Ultrahigh component assembling system and method

Abstract

The ultrahigh component assembling system comprises a bottom base, the front end of the bottom base is slidably provided with a front sailing stand column in the length direction of the bottom base, the rear end of the bottom base is fixedly provided with a rear sailing stand column, and a top cross beam is arranged between the top end of the front sailing stand column and the top end of the rear sailing stand column in a spanning mode; a side framework is arranged at the bottom of the top cross beam, and the side framework is arranged on the bottom base in a sliding mode in the width direction of the bottom base; a plurality of wing root positioning devices are distributed on the top of the bottom base in the length direction, an aileron positioning device is arranged on one side of the aft stand column, a front part positioning device is arranged at the bottom of the top cross beam, and a beam positioning device is arranged on the side face of the side framework. According to the ultrahigh part assembling system, the ultrahigh part can be integrally positioned and fixed in a surrounding manner at a time, so that the ultrahigh part is integrally positioned, and the position precision of the ultrahigh part in the subsequent assembling process is effectively guaranteed.

Description

Technical Field

[0001] The present invention belongs to the technical field of positioning and assembling of ultra-high components, and particularly relates to an ultra-high component assembling system and an assembling method. Background Art

[0002] The process of aircraft component assembly is the key and core process of aircraft manufacturing, which largely determines key parameters such as the performance and service life of the aircraft. The assembly tooling system for assisting aircraft assembly is the most important process equipment in the aircraft assembly process, and its positioning accuracy, stiffness, etc. directly affect the quality of aircraft assembly.

[0003] For the high-precision assembly of ultra-large size, extra-long span ultra-high components, due to their large volume, long span, high height, and many positioning structures, how to quickly and stably position and fix the ultra-high components to ensure their position accuracy in the subsequent assembly process is a technical problem to be solved urgently.

[0004] In the prior art, usually the ultra-high components are divided into different parts, and each part is positioned and fixed separately, without positioning the entire ultra-high component at one time. This leads to the accumulation of positioning errors between each part, resulting in the final assembly positioning error of the entire ultra-high component exceeding the standard, and then affecting the normal assembly of the ultra-high component.

[0005] Therefore, in view of the above technical problems existing in the prior art, the present invention discloses an ultra-high component assembling system and an assembling method. Summary of the Invention

[0006] The present invention discloses an ultra-high component assembling system and an assembling method, which can integrally enclose and position and fix the ultra-high component at one time, thereby realizing the positioning of the entire ultra-high component and effectively ensuring the position accuracy of the ultra-high component in the subsequent assembly process.

[0007] The present invention is realized through the following technical solutions: An ultra-high component assembling system includes a bottom base. A front-aft column is slidably arranged along the length direction of the bottom base at the front end of the bottom base. A rear-aft column is fixedly arranged at the rear end of the bottom base. A top cross beam is spanned between the top ends of the front-aft column and the rear-aft column. A side skeleton is arranged at the bottom of the top cross beam, and the side skeleton is slidably arranged on the bottom base along the width direction of the bottom base. A plurality of wing root positioning devices are distributed along the length direction at the top of the bottom base. A aileron positioning device is arranged on one side of the rear-aft column. A front flap positioning device is arranged at the bottom of the top cross beam. A beam positioning device is arranged on the side surface of the side skeleton.

[0008] To better implement the present invention, further, the top cross beam includes a front flight cross beam and a rear flight cross beam. The front end of the front flight cross beam is slidably and cooperatively connected to the top of the front flight column along the length direction of the bottom base. The rear end of the rear flight cross beam is fixedly connected to the top of the rear flight column. The rear end of the front flight cross beam is fixedly butted against the front end of the rear flight cross beam.

[0009] To better implement the present invention, further, the side skeleton includes a side detachable frame, a side fixed frame, and a middle fixed frame. The side fixed frame is slidably arranged on one side of the bottom base along the length direction of the bottom base. A side detachable frame is arranged on the side of the side fixed frame close to the bottom base. A beam positioning device is arranged on one side of the side detachable frame. A middle fixed frame is arranged on the side of the side fixed frame away from the bottom base.

[0010] To better implement the present invention, further, the wing root positioning device includes a column component, a feeding part, and a wing root positioning part. The column component is arranged on the bottom base along the length direction of the bottom base. The top of the column component is provided with a feeding part that feeds towards the wing root. One end of the feeding part is provided with a wing root positioning part. The wing root positioning part includes a wing root point positioning part, a wing root surface positioning part, and a wing root hole positioning part.

[0011] To better implement the present invention, further, the aileron positioning device includes a spiral feeding part. A joint positioning part is arranged at the feeding end of the spiral feeding part. A side of the joint positioning part is provided with an aileron positioning pin.

[0012] To better implement the present invention, further, the front flap positioning device includes a slide rail support arm feeding device. At least one of a beam process hole positioning component, a drill jig positioning component, a skin positioning component, and a contour positioning component is arranged at the feeding end of the double slide rail support arm feeding device.

[0013] To better implement the present invention, further, the slide rail support arm feeding device includes a welding skeleton, a slider slide rail mechanism, a positioning block, a screw rod feeding mechanism, and a bottom plate. The bottom plate is connected to the bottom of the top cross beam. A welding skeleton is slidably arranged on one side of the bottom plate through the slider slide rail mechanism. A positioning block for restricting the sliding stroke of the welding skeleton is arranged on one side of the welding skeleton. A screw rod feeding mechanism is arranged in the middle of the welding skeleton. At least one of a beam process hole positioning component, a drill jig positioning component, a skin positioning component, and a contour positioning component is arranged at the feeding end of the screw rod feeding mechanism.

[0014] To better implement the present invention, further, the beam positioning device includes a slide rail support arm, a fork-shaped support, and a beam positioning assembly. The slide rail support arm is slidably disposed on one side of the side frame. One end of the slide rail support arm is provided with a fork-shaped support, and one end of the fork-shaped support is rotatably provided with a beam positioning assembly.

[0015] An ultra-high component assembly method includes the following steps: Step 1: Lift the bottom base to the positioning area and level the bottom base so that the level error of the bottom base relative to the horizontal plane is within ±0.3 mm; Step 2: Lift the front navigation column and the rear navigation column at the front and rear ends of the bottom base, and then lift the side frame in the area between the front navigation column and the rear navigation column; Step 3: Lift the top cross beam between the tops of the front navigation column and the rear navigation column, and slidably connect the front end of the top cross beam to the top of the front navigation column along the length direction of the bottom base; Step 4: Calibrate the tool ball coordinates with a laser tracker and establish a measurement coordinate system; Step 5: Initially install and finely adjust the wing root positioning device, aileron positioning device, front flap positioning device, and beam positioning device under the established measurement coordinate system; Step 6: Use a laser tracker to measure and adjust the positioning points, positioning holes, and positioning surfaces to a non-out-of-tolerance state with the reference tool ball as the reference; Step 7: Position and assemble the components through the wing root positioning device, aileron positioning device, front flap positioning device, and beam positioning device.

[0016] Compared with the prior art, the present invention has the following advantages and beneficial effects: (1) Aiming at the problem that it is difficult to ensure the positioning accuracy of the assembly system under ultra-high dimensions and ultra-long spans, the present invention adopts the design concept of "lightweight and high rigidity" and a truss-type frame structure based on the frame skeleton scheme, achieving high-precision assembly of ultra-high dimensions and ultra-long spans. Compared with the traditional frame structure of the same size, it has remarkable effects in enhancing the structural stiffness, reducing the weight, and lowering the cost; (2) Aiming at the problem that the tooling structure has a large cantilever V-shaped structure due to the "V"-shaped special-shaped structure with a large depth dimension of the ultra-high product, the present invention adopts a side truss + V-shaped frame structure based on the truss structure to realize the assembly of "V"-shaped special-shaped structure products with large depth dimensions; (3) Aiming at the problem that it is difficult for ultra-large components to be placed in a narrow space, the present invention adopts a design scheme of a frame-type side frame based on the truss structure and a reconfigurable slide rail support arm. By retracting the structure locator within the stroke of the slide rail support arm, the space for the wall panel to be lifted and lowered is effectively vacated, and a detachable frame alternative is set to further vacate the space for the component to be lifted and lowered, realizing the quick and accurate placement of ultra-large components in a narrow space. Brief Description of the Drawings

[0017] Figure 1 It is a schematic structural diagram of an ultra-high component assembly system; Figure 2 It is an installation schematic diagram of the bottom base; Figure 3 It is a schematic structural diagram of the wing root positioning device; Figure 4 It is a schematic structural diagram of the aileron positioning device; Figure 5 It is a schematic structural diagram of the leading edge flap positioning device; Figure 6 It is a schematic structural diagram of the slide rail arm feeding device; Figure 7 It is a schematic structural diagram of the side skeleton; Figure 8 It is a schematic structural diagram of the beam positioning device.

[0018] Wherein: 1 - bottom base; 2 - front flight column; 3 - rear flight column; 4 - top cross beam; 5 - side skeleton; 6 - wing root positioning device; 7 - aileron positioning device; 8 - leading edge flap positioning device; 9 - beam positioning device; 11 - front flight base; 12 - middle base; 13 - rear flight base; 31 - rear flight bottom column; 32 - rear flight top column; 33 - V-shaped skeleton; 41 - front flight cross beam; 42 - rear flight cross beam; 51 - side detachable frame; 52 - side fixed frame; 53 - middle fixed frame; 54 - support plate; 61 - column assembly; 62 - rib intersection positioning assembly; 63 - beam process hole positioning assembly; 64 - skin support assembly; 65 - beam intersection positioning assembly; 66 - surface support assembly; 67 - rib process hole positioning assembly; 71 - joint positioning piece; 72 - gasket; 73 - aileron positioning pin; 74 - spiral feeding part; 81 - slide rail arm feeding device; 82 - beam process hole positioning assembly; 83 - drill jig positioning assembly; 84 - skin positioning assembly; 85 - profile positioning assembly; 91 - slide rail arm; 92 - fork-shaped support; 93 - hinge pin; 94 - beam positioning assembly; 811 - welded skeleton; 812 - slider slide rail mechanism; 813 - positioning block; 814 - feeding assembly; 815 - hand wheel; 816 - bottom plate; 817 - trapezoidal screw. Detailed Description of the Invention

[0019] Embodiment 1: An ultra-high component assembly system according to this embodiment, such as Figure 1 and Figure 2As shown in the figure, it includes a bottom base 1. A front flight column 2 is slidably arranged along the length direction of the bottom base 1 at the front end of the bottom base 1. A rear flight column 3 is fixedly arranged at the rear end of the bottom base 1. A top cross beam 4 is spanned between the top ends of the front flight column 2 and the rear flight column 3. A side frame 5 is arranged at the bottom of the top cross beam 4. The side frame 5 is slidably arranged on the bottom base 1 along the width direction of the bottom base 1. A plurality of wing root positioning devices 6 are distributed along the length direction on the top of the bottom base 1. A aileron positioning device 7 is arranged on one side of the rear flight column 3. A front flap positioning device 8 is arranged at the bottom of the top cross beam 4. A beam positioning device 9 is arranged on the side surface of the side frame 5.

[0020] The front flight column 2 can slide along the length direction of the bottom base 1, thereby adjusting the distance between the front flight column 2 and the rear flight column 3 to adapt to the installation of top cross beams 4 with different spans. A side frame 5 is arranged on one side of the bottom base 1, and the bottom frame 5 can slide along the width direction of the bottom base 1 to adjust the support position of the side frame 5 in the width direction of the bottom base 1. The bottom base 1, the front flight column 2, the rear flight column 3, the top cross beam 4, and the side frame 5 constitute a support foundation for the ultra-high component, providing guarantee for the stable support of the ultra-high component.

[0021] The wing root area of the ultra-high component is positioned and fixed by a plurality of wing root positioning devices 6 arranged along the length direction on the top of the bottom base 1. The aileron area of the ultra-high component is positioned and fixed by the aileron positioning device 7. The front flap area of the ultra-high component is positioned and fixed by the front flap positioning device 8. The beam structure of the ultra-high component is positioned and fixed by the beam positioning device 9, thereby realizing the support and stable positioning of the entire ultra-high component, and further ensuring the position accuracy of the ultra-high component in the subsequent assembly process.

[0022] Embodiment 2: An ultra-high component assembly system, improved on the basis of Embodiment 1, as Figure 2 shown, the bottom base 1 includes a front flight base 11, a middle base 12, and a rear flight base 13 connected in sequence. The front flight column 2 is slidably arranged on the top of the front flight base 11 along the length direction of the bottom base 1. The rear flight column 3 is fixedly installed on the top of the rear flight base 13. The front flight base 11, the middle base 12, and the rear flight base 13 themselves can all slide along the length direction of the bottom base 1. Leveling pads 14 are arranged at the bottoms of the front flight base 11, the middle base 12, and the rear flight base 13. The levelness of the front flight base 11, the middle base 12, and the rear flight base 13 can be adjusted through the leveling pads 14.

[0023] Other parts of this embodiment are the same as those of Embodiment 1, so they will not be elaborated here.

[0024] Embodiment 3: An ultra-high component assembly system, improved on the basis of Embodiment 1 or 2, such as Figure 2 and Figure 4 As shown, the post-column 3 after flight includes a bottom post-column 31 after flight, a top post-column 32 after flight, and a V-shaped framework 33. The bottom post-column 31 after flight adopts an L-shaped structure to avoid the product. The top post-column 32 after flight adopts a trapezoidal + L-shaped structure and is fixedly connected and stands on the bottom post-column 31 after flight. The rear flight sides of the V-shaped framework 33 are fixedly connected to the bottom post-column 31 after flight and the top post-column 32 after flight respectively.

[0025] Other parts of this embodiment are the same as those of Embodiment 1 or 2, so they will not be described in detail here.

[0026] Embodiment 4: An ultra-high component assembly system, improved on the basis of any one of Embodiments 1-3, such as Figure 5 As shown, the top cross beam 4 includes a front cross beam 41 and a rear cross beam 42 after flight. The front end of the front cross beam 41 is slidably and cooperatively connected to the top of the front post-column 2 along the length direction of the bottom base 1. The rear end of the rear cross beam 42 after flight is fixedly connected to the top of the post-column 3 after flight. The rear end of the front cross beam 41 is fixedly butted against the front end of the rear cross beam 42.

[0027] Other parts of this embodiment are the same as any one of Embodiments 1-3, so they will not be described in detail here.

[0028] Embodiment 5: An ultra-high component assembly system, improved on the basis of any one of Embodiments 1-4, such as Figure 7 As shown, the side framework 5 includes a detachable side frame 51, a fixed side frame 52, and a fixed middle frame 53. The fixed side frame 52 is slidably arranged on one side of the bottom base 1 along the width direction of the bottom base 1. A detachable side frame 51 is arranged on the side of the fixed side frame 52 close to the bottom base 1. A beam positioning device 9 is arranged on one side of the detachable side frame 51; A fixed middle frame 53 is arranged on the side of the fixed side frame 52 away from the bottom base 1, and a support plate 54 is also welded and arranged on the fixed side frame 52.

[0029] Other parts of this embodiment are the same as any one of Embodiments 1-4, so they will not be described in detail here.

[0030] Embodiment 6: An ultra-high component assembly system, improved on the basis of any one of Embodiments 1-5, such as Figure 3As shown, the wing root positioning device 6 includes a column assembly 61, a feed part, and a wing root positioning part. The column assembly 61 is arranged on the bottom base 1 along the length direction of the bottom base 1. The top of the column assembly 61 is provided with a feed part for feeding toward the wing root. One end of the feed part is provided with a wing root positioning part. The wing root positioning part includes a wing root point positioning part, a wing root surface positioning part, and a wing root hole positioning part.

[0031] The wing root point positioning part includes a rib intersection positioning component 62 and a beam intersection positioning component 65. The rib intersection positioning component 62 is used to perform interference positioning on the wing root rib intersection, and the beam intersection positioning component 65 is used to perform interference positioning on the wing root beam intersection.

[0032] The wing root surface positioning portion includes a skin support assembly 64 and a surface support assembly 66. The skin support assembly 64 is used to perform contact support positioning on the skin, and the surface support assembly 66 is used to perform contact support positioning on the wing root positioning surface.

[0033] The wing root hole positioning part includes a beam process hole positioning component 63 and a rib process hole positioning component 67. The beam process hole positioning component 63 is used to be inserted and matched with the wing root beam process hole, and the rib process hole positioning component 67 is used to be inserted and matched with the wing root rib process hole, thereby realizing the positioning and fixation of the wing root.

[0034] The rest of this embodiment is the same as any one of Embodiments 1-5, and therefore will not be described again here.

[0035] Example 7: A super high component assembly system, improved on the basis of any one of embodiments 1-6, such as Figure 4 As shown, the aileron positioning device 7 includes a spiral feed portion 74. A joint positioning member 71 is provided at the feed end of the spiral feed portion 74. An aileron positioning pin 73 is provided on one side of the joint positioning member 71. A gasket 72 is provided between the joint positioning member 71 and the superelevation component. The gasket is 0.05 mm thick and is used to eliminate the gap between the joint positioning member 71 and the superelevation component. The spiral feed portion 74 is used to drive the joint positioning member 71 and the aileron positioning pin 73 toward the superelevation component. The joint positioning member 71 engages with the joint of the aileron region, and the aileron positioning pin 73 engages with the positioning hole of the aileron region to achieve positioning and fixation of the aileron region.

[0036] The rest of this embodiment is the same as any one of Embodiments 1-6, and therefore will not be described again here.

[0037] Example 8: An ultra-high component assembly system, improved on the basis of any one of embodiments 1-7, such as Figure 5As shown, the front panel positioning device 8 includes a slide rail support arm feeding device 81, and at least one of a beam process hole positioning assembly 82, a drill jig positioning assembly 83, a skin positioning assembly 84, and a contour positioning assembly 85 is provided at the feeding end of the double slide rail support arm feeding device 81.

[0038] Further, as Figure 6 shown, the slide rail support arm feeding device 81 includes a welded framework 811, a slider slide rail mechanism 812, a positioning block 813, a lead screw feeding mechanism, and a bottom plate 816. The bottom plate 816 is connected to the bottom of the top cross beam 4. One side of the bottom plate 816 is slidably provided with a welded framework 811 through the slider slide rail mechanism 812. A positioning block 813 for restricting the sliding stroke of the welded framework 811 is provided on one side of the welded framework 811. A lead screw feeding mechanism is provided in the middle of the welded framework 811, and at least one of a beam process hole positioning assembly 82, a drill jig positioning assembly 83, a skin positioning assembly 84, and a contour positioning assembly 85 is provided at the feeding end of the lead screw feeding mechanism. The beam process hole positioning assembly 82 is used to be inserted into the beam process hole for positioning. The drill jig positioning assembly 83 is used to contact the drill jig surface for positioning. The skin positioning assembly 84 is used to contact the skin for positioning. The contour positioning assembly 85 is used to contact the front panel contour surface for positioning.

[0039] Further, as Figure 6 shown, the lead screw feeding mechanism includes a feeding assembly 814, a handwheel 815, and a trapezoidal screw 817. The feeding assembly 814 includes a mounting frame and a first bevel gear and a second bevel gear that are meshed with each other inside the mounting frame. The first bevel gear is provided at one end of the trapezoidal screw 817, and the second bevel gear is provided at one end of the rotating shaft of the handwheel 815. By rotating the handwheel 815, the trapezoidal screw 817 can be driven to rotate through the meshing structure of the first bevel gear and the second bevel gear, and then the trapezoidal screw 817 can be driven to feed through the thread matching structure between the threaded hole on the welded framework 811 and the trapezoidal screw 817. At the same time, by setting the slider slide rail mechanism 812, rapid secondary feeding can be achieved.

[0040] Other parts of this embodiment are the same as any one of Embodiments 1-7, so they will not be described in detail here.

[0041] Embodiment 9: A super-high component assembly system, improved on the basis of any one of Embodiments 1-8, as Figure 7 and Figure 8As shown in the figure, the beam positioning device 9 includes a slide rail support arm 91, a fork-shaped support 92, and a beam positioning assembly 94. The slide rail support arm 91 is slidably arranged on one side of the side frame 5. One end of the slide rail support arm 91 is provided with a fork-shaped support 92. One end of the fork-shaped support 92 is provided with a hinge pin 93. The beam positioning assembly 94 is rotatably connected to the hinge pin 93. The positioning end of the beam positioning assembly 94 is provided with any one of a positioning pin, a positioning card, and a positioning plate.

[0042] Other parts of this embodiment are the same as any one of Embodiments 1-8, so they will not be described in detail here.

[0043] Embodiment 10: A method for assembling ultra-high components, implemented based on an ultra-high component assembly system, includes the following steps: Step 1: Lift the bottom base 1 to the positioning area and level the bottom base 1 so that the level error of the bottom base 1 relative to the horizontal plane is within ±0.3 mm. Step 2: Lift the front navigation column 2 and the rear navigation column 3 at the front and rear ends of the bottom base 1, and then lift the side frame 5 in the area between the front navigation column 2 and the rear navigation column 3. Step 3: Lift the top cross beam 4 between the tops of the front navigation column 2 and the rear navigation column 3, and slidably connect the front end of the top cross beam 4 to the top of the front navigation column 2 along the length direction of the bottom base 1. Step 4: Calibrate the tool ball coordinates with a laser tracker and establish a measurement coordinate system. Step 5: Preliminarily install and finely adjust the wing root positioning device 6, aileron positioning device 7, front flap positioning device 8, and beam positioning device 9 under the established measurement coordinate system. Step 6: Use a laser tracker to measure and adjust the positioning points, positioning holes, and positioning surfaces to a non-out-of-tolerance state with the reference tool ball as the reference. Step 7: Position and assemble the components through the wing root positioning device 6, aileron positioning device 7, front flap positioning device 8, and beam positioning device 9.

[0044] As described above, these are only the preferred embodiments of the present invention, and do not impose any formal limitations on the present invention. Any simple modifications and equivalent changes made to the above embodiments based on the technical essence of the present invention all fall within the protection scope of the present invention.

Claims

1. An ultra-high component assembly system, characterized in that, It includes a bottom base (1), a front flight column (2) is slidably arranged along the length direction of the bottom base (1) at the front end of the bottom base (1), a rear flight column (3) is fixedly arranged at the rear end of the bottom base (1), a top cross beam (4) is spanned between the top ends of the front flight column (2) and the rear flight column (3), a side skeleton (5) is arranged at the bottom of the top cross beam (4), and the side skeleton (5) is slidably arranged on the bottom base (1) along the width direction of the bottom base (1); a plurality of wing root positioning devices (6) are distributed along the length direction at the top of the bottom base (1), a aileron positioning device (7) is arranged on one side of the rear flight column (3), a front flap positioning device (8) is arranged at the bottom of the top cross beam (4), and a beam positioning device (9) is arranged on the side surface of the side skeleton (5).

2. The ultra-high component assembly system according to claim 1, characterized in that, The top cross beam (4) includes a front flight cross beam (41) and a rear flight cross beam (42). The front end of the front flight cross beam (41) is slidably and cooperatively connected with the top of the front flight column (2) along the length direction of the bottom base (1), the rear end of the rear flight cross beam (42) is fixedly connected with the top of the rear flight column (3), and the rear end of the front flight cross beam (41) is fixedly butted with the front end of the rear flight cross beam (42).

3. The ultra-high component assembly system according to claim 1, characterized in that, The side skeleton (5) includes a side detachable frame (51), a side fixed frame (52), and a middle fixed frame (53). The side fixed frame (52) is slidably arranged on one side of the bottom base (1) along the width direction of the bottom base (1), a side detachable frame (51) is arranged on the side of the side fixed frame (52) close to the bottom base (1), and a beam positioning device (9) is arranged on one side of the side detachable frame (51); a middle fixed frame (53) is arranged on the side of the side fixed frame (52) far from the bottom base (1).

4. An ultra-high component assembly system according to claim 1, characterized in that, The wing root positioning device (6) includes a column component (61), a feeding part, and a wing root positioning part. The column component (61) is arranged on the bottom base (1) along the length direction of the bottom base (1), a feeding part for feeding towards the wing root is arranged at the top of the column component (61), a wing root positioning part is arranged at one end of the feeding part, and the wing root positioning part includes a wing root point positioning part, a wing root surface positioning part, and a wing root hole positioning part.

5. An ultra-high component assembly system according to claim 1, characterized in that, The aileron positioning device (7) includes a spiral feeding part (74), a joint positioning part (71) is arranged at the feeding end of the spiral feeding part (74), and an aileron positioning pin (73) is arranged on one side of the joint positioning part (71).

6. The ultra-high component assembly system according to claim 1, characterized in that, The front flap positioning device (8) includes a slide rail support arm feeding device (81), and at least one of a beam process hole positioning component (82), a drill die positioning component (83), a skin positioning component (84), and a profile positioning component (85) is arranged at the feeding end of the double slide rail support arm feeding device (81).

7. An ultra-high component assembly system according to claim 1, characterized in that, The slide rail support arm feeding device (81) includes a welding skeleton (811), a slider slide rail mechanism (812), a positioning block (813), a lead screw feeding mechanism, and a bottom plate (816). The bottom plate (816) is connected to the bottom of the top cross beam (4). One side of the bottom plate (816) is slidably provided with a welding skeleton (811) through a slider slide rail mechanism (812). One side of the welding skeleton (811) is provided with a positioning block (813) for restricting the sliding stroke of the welding skeleton (811). The middle of the welding skeleton (811) is provided with a lead screw feeding mechanism. The feeding end of the lead screw feeding mechanism is provided with at least one of a beam process hole positioning component (82), a drill jig positioning component (83), a skin positioning component (84), and an outer shape positioning component (85).

8. An ultra-high component assembly system according to claim 1, characterized in that, The beam positioning device (9) includes a slide rail support arm (91), a fork-shaped support (92), and a beam positioning component (94). The slide rail support arm (91) is slidably arranged on one side of the side skeleton (5). One end of the slide rail support arm (91) is provided with a fork-shaped support (92). One end of the fork-shaped support (92) is rotatably provided with a beam positioning component (94).

9. A method for assembling ultra-high components, implemented based on the ultra-high component assembly system according to any one of claims 1-8, characterized in that, It includes the following steps: Step 1: Lift the bottom base (1) to the positioning area and level the bottom base (1) so that the level error of the bottom base (1) relative to the horizontal plane is within ±0.3 mm; Step 2: Lift the front flight column (2) and the rear flight column (3) at the front and rear ends of the bottom base (1), and then lift the side skeleton (5) in the area between the front flight column (2) and the rear flight column (3); Step 3: Lift the top cross beam (4) between the tops of the front flight column (2) and the rear flight column (3), and slidably connect the front end of the top cross beam (4) to the top of the front flight column (2) along the length direction of the bottom base (1); Step 4: Calibrate the tool ball coordinates with a laser tracker and establish a measurement coordinate system; Step 5: Initially install and finely adjust the wing root positioning device (6), aileron positioning device (7), front flap positioning device (8), and beam positioning device (9) under the established measurement coordinate system; Step 6: Use a laser tracker, with the reference tool ball as the reference, measure and adjust the positioning points, positioning holes, and positioning surfaces to a non-out-of-tolerance state; Step 7: Position and assemble the components through the wing root positioning device (6), aileron positioning device (7), front flap positioning device (8), and beam positioning device (9).

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