Split type machining method for splicing type forming die of integral cylindrical composite part

Abstract

The invention discloses a split type machining method for a splicing type forming die of an integral cylindrical composite part, which realizes split type machining of the splicing type forming die of the integral cylindrical composite part, reduces the machine occupation time of a large five-axis numerical control machine tool, shortens the machining period and reduces the machining cost. Dead-weight deformation is compensated by adopting a mode of reversely constructing a process mathematical model by adopting finite element simulation deformation data, so that the precision of the die in a use state is optimal, and the forming quality of the whole cylindrical composite part is improved.

Description

Technical Field

[0001] This invention belongs to the technical field of CNC machining of composite parts, specifically relating to a split-type machining method for splicing molding molds of integral cylindrical composite parts. Background Technology

[0002] Carbon fiber reinforced resin matrix composites, with their superior specific strength and specific modulus characteristics, as well as their flexible design and processing advantages, have become key materials in the modern aerospace equipment manufacturing field, especially in the preparation of aircraft skin and load-bearing components. Currently, the mainstream integral cylindrical skin molding process mainly adopts spliced ​​thin-shell structure molding molds. These molds feature excellent ventilation performance and convenient assembly and disassembly. These thin-shell molds typically consist of multiple parting line components. These components are positioned and screwed together through overlapping structures to form an integral profile. After the individual parting line components are assembled, their ends need to cooperate with auxiliary molding components such as the integral end frame and molding frame. Therefore, the overall profile and end faces of this type of mold require precision machining. Thin-shell cylindrical molds are usually quite long. During the part molding process, to ensure the integrity of the overall cylindrical shape, only the two ends of the mold are supported. Under normal circumstances, the middle of the mold will deform due to insufficient overall rigidity and its own weight, which may lead to deviations in the shape of the molded part.

[0003] In existing technologies, for large, integral cylindrical composite parts forming and splicing molds, each parting component is typically rough-machined individually and then assembled into a whole. A horizontal machining method is then used for finishing the overall profile. This finishing process requires flipping the mold to the part-forming posture and supporting it at both ends, causing the mold to deform under its own weight. Process supports are then used to compensate for this deformation, ensuring optimal positional accuracy of the mold surface in the part-forming posture after finishing. This method requires multiple mold flips during processing, resulting in a long flipping and alignment process, a long overall processing cycle, and high processing costs.

[0004] Therefore, in view of the above-mentioned shortcomings of the prior art, the present invention discloses a split processing method for splicing molding molds of integral cylindrical composite parts. Summary of the Invention

[0005] This invention discloses a method for split-type processing of integral cylindrical composite parts using splicing molding dies. This method enables the split-type processing of integral cylindrical composite parts using splicing molding dies, shortens the processing cycle, reduces the time spent on large machine tools, and lowers processing costs.

[0006] This invention is achieved through the following technical solution: A method for processing integral cylindrical composite parts using a modular molding die, comprising the following steps: Step 1: Perform reverse self-weight stress analysis on the 3D digital model of the splicing molding mold and extract the surface point cloud data of the splicing molding mold under reverse self-weight state. Step 2: Reverse reconstruct the point cloud data of the surface into a NURBS parametric surface, use the NURBS parametric surface as the self-weight deformation compensation surface, and reconstruct the compensation digital model of the splicing molding die based on the self-weight deformation compensation surface. Step 3: Perform self-weight deformation compensation verification and local fine-tuning on the compensation model to ensure that the surface difference between the compensation model and the standard model meets the standard. Perform CNC machining on the parting components in the die-forming mold based on the compensation model. Step 4: Assemble the parting components on the reference platform using support components to obtain an assembly, and fit the surface allowance of the assembly to obtain the best fitting surface. Measure the pose parameters of the support components and the pose parameters of the parting components based on the best fitting plane. Step 5: Establish the support component digital model. Based on the pose parameters of the support component and the parting assembly measured in Step 4, assemble the support component digital model and the compensation digital model, and adjust the relative positional relationship between the support component digital model and the compensation digital model to obtain the overall machining process digital model. Step 6: Construct chuck models at both ends of each parting component in the overall machining process model, create reference holes and reference planes on the chuck models, and create stepped platforms at the edges of the parting component surfaces to form the final process model; Step 7: According to the overall machining process, perform CNC programming to align the reference holes and reference planes on the support and perform CNC machining on the end face mating surfaces of the parting assembly; Step 8: Install chucks at both ends of the parting assembly, and perform CNC machining on the reference holes and reference planes on the chucks according to the final process model CNC programming. Step 9: Keep the clamps at both ends of the parting assembly, disassemble each parting assembly in sequence, and use the final process model CNC programming based on the reference hole and reference plane to perform CNC machining on the surface of the parting assembly; Step 10: Assemble the machined parting components on the reference platform, check the gaps between each parting component, and check the step differences between the surfaces of each parting component.

[0007] To better realize the present invention, step 1 further includes: Step 1.1: Create a three-dimensional digital model of the splicing molding mold, import the three-dimensional digital model into the finite element simulation software, and create a finite element model of the splicing molding mold. Step 1.2: Divide the finite element model using a tetrahedral mesh; Step 1.3: Using the orientation of the splicing molding mold during molding as the positive orientation, adjust the orientation of the finite element model to a reverse orientation that is 180° opposite to the positive orientation. Step 1.4: Apply support constraints to both ends of the finite element model in reverse orientation, and then perform reverse self-weight force analysis on the finite element model in reverse orientation to extract the surface point cloud data of the spliced ​​molding die under reverse self-weight state.

[0008] To better realize the present invention, furthermore, a 1mm mesh size is used to divide the area within 10mm around the rounded corner region in the finite element model, and a 5mm mesh size is used to divide the remaining areas in the finite element model.

[0009] To better realize the present invention, step 3 further includes: Step 3.1: Import the compensation model into the finite element simulation software, apply support constraints to both ends of the compensation model, perform self-weight deformation simulation analysis, and extract the surface simulation point cloud data of the compensation model under self-weight. Step 3.2: Compare the simulation point cloud data with the standard surface data of the standard digital model. If the difference between the simulation point cloud data and the standard surface data is less than or equal to 0.1 mm, the compensation digital model verification is completed; if the difference between the simulation point cloud data and the standard surface data is greater than 0.1 mm, proceed to step 3.3. Step 3.3: Based on the difference between the simulation point cloud data and the standard surface data, perform local fine-tuning on the simulation point cloud data until the difference between the simulation point cloud data and the standard surface data is less than or equal to 0.1mm, and complete the compensation model verification. Step 3.4: Based on the completed compensation model, perform CNC machining on the parting components in the splicing molding mold. The machining allowance for the parting component's surface is 2mm, the machining allowance for the end face of the parting component is 2mm, and the machining allowance for the overlapping and bonding surfaces between the parting components is 0.05mm.

[0010] To better realize the present invention, step 4 further includes: Step 4.1: Use support members on the reference platform to provide conformal support for the parting assembly, with a spacing of 600-1000mm between the support members; Step 4.2: Assemble the parting components in sequence, and then fix each parting component to form a splicing molding mold; Step 4.3: Fit the allowance of the overall surface of the splicing molding die using the least squares method to obtain the best fitting coordinate system; Step 4.4: Under the best-fit coordinate system, measure the actual values ​​of the reference holes and reference planes on the support as the pose parameters of the support; measure the actual values ​​of the reference planes of the clamps at both ends of the parting assembly as the pose parameters of the parting assembly.

[0011] To better realize the present invention, further, in step 4.2, during the assembly of the parting components, the overlapping and bonding surfaces between the parting components are colored and adjusted until the colored area is greater than or equal to 95% of the overlapping and bonding surface, and the gap between the assembled parting components is less than or equal to 0.1mm.

[0012] To better realize the present invention, in step 6, the step platform is constructed in an area within 20mm of the edge of the parting assembly, and the height of the step plane is less than or equal to 0.05mm.

[0013] To better realize the present invention, step 9 further includes: Step 9.1: Support the non-shaped surfaces in the parting assembly at intervals of 600-1000mm; Step 9.2: Align the reference holes and reference planes of the clamps at both ends of the parting assembly based on the final process digital model; Step 9.3: Perform semi-finishing and finishing on the surface of the parting component. The machining allowance for semi-finishing is 0.3mm, and the machining allowance for finishing is 0mm.

[0014] To better realize the present invention, step 10 further includes: Step 10.1: Assemble the machined parting components on the reference platform and check the gap between each parting component until the gap is less than or equal to 0.1mm; Step 10.2: Measure the step difference between the surfaces of each parting component. If the step difference exceeds the standard, adjust the step difference area to ensure a smooth transition between the surfaces. Step 10.3: Remove the clamps at both ends of the parting assembly and grind the stepped platform at the edge of the parting assembly to make it flat.

[0015] Compared with the prior art, the present invention has the following advantages and beneficial effects: (1) This invention realizes the split processing of the integral cylindrical composite parts forming splicing mold, and compensates for the influence of self-weight deformation on the final processing state by reverse construction of process digital model through finite element simulation deformation data, thus ensuring the accuracy of the mold when forming integral cylindrical composite parts; (2) The requirements for machine tools are relatively low, which can effectively reduce the time occupied by large five-axis CNC machine tools. Each block is processed separately, and multiple blocks can be processed in parallel using smaller CNC machine tools, saving processing costs, shortening the processing cycle, and having better economic efficiency. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the process steps of the present invention; Figure 2 This is a structural schematic diagram of a modular molding die; Figure 3 This is a schematic diagram of finite element modeling for a splicing molding die; Figure 4 This is a schematic diagram of the assembly of the parting components from top to bottom; Figure 5 The reconstructed compensation model; Figure 6 A schematic diagram showing the individual processing of the parting component. Detailed Implementation

[0017] Example 1: This embodiment describes a modular processing method for a splicing molding die for an integral cylindrical composite part, such as... Figure 1 As shown, it includes the following steps: Step 1: Perform reverse self-weight stress analysis on the 3D digital model of the splicing molding mold and extract the surface point cloud data of the splicing molding mold under reverse self-weight state. Step 2: Reverse reconstruct the point cloud data of the surface into a NURBS parametric surface, use the NURBS parametric surface as the self-weight deformation compensation surface, and reconstruct the compensation digital model of the splicing molding die based on the self-weight deformation compensation surface. Step 3: Perform self-weight deformation compensation verification and local fine-tuning on the compensation model to ensure that the surface difference between the compensation model and the standard model meets the standard. Perform CNC machining on the parting components in the die-forming mold based on the compensation model. Step 4: Assemble the parting components on the reference platform using support components to obtain an assembly, and fit the surface allowance of the assembly to obtain the best fitting surface. Measure the pose parameters of the support components and the pose parameters of the parting components based on the best fitting plane. Step 5: Establish the support component digital model. Based on the pose parameters of the support component and the parting assembly measured in Step 4, assemble the support component digital model and the compensation digital model, and adjust the relative positional relationship between the support component digital model and the compensation digital model to obtain the overall machining process digital model. Step 6: Construct chuck models at both ends of each parting component in the overall machining process model, create reference holes and reference planes on the chuck models, and create stepped platforms at the edges of the parting component surfaces to form the final process model; Step 7: According to the overall machining process, perform CNC programming to align the reference holes and reference planes on the support and perform CNC machining on the end face mating surfaces of the parting assembly; Step 8: Install chucks at both ends of the parting assembly, and perform CNC machining on the reference holes and reference planes on the chucks according to the final process model CNC programming. Step 9: Keep the clamps at both ends of the parting assembly, disassemble each parting assembly in sequence, and use the final process model CNC programming based on the reference hole and reference plane to perform CNC machining on the surface of the parting assembly; Step 10: Assemble the machined parting components on the reference platform, check the gaps between each parting component, and check the step differences between the surfaces of each parting component.

[0018] Furthermore, step 1 specifically includes: Step 1.1: Create a three-dimensional digital model of the splicing molding mold, import the three-dimensional digital model into the finite element simulation software, and create a finite element model of the splicing molding mold. Step 1.2: Divide the finite element model using a tetrahedral mesh; Step 1.3: Using the orientation of the splicing molding mold during molding as the positive orientation, adjust the orientation of the finite element model to a reverse orientation that is 180° opposite to the positive orientation. Step 1.4: Apply support constraints to both ends of the finite element model in reverse orientation, and then perform reverse self-weight force analysis on the finite element model in reverse orientation to extract the surface point cloud data of the spliced ​​molding die under reverse self-weight state.

[0019] Furthermore, step 3 specifically includes: Step 3.1: Import the compensation model into the finite element simulation software, apply support constraints to both ends of the compensation model, perform self-weight deformation simulation analysis, and extract the surface simulation point cloud data of the compensation model under self-weight. Step 3.2: Compare the simulation point cloud data with the standard surface data of the standard digital model. If the difference between the simulation point cloud data and the standard surface data is less than or equal to 0.1 mm, the compensation digital model verification is completed; if the difference between the simulation point cloud data and the standard surface data is greater than 0.1 mm, proceed to step 3.3. Step 3.3: Based on the difference between the simulation point cloud data and the standard surface data, perform local fine-tuning on the simulation point cloud data until the difference between the simulation point cloud data and the standard surface data is less than or equal to 0.1mm, and complete the compensation model verification. Step 3.4: Based on the completed compensation model, perform CNC machining on the parting components in the splicing molding mold. The machining allowance for the parting component's surface is 2mm, the machining allowance for the end face of the parting component is 2mm, and the machining allowance for the overlapping and bonding surfaces between the parting components is 0.05mm.

[0020] Furthermore, step 4 specifically includes: Step 4.1: Use support members on the reference platform to provide conformal support for the parting assembly, with a spacing of 600-1000mm between the support members; Step 4.2: Assemble the parting components in sequence, and then fix each parting component to form a splicing molding mold; Step 4.3: Fit the allowance of the overall surface of the splicing molding die using the least squares method to obtain the best fitting coordinate system; Step 4.4: Under the best-fit coordinate system, measure the actual values ​​of the reference holes and reference planes on the support as the pose parameters of the support; measure the actual values ​​of the reference planes of the clamps at both ends of the parting assembly as the pose parameters of the parting assembly.

[0021] Furthermore, step 9 specifically includes: Step 9.1: Support the non-shaped surfaces in the parting assembly at intervals of 600-1000mm; Step 9.2: Align the reference holes and reference planes of the clamps at both ends of the parting assembly based on the final process digital model; Step 9.3: Perform semi-finishing and finishing on the surface of the parting component. The machining allowance for semi-finishing is 0.3mm, and the machining allowance for finishing is 0mm.

[0022] Furthermore, step 10 specifically includes: Step 10.1: Assemble the machined parting components on the reference platform and check the gap between each parting component until the gap is less than or equal to 0.1mm; Step 10.2: Measure the step difference between the surfaces of each parting component. If the step difference exceeds the standard, adjust the step difference area to ensure a smooth transition between the surfaces. Step 10.3: Remove the clamps at both ends of the parting assembly and grind the stepped platform at the edge of the parting assembly to make it flat.

[0023] Example 2: This embodiment discloses a split-type processing method for a splicing molding die for integral cylindrical composite parts, which is an optimization based on Embodiment 1, and is used for processing such as... Figure 2 The mold shown is a modular assembly mold for forming cylindrical composite parts with a length of 3000mm, a width of 1000mm, and a height of 600mm. Specifically: Simulation analysis of mold forming state in reverse self-weight deformation: like Figure 3 As shown, the 3D digital model of the splicing molding die for the integral cylindrical composite part is imported into the finite element simulation software. A finite element model of the splicing molding die is constructed in the finite element simulation software, and the mesh of the finite element model uses tetrahedral meshes. Within a 10mm radius of the four rounded corners of the cylindrical finite element model, a 1mm tetrahedral mesh is used, while the remaining areas are meshed using a 5mm tetrahedral mesh. In the finite element software, the finite element model is adjusted to the opposite posture to that during part forming; that is, the posture during splicing molding is taken as the positive posture, and the posture of the finite element model is adjusted to a reverse posture 180° opposite to the positive posture. Self-weight deformation simulation analysis is then performed with supports at both ends. The simulation analysis results are obtained, and the surface point cloud data of the finite element model under reverse self-weight deformation is extracted using the finite element software.

[0024] The acquired surface point cloud data is processed by point cloud processing software. Through non-uniform control point distribution, weighted least squares optimization and differential continuity constraints, the surface point cloud data is reverse reconstructed into NURBS parametric surface as a self-weight deformation compensation surface. The compensation digital model of the splicing forming mold of the integral cylindrical composite part is reconstructed by CATIA software. The constructed compensation model is imported into finite element simulation software to build a finite element simulation model. The mesh generation method during model construction is consistent with that used for the 3D model. Self-weight deformation simulation analysis is performed on the two supports of the compensation model. Simulation point cloud data of the surface shape under simulation conditions is extracted. This data is then compared with the standard surface data of the standard model in the point cloud processing software. If the difference between the simulation point cloud data and the standard surface data is less than or equal to 0.1 mm, the compensation model verification is complete. If the difference is greater than 0.1 mm, the simulation point cloud data is fine-tuned locally based on this difference until it is less than or equal to 0.1 mm, thus completing the compensation model verification.

[0025] Based on the verified compensation model, the parting line components in the splicing molding die are CNC machined. The machining allowance for the parting line components is 2mm, the machining allowance for the end faces of the parting line components is 2mm, and the machining allowance for the overlapping and mating surfaces between the parting line components is 0.05mm. During the machining of the parting line components, a three-axis CNC machine tool is used with a ball end mill in a traverse cutting mode. The ball end mill has a cutting width of 2mm, a rotation speed of 1500r / min, and a feed rate of 3500mm / min.

[0026] On the reference platform, the parting components are supported at 700mm intervals using support components such as simple assembly racks or processing brackets. For example... Figure 4 As shown, the parting components are then assembled from bottom to top. The overlapping and bonding surfaces between each parting component are visually inspected after being repaired with red lead powder to ensure that the red-painted area exceeds 95% of the overlapping and bonding surface. After assembly, the gap between each parting component is ≤0.1mm. The installation is then considered complete. After installation, the parting components are spot-welded to the support.

[0027] The overall surface allowance is measured using a laser tracker. The surface allowance is then best fitted using the least squares method to obtain the optimal surface allowance. Under the optimal fitted coordinate system, the measured values ​​of the reference holes and reference planes on the support are used as the pose parameters of the support. The actual values ​​of the reference planes at both ends of each parting assembly are also measured as the pose parameters of the parting assembly.

[0028] A support component digital model is established. Based on the measured pose parameters of the support component and the parting assembly, the support component digital model and the compensation digital model are assembled. Specifically, the relative positional relationship between the support component digital models (such as the simplified assembly frame and machining bracket) and the compensation digital model is adjusted in the assembled digital model, and the support component digital model is reconstructed in reverse to obtain the following result: Figure 5 The overall machining process is shown in the digital model.

[0029] Using the overall machining process model, chuck models are built at both ends of each parting component. Reference holes and reference planes are made on the chuck models. A stepped platform with a depth of 0.05mm is made within 20mm of the edge of the parting component to facilitate subsequent flattening of the joints and form the final process model.

[0030] According to the overall machining process, the reference holes and reference planes on the support are aligned, and the end face mating surfaces of the parting assembly are CNC machined with a machining allowance of 0.05mm.

[0031] like Figure 6As shown, chucks are installed at both ends of each parting component, and CNC programming is performed using the final process model to CNC machine the chucks at both ends of each parting component, machining the reference holes and reference surfaces on the chucks into place as references for the parting component split machining.

[0032] Retain the chucks at both ends of each parting assembly, and disassemble each parting assembly sequentially from top to bottom. Add simple supports to the non-shaped areas in the middle of each parting assembly, with support intervals of 950mm. Use the final process model for CNC programming, and align the reference holes and reference planes of the chucks at both ends of each parting assembly according to the final process model. Perform CNC semi-finishing and finishing on the shapes of the parting assemblies. CNC semi-finishing is performed on a five-axis CNC machine tool using a linear feed method, with a cutting width of 1.5mm, a speed of 2000r / min, a feed rate of 4000mm / min, and a machining allowance of 0.3mm. CNC finishing is performed on a five-axis CNC machine tool using a linear feed method, with a cutting width of 0.3mm, a speed of 4000r / min, a feed rate of 3000mm / min, and a machining allowance of 0mm.

[0033] Using the reference holes and reference planes of the clamps at both ends as references, the surface accuracy of each parting component is checked. On the reference platform, each parting component is assembled from bottom to top using the cylinder assembly frame assembly. After installation, the gaps between each parting component are checked. If the gap between the assembled parting components is ≤0.1mm, the installation is considered complete. After installation, the surface step difference at each parting point is checked. Step differences are repaired and polished to ensure a smooth transition and a smooth, flat surface. Then, the clamps at both ends of the parting component are removed, and the stepped platforms at the edges of the parting component are ground flat. Finally, the entire mold is supported by the positioning clamps at both ends, and the overall surface accuracy is checked.

[0034] The rest of this embodiment is the same as that of Embodiment 1, so it will not be described again.

[0035] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A method for split-type processing of a splicing molding die for an integral cylindrical composite part, characterized in that, Includes the following steps: Step 1: Perform reverse self-weight stress analysis on the 3D digital model of the splicing molding mold and extract the surface point cloud data of the splicing molding mold under reverse self-weight state. Step 2: Reverse reconstruct the point cloud data of the surface into a NURBS parametric surface, use the NURBS parametric surface as the self-weight deformation compensation surface, and reconstruct the compensation digital model of the splicing molding die based on the self-weight deformation compensation surface. Step 3: Perform self-weight deformation compensation verification and local fine-tuning on the compensation model to ensure that the surface difference between the compensation model and the standard model meets the standard. Perform CNC machining on the parting components in the die-forming mold based on the compensation model. Step 4: Assemble the parting components on the reference platform using support components to obtain an assembly, and fit the surface allowance of the assembly to obtain the best fitting surface. Measure the pose parameters of the support components and the pose parameters of the parting components based on the best fitting plane. Step 5: Establish the support component digital model. Based on the pose parameters of the support component and the parting assembly measured in Step 4, assemble the support component digital model and the compensation digital model, and adjust the relative positional relationship between the support component digital model and the compensation digital model to obtain the overall machining process digital model. Step 6: Construct chuck models at both ends of each parting component in the overall machining process model, create reference holes and reference planes on the chuck models, and create stepped platforms at the edges of the parting component surfaces to form the final process model; Step 7: According to the overall machining process, perform CNC programming to align the reference holes and reference planes on the support and perform CNC machining on the end face mating surfaces of the parting assembly; Step 8: Install chucks at both ends of the parting assembly, and perform CNC machining on the reference holes and reference planes on the chucks according to the final process model CNC programming. Step 9: Keep the clamps at both ends of the parting assembly, disassemble each parting assembly in sequence, and use the final process model CNC programming based on the reference hole and reference plane to perform CNC machining on the surface of the parting assembly; Step 10: Assemble the machined parting components on the reference platform, check the gaps between each parting component, and check the step differences between the surfaces of each parting component.

2. The method for separate processing of a splicing molding die for an integral cylindrical composite part according to claim 1, characterized in that, Step 1 specifically includes: Step 1.1: Create a three-dimensional digital model of the splicing molding mold, import the three-dimensional digital model into the finite element simulation software, and create a finite element model of the splicing molding mold. Step 1.2: Divide the finite element model using a tetrahedral mesh; Step 1.3: Using the orientation of the splicing molding mold during molding as the positive orientation, adjust the orientation of the finite element model to a reverse orientation that is 180° opposite to the positive orientation. Step 1.4: Apply support constraints to both ends of the finite element model in reverse orientation, and then perform reverse self-weight force analysis on the finite element model in reverse orientation to extract the surface point cloud data of the spliced ​​molding die under reverse self-weight state.

3. The method for separate processing of a splicing molding die for an integral cylindrical composite part according to claim 2, characterized in that, For the area within 10mm around the rounded corner region in the finite element model, a mesh size of 1mm is used for division, while for the remaining areas in the finite element model, a mesh size of 5mm is used for division.

4. The method for separate processing of a splicing molding die for an integral cylindrical composite part according to claim 1, characterized in that, Step 3 specifically includes: Step 3.1: Import the compensation model into the finite element simulation software, apply support constraints to both ends of the compensation model, perform self-weight deformation simulation analysis, and extract the surface simulation point cloud data of the compensation model under self-weight. Step 3.2: Compare the simulation point cloud data with the standard surface data of the standard digital model. If the difference between the simulation point cloud data and the standard surface data is less than or equal to 0.1 mm, the compensation digital model verification is completed; if the difference between the simulation point cloud data and the standard surface data is greater than 0.1 mm, proceed to step 3.

3. Step 3.3: Based on the difference between the simulation point cloud data and the standard surface data, perform local fine-tuning on the simulation point cloud data until the difference between the simulation point cloud data and the standard surface data is less than or equal to 0.1mm, and complete the compensation model verification. Step 3.4: Based on the completed compensation model, perform CNC machining on the parting components in the splicing molding mold. The machining allowance for the parting component's surface is 2mm, the machining allowance for the end face of the parting component is 2mm, and the machining allowance for the overlapping and bonding surfaces between the parting components is 0.05mm.

5. The method for separate processing of a splicing molding die for an integral cylindrical composite part according to claim 1, characterized in that, Step 4 specifically includes: Step 4.1: Use support members on the reference platform to provide conformal support for the parting assembly, with a spacing of 600-1000mm between the support members; Step 4.2: Assemble the parting components in sequence, and then fix each parting component to form a splicing molding mold; Step 4.3: Fit the allowance of the overall surface of the splicing molding die using the least squares method to obtain the best fitting coordinate system; Step 4.4: Under the best-fit coordinate system, measure the actual values ​​of the reference holes and reference planes on the support as the pose parameters of the support; measure the actual values ​​of the reference planes of the clamps at both ends of the parting assembly as the pose parameters of the parting assembly.

6. The method for separate processing of a splicing molding die for an integral cylindrical composite part according to claim 5, characterized in that, In step 4.2, during the assembly of the parting components, the overlapping and mating surfaces between the parting components are colored and adjusted until the colored area is greater than or equal to 95% of the overlapping and mating surfaces, and the gap between the assembled parting components is less than or equal to 0.1mm.

7. The method for separate processing of a splicing molding die for an integral cylindrical composite part according to claim 1, characterized in that, In step 6, the step platform is constructed in an area within 20mm of the edge of the parting assembly, and the height of the step plane is less than or equal to 0.05mm.

8. The method for separate processing of a splicing molding die for an integral cylindrical composite part according to claim 1, characterized in that, Step 9 specifically includes: Step 9.1: Support the non-shaped surfaces in the parting assembly at intervals of 600-1000mm; Step 9.2: Align the reference holes and reference planes of the clamps at both ends of the parting assembly based on the final process digital model; Step 9.3: Perform semi-finishing and finishing on the surface of the parting component. The machining allowance for semi-finishing is 0.3mm, and the machining allowance for finishing is 0mm.

9. The method for separate processing of a splicing molding die for an integral cylindrical composite part according to claim 1, characterized in that, Step 10 specifically includes: Step 10.1: Assemble the machined parting components on the reference platform and check the gap between each parting component until the gap is less than or equal to 0.1mm; Step 10.2: Measure the step difference between the surfaces of each parting component. If the step difference exceeds the standard, adjust the step difference area to ensure a smooth transition between the surfaces. Step 10.3: Remove the clamps at both ends of the parting assembly and grind the stepped platform at the edge of the parting assembly to make it flat.

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