Process method for integrally manufacturing aircraft assembly parts without disassembly

Abstract

The invention discloses a process method for integrally manufacturing aircraft assembly parts without disassembly. The process method comprises the following steps of: coating a sealant on a binding surface of each component of a certain aircraft connecting part; maintaining the sealing glue joint state, installing the product in the assembly fixture, and completing global positioning of the product, the assembly fixture and the drilling equipment; assembly connecting holes are prepared in the hole making positions based on non-contact high-energy laser beams; quantitative characterization is carried out on the drilling result, and the supplementary machining allowance is determined; fastening piece installation is completed on each hole site in the hole forming molded surface; sealant coating on the fastening piece in the connecting part and the area outside the joint of the binding face is completed; and disassembling and separating the connected and formed integral part and the assembly fixture, and transferring to a part butt-joint to-be-assembled area. The non-contact high-energy laser beam is used for replacing a traditional tool for cutting machining, the process characteristic of high precision and no pollution is used for forbidding the process of repeated disassembly and reset in the aircraft component assembling link, the assembling process is simplified, and the assembling quality is efficiently guaranteed.

Description

Technical Field

[0001] The present invention relates to the field of, but is not limited to, automated hole-making technology, and in particular to a process for integrally manufacturing aircraft assembly parts without requiring disassembly. Background Art

[0002] Aircraft assembly hole making is a crucial step in the overall aircraft manufacturing process, involving the assembly of components with different structures and functions into a complete unit through mechanical connection, welding, gluing, and other methods. Rivets and bolts are commonly used in aircraft assembly, and both require the machining of holes in the connected components.

[0003] The machining of these connection holes is the largest single-process operation and the final, critical step involving material removal. To ensure precise connections between aircraft components, this process requires that the holes be machined while maintaining the assembly position. However, existing hole-making processes inevitably generate metal debris and process media. These artifacts can adhere to the mating interfaces of the assembled components, severely impacting the performance of subsequent connections. Therefore, auxiliary cleaning methods are necessary to remove these artifacts before achieving the final assembly state. Due to this technical difficulty, the hole-making process must employ a pre-connection-then-disassembly approach: after the hole is machined, the various assembly components must be disassembled one by one, cleaned, and then reassembled. This repeated disassembly and assembly process not only significantly reduces production cycle efficiency, but also reduces assembly accuracy due to adjustment errors, resulting in significant waste of manpower and resources. Consequently, this technical challenge has become a significant bottleneck hindering improvements in aircraft assembly efficiency and quality. Summary of the Invention

[0004] In order to promote the unidirectional optimization of the assembly process and innovate the traditional assembly process, it is necessary to develop a process method for the integrated manufacturing of aircraft assembly parts without disassembly, effectively avoiding the necessity of repeatedly putting assembly components on the shelf for repair, thereby significantly reducing the complexity of the assembly process and the frequency of rework.

[0005] In order to solve the above problems, the present invention provides a process method for the integrated manufacturing of aircraft assembly parts without disassembly, so as to solve the problem in the prior art that low manufacturing precision causes the connection parts to need to be repeatedly disassembled and reset, seriously affecting the production cycle.

[0006] A process for integrally manufacturing aircraft assembly parts without disassembly, comprising: Step 1: Apply sealant to the mating surfaces of each component of an aircraft connection part to form an assembled component, ensuring that the sealant fully covers the mating areas of the components and is continuously squeezed out from the seams of small components; Step 2, keep the current seal of the assembly component installed in the assembly jig, and complete the global positioning of the assembly component-assembly jig-hole making equipment; Step 3, based on the non-contact high-energy laser beam, the assembly connection hole of the assembly component is prepared; Step 4, the quantitative characterization of the hole making result is performed by the self-adaptive detection unit, the allowance for reprocessing is determined, and the reprocessing is completed; Step 5, the fastener installation is completed for each connection hole position in the product assembly connection component; Step 6, the sealant coating of the fastener, the joint surface seam and the outer area is completed; Step 7, the connected and shaped overall connection component is separated from the assembly jig and transferred to the component butt joint area to be assembled.

[0007] Preferably, the step 1 joint surface sealing process comprises: Step 11, uniformly coat the joint surface with sealant, and keep the shape of the sealant after coating, with the ability of automatic flowing and filling; Step 12, each connection component is adhered to the specified position according to the overall component configuration; Step 13, according to the design file, the installation of the temporary fastener at the specified position is completed, and the joint surface sealant is kept bubble-free and gap-free.

[0008] Preferably, the step 2 global positioning method comprises: Step 21, through the assembly jig positioning device such as positioning pin, cup cone locator, the assembly jig is fixed in the global coordinate system of the hole making station; Step 22, through the space coordinate measuring instrument, the space fitting of the assembly jig coordinate and the coordinate system of the hole making equipment is completed; Step 23, according to the specified installation method in the design file, the assembly component with pre-gluing is installed in the assembly jig, and the position is fixed by relying on the mechanical limit in the assembly jig; Step 24, through the coordinate sensing module in the end effector of the hole making equipment, the coordinates of the positioning target in the outer shape surface of the assembly component are identified, and the fitting of the assembly component and the coordinate system of the hole making equipment is completed.

[0009] Preferably, the step 3 of preparing the assembly connection hole of the assembly component based on the non-contact high-energy laser beam comprises: Step 31, through the normal alignment module in the end effector of the equipment, the current posture of the hole making equipment is adjusted, so that the irradiation direction of the high-energy laser beam is the normal direction of the assembly component; Step 32, through the pressure foot module in the end effector of the hole making equipment, the assembly component structure at the current hole making position is locally pressed; Step 33, the assembly component is obliquely cut by the high-energy laser beam coupling module in the end effector of the hole making equipment, and a circular spiral scan is performed until a conical blind hole type surface is formed; Step 34, adjust the normal posture of the high-energy laser beam coupling module in the end effector of the hole making equipment for the hole making position, keep the posture and perform circular cutting straight hole processing with the center of the conical blind hole as the center, until a complete assembly through hole is formed.

[0010] If the type of the hole to be machined is a countersunk round straight hole, the above steps are executed; if the type of the hole to be machined is a round straight hole, the above steps 31, 32 and 34 are executed.

[0011] Preferably, the quantitative characterization type of the hole making result in step 4 includes: The detection items of the protruding head riveting / screwing hole include hole diameter, hole wall roughness and hole roundness. The detection items of the countersunk riveting / screwing hole include hole diameter, hole wall roughness, hole roundness, countersunk depth and countersunk surface roughness. The measurement positions of the hole diameter include multiple position points such as the inlet of the upper plate hole, the outlet of the upper plate hole, the inlet of the lower plate hole and the outlet of the lower plate hole, and the measurement angles include 0°, 45°, 90° and 135°.

[0012] Preferably, the supplementary machining process in step 4 includes countersunk depth supplementary machining and rounding machining of the connection between the countersunk surface and the hole.

[0013] The supplementary machining completed in this stage is the repair of the single-layer product assembly of the bonding interface, and does not involve machining processes that penetrate the upper and lower product assemblies, so as to prevent contamination of the bonding interface.

[0014] Preferably, the fastener installation method in step 5 includes: Step 51, remove the pre-tensioning temporary fasteners such as positioning pins and tension bolts, and replace them with permanent fasteners; Step 52, clean and dry the permanent fasteners to be connected; Step 53, apply a sealant to the top rod and pin head surface of the cleaned permanent fastener to be connected; Step 54, assemble according to the assembly sequence required by the design document, and use a needle with the same diameter as the permanent fastener to align the hole position during assembly to ensure that the permanent fastener is installed after the hole positions of the layers are concentric. Step 55, for the sealant squeezed out of the connection gap, it needs to be corrected and shaped, and the head of the sealing fastener is sealed to ensure the cleanliness of the connection part.

[0015] Preferably, the sealant coating method of the fastener and the outer area of the joint surface seam in step 6 includes: The top rod extending part after the fastener connection is sealed to ensure that the fastener is completely covered by the sealant except the head end surface; The sealant is applied to the structure of each component along the entire joint (including the joint surface between each layer such as gasket), and the extrusion is rectified.

[0016] Preferably, the step 7 of transferring the entire connecting component includes: Step 71, the connecting component in the assembly jig is stress-free disassembled to ensure that the structure of each component in the connecting component does not shift with the sealant in the wet state; Step 72, after the connecting component is transferred to the waiting assembly area, it needs to be placed still and naturally vulcanized at room temperature until the hardness of the glue joint interface reaches Shore 30 degrees, and then it can be transferred to the next assembly station.

[0017] Beneficial effects: In order to improve the one-way connection of aircraft assembly process and efficiently ensure the production rhythm, the present application provides a process method for integrally manufacturing aircraft assembly components without disassembly. Based on the characteristics of ultra-high precision and high cleanliness of non-contact hole making process, the method avoids repeated assembly and disassembly of products caused by multiple repair links, thereby effectively reducing the low assembly precision problem caused by multiple assembly and disassembly of products. The special process single station machining is compatible with the multi-process in the component assembly connection process, which is a low-cost, efficient and highly intensive component assembly method. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 Flowchart of a process method for integrally manufacturing aircraft assembly components without disassembly; Figure 2 Layout and distribution of aircraft assembly hole making station; Figure 3 Sealing process diagram of assembly component; Figure 4 Observation diagram of surface morphology of double-double layered material with glue hole making; Figure 5 Roughness detection diagram of double-double layered material with glue hole making; Figure 6 Observation diagram of surface morphology of double-aluminum layered material with glue hole making; Figure 7 Roughness detection diagram of double-aluminum layered material with glue hole making; Figure 8 Hole making precision detection diagram under various working conditions.

[0019] Numbering in the figure: 1, assembly component; 2, to be drilled hole; 3, cantilever tool joint; 4, end moving carrier; 5, end effector; 6, non-contact high-energy laser beam processing head; 7, No. 001 drilling hole; 8, No. 002 drilling hole; 9, No. 003 drilling hole; 10, No. 004 drilling hole; 11, wing box front edge assembly; 12, wing box wallboard assembly; 13, wing box rib bulkhead assembly; 14, wing box rear edge assembly; 15, automatic drilling equipment; 16, wing box assembly tooling; 17, wing box assembly component to be assembled; 18, wing box assembly component. DETAILED DESCRIPTION

[0020] The embodiments of the present application will be further described below in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present application, but cannot be used to limit the scope of the present application.

[0021] The embodiment of the present application provides a process method for integrally manufacturing an aircraft assembly component without disassembly, comprising: Step 1, applying sealant to the bonding surface of each subassembly of a certain aircraft connecting component to form an assembly component, ensuring that the sealant fully covers the bonding area of the subassembly and is continuously extruded from the seam outside the subassembly; Step 2, installing the assembly component in the current sealant state into the assembly jig, and completing the global positioning of the assembly component-assembly jig-drilling equipment; Step 3, preparing the assembly connection hole based on the non-contact high-energy laser beam for the drilling hole of the assembly component; Step 4, quantitatively characterizing the drilling results by the self-adaptive detection unit, determining the reprocessing allowance and completing the reprocessing; Step 5, completing the fastener installation for each connecting hole in the product assembly connecting component; Step 6, applying sealant to the fastener and the seam outside the bonding surface in the connecting component; Step 7, completing the disassembly and separation of the connected and formed overall connecting component from the assembly jig, and transferring to the component butt joint assembly area.

[0022] The step 1 bonding surface sealing process comprises: Step 11, uniformly applying sealant to the bonding surface, and maintaining the shape of the sealant after application, with the ability to automatically flow and fill; Step 12, adhering each connecting subassembly to the specified position according to the overall component configuration; Step 13, installing temporary fasteners at the specified position according to the design file, and tightening to keep the bonding surface sealant free of air bubbles and gaps.

[0023] The step 2 global positioning method comprises: Step 21, complete the fixation of the assembly jig in the global coordinate system of the hole making station by positioning the jig positioning device such as positioning pins, cup cone locators, etc. Step 22, complete the spatial fitting of the assembly jig coordinate and the hole making device coordinate system by the spatial coordinate measuring instrument. Step 23, according to the specified installation method in the design file, install the pre-glued assembly component in the assembly jig, and complete the position fixation by relying on the mechanical limit in the assembly jig. Step 24, identify the coordinates of the positioning target in the assembly component contour surface through the coordinate sensing module in the end effector of the hole making device, and complete the fitting of the assembly component and the hole making device coordinate system.

[0024] The specific steps of preparing the assembly connection hole of the assembly component based on the non-contact high-energy laser beam in step 3 include: Step 31, adjust the current posture of the hole making device by the normal alignment module in the end effector of the device, so that the irradiation direction of the high-energy laser beam is the normal direction of the assembly component; Step 32, locally press the structure of the assembly component at the current hole making position by the pressure foot module in the end effector of the hole making device; Step 33, perform inclined cutting and circular spiral scanning on the assembly component by the high-energy laser beam coupling module in the end effector of the hole making device, until a conical blind hole surface is formed; Step 34, adjust the high-energy laser beam coupling module in the end effector of the hole making device to the normal posture of the hole making position, and keep the posture to perform ring cutting and straight hole processing with the center of the conical blind hole as the center, until a complete assembly through hole is formed.

[0025] If the type of the hole to be processed is a countersunk round straight hole, the above steps are executed; if the type of the hole to be processed is a round straight hole, steps 31, 32 and 34 are executed.

[0026] The quantitative characterization type of the hole making result in step 4 includes: Punch riveting / screwing hole: detection items include hole diameter, hole wall roughness, and hole roundness; Countersunk riveting / screwing hole: detection items include hole diameter, hole depth, hole wall roughness, countersunk surface roughness, and hole roundness; The measurement positions of the hole diameter include multiple position points such as the entrance of the upper plate hole, the exit of the upper plate hole, the entrance of the lower plate hole, and the exit of the lower plate hole, and the measurement angles include 0°, 45°, 90°, and 135°.

[0027] The reprocessing procedure in step 4 includes reprocessing of countersunk depth and rounding of the connection between the countersunk surface and the hole making.

[0028] In this stage, the finishing work completed is the repair of the single-layer product assembly at the bonding interface, and no machining process is involved that penetrates the upper and lower product assemblies to prevent contamination of the bonding interface.

[0029] The fastener installation method in step 5 includes: Step 51, remove the positioning pins, tension bolts, and other pre-tensioned temporary fasteners, and replace them with permanent fasteners; Step 52, clean and dry the permanent fasteners to be connected; Step 53, apply sealant to the top rod and nail head socket surface of the cleaned permanent fasteners to be connected; Step 54, assemble according to the assembly sequence required by the design document. When assembling, use a needle with the same diameter as the permanent fastener to align the hole position, ensuring that the stack hole position is concentric before installing the permanent fastener; Step 55, for the sealant squeezed out from the connection gap, it needs to be corrected and shaped, and the fastener head is sealed to ensure the cleanliness of the connection part.

[0030] The sealant coating method for the fastener and the outer area of the joint surface in step 6 includes: Seal the top rod extension part after the fastener connection is completed to ensure that the fastener is completely covered with sealant except for the nail head end surface; Apply sealant to the structure of each component along the entire joint (including the gap between each layer of the joint surface), and complete the flow regulation of the extrudate.

[0031] The handover step of the overall connected component in step 7 includes: Step 71, disassemble the connected components in the assembly jig without stress to ensure that the structure of each component in the connected component does not shift with the wet state of the sealant; Step 72, after the connected components are transferred to the waiting assembly area, they need to be placed and naturally vulcanized at room temperature until the hardness of the bonding interface reaches Shore 30 degrees, and then they can be transferred to the next assembly station.

[0032] Figure 1This embodiment provides a flow chart of a process method for the integrated, non-disassembly-required manufacturing of aircraft assembly components. The assembly involves the precise alignment of multiple connecting components within a specific aircraft assembly component. Sealant is applied to the mating surfaces of the connecting components and bonded according to the component assembly engineering drawings. While bonded, the assembled component is installed within the assembly jig, ensuring it is positioned within the pre-set global coordinate system. Global positioning is performed within the global coordinate system, with the jig assembled first and the product next. Non-contact hole drilling equipment then drills holes sequentially based on the hole location information and manufacturing tolerances provided in the process documentation. After drilling is complete, the drilling equipment switches to adaptive inspection mode, characterizing and evaluating each hole result. Precision cutting corrections are performed for holes detected that exceed the specified tolerances. Fasteners are connected in this position, and the joint areas, such as the outer seam of the mating surfaces and the tail end of the fastener bolt, are sealed. This assembly process encompasses key processes such as positioning, drilling, connection, and sealing, ensuring assembly accuracy and structural integrity. After completing these steps, the assembled component can be separated from the tooling and transferred to the next assembly station for subsequent adjustment.

[0033] Figure 2 The aircraft assembly drilling station layout and hole position distribution diagram provided for the embodiment of the present disclosure include 1. assembly parts; 2. hole positions to be drilled; 3. cantilevered tooling joint; 4. end moving carrier; 5. end effector; 6. non-contact high-energy laser beam processing head; 7. hole position No. 001; 8. hole position No. 002; 9. hole position No. 003; 10. hole position No. 004.

[0034] For example, as shown in the above assembly component hole making diagram, the material of the connection component is composed of an upper composite material and a lower aluminum alloy material. The working condition of hole making position 001 is an assembly connection hole with a laminate thickness of 7mm, a processing hole diameter d=8mm, a countersink diameter D=16mm, and a countersink angle 2θ=100°; the working condition of hole making position 002 is an assembly connection hole with a laminate thickness of 10mm, a processing hole diameter d=10mm, a countersink diameter D=20mm, and a countersink angle 2θ=100°; the working condition of hole making position 003 is an assembly connection straight hole with a laminate thickness of 10mm and a processing hole diameter of 10mm. The center O of the countersink conical hole is the laser beam processing origin, and the distance between the origin O and the product surface is ; The machining origin of the straight hole is O', and the distance from the origin O' to the product surface is .

[0035] For No. 001 hole, the first step is to adjust the laser beam to the product normal attitude as the original state of motion, set the end effector machine tool origin to the position of 6.71 mm away from the surface along the product thickness direction, and scan around the origin at an inclination angle of 50° until the complete conical blind hole profile is formed. The end effector posture is reset, the laser beam processing posture is fixed in the product normal attitude, the end effector machine tool origin is set to the position of 3.35 mm away from the surface along the product thickness direction, the single-channel ring-cut hole scanning is performed with a straight hole radius of 4 mm as the scanning radius, and the machining is completed until the through hole is formed.

[0036] For No. 002 hole, the first step is to adjust the laser beam to the product normal attitude as the original state of motion, set the end effector machine tool origin to the position of 8.39 mm away from the surface along the product thickness direction, and scan around the origin at an inclination angle of 50° until the complete conical blind hole profile is formed. The end effector posture is reset, the laser beam processing posture is fixed in the product normal attitude, the end effector machine tool origin is set to the position of 4.19 mm away from the surface along the product thickness direction, the single-channel ring-cut hole scanning is performed with a straight hole radius of 5 mm as the scanning radius, and the machining is completed until the through hole is formed.

[0037] For No. 003 hole, the laser beam processing posture is fixed in the product normal attitude, the single-channel ring-cut hole scanning is performed with a straight hole radius of 5 mm as the scanning radius, and the machining is completed until the through hole is formed.

[0038] Figure 3 The assembly part sealing process diagram is shown. The wing part 17 to be assembled is composed of a wing box front edge assembly 11, a wing box wall plate assembly 12, a wing box rib partition assembly 13, and a wing box rear edge assembly 14. Each connected assembly needs to be sealed on the fitting surface outside the frame before entering the hole making unit. The hole making unit is completed by the automatic hole making equipment 15, and the fastener sealing and fastener packaging are completed on the frame. The wing part is disassembled and transferred to the outside of the frame with the wing box assembly tool 16, and the supplementary sealing processes such as the joint sealing and the fillet sealing are completed, forming a complete wing box whole assembly part 18.

[0039] Figure 4 The surface morphology observation diagram of the composite-composite laminated material with adhesive hole making is shown. The feasibility analysis of the processing macroscopic performance is carried out by observing the morphology of the laminated fracture and the adhesive interface after the adhesive hole making, and the process including equipment hole making, manual hole making, and laser hole making is verified. As shown in the figure, the tool hole and the manual hole have different degrees of debris sticking phenomenon, and a large amount of dust and debris is mixed and solidified in the sealing adhesive of the fitting surface. In comparison, the degree of debris sticking of the manual hole is larger; after the laser hole making, the fracture has no dust and debris sticking, the adhesive interface appears partial embrittlement, and due to the influence of high-temperature ablation, there is a small amount of subsidence of the interface adhesive layer, and the subsidence depth is not greater than 0.1 mm.

[0040] Figure 5 This image shows the roughness of the composite-to-composite laminate interface after adhesive drilling. Testing the surface roughness of the composite material in both the X and Y directions after adhesive drilling revealed that both bidirectional roughness values ​​were within the 2.0-3.0μm range, meeting the manufacturing specification of Ra < 3.2.

[0041] Figure 6 This is an observation image of the surface morphology of a composite-aluminum laminate after adhesive drilling. The feasibility of the macro-performance of the process was analyzed by observing the laminate fracture and the bonding interface morphology after adhesive drilling. The verification process included three types of drilling: machine drilling, manual drilling, and laser drilling. Mechanical drilling methods all showed varying degrees of debris adhesion within the sealant, and a small amount of embrittlement was observed at the interface. The cross-sectional morphology after laser drilling showed no obvious contamination or damage, and there was a slight sinking of the sealant at the bonded joint, with a depth of no more than 0.1 mm.

[0042] Figure 7 The roughness test results for the aluminum-composite laminate surface are shown in the figure. The aluminum layer has a roughness of less than 1.0 μm. Due to colloid ablation and depression at the bond line, the roughness of the aluminum-composite bonded interface is slightly higher than that of a single substrate material. The roughness in the X-direction (i.e., along the sealant's length) reaches 8.4 μm, while the roughness in the Y-direction (i.e., along the aluminum-sealant-composite direction) reaches 4.6 μm.

[0043] Figure 8 The following diagrams show the hole-making accuracy test results under various operating conditions. Continuous hole-making was conducted on φ4-φ20 holes with 2mm diameter increments. The results are shown in the figure. After hole-making, the adhesive layer was impacted by the impact of the adjacent hole-making process, causing it to continuously overflow onto the inner wall of the hole. After batch-making, the residual adhesive layer thickness was 0.15mm. The sealant layer on the cut end face was free of debris and contamination, remaining close to its original state. Characterization tests were conducted on the hole-making accuracy and roundness after batch-making, as shown in the figure. Considering that the hole-making process involves the laser beam driven by the device carrier performing spatial circular cutting, a circular cutting rate that increases with increasing hole diameter is employed to ensure hole-making efficiency. This results in reduced accuracy at high speeds, affecting both hole-making accuracy and roundness. Processing time increases nonlinearly with hole diameter. For small holes, processing time can be effectively controlled within 4 minutes. However, processing time increases significantly for holes exceeding 14mm, reaching approximately 16 minutes for a φ20 hole.

[0044] The foregoing description has shown and described preferred embodiments of the application, but it will be understood that the application is not limited to the particular embodiments shown and described, as such will have many modifications, permutations, additions and subtractions and changes as are obvious to one skilled in the art, and it is therefore intended to cover all such modifications and changes as fall within the scope of the application, including full use of the principles and features described herein. Changes and modifications can be made to the application in light of this teaching and it is therefore intended to cover in the appended claims all such changes and modifications that fall within the scope of the application.

Claims

1. A process for integrally manufacturing aircraft assembly parts without disassembly, characterized in that: include: Step 1: Apply sealant to the mating surfaces of each component of an aircraft connection part to form an assembled component, ensuring that the sealant fully covers the mating areas of the components and is continuously squeezed out from the seams of small components; Step 2: The assembly component is installed in the assembly jig while maintaining its current sealing and gluing state, and the global positioning of the assembly component, the assembly jig, and the hole-making device is completed; Step 3, preparing assembly connection holes at the hole-making positions of the assembly component using a non-contact high-energy laser beam; Step 4: quantitatively characterize the hole-making results through the adaptive detection unit, determine the supplementary machining allowance, and complete the supplementary machining; Step 5: Install fasteners on each connection hole in the product assembly connection parts; Step 6: Complete the application of sealant to the fasteners and the outer area of ​​the joint seam in the connecting parts; Step 7: Complete the disassembly and separation of the connected integral connection components from the assembly jig and transfer them to the component matching pre-assembly area.

2. The process for manufacturing aircraft assembly parts without disassembly according to claim 1, characterized in that: The step 1 of the sealing coating process comprises: Step 11, evenly apply sealant to the bonding surface; Step 12: Each connecting component is glued to a designated position according to the overall component configuration; Step 13: Complete the installation of temporary fasteners at designated locations according to the design documents, and tighten the sealant to ensure there are no bubbles or gaps in the fitting surface.

3. The process for manufacturing aircraft assembly parts without disassembly according to claim 1, characterized in that: The global positioning method in step 2 includes: Step 21, using the assembly jig positioning device, completes the fixation of the assembly jig in the global coordinate system of the hole making station; Step 22, completing the spatial fitting of the assembly jig coordinate system and the hole making equipment coordinate system by using a spatial coordinate measuring instrument; Step 23: Install the pre-glued assembly components in the assembly jig according to the installation method specified in the design document, and fix the position by mechanical limiters in the assembly jig; Step 24 : Using the coordinate sensing module in the end effector of the hole-making device, the coordinates of the positioning target within the outer surface of the assembly component are identified, and the fitting of the assembly component and the coordinate system of the hole-making device is completed.

4. The process for manufacturing aircraft assembly parts without disassembly according to claim 1, characterized in that: In step 3, the assembly connection holes are prepared at the hole-making positions of the assembly component based on a non-contact high-energy laser beam, and the specific steps include: Step 31, adjusting the current posture of the hole-making device through the normal alignment module in the end effector of the hole-making device so that the irradiation direction of the high-energy laser beam is the normal direction of the assembly component; Step 32: locally compressing the assembly component structure at the current hole-making position by using the pressure foot module in the end effector of the hole-making equipment; Step 33, using a high-energy laser beam coupling module in the end effector of the hole-making equipment to perform an oblique circular spiral scanning on the assembly component until a conical blind hole surface is formed; Step 34: Adjust the high-energy laser beam coupling module in the end effector of the hole-making equipment to a normal posture at the hole-making position, maintain this posture, and perform circular cutting straight hole processing with the center of the conical blind hole as the center of the circle until a complete assembly through hole is formed; Among them, if the type of hole to be processed is a countersunk round straight hole, the above steps are executed; if the type of hole to be processed is a round straight through hole, the above steps 31, 32, and 34 are executed. At this time, the center of the round straight through hole is the spatial coordinate of the hole making point.

5. The process for manufacturing aircraft assembly parts without disassembly according to claim 1, characterized in that: The quantitative characterization of the pore preparation results in step 4 includes: Protruding head riveted / screwed holes: Inspection items include hole diameter, hole wall roughness, and hole roundness; Countersunk riveted / screwed holes: Inspection items include hole diameter, socket depth, hole wall roughness, socket surface roughness, and hole roundness; The aperture measurement positions include the upper plate hole entrance, upper plate hole exit, lower plate hole entrance, and lower plate hole exit, and the measurement angles include 0°, 45°, 90°, and 135°.

6. The process for manufacturing aircraft assembly parts without disassembly according to claim 1, characterized in that: The supplementary processing steps in step 4 include: supplementary processing of the countersink depth, and chamfering processing of the connection between the countersink surface and the hole; Among them, the supplementary processing completed in this stage is the repair of single-layer product components at the bonding interface, and does not involve processing procedures that run through the upper and lower layer product components.

7. The process for manufacturing aircraft assembly parts without disassembly according to claim 1, characterized in that: The fastener installation method in step 5 includes: Step 51, removing the pre-tensioned temporary fasteners and replacing them with permanent fasteners; Step 52, degreasing and cleaning the permanent fasteners to be connected, and completing drying; Step 53, applying sealant to the cleaned top rod and nail head socket surface of the permanent fastener to be connected; Step 54: Assemble according to the assembly sequence specified in the design documents. During assembly, align the holes with a needle of the same diameter as the permanent fasteners to ensure that the stacked holes are concentric before installing the permanent fasteners. In step 55, the sealant squeezed out from the connection gap needs to be corrected and shaped, and the head of the sealing fastener needs to be sealed to ensure the cleanliness of the connection part.

8. The process for manufacturing aircraft assembly parts without disassembly according to claim 1, characterized in that: The method of applying sealant to the fasteners and the outer area of ​​the joint seam in step 6 includes: Seal the extended part of the push rod after the fastener is connected, so that the rest of the joint of the fastener except the nail head end is completely covered with sealant; Apply sealant along the entire joint of each component structure in the connecting part and complete the flow of the extrudate.

9. The process for manufacturing aircraft assembly parts without disassembly according to claim 1, characterized in that: The step of transferring the integral connection component in step 7 includes: Step 71: Disassemble the connecting components in the assembly jig without stress to ensure that the components in the connecting components do not shift due to the wet sealant. Step 72 : After the connecting parts are transferred to the assembly area to be connected, they are left to stand and naturally vulcanize at room temperature until the hardness of the bonding interface reaches 30 degrees Shore, and then transferred to the next assembly station.

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