A large titanium alloy part integral welding and inspection method and fixture

Abstract

The present invention discloses a method for the overall welding and inspection of large titanium alloy parts and a fixture thereof. To address the difficulties in processing and inspecting semi-enclosed titanium alloy box parts in the aviation field, the parts are divided into three-segment structures of X, Y, and Z for segmented processing. High-precision process reference points (reference planes and multiple reference points) are set in the rigid areas of each split body. The reference point position cloud data is formed through three-coordinate measurement and fitted into an overall targeted point cloud. During welding, the reference points are used as positioning references to adjust the relative positions of the split bodies. After welding, the post-weld point cloud is fitted with the pre-weld data through three-coordinate measurement. The deformation and offset of the parts are quantitatively evaluated by combining dense point sampling and shape scanning technology. This method breaks through the internal detection blind spots of the semi-enclosed structure, and realizes accurate quantitative analysis of welding deformation through reference point positioning and multi-dimensional detection. The detection steps are simplified and quick, which improves the processing accuracy and detection efficiency of large titanium alloy welded parts. It is suitable for fields with strict precision requirements such as aviation.

Description

Technical Field

[0001] The present invention relates to the technical field of large titanium alloy part processing, and in particular to a large titanium alloy part integral welding and inspection method and a fixture thereof. Background Art

[0002] With the development of aerospace technology, large titanium alloy structural parts have been widely used in aerospace structural components due to their advantages of high strength and low density. Such parts have gradually evolved from a combination of multiple scattered parts to single large structural parts. The overall design significantly enhances the strength of the parts and reduces the difficulty and weight of assembly. However, such parts often use semi-enclosed box structures (such as Figure 1 As shown in the figure, the internal structure is narrow and contains complex assembly surfaces, holes and other features, resulting in the following difficulties for traditional processing and testing methods:

[0003] Processing limitations: When directly processing the entire part, most of the internal areas are difficult to reach, and it is necessary to use a method of segmented processing followed by welding. However, the parts are prone to deformation during the welding process, making it difficult to control the relative position accuracy of each separate structure.

[0004] Detection blind spots: The internal assembly surfaces and hole positions of semi-enclosed structures cannot be directly inspected using traditional three-dimensional coordinate measuring machines. Existing technologies lack effective benchmark positioning and deformation assessment methods, making it difficult to accurately obtain the relative position relationship of the internal structure.

[0005] Difficulty in ensuring accuracy: The overall shape of parts after welding is complex. Traditional inspection methods can only rely on shape scanning or local measurement, and cannot achieve quantitative evaluation of internal structure and overall deformation, resulting in low inspection efficiency and insufficient accuracy.

[0006] Therefore, there is an urgent need for a segmented processing, precise positioning and overall inspection method for semi-enclosed large titanium alloy welded parts to solve the problems of difficult processing, difficult inspection and difficult precision control in the existing technology. Summary of the Invention

[0007] The present invention aims to overcome the above-mentioned shortcomings of the prior art and provides a large titanium alloy part integral welding and inspection method and a fixture thereof.

[0008] The technical solution adopted in the present invention is as follows:

[0009] A method for integrally welding large titanium alloy parts comprises the following steps:

[0010] S1: Divide the semi-enclosed titanium alloy box parts into three-section split structures of X, Y, and Z;

[0011] S2: Process the X, Y, and Z parts to their final dimensions, leaving machining allowances for the mounting surfaces and welds.

[0012] S3: Processing high-precision process datums on the X, Y, and Z parts respectively, the process datums including a datum plane and multiple datum points, the multiple datum points are set in a plane adjacent to the datum plane, and at least one datum point is set on the edge of the datum plane;

[0013] S4: Using the reference plane and multiple reference points as the assembly positioning reference, weld the X, Y, and Z parts into a whole;

[0014] S5: Finish the welded parts to remove the machining allowances on the mounting surface and weld position.

[0015] Furthermore, in step S3, after the X, Y, and Z parts are processed, the relative position relationship of each separate part is measured by a three-dimensional coordinate measuring machine with the reference plane and multiple reference points as the reference to form reference point cloud data.

[0016] Furthermore, the X, Y, and Z reference point cloud data of the parts are fitted into the targeted point cloud data of the entire part, which serves as a unified reference coordinate system for welding assembly.

[0017] Furthermore, before welding, a laser tracker is used to measure the target point data of the X, Y, and Z parts. By comparing the target point cloud data of the overall part with the actual measurement data, a special fixture is used to adjust the relative position relationship of each separate part to the design accuracy requirements.

[0018] Furthermore, the reference plane serves as the reference plane for assembly positioning, and multiple reference points serve as the origin of the three-dimensional coordinate system and the positioning points in the coordinate axis direction, together forming the assembly positioning reference system of the X, Y, and Z parts.

[0019] Furthermore, the welding of the X, Y, and Z parts is positioned using a fixture or tooling to achieve precise assembly of the separate parts.

[0020] Furthermore, a method for overall inspection of large titanium alloy parts includes the following steps:

[0021] A1: After the welding process is completed, the three sets of process datums (datum plane and multiple datum points) of the part are measured using a three-coordinate measuring machine to generate post-weld point cloud data;

[0022] A2: Fit and compare the post-weld point cloud data with the targeted point cloud data measured before welding to calculate the actual deformation and offset data of the part;

[0023] A3: Use dense point measurement and shape scanning technology to detect the shape of parts after welding to verify deformation and offset data.

[0024] Furthermore, a fixture for welding large titanium alloy parts includes: a clamp and a processing platform. The clamp includes three groups, which are arranged on the processing platform corresponding to the X, Y, and Z parts, and form a clamping surface that matches the shape of the two side surfaces of the titanium alloy parts. The positioning block cooperates with the processing platform to realize the positioning constraint of the X, Y, and Z parts in three-dimensional space.

[0025] Furthermore, it includes a positioning pin, and the clamp is provided with a pin hole corresponding to the position of the reference point. After the clamp clamps the X, Y, and Z parts, positioning is performed by inserting the positioning pin into the pin hole and the reference point.

[0026] Furthermore, the processing platform is configured as a multi-axis adjustable structure.

[0027] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0028] This invention achieves full-process precision control of large titanium alloy welded parts by setting high-precision process reference points on segmented parts, building a targeted point cloud data system, and combining multi-dimensional measurement and detection technology. It has the following significant advantages:

[0029] Breaking through detection blind spots:

[0030] By setting process benchmarks such as reference planes and multiple reference points in the rigid area of ​​the split parts, the internal position relationship of the semi-closed structure is converted into externally measurable targeted point cloud data, which solves the problem that traditional methods cannot detect internal structures. The assembly surface and hole position accuracy of complex internal cavities can be indirectly evaluated through external benchmarks.

[0031] Quantitative deformation assessment:

[0032] The fitting and comparison of targeted point cloud data before and after welding can accurately calculate the three-dimensional deformation of parts (such as displacement, torsion, and bending), with the error controlled within ±0.05mm. This realizes the quantitative analysis of welding deformation, replaces traditional empirical judgment, and improves detection accuracy and reliability.

[0033] Improve processing efficiency:

[0034] The segmented processing combined with special fixture positioning shortens the part assembly time before welding, and after welding, the dual evidence of three-coordinate intensive point sampling and appearance scanning improves the inspection efficiency compared with traditional methods.

[0035] Full process precision assurance:

[0036] The reference point processing accuracy is controlled at the μm level, and the laser tracker adjusts the welding positioning error in real time. Combined with the adjustable positioning block structure of the fixture, it ensures that the overall position accuracy of the parts after welding meets aviation-grade requirements (such as assembly hole position accuracy ≤ 0.1mm), significantly reducing the rework rate caused by deformation tolerance. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 It is a schematic diagram of the semi-enclosed structure titanium alloy box parts;

[0038] Figure 2 It is a schematic diagram of the segmented front view of the parts of the present invention;

[0039] Figure 3 It is a schematic top view of the parts of the present invention in sections;

[0040] Figure 4 It is a schematic diagram of the X-piece split of the present invention;

[0041] Figure 5 This is a schematic diagram of the Z component of the present invention;

[0042] Figure 6 This is a schematic diagram of the split Y component of the present invention;

[0043] Figure 7 It is a schematic diagram of the parts after welding and assembly;

[0044] Figure 8 It is a schematic structural diagram of the clamping state of the clamp of the present invention.

[0045] Markings in the figure:

[0046] 1-reference plane, 2-reference point, 3-splint, 4-machining platform, 5-pin hole, 6-X piece, 7-Y piece, 8-Z piece. DETAILED DESCRIPTION

[0047] The present invention will be described in detail below with reference to the accompanying drawings.

[0048] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0049] Example 1

[0050] In this embodiment, if Figure 1 、 2 As shown, a method for integrally welding a large titanium alloy part comprises the following steps:

[0051] S1: Divide the semi-enclosed titanium alloy box parts into three-section split structures of X, Y, and Z;

[0052] S2: Process the X, Y, and Z parts to their final dimensions, leaving machining allowances for the mounting surfaces and welds.

[0053] S3: Processing high-precision process datums on the X, Y, and Z parts respectively, the process datums including a datum plane 1 and a plurality of datum points 2, the plurality of datum points 2 being arranged in a plane adjacent to the datum plane 1, and at least one datum point 2 being arranged on the edge of the datum plane 1;

[0054] S4: Using the reference plane 1 and multiple reference points 2 as the assembly positioning reference, weld the X, Y, and Z parts into a whole;

[0055] S5: Finish the welded parts to remove the machining allowances on the mounting surface and weld position.

[0056] Steps S1-S5 involve geometrically dividing a semi-enclosed titanium alloy housing (e.g., a load-bearing housing for an aircraft engine) into three separate sections: X (front), Y (middle), and Z (rear). This division is achieved by cutting along the length of the housing at the boundaries of the complex internal structure, forming three independent components. During the machining phase, the X, Y, and Z components are CNC-machined separately. A machining allowance of 0.5-1mm is reserved for mounting surfaces (e.g., flanges connecting to other components) and welds (e.g., butt joints between components). This allowance is designed to account for dimensional deviations caused by thermal deformation during welding, and to provide correction margin for subsequent finishing. High-precision process datums are machined on each component: the top surface of component X (6) is selected as datum plane 1 (this plane is the largest flat surface, facilitating positioning). Three datum points 2 (cylindrical pin holes 5) are set on the front surface adjacent to datum plane 1, with at least one datum point 2 located at the edge of the top and front surfaces. Datum plane 1 and datum point 2 together form the positioning datum. During assembly welding, datum plane 1 is placed on the tooling platform. Datum point 2 cooperates with the fixture's locating pins to precisely align the X, Y, and Z parts. TIG welding is performed, starting from the middle section Y and moving symmetrically toward the X and Z ends to reduce thermal stress concentration. After welding, a five-axis machining center is used to fine-machine the mounting surface and weld position. Datum plane 1 and datum point 2 are used to reposition the parts, ensuring that the machining coordinate system is consistent with the assembly datum. The reserved machining allowance is removed to achieve the designed dimensional accuracy of the part.

[0057] The three-section split structure solves the problem that the internal structure of the semi-enclosed box is difficult to directly process, and avoids the influence of welding deformation on key dimensions by reserving processing allowance; the setting of high-precision process datum provides a reliable geometric reference for assembly positioning, ensuring the relative position accuracy of the split parts during welding, and controlling the dimensional accuracy of the overall parts from the source, solving the problem of difficult-to-control welding deformation caused by inconsistent positioning datums in traditional segmented processing.

[0058] Furthermore, in step S3, after the X, Y, and Z parts are processed, the relative position relationship of each split part is measured by a three-dimensional coordinate measuring machine with the reference plane 1 and multiple reference points 2 as references to form reference point 2-bit cloud data.

[0059] After rough machining of the X, Y, and Z parts (reserving allowance), a three-dimensional coordinate measuring machine is used to collect reference data for each component: using reference plane 1 as the measurement reference surface and reference point 2 as the three-dimensional coordinate to construct reference point 2. During the measurement process, the coordinate system of the three-dimensional coordinate measuring machine is aligned with the designed three-dimensional coordinates of reference point 2 of the part to ensure data consistency. The coordinates of reference plane 1 (plane equation) and reference point 2 of each component are obtained through measurement, forming point cloud data containing three-dimensional coordinate information (for example, each component contains one plane point cloud cluster and 2-3 single-point coordinates). This data reflects the actual reference position of each component after machining, providing accurate geometric parameters for subsequent assembly.

[0060] The high-precision measurement of the three-dimensional coordinate measuring machine (accuracy can reach ±0.01mm) can accurately obtain the actual reference position of each component. The resulting two-bit cloud data of the reference point serves as the actual measurement basis for subsequent assembly positioning, solving the problem of large errors in traditional manual measurement of reference positions. It provides data support for establishing a unified assembly reference coordinate system and ensures the consistency between the theoretical design reference and the actual processing reference.

[0061] Furthermore, the 2-bit cloud data of the reference points of the X, Y, and Z parts are fitted into the targeted point cloud data of the entire part as a unified reference coordinate system for welding assembly.

[0062] Import the 2-bit cloud data of the reference points of the X, Y, and Z parts into the computer-aided measurement software. First, use the reference plane 1 of the X part 6 as the overall reference plane 1, and uniformly convert the coordinates of the reference points 2 of the three separate parts to the overall coordinate system to form targeted point cloud data containing all reference points 2 (that is, the targeted point cloud data of the entire part). This data serves as a unified reference for welding assembly to ensure that the three separate parts are positioned in the same coordinate system.

[0063] By establishing a unified reference coordinate system through coordinate fitting, the assembly error problem caused by the inconsistent references of the separate parts in traditional segmented processing is solved. This enables the welding assembly process to be precisely adjusted based on the same geometric reference, ensuring the relative position accuracy between the separate parts from a data level and providing a unified theoretical reference benchmark for the subsequent real-time measurement of the laser tracker.

[0064] Furthermore, before welding, a laser tracker is used to measure the target point data of the X, Y, and Z parts. By comparing the target point cloud data of the overall part with the actual measurement data, a special fixture is used to adjust the relative position relationship of each separate part to the design accuracy requirements.

[0065] An adjustable positioning fixture is installed on the welding platform. A laser tracker is used to measure the target points of each component (i.e., reference point 2 and key positioning points) in real time. The measured coordinate data is compared with the target point cloud data of the entire part to calculate the translational deviation of each component in the three-dimensional coordinate direction. Based on this deviation data, the position and posture of the component are adjusted by controlling the position of the fixture. After adjustment, measurement and verification are carried out again until the deviation is within the design accuracy requirements.

[0066] The combination of high-precision real-time measurement from a laser tracker and automated fixture adjustment enables dynamic calibration of component positions, resolving the inaccuracy inherent in traditional manual assembly, which relies on empirical adjustments. By comparing theoretical targeted point cloud data with measured data, deviations in all directions can be quantified and accurately corrected, ensuring that the relative positions of components before welding fully meet design requirements, thus limiting the source of welding deformation errors during assembly.

[0067] Furthermore, the reference plane 1 serves as the reference plane 1 for assembly positioning, and the multiple reference points 2 serve as the origin of the three-dimensional coordinate system and the positioning points in the coordinate axis direction, together forming the assembly positioning reference system of the X, Y, and Z parts.

[0068] The datum plane 1 serves as the main positioning surface for assembly, and its function is to limit the plane position of the split part. Among multiple datum points 2, the datum point 2 at the edge of the datum plane 1 is selected as the origin of the coordinate system. The other datum points 2 and the origin form the positioning datum of the three-dimensional coordinate system. The three-coordinate measuring instrument measures the overall position of the part through a coordinate system consisting of a datum plane and three points.

[0069] The coordination between datum plane 1 and datum point 2 not only provides an accurate coordinate reference, but also provides a stable support foundation for resisting thermal deformation during welding, ensuring that the split parts will not shift or rotate during welding, and guaranteeing the overall assembly accuracy from the positioning principle.

[0070] Furthermore, the welding of the X, Y, and Z parts is positioned using a fixture or tooling to achieve precise assembly of the separate parts.

[0071] The welding fixture consists of a base plate and three sets of clamping plates 3 (one for each of the X, Y, and Z components). Each set of clamping plates 3 consists of two perpendicularly arranged clamping plates 3. The clamping surfaces of the clamping plates 3 are machined to match the curved shape of the titanium alloy part's side surface (formed by obtaining part shape data through 3D scanning). Elastic rubber pads are installed on the clamping surfaces to prevent surface damage during clamping. During positioning, the X component 6 is first placed on the base plate, with the datum plane 1 aligned with the base plate's support surface. The side clamping plates 3 are moved via a screw-nut mechanism to clamp the X component 6. The Y component 7 and Z component 8 are then installed in sequence. The datum point 2 of each split component corresponds to a locating pin on the fixture (the diameter of the pin hole 5 matches the pin hole 5 of the datum point 2). After the locating pin is inserted into the pin hole 5 of the datum point 2, the split component is secured by the lateral clamping force of the clamping plates 3. During the clamping process, the displacement of the clamping plates 3 is monitored using a micrometer to ensure uniform clamping force and prevent deformation of the split component due to uneven force.

[0072] Beneficial Effects: The curved clamping surface of the specialized fixture matches the part's contour, providing uniform clamping force and preventing localized stress concentration caused by traditional flat clamping. The precise alignment of the locating pin and datum point 2 allows for rapid positioning of the split component, eliminating the tedious centering process. The fixture's structural design combines a positioning datum with a clamping mechanism to ensure the relative position of the split components remains constant during welding. This solves the problem of assembly displacement of large parts caused by their own weight and welding thermal stress, significantly improving the efficiency and accuracy of welding assembly.

[0073] Furthermore, a method for overall inspection of large titanium alloy parts includes the following steps:

[0074] A1: After the welding process is completed, a three-coordinate measuring machine is used to measure three sets of process datums (datum plane 1 and multiple datum points 2) of the three parts to generate post-weld point cloud data;

[0075] A2: Fit and compare the post-weld point cloud data with the targeted point cloud data measured before welding to calculate the actual deformation and offset data of the part;

[0076] A3: Use dense point measurement and shape scanning technology to detect the shape of parts after welding to verify deformation and offset data.

[0077] After finishing welding, the part's three sets of process datums (datum plane 1 and datum point 2) are first remeasured using a three-dimensional coordinate measuring machine (CMM). This generates post-weld point cloud data (including the plane equations and the 3D coordinates of each datum point 2). This post-weld point cloud data, along with the pre-weld fitted, targeted point cloud data for the entire part, is imported into analysis software for automatic fitting. The software then calculates the part's translational deformation along its 3D coordinate axes and its rotational deformation about the three axes. To corroborate this deformation data, a laser scanner scans the part's contours densely, generating point cloud data. This data is then compared with the design model to detect deviations in the overall contour. This is particularly true for the internal assembly surfaces of semi-enclosed structures. A probe probe is inserted into the interior to collect data on key points, ensuring that deformation within the internal structure is accurately captured.

[0078] This inspection method quantitatively assesses welding deformation by comparing data before and after reference point 2, resolving the inability of traditional inspections to accurately capture internal structural deformation. Combining dense sampling with contour scanning technology not only verifies deformation in the reference positioning area but also covers the entire contour, forming a multi-dimensional inspection system. Through data fitting and comparison, it can accurately determine whether deformation exceeds the design tolerance, providing a scientific basis for subsequent process optimization and addressing the challenges of blind spots and insufficient accuracy assessment in existing technologies.

[0079] Furthermore, a fixture for welding large titanium alloy parts includes: a splint 3 and a processing platform 4. The splint 3 includes three groups, which are arranged on the processing platform 4 corresponding to the X, Y, and Z parts, and form a clamping surface that matches the shape of the two side surfaces of the titanium alloy parts. The splint 3 cooperates with the processing platform 4 to realize the positioning constraint of the X, Y, and Z parts in three-dimensional space.

[0080] Furthermore, it includes a positioning pin, and the clamping plate 3 is provided with a pin hole 5 corresponding to the position of the reference point 2. After the clamping plate 3 clamps the X, Y, and Z parts, the positioning is performed by inserting the positioning pin into the pin hole 5 and the reference point 2.

[0081] Furthermore, the processing platform 4 is configured as a multi-axis adjustable structure.

[0082] The fixture includes a processing platform 4 and three sets of clamping plates 3: The processing platform 4 is a steel structure platform that can be raised and lowered and translated in a two-dimensional plane. Four servo motor-driven screw and nut mechanisms are installed at the bottom. The platform height and position can be adjusted via a control panel to accommodate the centering requirements of welding positions at different heights. Each set of clamping plates 3 (X clamping plate, Y clamping plate, and Z clamping plate) is installed on the processing platform 4 via T-slots. The clamping surfaces of the clamping plates 3 are curved surfaces that match the shape of the two side surfaces of the titanium alloy part (customized based on the three-dimensional model of the part through reverse engineering technology). Pressure sensors are installed inside the clamping surfaces to monitor the clamping force in real time. Pin holes 5 corresponding to the position of reference point 2 are set on the clamping plates 3 (with the same diameter as the pin holes 5 of reference point 2). When the clamping plates 3 clamp the X, Y, and Z parts, the locating pins are inserted into the pin holes 5 and the pin holes 5 of the reference point 2 of the part to achieve precise positioning.

[0083] The height of the elevating processing platform 4 allows for alignment and centering of parts at various heights and planes. The curved clamping surface of the clamping plate 3 conforms to the part's contour, evenly distributing the clamping force and preventing deformation. The alignment pins and datum points 2 ensure "pin hole 5 positioning," ensuring that the position of the split component in the fixture is consistent with the design datum. This fixture structure precisely secures the split component in place for welding through three-dimensional positioning constraints, resolving the difficulty of positioning large parts during assembly. Its adjustability and high-precision fit significantly improve the stability of the welding process and the overall assembly accuracy of the part.

[0084] The above description is only a preferred embodiment of the invention and is not intended to limit the invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the invention should be included in the scope of protection of the invention.

Claims

1. A method for integrally welding large titanium alloy parts, characterized by: The following steps are involved: S1: Divide the semi-enclosed titanium alloy box parts into three-section split structures of X, Y, and Z; S2: Processing the X, Y, and Z parts to their final sizes, with machining allowances reserved for the mounting surfaces and weld positions; S3: Processing high-precision process datums on the X, Y, and Z parts respectively, wherein the process datums include a datum plane and multiple datum points, wherein the multiple datum points are arranged in a plane adjacent to the datum plane, and at least one datum point is arranged on the edge of the datum plane; after the X, Y, and Z parts are processed, the relative position relationship of each separate part is measured by a three-dimensional coordinate measuring machine with the datum plane and the multiple datum points as the datum, to form datum point cloud data, and the datum point cloud data of the X, Y, and Z parts are fitted into the targeted point cloud data of the entire part as a unified datum coordinate system for welding assembly; S4: Using the reference plane and multiple reference points as assembly positioning references, wherein the reference plane is used as the reference plane for assembly positioning, and the multiple reference points are used as the origin of the three-dimensional coordinate system and the positioning points in the coordinate axis direction, together forming the assembly positioning reference system of the X, Y, and Z parts. Before welding, using a laser tracker to measure the target point data of the X, Y, and Z parts, by comparing the target point cloud data of the overall part with the actual measurement data, adjusting the relative position relationship of each separate part to the design accuracy requirement through a special fixture, and welding the X, Y, and Z parts into a whole; S5: Finish the welded parts to remove the machining allowances on the mounting surface and weld position.

2. A method for integrally welding large titanium alloy parts according to claim 1, characterized in that: The welding of the X, Y, and Z parts adopts fixtures or tooling for positioning to achieve accurate assembly of the separate parts.

3. The method for integrally welding large titanium alloy parts according to claim 1, characterized in that: The following steps are also included: A1: After the welding process is completed, a three-coordinate measuring machine is used to measure the three sets of process datums of the part, including the datum plane and multiple datum points, to generate post-weld point cloud data; A2: Fit and compare the post-weld point cloud data with the targeted point cloud data measured before welding to calculate the actual deformation and offset data of the part; A3: Use dense point measurement and shape scanning technology to detect the shape of parts after welding to verify deformation and offset data.

4. A method for integrally welding large titanium alloy parts according to claim 2, characterized in that: The fixture includes a clamping plate and a processing platform. The clamping plate includes three groups, which are arranged on the processing platform corresponding to the X, Y, and Z parts, and form a clamping surface that matches the shape of the two side surfaces of the titanium alloy part. The clamping plate cooperates with the processing platform to achieve positioning constraints of the X, Y, and Z parts in three-dimensional space.

5. A method for integrally welding large titanium alloy parts according to claim 4, characterized in that: It includes a positioning pin, and the clamp is provided with a pin hole corresponding to the reference point position. After the clamp clamps the X, Y, and Z parts, the positioning is performed by inserting the positioning pin into the pin hole and the reference point.

6. A method for integrally welding large titanium alloy parts according to claim 4, characterized in that: The processing platform is configured as a multi-axis adjustable structure.

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