioner 32, the third numerical control positioner 33 and the fourth numerical control positioner 34 are connected with the integral upper wall plate shape-retaining frame 30 and used for controlling the positioning of the integral upper wall plate shape-retaining frame 30, the integral upper wall plate shape-retaining frame 30 is connected with the upper wall plate 14 of the wing, wherein the first numerical control positioner 31 and the fourth numerical control positioner 34 are positioned at the left end and the right end of the upper wall plate 14 and are respectively provided with two sub numerical control positioners for respectively adjusting the upper end and the lower end of the left end and the right end of the upper wall plate 14, and the second numerical control positioner 32 and the third numerical control positioner 33 are positioned in the middle of the upper wall plate 14 and are only provided with one self numerical control positioner for adjusting the middle of the upper wall plate 14.
Specifically, the integral shape-keeping frame 30 of the upper wall plate is composed of an integral frame, 4 sets of process connectors, 7 sets of shape-keeping boards and 3 sets of process connectors with the shape-keeping boards, the numerical control positioner is connected with the integral shape-keeping frame 30 of the upper wall plate through a process ball head, and the upper wall plate 14 is connected with the integral shape-keeping frame 30 of the upper wall plate through 4 sets of process connectors and 3 sets of process connectors with the shape-keeping boards.
Furthermore, because the wing has a large volume and a certain height in the final assembly process, a plurality of working steps 21 are arranged on the integrated working platform 3 for facilitating the relevant operation of technicians.
The use method of the system in the process of assembling the wing assembly is as follows:
the rear two-section positioner of 10 groups of the rear beam positioning device 7 moves to the uppermost end, the rear beam positioning device 7 moves to one side of the lower wall plate 15 to avoid an overhead space, the front beam 12 is hoisted into a position, and the front beam 12 of the wing is supported and positioned by the supporting and positioning seat 20 of the front beam positioning device 6;
the wing root rib positioning device 8 and the wing tip rib positioning device 9 are driven by a motor to enable the wing root rib positioning frame assembly 28 and the wing tip rib positioning frame assembly 45 to move in place and position the end head of the front beam 12;
the rear beam 13 is hoisted into position, the rear beam positioning device 7 moves in place, and the 10 groups of rear beam joint positioners 23 move downwards in place and are connected with the process joints on the rear beam 13 to position the rear beam 13;
the lower wall plate integral shape-retaining frame 35 carries the lower wall plate 15 to be integrally hoisted into position, 6 groups of process ball heads fall into ball seats of first to fourth numerical control positioners 34 and are locked, measuring points on the lower wall plate 15 and the lower wall plate integral shape-retaining frame 35 through the laser measuring device 5, automatically inputting measuring point information into the integrated control device 4, calculating the current and target postures of the lower wall plate 15 through a built-in track algorithm by the integrated control device 4, and performing joint adjustment movement through 6 sub numerical control positioners to enable the lower wall plate 15 to move along the vertical direction of the airplane and position the lower wall plate 15 of the airplane;
the lower wall plate 15 is respectively connected with the front beam 12 and the rear beam 13 for hole making, chip cleaning, glue coating and connection;
the wing ribs of the wing are respectively drilled with the front beam 12, the rear beam 13 and the lower wall plate 15, and are subjected to chip cleaning, gluing and connection;
the upper wall plate integral shape-keeping frame 30 carries the upper wall plate 14 to be integrally hoisted into position, 6 groups of process ball heads fall into ball seats of first to fourth numerical control positioners 34 and are locked, measuring points on the upper wall plate 14 and the upper wall plate integral shape-keeping frame 30 through a laser measuring device 5, automatically inputting measuring point information into an integrated control device 4, calculating the current and target postures of the upper wall plate 14 through a built-in track algorithm by the system, and performing joint adjustment movement through 6 numerical control positioners to enable the upper wall plate 14 to vertically move along the airplane and position the upper wall plate 14 of the airplane;
the upper wall plate 14 is respectively connected with the front wing beam 12, the rear wing beam 13 and all the wing ribs for hole making, chip cleaning, glue coating and connection;
after the wing assembly is finished, the process joint positioning pins of 10 groups of back beam joint positioners 23 of the back beam positioning device 7 are disassembled, and the 10 groups of back beam joint positioners 23 move upwards to avoid the space of the lower frame of the wing. The back beam positioning device 7 moves to one side of the lower wall plate 15 to avoid the lower frame space of the wing;
the bolts of the upper/lower wall plate shape-retaining frames and the upper wall plate 14 and the lower wall plate 48 are disassembled; the upper wall plate posture adjusting positioning device 10 and the lower wall plate posture adjusting positioning device 11 are linked to be far away from the space of the lower frame of the wing; disassembling the space positioning device of the wing root rib 16 and the gasket and the positioning pin at the wing tip rib positioning device 9, and driving the wing root rib positioning device 8 and the wing tip rib positioning device 9 by a motor to enable the wing root rib positioning frame assembly 28 and the wing tip rib positioning frame assembly 45 to be far away from the wing root rib 16 and the wing tip rib 17 to avoid the space of the whole lower wing frame;
and (4) disassembling the positioning bolt of the supporting and positioning seat 20 of the front beam positioning device 6, and integrally hoisting the lower frame of the wing.
The invention adopts the digitization and automation technology to carry out digitization and automation assembly on the front beam 12, the rear beam 13, the upper wall plate 14, the lower wall plate 15 and the wing ribs of the integral wing of the airplane, thereby improving the positioning precision, providing the open lower shelf space of the integral wing of the airplane, simultaneously improving the manual assembly efficiency and improving the assembly quality and precision of the airplane wing.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (6)
1. A digital assembly system for airplane wings is characterized by comprising a wing assembly device, an integrated working platform, an integrated control device and a laser measuring device; the wing general assembly device, the integrated control device and the laser measuring device are all arranged on the integrated working platform;
the wing general assembly device is used for positioning and assembling the wings of the airplane;
the laser measuring device is used for measuring data of the wing general assembly device in the process of positioning and assembling the wings of the airplane;
the integrated control device is used for calculating a posture adjusting path according to data measured by the laser measuring device, and then controlling the wing general assembly device to position and assemble the airplane wing through the posture adjusting path.
The wing general assembly device comprises a left wing general assembly device and a right wing general assembly device, and the left wing general assembly device and the right wing general assembly device are identical in structure and symmetrically arranged on the integrated working platform in parallel;
the left wing general assembly device specifically comprises: the front beam positioning device, the rear beam positioning device, the upper wall plate posture adjusting positioning device and the lower wall plate posture adjusting positioning device;
the front beam positioning device is used for supporting and positioning the wing front beam;
the back beam positioning device is used for supporting and positioning the wing back beam;
the upper wall plate posture adjusting and positioning device is used for positioning the upper wall plate of the wing to be attached to the front beam and the rear beam of the wing;
the lower wall plate posture adjusting and positioning device is used for positioning the lower wall plate of the wing to be attached to the front beam and the rear beam of the wing;
the back beam positioning device comprises a back beam cross beam, a back beam joint positioner, a wing root rib positioning device and a wing tip rib positioning device, the wing root rib positioning device and the wing tip rib positioning device are fixedly connected with the foundation through foundation bolts, the top of the wing root rib positioning device is connected with one end of the back beam cross beam, the top of the wing tip rib positioning device is connected with the other end of the back beam cross beam, the joints of the wing root rib positioning devices and the wing tip rib positioning devices and the back beam cross beam are provided with driving components, the driving assembly controls the back beam cross beam to do linear motion perpendicular to the length direction of the back beam cross beam on the wing root rib positioning device and the wing tip rib positioning device, a plurality of back beam joint positioners are arranged on the side wall of the back beam cross beam and used for connecting and positioning the back beam, the external control unit controls the rear beam to do linear motion in the vertical direction on the side wall of the rear beam cross beam;
the wing root rib positioning device comprises a first box body base, a first left box body upright post, a first right box body upright post, a first longitudinal box body assembly and a wing root rib positioning frame assembly;
a first left box body upright post and a first right box body upright post are arranged between the first box body base and the first longitudinal box body assembly, a gap is reserved between the first left box body upright post and the first right box body upright post, the wing root rib positioning frame assembly is arranged in the gap and used for positioning a wing root rib of a wing back beam, and horizontal sliding rails are arranged between the wing root rib positioning frame assembly and the first left box body upright post and the first right box body upright post; the wing root rib positioning frame assembly moves forwards and backwards through the driving assembly to position the wing root ribs;
one end of the back beam cross beam is arranged at the top of the first longitudinal box body assembly, and the back beam cross beam is driven by the driving assembly to move at the top of the first longitudinal box body assembly.
2. The system according to claim 1, wherein the front beam positioning device comprises an upright column, a front beam cross beam and supporting positioning seats, the upright column is fixedly connected with the foundation through foundation bolts, the front beam cross beam is fixed on the top of the upright column through screws, a plurality of supporting positioning seats are arranged on the front beam cross beam side by side, and the supporting positioning seats are used for supporting and positioning the wing front beam.
3. The system of claim 1, wherein the wingtip rib positioning device comprises a second box base, a second left box upright, a second right box upright, a second longitudinal box assembly, and a wingtip rib positioning frame assembly;
a second left box upright and a second right box upright are arranged between the second box base and the second longitudinal box assembly, a gap is reserved between the second left box upright and the second right box upright, the wing tip rib positioning frame assembly is arranged in the gap and used for positioning a wing tip rib of a wing back beam, and horizontal sliding rails are arranged between the wing tip rib positioning frame assembly and the second left box upright and the second right box upright; the wing tip rib positioning frame assembly positions the wing tip ribs through the forward and backward movement of the driving assembly;
the other end of the back beam cross beam is arranged at the top of the second longitudinal box body assembly, and the back beam cross beam is driven by the driving assembly to move at the top of the second longitudinal box body assembly.
4. The system according to claim 1, wherein the upper wall plate posture adjusting and positioning device and the lower wall plate posture adjusting and positioning device have the same structure, and the upper wall plate posture adjusting and positioning device specifically comprises: the integral shape-retaining frame of the upper wall plate, the first numerical control positioner, the second numerical control positioner, the third numerical control positioner and the fourth numerical control positioner;
the first numerical control positioner, the second numerical control positioner, the third numerical control positioner and the fourth numerical control positioner are connected with the integral shape-preserving frame of the upper wallboard and used for controlling the positioning of the integral shape-preserving frame of the upper wallboard, the integral shape-preserving frame of the upper wallboard is connected with the upper wallboard of the wing, the first numerical control positioner and the fourth numerical control positioner are positioned at the left end and the right end of the upper wallboard, two sub numerical control positioners are respectively arranged on the left end and the right end of the upper wallboard and used for adjusting the posture of the upper end and the lower end of the left end and the right end of the upper wallboard respectively, the second numerical control positioner and the third numerical control positioner are positioned in the middle of the upper wallboard and only one sub numerical control positioner is arranged and used for adjusting the posture of the middle of the upper wallboard.
5. The system according to claim 1, wherein the integrated working platform is further provided with a manual operation platform for hole making, chip cleaning, glue coating and/or riveting.
6. The method of using the system of claim 5, wherein the method comprises:
the rear beam joint positioner of the rear beam positioning device moves to the topmost end, the rear beam positioning device moves to one side of the positioning lower wall plate, the front beam is hoisted into a position, and the front beam of the wing is supported and positioned by the supporting and positioning seat of the front beam positioning device;
the wing root rib positioning frame assembly and the wing tip rib positioning frame assembly are driven by a motor to move in place, and the end head of the front beam is positioned;
hoisting and pre-positioning the back beam, moving the back beam positioning device in place, moving the back beam joint positioner downwards in place, and connecting and positioning the back beam;
the lower wallboard integral shape-preserving frame is integrally hoisted into position with the lower wallboard, a first numerical control positioner, a second numerical control positioner, a third numerical control positioner and a fourth numerical control positioner are locked with the lower wallboard integral shape-preserving frame, a laser measuring device is used for measuring points on the lower wallboard and the lower wallboard integral shape-preserving frame and sending the measuring points to an integrated control device to obtain the current posture of the lower wallboard, and the first numerical control positioner, the second numerical control positioner, the third numerical control positioner and the fourth numerical control positioner are controlled to move in a joint adjustment mode according to the target posture of the lower wallboard, so that the lower wallboard moves along the vertical direction of the airplane, and the lower wallboard of the airplane is positioned;
carrying out hole making, chip cleaning, gluing and connecting treatment on a wing front beam, a wing rear beam, a lower wall plate, a wing root rib and a wing tip rib;
the integral shape-preserving frame of the upper wall plate is integrally hoisted into position with the upper wall plate, a first numerical control positioner, a second numerical control positioner, a third numerical control positioner and a fourth numerical control positioner are locked with the integral shape-preserving frame of the upper wall plate, a laser measuring device is used for measuring points on the integral shape-preserving frame of the upper wall plate and sending the measuring points to an integrated control device to obtain the current posture of the upper wall plate, and the first numerical control positioner, the second numerical control positioner, the third numerical control positioner and the fourth numerical control positioner are controlled to move in a joint adjustment mode according to the target posture of the upper wall plate, so that the upper wall plate moves along the vertical direction of the airplane to position the upper wall plate of;
carrying out hole making, scrap cleaning, gluing and connecting treatment on the upper wall plate;
after the wing assembly is finished, separating a back beam joint positioner of the back beam positioning device from a back beam, enabling the back beam joint positioner to move upwards, and moving the back beam positioning device to one side of the positioning lower wall plate;
bolts for separating the upper/lower wall plate shape-retaining frames from the upper and lower wall plates; the upper and lower wall plate posture adjusting positioning devices are linked to be far away from the space of the lower frame of the wing;
separating the wing root rib positioning device from the wing root rib, and separating the wing tip rib positioning device from the wing tip rib;
separating the supporting and positioning seat of the front beam positioning device from the front beam, and integrally hoisting the wing to the lower frame.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711135624.4A CN109204874B (en) | 2017-11-16 | 2017-11-16 | Digital final assembly system for airplane wings and application method thereof |
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| CN201711135624.4A CN109204874B (en) | 2017-11-16 | 2017-11-16 | Digital final assembly system for airplane wings and application method thereof |
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| CN109204874B true CN109204874B (en) | 2020-08-04 |
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| CN111137468B (en) * | 2019-12-20 | 2021-08-31 | 清华大学 | Multi-constraint-condition aircraft skin attitude adjusting method and system |
| CN112373716B (en) * | 2020-10-14 | 2022-09-20 | 浙江大学 | Large aircraft outer wing box digital assembly system |
| CN114013680B (en) * | 2021-11-19 | 2023-04-18 | 航天特种材料及工艺技术研究所 | Assembly fixture for wing end ribs and assembly method for wing butt joint mounting seat |
| CN114291288A (en) * | 2022-01-05 | 2022-04-08 | 中国航空制造技术研究院 | Production line system suitable for fuselage assembly |
| CN115519344A (en) * | 2022-09-28 | 2022-12-27 | 陕西飞机工业有限责任公司 | Rapid posture adjusting device and method for inner clamping plate and outer clamping plate of fixture |
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| US9676497B2 (en) * | 2010-01-21 | 2017-06-13 | The Boeing Company | High rate pulsing wing assembly line |
| US9943937B2 (en) * | 2012-09-28 | 2018-04-17 | The Boeing Company | System and method for manufacturing a wing panel |
| CN104647028A (en) * | 2014-12-29 | 2015-05-27 | 西北工业大学 | Digital assembly tooling of wing box |
| CN106275501B (en) * | 2016-08-30 | 2018-08-14 | 深圳市劲拓自动化设备股份有限公司 | A kind of control system and control method of six degree of freedom posture adjustment platform |
| CN106976032B (en) * | 2017-04-27 | 2018-10-12 | 浙江大学 | A kind of assembly tooling system of large aircraft outer wing wing box |
| CN107323684B (en) * | 2017-06-06 | 2019-06-25 | 浙江大学 | A kind of aircraft wing Digital assembly system |
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