CN115071997A - Aircraft wing assembling device and method - Google Patents
Aircraft wing assembling device and method Download PDFInfo
- Publication number
- CN115071997A CN115071997A CN202210695677.6A CN202210695677A CN115071997A CN 115071997 A CN115071997 A CN 115071997A CN 202210695677 A CN202210695677 A CN 202210695677A CN 115071997 A CN115071997 A CN 115071997A
- Authority
- CN
- China
- Prior art keywords
- sliding
- aircraft wing
- vertical
- fixed
- wing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 26
- 230000007246 mechanism Effects 0.000 claims abstract description 28
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automatic Assembly (AREA)
Abstract
The application discloses an aircraft wing assembling device and an assembling method, relates to the technical field of aircraft wing assembling, and is used for solving the technical problem that an aircraft wing assembling tool in the prior art cannot assemble more aircraft types, so that the aircraft wing assembling efficiency is reduced; the fixed upright post is arranged on the top surface of the base platform; a plurality of fixed locators are mounted on the fixed posts for locating the aft end of the aircraft wing; a plurality of sliding upright posts are arranged on the top surface of the base platform through a horizontal sliding mechanism; a plurality of slide retainers are mounted on the slide posts. The same assembling device can assemble the airplane wings of different types, so that the corresponding assembling device does not need to be replaced by time, and the assembling efficiency of the airplane wings can be improved through the assembling device.
Description
Technical Field
The application relates to the technical field of aircraft wing assembly, in particular to an aircraft wing assembly device and an assembly method.
Background
The traditional aircraft wing assembly tool adopts a truss type welding framework, and the positioner is fixedly connected with the framework, so that the tool is high in specificity, low in repeated utilization rate and complex in structure; in addition, on the assembly process, more than 90% of parts need to be positioned and assembled by the tool, the number of the positioners is large, the assembly space of the tool is further compressed, the space is closed, the openness is poor, the operation of workers and the putting on and off of products are inconvenient, and the parts cannot be reused for other types of models.
In conclusion, in the prior art, the aircraft wing assembling tool can only assemble corresponding aircraft wings, cannot assemble other types of aircraft, and is low in universality, so that the assembling efficiency of the aircraft wings is reduced.
Disclosure of Invention
The application mainly aims to provide an aircraft wing assembling device and an assembling method, and aims to solve the technical problem that the universality of an aircraft wing assembling tool in the prior art is not strong.
To achieve the above object, a first aspect of the present application provides an aircraft wing assembly apparatus, the apparatus comprising:
a base platform;
the fixed upright post is arranged on the top surface of the base platform;
a plurality of fixed locators mounted on the fixed posts for locating the aft end of the aircraft wing;
the sliding upright columns are installed on the top surface of the base platform through a horizontal sliding mechanism and are arranged opposite to the fixed upright columns;
a plurality of sliding locators mounted on the sliding columns for locating the front end of the aircraft wing.
Optionally, the horizontal sliding mechanism comprises:
a plurality of horizontal guide rails, all mounted on the top surface of the base platform;
and the horizontal sliding blocks are all installed on the bottom surface of the sliding upright post, and the horizontal sliding blocks are in one-to-one correspondence with the horizontal guide rails and are in sliding connection with each other.
Optionally, a lower connecting plate is mounted on the top surface of the base platform; the top surface of the lower connecting plate is also provided with an upper connecting plate, the horizontal guide rail is arranged on the top surface of the upper connecting plate, a dislocation component is arranged between the upper connecting plate and the lower connecting plate, and the dislocation component is used for adjusting the relative position between the upper connecting plate and the lower connecting plate.
Optionally, the dislocation assembly comprises a plurality of threaded holes and a plurality of strip-shaped holes, and a fixing bolt is connected between the threaded holes and the strip-shaped holes;
the plurality of threaded holes are uniformly formed in the lower connecting plate;
and the strip-shaped holes are uniformly formed in the upper connecting plate.
Optionally, the side of the sliding column is provided with a sliding groove along the height direction thereof, the sliding positioner is mounted on the sliding column through a vertical sliding mechanism, and the vertical sliding mechanism includes:
the mounting plates are sequentially arranged along the height direction of the sliding groove;
the screw rods correspond to the mounting plates one by one, and the screw rods are connected with the corresponding mounting plates through nuts;
the rotating motor is arranged in the sliding groove, a motor shaft of the rotating motor is connected with one end of the screw rod, and the rotating motor is used for driving the screw rod to rotate;
the mounting panel with still install vertical direction subassembly between the slip stand, vertical direction subassembly is used for the guide the mounting panel slides in vertical direction.
Optionally, the vertical guide assembly comprises a plurality of vertical guide rails and a plurality of vertical sliders;
the plurality of vertical guide rails are all installed on the sliding upright column along the vertical direction;
the vertical sliding blocks are all arranged on the side surface of the mounting plate;
the plurality of vertical guide rails correspond to the plurality of vertical sliding blocks one by one, and the vertical guide rails are connected with the vertical sliding blocks in a sliding mode.
Optionally, a support arm located in the horizontal direction is installed on the installation plate, the sliding positioner is installed on the support arm, and a sliding mechanism is arranged between the support arm and the installation plate.
Optionally, the glide machanism includes the slider and the slide rail that slides, the slider that slides is installed on the mounting panel, the slide rail that slides is installed along the horizontal direction on the support arm, the slide rail that slides with sliding connection between the slider that slides.
Optionally, all install the locating plate on the both sides face of support arm, install the locating pin on the locating plate, the locating pin is used for fixing the support arm.
In a second aspect, the present application provides a method of assembling an aircraft wing, the method comprising:
positioning by using a fixed positioner of a wing assembly device by taking a main bearing beam of an airplane wing as a positioning reference; wherein the wing assembly device is the aircraft wing assembly device described in the embodiments;
positioning through the fixed positioner by taking a tip rib of the airplane wing as a positioning reference so as to assemble the front end of the airplane wing;
and positioning by using a rear beam of the airplane wing as a positioning reference through a sliding positioner of the wing assembling device so as to assemble the rear end of the airplane wing.
Through above-mentioned technical scheme, this application has following beneficial effect at least:
the aircraft wing assembling device provided by the embodiment of the application comprises a base platform, a fixed upright post, a plurality of fixed positioners, a plurality of sliding upright posts and a plurality of sliding positioners; the fixed upright post is arranged on the top surface of the base platform; a plurality of fixed locators are mounted on the fixed posts for locating the aft end of the aircraft wing; the sliding upright posts are installed on the top surface of the base platform through a horizontal sliding mechanism, and the sliding upright posts are arranged opposite to the fixed upright posts; a plurality of sliding locators are mounted on the sliding columns for locating the front end of the aircraft wing. Because the sliding upright post is arranged on the top surface of the base platform through the horizontal sliding mechanism, the relative position between the sliding upright post and the fixed upright post can be adjusted through the horizontal sliding mechanism, and then the relative position between the fixed positioner and the sliding positioner is adjusted.
Drawings
FIG. 1 is a schematic perspective view of an aircraft wing assembly apparatus provided herein;
FIG. 2 is a schematic perspective view of the horizontal sliding mechanism provided in the present application mounted on the upper connecting plate;
fig. 3 is a schematic perspective view of a vertical sliding mechanism and the like provided by the present application, mounted on a sliding column;
FIG. 4 is an enlarged schematic view at A of FIG. 1 as provided herein;
FIG. 5 is an enlarged schematic view at B of FIG. 2 as provided herein;
FIG. 6 is an enlarged schematic view at C of FIG. 3 as provided herein;
fig. 7 is a flow chart of a method of assembling an aircraft wing provided herein.
Reference numerals: 1. a base platform; 2. a lower connecting plate; 21. a threaded hole; 3. sliding the upright post; 4. an aircraft wing; 5. a slide locator; 6. fixing the upright post; 7. fixing a locator; 8. a vertical sliding mechanism; 81. a rotating electric machine; 82. a screw rod; 83. a vertical guide assembly; 831. a vertical slide block; 832. a vertical guide rail; 9. a horizontal sliding mechanism; 91. a horizontal guide rail; 92. a horizontal slider; 10. an upper connecting plate; 101. a strip-shaped hole; 11. a sliding groove; 12. a support arm; 13. mounting a plate; 14. a sliding mechanism; 141. a sliding rail; 142. a sliding block; 15. positioning pins; 16. and (7) positioning the plate.
The implementation, functional features and advantages of the objectives of the present application will be further explained with reference to the accompanying drawings.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
The traditional aircraft wing assembly tool adopts a truss type welding framework, and the positioner is fixedly connected with the framework, so that the tool is high in specificity, low in repeated utilization rate and complex in structure; in addition, in the assembly process, more than 90% of parts need to be positioned and assembled by tools, the positioning devices are multiple, the assembly space of the tools is further compressed, the space is closed, the openness is poor, the operation of workers and the putting on and off of products are inconvenient, and the parts cannot be reused for other types of machines. Therefore, how fully consider the different demands of the aircraft assembly of different grade type, improve the assembly quality and the assembly efficiency of aircraft, shorten assembly cycle, how realize the accurate location of self-align in the aircraft assembly process, realize few frame assembly, improve the place utilization ratio in order to improve production efficiency, become the technological problem that the aircraft assembly technical field is waited to solve urgently.
In order to solve the above technical problem, as shown in fig. 1, the present embodiment provides an aircraft wing assembling device, including: comprises a base platform 1, a fixed upright post 6, a plurality of fixed locators 7, a plurality of sliding upright posts 3 and a plurality of sliding locators 5; the fixed upright post 6 is arranged on the top surface of the base platform 1; a plurality of fixed locators 7 are mounted on the fixed uprights 6 for locating the rear end of the aircraft wing 4; the sliding upright posts 3 are arranged on the top surface of the base platform 1 through a horizontal sliding mechanism 9, and the sliding upright posts 3 are arranged opposite to the fixed upright posts 6; a plurality of sliding locators 5 mounted on the sliding uprights 3 for locating the front ends of the aircraft wings 4.
In the embodiment, the base platform 1 is used as a base of the overall tool structure and can be formed by splicing and combining a plurality of small platforms, the combination of the fixed upright post 6 and the sliding upright post 3 breaks through the closed frame-beam structure type of the traditional tool framework, the structural layout of upright post groups is adopted, the openness of the assembly device is improved, the assembly device is simple and convenient, the fixed upright post 6 and the sliding upright post 3 are oppositely arranged and are jointly installed on the base platform 1, and the specific oppositely arranged position relationship can be determined according to the types of the main assembled airplane wings and the like; when the positioning device for the airplane wing 4 is needed, the front end of the airplane wing 4 is positioned through the fixed positioner 7, the rear end of the airplane wing 4 is positioned through the sliding positioner 5, and therefore positioning and assembling of the airplane wing 4 are achieved, the fixed positioner 7 and the sliding positioner 5 can be selected according to actual assembling requirements of the airplane wing 4, for example, a wing body intersection joint positioner, a fabrication hole positioner, a tooling process part positioner and the like can be selected. When the airplane wings 4 of different types are positioned and assembled, the rear ends of the airplane wings 4 are positioned by taking the fixed positioners 7 on the fixed upright posts 6 as references, because the sizes of the airplane wings 4 of different types are different, in order to ensure that the airplane wings 4 can be normally positioned on the sliding positioners 5, the airplane wings 4 can apply force to the sliding upright posts 3 (or apply force to the sliding upright posts 3 by assembly workers), the sliding upright posts 3 can slide on the base platform 1 through the horizontal sliding mechanisms 9 after being applied with the force, the sliding upright posts 3 can move together with the sliding positioners 5 when sliding, so that the relative positions between the sliding upright posts 3 and the fixed upright posts 6 can be adjusted, and then the relative positions between the fixed positioners 7 and the sliding positioners 5 can be adjusted, when the airplane wings 4 of different types are assembled, the sliding positioners 5 can automatically move along with the sliding upright posts 3 according to different types, the assembling device is suitable for airplane wings 4 of different types, flexible assembling is achieved, so that more airplane wings 4 of different types can be assembled through the assembling device, and the universality of the assembling tool is improved because the same assembling device can assemble the airplane wings 4 of different types, so that the corresponding assembling device does not need to be replaced in time, and the assembling efficiency of the airplane wings 4 can be improved through the assembling device.
In some embodiments, as shown in fig. 2, in order to realize the relative movement between the fixed upright 6 and the sliding upright 3, this embodiment provides a preferred structure of the horizontal sliding mechanism 9, which specifically includes: a plurality of horizontal rails 91 and a plurality of horizontal sliders 92, the plurality of horizontal rails 91 being mounted on the top surface of the base platform 1; the plurality of horizontal sliding blocks 92 are all installed on the bottom surface of the sliding column 3, and the plurality of horizontal sliding blocks 92 correspond to the plurality of horizontal guide rails 91 one to one and are connected in a sliding manner.
In this embodiment, after the sliding column 3 receives the force of a worker or an airplane wing 4, the force can be transmitted to the horizontal slider 92, the horizontal slider 92 can slide along the horizontal guide rail 91 after being stressed, the horizontal slider 92 drives the sliding column 3 to move in turn, and finally the sliding positioner 5 is driven to move.
In some embodiments, as shown in fig. 4 and 5, in order to compensate for the relative position between the sliding column 3 and the base platform 1, which is spatially perpendicular to the sliding direction of the sliding column 3 along the horizontal sliding mechanism 9, the following preferred implementation structure is given in this embodiment: the top surface of the base platform 1 is provided with a lower connecting plate 2; the top surface of the lower connecting plate 2 is also provided with an upper connecting plate 10, the horizontal guide rail 91 is arranged on the top surface of the upper connecting plate 10, a dislocation assembly is arranged between the upper connecting plate 10 and the lower connecting plate 2 and used for adjusting the relative position between the upper connecting plate 10 and the lower connecting plate 2, the dislocation assembly comprises a plurality of threaded holes 21 and a plurality of strip-shaped holes 101, and a fixing bolt is connected between the threaded holes 21 and the strip-shaped holes 101; a plurality of threaded holes 21 are uniformly formed in the lower connecting plate 2; a plurality of the strip-shaped holes 101 are uniformly formed in the upper connecting plate 10.
In the embodiment, the horizontal, vertical, upper, lower and the like are only used for distinguishing and do not indicate the limitation of specific positions of the fixed upright column, two groups of array holes are arranged at the bottom of the fixed upright column 6, the distance between the two groups of array holes in the x-axis direction is 50mm and used for compensating 100mm interval adjustment of the base platform 1, long round holes are adopted in the y-axis direction for compensation, the center distance of the long round holes is 50mm, and the compensation amount is less than 50mm, so that the adjustment amount between the fixed upright column 6 and the base platform 1 is shortened, and the flexibility and the reconfigurability of the tool are improved; the threaded holes 21 and the strip-shaped holes 101 can be set with sizes and numbers according to actual needs, for example, a criss-cross array threaded hole system with a distance M16 of 100mm is arranged on the lower connecting plate 2, two strip-shaped holes 101 with a distance of 500mm are arranged on the upper connecting plate 10, the center distance of two round holes in the same strip-shaped hole 101 is 100mm, so that the sliding column 3 can be conveniently connected with the base platform 1, the upper connecting plate 10 can be freely moved along the base platform 1 with an equal distance of 100mm in the directions of the x axis and the y axis, after the upper connecting plate is moved to a certain position, the upper connecting plate 10 and the lower connecting plate 2 are fixed by sequentially penetrating the strip-shaped holes 101 and the threaded holes 21 through fixing bolts, thereby the position of the sliding column 3 on the base platform 1 is convenient to be changed, meanwhile, because the center distance of two round holes in the same strip-shaped hole 101 is 100mm, the sliding column can be used for compensating the movement amount of the upper connecting plate 10 and the lower connecting plate 2 along the length direction of the strip-shaped holes 101 less than 100mm, thereby realizing the compensation adjustment of the sliding upright 3 relative to the base platform 1.
In some embodiments, as shown in fig. 3, a preferred structure is given that can move the slide positioner 5 in the vertical direction: the side surface of the sliding upright post 3 is provided with a sliding groove 11 along the height direction thereof, the sliding positioner 5 is mounted on the sliding upright post 3 through a vertical sliding mechanism 8, the vertical sliding mechanism 8 comprises a plurality of mounting plates 13, a plurality of screw rods 82 and a rotating motor 81, wherein the mounting plates 13 are sequentially arranged along the height direction of the sliding groove 11; the plurality of screw rods 82 correspond to the plurality of mounting plates 13 one by one, and the screw rods 82 are connected with the corresponding mounting plates 13 through nuts (the screw rods 82 are not contacted with the rest mounting plates 13, namely the screw rods 82 can directly penetrate through the non-corresponding mounting plates 13); a rotating motor 81 is installed in the sliding groove 11, a motor shaft of the rotating motor 81 is connected with one end of the screw rod 82, and the rotating motor 81 is used for driving the screw rod 82 to rotate; the mounting panel 13 with still install vertical guide subassembly 83 between the slip stand 3, vertical guide subassembly 83 is used for the guide mounting panel 13 slides in the vertical direction.
In this embodiment, the rotating electrical machine 81 can select the corresponding specification and model according to the actual requirement, based on different models, when the height of a certain sliding positioner 5 in the vertical direction needs to be adjusted, the corresponding rotating motor 81 is electrified in a conventional mode, the rotating motor 81 drives the screw rod 82 to rotate after being electrified, as the screw rod 82 is connected with the nut through the threads, according to the working principle of the screw rod nut, the nut can move along the screw rod 82, then the nut drives the mounting plate 13 to move in the vertical direction, the mounting plate 13 is guided by the vertical guide component 83 in the moving process, and finally the sliding positioner 5 is driven to move in the vertical direction, the relative position of the sliding positioner 5 and the fixed positioner 7 in the vertical direction can be adjusted, and the relative position between the sliding locator 5 and the sliding locator 5 is adjusted, so that the flexible assembly and positioning of the airplane wings 4 of different types can be more conveniently carried out.
In some embodiments, as shown in FIG. 6, a preferred configuration of the vertical guide assembly 83 is given by: the vertical guide assembly 83 includes a plurality of vertical guide rails 832 and a plurality of vertical sliders 831; a plurality of the vertical guide rails 832 are all installed on the sliding column 3 along the vertical direction; the plurality of vertical sliders 831 are mounted on the side surface of the mounting plate 13; the plurality of vertical guide rails 832 correspond to the plurality of vertical sliding blocks 831 one to one, and the vertical guide rails 832 are slidably connected with the vertical sliding blocks 831.
In this embodiment, when the mounting plate 13 moves in the vertical direction, the vertical slider 831 is driven to slide along the vertical guide rail 832, because the direction of the vertical guide rail 832 is fixed, the movement of the mounting plate 13 can be guided, and the mounting plate 13 can be moved in the vertical direction more conveniently.
In some embodiments, as shown in fig. 3 and 6, the mounting plate 13 is mounted with a support arm 12 in a horizontal direction, the slide positioner 5 is mounted on the support arm 12, and a sliding mechanism 14 is provided between the support arm 12 and the mounting plate 13. Specifically, the sliding mechanism 14 includes a sliding block 142 and a sliding rail 141, the sliding block 142 is mounted on the mounting plate 13, the sliding rail 141 is mounted on the support arm 12 along the horizontal direction, and the sliding rail 141 is connected to the sliding block 142 in a sliding manner.
In this embodiment, the sliding rail 141 and the horizontal rail 91 are spatially perpendicular, the horizontal rail 91 is disposed along the y-axis direction, the sliding rail 141 is disposed along the x-axis direction, the support arm 12 can make the spatial arrangement of the sliding positioner 5 wider, when it is required to adjust the relative position of the sliding positioner 5 with respect to the fixed positioner 7, a force can be applied to the fixed positioner 7 in the length direction of the sliding rail 141, the force is transmitted to the sliding block 142, the sliding block 142 moves along the sliding rail 141, the sliding block 142 drives the support arm 12 and the fixed positioner 7 to move, so that the fixed positioner 7 can move along the y-axis direction with respect to the fixed positioner 7 via the horizontal rail 91, move along the z-axis direction with respect to the fixed positioner 7 via the vertical rail 832, and move along the x-axis direction with respect to the fixed positioner 7 via the sliding rail 141, thereby realizing stepless adjustment of the sliding positioner 5 in the up-down direction, meanwhile, the operation of workers is facilitated, so that the adjustment between the sliding positioner 5 and the fixed positioner 7 is more sensitive, the assembly of the airplane wings 4 of different types is more convenient, the airplane wings 4 are self-positioned by adopting various positioners, the self-positioning assembly of the airplane wings 4 is realized, the purposes of saving space and fields, simplifying the tool structure are achieved, the airplane assembly efficiency and the assembly quality are improved, and the assembly cost of the airplane wings 4 is reduced.
In some embodiments, as shown in fig. 6, positioning plates 16 are mounted on both sides of the supporting arm 12, and positioning pins 15 are mounted on the positioning plates 16, and the positioning pins 15 are used for fixing the supporting arm 12.
In this embodiment, when the through hole is opened on the positioning plate 16, the positioning pin 15 is installed in the through hole, when the sliding locator 5 needs to be stopped to move along the direction of the sliding rail 141, the positioning pin 15 can be rotated, the positioning pin 15 passes through the through hole and abuts against the mounting plate 13, so that the positioning plate 16 can be fixed to move, the support arm 12 is further fixed, the sliding locator 5 is finally fixed, the sliding locator 5 is enabled not to move along the direction of the sliding rail 141 any more, and the positioning of the sliding locator 5 is facilitated.
In another embodiment, as shown in fig. 7, the present application provides a method of assembling an aircraft wing, the method comprising:
s10: the main bearing beam of the airplane wing 4 is used as a positioning reference, and the positioning is carried out through a fixed positioner 7 of the wing assembling device; wherein the wing assembly device is an aircraft wing 4 assembly device as described in the examples;
s11: positioning by the fixed positioner 7 by taking the tip rib of the airplane wing 4 as a positioning reference so as to assemble the front end of the airplane wing 4;
s12: and taking the rear beam of the airplane wing 4 as a positioning reference, and positioning through a sliding positioner 5 of the wing assembling device so as to assemble the rear end of the airplane wing 4.
In the embodiment, the front end of the airplane wing 4 is positioned and assembled through the fixed positioner 7, the rear end of the airplane wing 4 is positioned and assembled through the sliding positioner 5, namely the sliding upright column 3 of the wing assembling device is used for installing and supporting a wing side positioner, the fixed upright column 6 is used for installing a wing body intersection point and a trailing edge part positioner of the airplane wing, the wings of different types have the same structure size, but the assembling modes are consistent, meanwhile, the positioner of the wing surface part can automatically adapt through the movement of the flexible upright column unit 9, the flexible assembling is realized, and the relative position between the sliding positioner 5 and the fixed positioner 7 can be automatically adjusted, so that more airplane wings 4 of different types can be assembled through the method, and the same assembling device can assemble the airplane wings 4 of different types, it is therefore not necessary to take time to replace the corresponding fitting device, so that the efficiency of fitting the aircraft wing 4 can be increased by means of the fitting device.
More specifically, on the design of an airfoil product, based on the concept of self-positioning assembly, except for characteristic structures such as a main bearing beam, a key coordination intersection point, a key appearance intersection point and the like, other structures are designed with self-positioning assembly characteristics such as a nesting profile, a fitting profile, a self-positioning hole system and the like; according to the characteristics of products, in the assembly process, the main bearing beam, the key coordination intersection point, the key appearance intersection point and other characteristic structures are positioned and assembled through an assembly tool, and other structures are self-assembled through self-positioning characteristics, and the method specifically comprises the following steps:
step 1: firstly, three main bearing beams are used as positioning reference for assembly, and positioning is carried out through a tool wing body intersection point joint positioner and a fabrication hole positioner;
step 2: the front section takes the wing tip rib of the wing as a positioning reference and is positioned by two groups of process hole positioners;
and step 3: the lower end of the wing is positioned and supported by using the rear wing beam as a positioning reference through three groups of supporting block assemblies and two groups of process hole positioners;
and 4, step 4: the key coordination intersection point only requires relative position precision, so that the key coordination intersection point is positioned by a tooling process part positioner;
and 5: and other structures such as auxiliary beams, small ribs and the like are subjected to self-positioning assembly through the positioned products.
Based on the assembly method, according to the characteristics of self-positioning assembly and flattening of wing products, the whole assembly device is designed by adopting a guide rail movable positioning framework and a flattening structure; the vertical assembly posture is adopted, the rear edge is downward, the front edge is placed upward, the right side is positioned by the wing body intersection point joint positioner, the rest auxiliary process hole positioners and the appearance positioners are positioned, the number of the tool positioners is greatly reduced, the assembly space is improved, the self-positioning assembly and the modularized assembly of the airplane are realized, the airplane self-positioning assembly and modularized assembly are applicable to the assembly of different airplane types, and the tool reconfigurable utilization rate is improved.
The above description is only a preferred embodiment of the present application, and not intended to limit the scope of the present application, and all the equivalent structures or equivalent processes that can be directly or indirectly applied to other related technical fields by using the contents of the specification and the drawings of the present application are also included in the scope of the present application.
Claims (10)
1. An aircraft wing assembly device, the device comprising:
a base platform (1);
the fixed upright post (6) is arranged on the top surface of the base platform (1);
a plurality of fixed locators (7) mounted on the fixed posts (6) for locating the rear ends of the aircraft wings (4);
the sliding columns (3) are mounted on the top surface of the base platform (1) through a horizontal sliding mechanism (9), and the sliding columns (3) are arranged opposite to the fixed columns (6);
a plurality of sliding locators (5) mounted on the sliding uprights (3) for locating the front ends of the aircraft wings (4).
2. An aircraft wing assembly device according to claim 1, characterised in that the horizontal sliding mechanism (9) comprises:
a plurality of horizontal guide rails (91) all mounted on the top surface of the base platform (1);
the horizontal sliding blocks (92) are installed on the bottom surface of the sliding upright post (3), and the horizontal sliding blocks (92) are in one-to-one correspondence with the horizontal guide rails (91) and are in sliding connection with each other.
3. An aircraft wing assembly device according to claim 2, characterised in that the top surface of the base platform (1) is fitted with a lower web (2); the top surface of lower connecting plate (2) still installs upper junction plate (10), horizontal guide (91) are installed the top surface of upper junction plate (10), upper junction plate (10) with be equipped with dislocation subassembly between lower connecting plate (2), dislocation subassembly is used for adjusting upper junction plate (10) with relative position between lower connecting plate (2).
4. An aircraft wing assembly device according to claim 3, characterized in that the dislocation assembly comprises a plurality of threaded holes (21) and a plurality of strip-shaped holes (101), and fixing bolts are connected between the threaded holes (21) and the strip-shaped holes (101);
the threaded holes (21) are uniformly formed in the lower connecting plate (2);
the strip-shaped holes (101) are uniformly formed in the upper connecting plate (10).
5. An aircraft wing assembly device according to claim 1, characterised in that the sliding upright (3) is provided with sliding grooves (11) on its side in the direction of its height, the sliding retainer (5) being mounted on the sliding upright (3) by means of a vertical sliding mechanism (8), the vertical sliding mechanism (8) comprising:
a plurality of mounting plates (13), the mounting plates (13) being arranged in sequence in the height direction of the slide groove (11);
the screw rods (82) correspond to the mounting plates (13) one by one, and the screw rods (82) are connected with the corresponding mounting plates (13) through nuts;
the rotating motor (81) is installed in the sliding groove (11), a motor shaft of the rotating motor (81) is connected with one end of the screw rod (82), and the rotating motor (81) is used for driving the screw rod (82) to rotate;
mounting panel (13) with still install vertical guide subassembly (83) between slip stand (3), vertical guide subassembly (83) are used for guiding mounting panel (13) slide in vertical direction.
6. An aircraft wing assembly device according to claim 5, characterised in that the vertical guide assembly (83) comprises a plurality of vertical guide rails (832) and a plurality of vertical sliders (831);
a plurality of vertical guide rails (832) are all installed on the sliding upright (3) along the vertical direction;
the vertical sliding blocks (831) are all arranged on the side surface of the mounting plate (13);
the vertical guide rails (832) correspond to the vertical sliding blocks (831) one by one, and the vertical guide rails (832) are connected with the vertical sliding blocks (831) in a sliding mode.
7. An aircraft wing assembly device according to claim 5 or 6, characterised in that the mounting plate (13) has mounted thereon a horizontally oriented arm (12), the slide locator (5) being mounted on the arm (12), and a slide mechanism (14) being provided between the arm (12) and the mounting plate (13).
8. An aircraft wing assembly device according to claim 7, wherein the sliding mechanism (14) comprises a sliding block (142) and a sliding rail (141), the sliding block (142) is mounted on the mounting plate (13), the sliding rail (141) is mounted on the arm (12) in a horizontal direction, and the sliding rail (141) is slidably connected with the sliding block (142).
9. An aircraft wing assembly device according to claim 7, characterised in that locating plates (16) are mounted on both sides of the arm (12), locating pins (15) being mounted on the locating plates (16), the locating pins (15) being used to secure the arm (12).
10. A method of assembling an aircraft wing, the method comprising:
the main bearing beam of the airplane wing (4) is taken as a positioning reference, and the main bearing beam is positioned by a fixed positioner (7) of the wing assembling device; wherein the wing assembly device is an aircraft wing assembly device as claimed in any one of claims 1 to 9;
positioning by using a tip rib of the airplane wing (4) as a positioning reference through the fixed positioner (7) so as to assemble the front end of the airplane wing (4);
and taking the rear beam of the airplane wing (4) as a positioning reference, and positioning through a sliding positioner (5) of the wing assembling device so as to assemble the rear end of the airplane wing (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210695677.6A CN115071997B (en) | 2022-06-20 | 2022-06-20 | Aircraft wing assembly device and assembly method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210695677.6A CN115071997B (en) | 2022-06-20 | 2022-06-20 | Aircraft wing assembly device and assembly method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115071997A true CN115071997A (en) | 2022-09-20 |
| CN115071997B CN115071997B (en) | 2024-06-11 |
Family
ID=83252970
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210695677.6A Active CN115071997B (en) | 2022-06-20 | 2022-06-20 | Aircraft wing assembly device and assembly method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115071997B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116443262A (en) * | 2023-06-14 | 2023-07-18 | 陕西德鑫智能科技有限公司 | Wing bracket, wing transferring and installing method |
| CN117508630A (en) * | 2024-01-04 | 2024-02-06 | 成都市鸿侠科技有限责任公司 | Size-adjustable aircraft side aileron assembly type frame |
Citations (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005153102A (en) * | 2003-11-27 | 2005-06-16 | Fuji Heavy Ind Ltd | Wing spar assembling tool |
| EP2138402A2 (en) * | 2008-04-07 | 2009-12-30 | Multiprojekt Kft. | Variable modular docking system |
| CN101745905A (en) * | 2010-02-03 | 2010-06-23 | 北京航空航天大学 | Multi-degree of freedom adjustable assembling platform used for butt joint of aircraft wings |
| CN102092478A (en) * | 2010-12-30 | 2011-06-15 | 中国商用飞机有限责任公司 | Positioning device for butting wing body |
| CN103496449A (en) * | 2013-08-29 | 2014-01-08 | 北京航空航天大学 | Pose adjustment track planning method for plane side wall component assembling |
| CN103921116A (en) * | 2014-04-24 | 2014-07-16 | 浙江大学 | Flexible assembly system for aircraft panel |
| CN104647028A (en) * | 2014-12-29 | 2015-05-27 | 西北工业大学 | Digital assembly tooling of wing box |
| CN206125462U (en) * | 2016-11-03 | 2017-04-26 | 浙江日发航空数字装备有限责任公司 | Installation auxiliary assembly is connected to aircraft wing |
| CN206579861U (en) * | 2017-01-22 | 2017-10-24 | 艾雷奥特（江苏）飞机工业有限公司 | Small General Aircraft wing assembles support jig |
| CN107352044A (en) * | 2017-07-07 | 2017-11-17 | 浙江大学 | The layout method of large aircraft trailing edge component posture adjusting system |
| CN108001708A (en) * | 2017-12-20 | 2018-05-08 | 西北工业大学 | A kind of aircraft wing docks posture adjustment reconfigurable device |
| RU2657816C1 (en) * | 2016-07-05 | 2018-06-15 | Публичное акционерное общество "Туполев" | Method for assembling wing of flying apparatus |
| CN109204874A (en) * | 2017-11-16 | 2019-01-15 | 中国航空制造技术研究院 | One kind is for aircraft wing digitlization general assembly assembly system and its application method |
| CN210212814U (en) * | 2019-07-02 | 2020-03-31 | 贵州弘安鑫晟航空科技有限责任公司 | Unmanned aerial vehicle wing assembly fixture of adaptable different wings |
| US20200172267A1 (en) * | 2018-12-04 | 2020-06-04 | Airbus Sas | Transport and referencing carriage for wings of an aircraft |
| US20210163153A1 (en) * | 2017-06-16 | 2021-06-03 | Mitsubishi Heavy Industries, Ltd. | Aircraft structure manufacturing device |
| CN113245813A (en) * | 2021-07-16 | 2021-08-13 | 成都飞机工业（集团）有限责任公司 | Self-positioning assembly system and method for rapid assembly of airplane |
| CN113524105A (en) * | 2021-06-30 | 2021-10-22 | 何怀彬 | Aircraft wing multi-angle freely adjusts assembly quality |
| CN113772116A (en) * | 2021-09-18 | 2021-12-10 | 中航西安飞机工业集团股份有限公司 | Modular reconfigurable aircraft movable wing surface assembly tool and assembly method |
| CN114013680A (en) * | 2021-11-19 | 2022-02-08 | 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 |
| US20220153441A1 (en) * | 2020-11-18 | 2022-05-19 | The Boeing Company | Assembly line fabrication and assembly of aircraft wings |
-
2022
- 2022-06-20 CN CN202210695677.6A patent/CN115071997B/en active Active
Patent Citations (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005153102A (en) * | 2003-11-27 | 2005-06-16 | Fuji Heavy Ind Ltd | Wing spar assembling tool |
| EP2138402A2 (en) * | 2008-04-07 | 2009-12-30 | Multiprojekt Kft. | Variable modular docking system |
| CN101745905A (en) * | 2010-02-03 | 2010-06-23 | 北京航空航天大学 | Multi-degree of freedom adjustable assembling platform used for butt joint of aircraft wings |
| CN102092478A (en) * | 2010-12-30 | 2011-06-15 | 中国商用飞机有限责任公司 | Positioning device for butting wing body |
| CN103496449A (en) * | 2013-08-29 | 2014-01-08 | 北京航空航天大学 | Pose adjustment track planning method for plane side wall component assembling |
| CN103921116A (en) * | 2014-04-24 | 2014-07-16 | 浙江大学 | Flexible assembly system for aircraft panel |
| CN104647028A (en) * | 2014-12-29 | 2015-05-27 | 西北工业大学 | Digital assembly tooling of wing box |
| RU2657816C1 (en) * | 2016-07-05 | 2018-06-15 | Публичное акционерное общество "Туполев" | Method for assembling wing of flying apparatus |
| CN206125462U (en) * | 2016-11-03 | 2017-04-26 | 浙江日发航空数字装备有限责任公司 | Installation auxiliary assembly is connected to aircraft wing |
| CN206579861U (en) * | 2017-01-22 | 2017-10-24 | 艾雷奥特（江苏）飞机工业有限公司 | Small General Aircraft wing assembles support jig |
| US20210163153A1 (en) * | 2017-06-16 | 2021-06-03 | Mitsubishi Heavy Industries, Ltd. | Aircraft structure manufacturing device |
| CN107352044A (en) * | 2017-07-07 | 2017-11-17 | 浙江大学 | The layout method of large aircraft trailing edge component posture adjusting system |
| CN109204874A (en) * | 2017-11-16 | 2019-01-15 | 中国航空制造技术研究院 | One kind is for aircraft wing digitlization general assembly assembly system and its application method |
| CN108001708A (en) * | 2017-12-20 | 2018-05-08 | 西北工业大学 | A kind of aircraft wing docks posture adjustment reconfigurable device |
| US20200172267A1 (en) * | 2018-12-04 | 2020-06-04 | Airbus Sas | Transport and referencing carriage for wings of an aircraft |
| CN210212814U (en) * | 2019-07-02 | 2020-03-31 | 贵州弘安鑫晟航空科技有限责任公司 | Unmanned aerial vehicle wing assembly fixture of adaptable different wings |
| US20220153441A1 (en) * | 2020-11-18 | 2022-05-19 | The Boeing Company | Assembly line fabrication and assembly of aircraft wings |
| CN113524105A (en) * | 2021-06-30 | 2021-10-22 | 何怀彬 | Aircraft wing multi-angle freely adjusts assembly quality |
| CN113245813A (en) * | 2021-07-16 | 2021-08-13 | 成都飞机工业（集团）有限责任公司 | Self-positioning assembly system and method for rapid assembly of airplane |
| CN113772116A (en) * | 2021-09-18 | 2021-12-10 | 中航西安飞机工业集团股份有限公司 | Modular reconfigurable aircraft movable wing surface assembly tool and assembly method |
| CN114013680A (en) * | 2021-11-19 | 2022-02-08 | 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 |
Non-Patent Citations (1)
| Title |
|---|
| 王乾杰: "面向大型航空构件装配的异形垫片机器人加工系统设计与实现", 中国优秀硕士学位论文全文数据库工程科技II辑, no. 5, 15 May 2022 (2022-05-15), pages 13 - 65 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116443262A (en) * | 2023-06-14 | 2023-07-18 | 陕西德鑫智能科技有限公司 | Wing bracket, wing transferring and installing method |
| CN116443262B (en) * | 2023-06-14 | 2023-09-08 | 陕西德鑫智能科技有限公司 | Wing bracket, wing transferring and installing method |
| CN117508630A (en) * | 2024-01-04 | 2024-02-06 | 成都市鸿侠科技有限责任公司 | Size-adjustable aircraft side aileron assembly type frame |
| CN117508630B (en) * | 2024-01-04 | 2024-04-05 | 成都市鸿侠科技有限责任公司 | Size-adjustable aircraft side aileron assembly type frame |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115071997B (en) | 2024-06-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8220134B2 (en) | Flexible fastening machine tool | |
| US6877203B2 (en) | Device and method for fixation of airframe pieces | |
| CN115071997A (en) | Aircraft wing assembling device and method | |
| CN110125600B (en) | Welding positioning frame and tool with same | |
| CN105109706B (en) | One kind is used for aircraft thin-wall part positioning clamping experimental provision | |
| CN104760000A (en) | Vertical column type flexible tool of machine tool | |
| CN112570987B (en) | Flexible posture-adjusting and involuting tool and assembling method thereof | |
| CN112937907B (en) | Movable posture adjusting bracket for rear body of airplane | |
| CN111940977B (en) | Bogie frame manipulator welding fixture positioned by utilizing air spring guide post holes | |
| CN112373715A (en) | Device for mounting wing leading edge component of large aircraft | |
| CN106799554B (en) | Special welding jig system of air spring type full-load frame assembly | |
| CN112743029B (en) | Automatic drilling and riveting device and method | |
| CN206407165U (en) | A kind of undercarriage erecting device | |
| CN217368889U (en) | Equipment for automatically spraying large-scale overlong workpiece | |
| CN113102679B (en) | Flexible positioning frame for positioning aircraft wall plate | |
| CN112658560B (en) | Production equipment of guardrail cat ladder | |
| CN213411015U (en) | General frame of appearance equipment frock | |
| CN114394252A (en) | Solar unmanned aerial vehicle wing rib assembly pose adjusting system | |
| CN109357858B (en) | Car coupler coupling test bed | |
| CN210334939U (en) | Reconfigurable flexible tool for airplane framework | |
| CN109357860B (en) | Bend simulation mechanism, car coupler coupling test bed and test system thereof | |
| CN114323541B (en) | Train wind tunnel test system applying motion simulation device and attitude adjustment method | |
| CN220993123U (en) | Double-row multipoint controllable rolling type welding machine | |
| CN112498732B (en) | Multi-degree-of-freedom floating platform for narrow space assembly and assembly method | |
| CN218311716U (en) | Automobile top cover centering mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |