Butt-joint assembly error elimination method for large fuselage barrel section
By combining the methods of benchmark drilling and hole enlargement, secondary positioning of the stringer locator, and laser ranging system, the problem of error elimination during the docking of large fuselage sections was solved, achieving efficient and accurate control of key elements of the docking interface and improving production efficiency and economy.
Patent Information
- Application Number
- CN202511665866.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-11-14
- Publication Date
- 2026-02-06
AI Technical Summary
During the docking process of large fuselage barrel sections, traditional tooling cannot adjust the attitude, which makes it easy for key elements of the aircraft docking interface to exceed tolerances after assembly. Digital tooling is costly and inefficient, making it difficult to achieve low-cost and efficient error elimination.
A combination of a reference drilling jig, a stringer locator for secondary positioning, and a laser ranging system is used to ensure the accuracy of key elements at the docking interface by eliminating accumulated errors through hole reaming, fine-tuning with the stringer locator for secondary positioning, and fine-tuning with the laser ranging system.
It significantly improves the accuracy of laser measurement references and key elements of the docking interface, reduces the difficulty of assembly coordination, increases production efficiency and labor productivity, and has good economic benefits.
Smart Images
Figure CN121469880A_ABST
Abstract
Description
Technical Field
[0001] This application relates to a method for eliminating assembly errors in the docking of large fuselage barrel sections, which belongs to the field of aircraft manufacturing. Background Technology
[0002] The docking interface of large fuselage sections is complex in shape, with some structures being non-rigid. Key elements (such as the outline of the cover plate, the position of the stringer, and the position of the slide rails) require high precision, making control difficult. Currently, the docking of large fuselage sections is mainly accomplished using traditional or digital docking fixtures. Using traditional fixtures makes it impossible to adjust the attitude of the section, and the key elements of the aircraft docking interface are prone to exceeding tolerances after assembly. Digital docking fixtures are complex in structure, expensive, and have a slow attitude adjustment process, resulting in low assembly efficiency. Therefore, there is an urgent need for technological innovation to find a low-cost method for eliminating assembly errors in the docking of large fuselage sections. Summary of the Invention
[0003] According to one aspect of this application, a method for eliminating assembly errors in the docking of large fuselage sections is provided, comprising the following steps:
[0004] (1) Use a reference drill jig to enlarge the reference holes on the floor beams of the front and rear barrel sections;
[0005] The reference drill jig includes a base 1, a handle 2, a positioning pin 3, a locking nut 4, and a drill sleeve 5;
[0006] The floor beams of the front and rear barrel sections each have two corresponding reference holes.
[0007] The base 1 is provided with a positioning hole, which cooperates with the positioning pin 3 and the locking nut 4 to realize the positioning and locking of the reference drill jig;
[0008] The handle 2 is connected to the base 1 by screws, which is used to assist the operator in disassembling and assembling the drill jig;
[0009] The positioning pin 3 is used for positioning the base 1;
[0010] The locking nut 4 is threadedly connected to the positioning pin 3 and is used to clamp and fasten the base 1.
[0011] The drill sleeve 5 is connected to the base 1 and is used for drilling operations to ensure the position and perpendicularity of the reference hole.
[0012] The MA1, MA2, MA3, and MA4 reference holes for the large fuselage section are located on the floor beam. After the floor beam assembly, lower half-shell floor mounting, upper and lower half-shell assembly, and final assembly docking stages, cumulative errors occur, affecting the laser measurement results of key elements at the product's docking interface. Therefore, eliminating reference hole errors is crucial to ensuring the accuracy of the aircraft fuselage section docking interface.
[0013] To ensure the accuracy of the aircraft's MA1, MA2, MA3, and MA4 reference points after the barrel sections are joined, the reference holes on the floor beams are designed with allowance during the assembly process before joining. The floor beam assembly fixture is designed with a fixture locator based on the dimensions of the allowance holes.
[0014] Four drilling jigs are designed on the assembly docking fixture for the fuselage barrel section. After the mid-front / mid-rear barrel section is positioned, the reference hole of the crossbeam is enlarged to the final hole through the drilling jig to eliminate the accumulated error in the previous assembly stage and ensure that the reference positions of the aircraft barrel sections MA1, MA2, MA3, and MA4 after docking meet the drawing requirements.
[0015] (2) During the docking process of the front barrel section, the middle barrel section and the rear barrel section, after the long string is positioned at the wall panel, a part of the docking part between the barrel sections is left without drilling. After docking, the long string positioner is used to perform secondary positioning of the long string end, and drilling, gluing and riveting are completed.
[0016] The stringer positioner includes a stringer positioner body 6, a handle nut 7, and a locking plate 8.
[0017] The stringer positioner body 6 includes a stringer positioning surface and a fixed positioning pin.
[0018] The stringer positioning surface is used to position the web surface of the stringer.
[0019] Two fixed positioning pins are provided on the main body 6 of the stringer locator, and the positioning and locking of the main body 6 of the stringer locator on the clamping plate 8 are realized by the handle nut 7.
[0020] To ensure the positional accuracy of the girder at the barrel section docking interface, after the girder is positioned at the wall panel location, the docking point is retained.
[0021] No holes will be drilled in certain areas of the interface. Considering that the assembly stress does not exceed 20 pounds, and to reduce the amount of work required, the area to be drilled is limited to a frame spacing range.
[0022] The stringer end is repositioned using the stringer locator in the final assembly fixture, followed by drilling, gluing, and riveting. This method, combined with a process-compensated method for eliminating assembly errors using reference holes, significantly improves the stringer's positional accuracy.
[0023] The docking interface is equipped with a total of 68 long-strut positioners.
[0024] (3) During the overall docking process, the positions of the front and rear sections of the barrel are controlled by two laser emitters and two laser receivers installed on the ear holes of the front and middle sections of the barrel and two laser emitters and two laser receivers installed on the ear holes of the rear and middle sections of the barrel.
[0025] During fuselage section docking, the heading positions of the forward and aft sections need to be fine-tuned to align with the reference points. The laser ranging system consists of four laser transmitters and four receivers. The laser transmitters are installed on the skin lug holes of the forward / aft section, two at the front and two at the rear.
[0026] At the fuselage section assembly and docking station, after the front and rear mid-sections are mounted, the sections are adjusted to their docking positions using tooling, and the laser emitters are installed on the skin lug holes. The laser emission ranging system is activated, with two emitters on each side. The circumferential positioning of the emitters is adjusted using readings on the control panel. Then, referring to the data deviation on the control interface, the positions of the front and rear mid-sections are fine-tuned to ensure that the heading deviation of the sections meets the drawing requirements. Applying this method can significantly improve the accuracy of the laser measurement reference, thereby improving the accuracy of key elements at the product docking interface.
[0027] The two laser emitters installed on the ear plate holes of the middle and front barrel section skin are matched with the two laser receivers installed on the ear plate holes of the middle and rear barrel section skin.
[0028] The two laser receivers installed on the ear plate holes of the front and middle sections of the barrel are matched with the two laser emitters installed on the ear plate holes of the rear and middle sections of the barrel.
[0029] This application discloses a control method for key elements of the docking interface of large fuselage barrel sections, applicable to the docking of large commercial aircraft fuselage barrel sections. It reduces the difficulty of assembly coordination, significantly improves the product quality of the docking interface, increases assembly efficiency and labor productivity, and can meet the needs of rapid capacity expansion for docking of large fuselage barrel sections.
[0030] This application has the following advantages over the prior art:
[0031] 1. This application can be used for the assembly of barrel sections in large commercial aircraft, which can significantly improve the accuracy of laser measurement reference, the accuracy of key elements of the docking interface, and production efficiency;
[0032] 2. This application has strong versatility and can be applied to the control of key elements of the docking interface of barrel sections in various types of large commercial aircraft;
[0033] 3. This application has low application cost, is easy to implement, and has good economic benefits. Attached Figure Description
[0034] Figure 1 This is a schematic diagram of the docking and assembly of a large fuselage barrel section.
[0035] Figure 2 It is a tooling for docking traditional large aircraft barrel sections.
[0036] Figure 3This is a schematic diagram showing the locations of the reference holes for the floor beam, where MA1, MA2, MA3, and MA4 are four reference holes.
[0037] Figure 4 A schematic diagram of the docking and assembly process of a large fuselage section.
[0038] Figure 5 This is a schematic diagram showing the location of the reference hole for the floor beam.
[0039] Figure 6 Schematic diagram of the reference drill jig.
[0040] Figure 7 The diagram shows the base 1, where a is the top view, b is the side view, and c is the front view.
[0041] Figure 8 This is a schematic diagram of handle 2, where a is a side view, b is a top view, and c is a front view.
[0042] Figure 9 This is a schematic diagram of locating pin 3, where a is the top view, b is the side view, and c is the front view.
[0043] Figure 10 This is a schematic diagram of the locking nut 4, where a is the front view, b is the side view, and c is the top view.
[0044] Figure 11 This is a schematic diagram of drill sleeve 5, where a is the front view, b is the side view, and c is the top view.
[0045] Figure 12 This is a schematic diagram of the area where holes are not drilled.
[0046] Figure 13 A schematic diagram of secondary positioning of the end of the stringer.
[0047] Figure 14 This is a schematic diagram of the overall process of using the stringer positioner.
[0048] Figure 15 This is a schematic diagram of a stringer locator.
[0049] Figure 16 The diagram shows the main body 6 of the stringer locator, where a is the front view, b is the side view, and c is the top view.
[0050] Figure 17 The diagram shows the handle nut 7, where a is the top view, b is the side view, and c is the front view.
[0051] Figure 18 This is a schematic diagram of the distribution of a laser ranging system.
[0052] Figure 19 This is a schematic diagram of a laser transmitter and a laser receiver.
[0053] The components include: 1. base, 2. handle, 3. positioning pin, 4. locking nut, 5. drill bushing, 6. long stringer positioner body, 7. handle nut, and 8. clamping plate. Detailed Implementation
[0054] The present application is described in detail below with reference to the embodiments, but the present application is not limited to these embodiments.
[0055] Example 1
[0056] A method for eliminating assembly errors in the docking of large fuselage sections includes the following steps:
[0057] (1) Use a reference drill jig to enlarge the reference holes on the floor beams of the front and rear barrel sections;
[0058] The reference drill jig includes a base 1, a handle 2, a positioning pin 3, a locking nut 4, and a drill sleeve 5;
[0059] The floor beams of the front and rear barrel sections each have two corresponding reference holes.
[0060] The base 1 is provided with a positioning hole, which cooperates with the positioning pin 3 and the locking nut 4 to realize the positioning and locking of the reference drill jig;
[0061] The handle 2 is connected to the base 1 by screws, which is used to assist the operator in disassembling and assembling the drill jig;
[0062] The positioning pin 3 is used for positioning the base 1;
[0063] The locking nut 4 is threadedly connected to the positioning pin 3 and is used to clamp and fasten the base 1.
[0064] The drill sleeve 5 is connected to the base 1 and is used for drilling operations to ensure the position and perpendicularity of the reference hole.
[0065] The MA1, MA2, MA3, and MA4 reference holes for the large fuselage section are located on the floor beam. After the floor beam assembly, lower half-shell floor mounting, upper and lower half-shell assembly, and final assembly docking stages, cumulative errors occur, affecting the laser measurement results of key elements at the product's docking interface. Therefore, eliminating reference hole errors is crucial to ensuring the accuracy of the aircraft fuselage section docking interface.
[0066] To ensure the accuracy of the aircraft's MA1, MA2, MA3, and MA4 reference points after the barrel sections are joined, the reference holes on the floor beams are designed with allowance during the assembly process before joining. The floor beam assembly fixture is designed with a fixture locator based on the dimensions of the allowance holes.
[0067] Four drilling jigs are designed on the assembly docking fixture for the fuselage barrel section. After the mid-front / mid-rear barrel section is positioned, the reference hole of the crossbeam is enlarged to the final hole through the drilling jig to eliminate the accumulated error in the previous assembly stage and ensure that the reference positions of the aircraft barrel sections MA1, MA2, MA3, and MA4 after docking meet the drawing requirements.
[0068] (2) During the docking process of the front barrel section, the middle barrel section and the rear barrel section, after the long string is positioned at the wall panel, a part of the docking part between the barrel sections is left without drilling. After docking, the long string positioner is used to perform secondary positioning of the long string end, and drilling, gluing and riveting are completed.
[0069] The stringer positioner includes a stringer positioner body 6, a handle nut 7, and a locking plate 8.
[0070] The stringer positioner body 6 includes a stringer positioning surface and a fixed positioning pin.
[0071] The stringer positioning surface is used to position the web surface of the stringer.
[0072] Two fixed positioning pins are provided on the main body 6 of the stringer locator, and the positioning and locking of the main body 6 of the stringer locator on the clamping plate 8 are realized by the handle nut 7.
[0073] To ensure the positional accuracy of the girder at the barrel section docking interface, after the girder is positioned at the wall panel location, the docking point is retained.
[0074] No holes will be drilled in certain areas of the interface. Considering that the assembly stress does not exceed 20 pounds, and to reduce the amount of work required, the area to be drilled is limited to a frame spacing range.
[0075] The stringer end is repositioned using the stringer locator in the final assembly fixture, followed by drilling, gluing, and riveting. This method, combined with a process-compensated method for eliminating assembly errors using reference holes, significantly improves the stringer's positional accuracy.
[0076] The docking interface is equipped with a total of 68 long-strut positioners.
[0077] (3) During the overall docking process, the positions of the front and rear sections of the barrel are controlled by two laser emitters and two laser receivers installed on the ear holes of the front and middle sections of the barrel and two laser emitters and two laser receivers installed on the ear holes of the rear and middle sections of the barrel.
[0078] During fuselage section docking, the heading positions of the forward and aft sections need to be fine-tuned to align with the reference points. The laser ranging system consists of four laser transmitters and four receivers. The laser transmitters are installed on the skin lug holes of the forward / aft section, two at the front and two at the rear.
[0079] At the fuselage section assembly and docking station, after the front and rear mid-sections are mounted, the sections are adjusted to their docking positions using tooling, and the laser emitters are installed on the skin lug holes. The laser emission ranging system is activated, with two emitters on each side. The circumferential positioning of the emitters is adjusted using readings on the control panel. Then, referring to the data deviation on the control interface, the positions of the front and rear mid-sections are fine-tuned to ensure that the heading deviation of the sections meets the drawing requirements. Applying this method can significantly improve the accuracy of the laser measurement reference, thereby improving the accuracy of key elements at the product docking interface.
[0080] The two laser emitters installed on the ear plate holes of the middle and front barrel section skin are matched with the two laser receivers installed on the ear plate holes of the middle and rear barrel section skin.
[0081] The two laser receivers installed on the ear plate holes of the front and middle sections of the barrel are matched with the two laser emitters installed on the ear plate holes of the rear and middle sections of the barrel.
[0082] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any modifications or substitutions made by those skilled in the art within the scope of the technology disclosed in this application should be covered within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A method for eliminating assembly errors in the docking of large fuselage sections, characterized in that, The process includes the following: (1) Use a reference drill jig to enlarge the reference holes on the floor beams of the front and rear barrel sections; The reference drill jig includes a base 1, a handle 2, a positioning pin 3, a locking nut 4, and a drill sleeve 5; (2) During the docking process of the front barrel section, the middle barrel section and the rear barrel section, after the long string is positioned at the wall panel, a part of the docking part between the barrel sections is left without drilling. After docking, the long string positioner is used to perform secondary positioning of the long string end, and drilling, gluing and riveting are completed. The stringer positioner includes a stringer positioner body 6, a handle nut 7, and a locking plate 8. (3) During the overall docking process, the positions of the front and rear sections of the barrel are controlled by two laser emitters and two laser receivers installed on the ear holes of the front and middle sections of the barrel and two laser emitters and two laser receivers installed on the ear holes of the rear and middle sections of the barrel.
2. The method for eliminating assembly errors in the docking of large fuselage sections according to claim 1, characterized in that, The floor beams of the front and rear barrel sections each have two corresponding reference holes.
3. The method for eliminating assembly errors in the docking of large fuselage sections according to claim 2, characterized in that, The base 1 is provided with a positioning hole, which cooperates with the positioning pin 3 and the locking nut 4 to realize the positioning and locking of the reference drill jig; The handle 2 is connected to the base 1 by screws, which is used to assist the operator in disassembling and assembling the drill jig; The positioning pin 3 is used for positioning the base 1; The locking nut 4 is threadedly connected to the positioning pin 3 and is used to clamp and fasten the base 1. The drill sleeve 5 is connected to the base 1 and is used for drilling operations to ensure the position and perpendicularity of the reference hole.
4. The method for eliminating assembly errors in the docking of large fuselage sections according to claim 3, characterized in that, The stringer positioner body 6 includes a stringer positioning surface and a fixed positioning pin. The stringer positioning surface is used to position the web surface of the stringer. Two fixed positioning pins are provided on the main body 6 of the stringer locator, and the positioning and locking of the main body 6 of the stringer locator on the clamping plate 8 are realized by the handle nut 7.
5. The method for eliminating assembly errors in the docking of large fuselage sections according to claim 4, characterized in that, The two laser emitters installed on the ear plate holes of the middle and front barrel section skin are matched with the two laser receivers installed on the ear plate holes of the middle and rear barrel section skin. The two laser receivers installed on the ear plate holes of the front and middle sections of the barrel are matched with the two laser emitters installed on the ear plate holes of the rear and middle sections of the barrel.