A method for machining a monolithic composite cylindrical member and a cylindrical member obtained using the method

Abstract

This application discloses a method for processing an integral composite cylindrical component and the cylindrical component obtained by the method, relating to the field of CNC machine tool processing technology. This application involves installing and positioning the component in a first state, transferring the reference, then measuring the reference, and fitting the reference remeasurement results in a second state to achieve reference transformation. The processing coordinate offset value is obtained in the obtained measurement coordinate system. Then, the component is restored to the first state. If the processing coordinate offset value is verified to be correct, the first processing is performed, followed by installing a reference block and measuring the three-dimensional reference. Then, the reference remeasurement results in a third state are fitted to achieve reference transformation again. Finally, if the processing coordinate offset value is verified to be correct, the second processing is performed to achieve precise CNC machining of all surfaces of the integral cylindrical component.

Description

Technical Field

[0001] This application relates to the field of CNC machine tool processing technology, specifically to a method for processing integral composite cylindrical components and the cylindrical components obtained by using this method. Background Technology

[0002] Carbon fiber reinforced composites, due to their superior mechanical properties, have gradually replaced traditional metal materials such as aluminum alloys and high-strength steel as the mainstream material for aerospace structural components. With the development of molding technology, product structures have evolved from single parts to large, complex components, exhibiting characteristics such as large spatial dimensions, high machining precision, and complex shapes. Although composite materials have been widely used in aircraft components, numerous engineering applications have revealed that composite materials generally exhibit large and irregular curing deformation. Traditional clamping and positioning methods cannot meet the requirements for precise clamping and CNC machining of complex three-dimensional cylindrical structures. Summary of the Invention

[0003] The main objective of this application is to provide a method for processing integral composite cylindrical components and the cylindrical components obtained by the method, aiming to solve the problem that the existing technology cannot meet the requirements for precise clamping and CNC machining of complex cylindrical structures.

[0004] To achieve the above objectives, the technical solutions adopted in the embodiments of this application are as follows:

[0005] In a first aspect, embodiments of this application provide a method for processing an integral composite cylindrical component, comprising the following steps:

[0006] Obtain the blank profiles of the target component on surfaces A, B, and C in the first state and the center of the reference holes on them, and the center of the reference holes on surfaces A, B, and C in the second state of the target component; wherein, the first state is positioned by the DA hole, the second state is positioned by the reference holes on surface C, and the second state is the target component rotated 90 degrees in the first state.

[0007] The least squares method is used to fit the center of the reference hole on surfaces A, B, and C in the first and second states, and the measurement coordinate system is obtained.

[0008] The least squares method is used to fit the blank profiles of surfaces A and B in the first and second states and the center of the reference hole on them to obtain the machining coordinate offset value in the first state; wherein, the blank profiles of surfaces A and B in the second state are measured in the measurement coordinate system.

[0009] If the machining coordinate offset value in the first state is verified to be correct, perform the first machining on surface A, surface B and surface C, install the reference block in the machined surface area and measure its three-dimensional reference.

[0010] The least squares method is used to fit the three-dimensional reference of the reference block measured in the third state and the first state to obtain the machining coordinate offset value in the third state; wherein, the third state is positioned by the reference hole on the C surface, and the third state is the target component rotated 180 degrees in the first state.

[0011] If the machining coordinate offset value in the third state is verified to be correct, perform the second machining on surfaces A, B, and D.

[0012] In one possible implementation of the first aspect, the reference holes are evenly distributed on surfaces A, B, and C, and are not located in the R-corner region of the target component.

[0013] In one possible implementation of the first aspect, in the second state, the target component is installed by multiple support blocks, which are distributed along the length of the target component, and the overlap between the R-corner region of the support blocks and the R-corner region of the target component does not exceed 30%.

[0014] In one possible implementation of the first aspect, before verifying that the machining coordinate offset value in the first state is correct, the method further includes:

[0015] Based on the blank profiles of surfaces A, B, and C, and the magnitude of the machining coordinate offset values ​​in the first state, the correctness of the machining coordinate offset values ​​is verified.

[0016] In one possible implementation of the first aspect, before verifying that the machining coordinate offset value in the first state is correct, the method further includes:

[0017] Verify whether the target area exists on the blank surface of surface C, and adjust the machining program of the first machining step based on the verification results.

[0018] In one possible implementation of the first aspect, the method further includes, prior to verifying the correctness of the machining coordinate offset value in the third state:

[0019] Verify whether the target area exists on the blank surface of surface D, and adjust the machining program for the second machining step based on the verification results.

[0020] In one possible implementation of the first aspect, before obtaining the blank profiles of surfaces A, B, and C of the target component in its first state and the center of the orifice of the reference hole thereon, the method further includes:

[0021] Positioning is achieved using the DA hole, and the target component is fixed on the milling fixture using a series of coarse positioning pins, so that the target component is in the first state.

[0022] In one possible implementation of the first aspect, the target component is fixed to the milling fixture using a coarse locating series pins with DA holes for positioning, so that after the target component is in the first state, the method further includes:

[0023] In the first state, the target component is rotated 90 degrees and positioned using the reference hole on the C-face. The target component is then fixed to the support block using a precision positioning pin.

[0024] In one possible implementation of the first aspect, the least squares method is used to fit the blank profiles of surfaces A and B in the first and second states, as well as the center of the reference hole on them, to obtain the machining coordinate offset value in the first state, including:

[0025] Based on the principle of the minimum solid part being enveloped by the machining allowance, the least squares method is used to fit the blank surfaces of surfaces A and B in the first and second states and the center of the reference hole on them to obtain the machining coordinate offset value in the first state.

[0026] Secondly, embodiments of this application provide a cylindrical component, which is obtained by the integral composite cylindrical component processing method provided in any of the first aspects above.

[0027] Compared with the prior art, the beneficial effects of this application are:

[0028] This application proposes a method for processing an integral composite cylindrical component and the cylindrical component obtained by the method. The method involves installing and positioning the component in a first state, transferring the reference, measuring the reference, and fitting the results of the reference remeasurement in a second state to achieve reference transformation. The processing coordinate offset value is obtained in the calculated measurement coordinate system. The component is then restored to the first state. If the processing coordinate offset value is verified to be correct, the first processing is performed, a reference block is installed, and three-dimensional references are measured. The reference transformation is then achieved again by fitting the results of the reference remeasurement in a third state. Finally, if the processing coordinate offset value is verified to be correct, the second processing is performed to achieve precise CNC machining of all surfaces of the integral cylindrical component. Attached Figure Description

[0029] Figure 1 A schematic flowchart illustrating the processing method for an integral composite cylindrical component provided in this application embodiment;

[0030] Figure 2 This is a schematic diagram of the clamping of the target component in the first state in the integral composite cylindrical component processing method provided in the embodiments of this application;

[0031] Figure 3 This is a schematic diagram of the clamping of the target component in the second state in the integral composite cylindrical component processing method provided in the embodiments of this application;

[0032] Figure 4 This is a schematic diagram of the installation of the reference block of the target component in the integral composite cylindrical component processing method provided in the embodiments of this application;

[0033] Figure 5 A schematic diagram of the clamping of the target component in the third state in the integral composite cylindrical component processing method provided in the embodiments of this application;

[0034] Figure 6 A flowchart illustrating one implementation of the method for processing integral composite cylindrical components provided in this application.

[0035] The markings in the diagram are: 1-Target component, 2-DA hole, 3-Rough positioning series pin, 4-Milling clamping fixture, 5-Reference hole, 6-Tooling process hole, 7-Tooling ZO plane, 8-Fine positioning pin, 9-Support block, 10-Reference block, 11-Reference block mounting hole, 12-Reference block X-direction reference surface, 13-Reference block process hole. Detailed Implementation

[0036] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0037] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in the embodiments of this application are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0038] In this application, unless otherwise expressly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0039] Furthermore, if the embodiments of this application involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0040] Carbon fiber reinforced composite materials have gradually replaced traditional metal materials such as aluminum alloys and high-strength steel as the mainstream material for aerospace structural components due to their excellent mechanical properties. With the development of molding technology, the product structure has shifted from single parts to large and complex components, exhibiting characteristics such as large spatial dimensions, high processing precision, and complex shapes.

[0041] For critical functional components such as the cylindrical structure of aircraft engine air intakes, existing technologies propose a design scheme of "integral composite thick skin inner cylinder + sparse bulkhead" to replace the original structural design of "segmented thin metal skin + dense bulkhead". This transforms the previously multi-part assembly into a single integral unit and introduces more self-positioning structures, reducing the number of structural parts and connectors from the source, thus lowering assembly complexity. This not only improves the aircraft's "fewer-piece" assembly and delivery capabilities but also achieves lightweight aircraft design and efficient bleed air transmission. Simultaneously, it fully utilizes the radar wave absorption capabilities of carbon fiber composite materials and the integral air duct profile to enhance the aircraft's overall stealth capabilities.

[0042] Existing technologies for integral molding of cylindrical carbon fiber reinforced composite materials are relatively mature. Through the design of various types of cylindrical components and research on CNC machining technology, as well as machining experiments on typical features such as assembly surface milling, contour trimming, and various connection and positioning holes, a complete technical system covering clamping, machining, and testing technologies has been formed. Although composite materials have been widely used in aircraft components in China, numerous engineering applications have revealed that composite materials generally exhibit large and irregular curing deformation. Traditional clamping and positioning methods cannot meet the requirements for precise clamping and CNC machining of complex three-dimensional cylindrical structures.

[0043] Therefore, embodiments of this application provide a method for processing integral composite cylindrical components, as shown in the attached figure. Figure 1-6 As shown, it includes the following steps:

[0044] S10: Obtain the blank profiles of the target component on surfaces A, B, and C in the first state and the center of the reference holes on them, and the center of the reference holes on surfaces A, B, and C in the second state of the target component; wherein, the first state is positioned by the DA hole, the second state is positioned by the reference hole on surface C, and the second state is the target component rotated 90 degrees in the first state.

[0045] In the specific implementation process, target component 1, namely an aircraft part, is a cylindrical component. It is a monolithic composite cylindrical component, integrally cured from carbon fiber material, with a tetrahedral hollow structure. The cross-sectional width (height) is 1-3 meters, and the length spans 2-5 meters. The main processing involves milling the cylindrical surface, creating assembly positioning holes, and cutting the port contours. Only a rough allowance is laid on the surface of the cylindrical body to be processed, with a thickness of 2-2.5 mm. The width is generally 110% of the theoretical width of the cylindrical surface, with a theoretical machining allowance of 1-1.5 mm and a machining compensation of 0.5-1.5 mm. Positioning is achieved using hole DA 2, and the target component is fixed to the milling clamp 4 using coarse positioning pins 3. A coordinate system is established using the 3-Φ16H9 tooling process holes 6 and the ZO plane 7 on the milling clamp 4, as shown in the attached diagram. Figure 2 As shown, the clamping state can be defined as the 0° clamping state, i.e., the first state, and reference holes 5 are made on surfaces A, B, and C at the end allowances of the cylinder. That is, before obtaining the blank profiles of surfaces A, B, and C of the target component in the first state and the center of the reference holes thereon, the method further includes:

[0046] Positioning is achieved using the DA hole, and the target component is fixed on the milling fixture using a series of coarse positioning pins, so that the target component is in the first state.

[0047] Furthermore, DA holes 2 are formed on the molding fixture at the end contour allowances after the carbon fiber composite cylindrical component has cured. The hole diameter is generally Φ8.2H9, and the hole position accuracy is ±0.1mm. The contour allowance at both ends of the cylindrical body is generally 40 (+5 / 0mm), and the DA holes should be distributed in the middle of the allowance. To mitigate the impact of DA hole position deviation and misalignment with the milling clamp positioning holes caused by curing deformation after demolding, the milling clamp fixture 4 is equipped with a series of coarse positioning pins 3, such as Φ8.2H9, Φ8.1H9, and Φ8.0H9. During assembly, the matching series of coarse positioning pins 3 can be selected according to the amount of hole misalignment to achieve coarse positioning of part 1 and milling clamp fixture 4.

[0048] The reference holes 5 are evenly distributed on surfaces A, B, and C of the cylinder. The holes should be positioned to avoid the radius (R-angle) area, at least 40mm from the edge of the R-angle. The hole diameter is generally Φ6.35H9, and the hole position accuracy is ±0.1mm. The column height where the 16H9 process hole is located on the milling fixture 4 is generally 150mm, and the distance from the cylinder end face is ≥500mm to avoid interference and collision between the machine tool spindle and the column during machining.

[0049] Under the aforementioned coordinate system, the center of the borehole of the reference hole 5 on the blank surfaces A, B, and C of the cylinder is measured using a measuring machine. After rotating the cylinder 90 degrees, the reference hole is re-measured. The cylinder is then rotated 90 degrees counterclockwise and positioned using the reference hole 5 on surface C. The entire target component 1 is fixed to the support block 9 using precision positioning pins 8. At this point, the clamping state can be defined as a 90° clamping state, as shown in the attached figure. Figure 3 As shown, in the second state, the center of the remaining reference holes 5 is re-measured using a measuring machine. That is: using hole DA for positioning, the target component is fixed to the milling fixture using coarse positioning pins, so that after the first state, the method further includes:

[0050] In the first state, the target component is rotated 90 degrees and positioned using the reference hole on the C-face. The target component is then fixed to the support block using a precision positioning pin.

[0051] All support blocks 9 are distributed along the length of the cylinder, with 3-5 blocks in total. The contact gap between the support surface and the theoretical blank surface of the cylinder is ≤0.1mm. The overlap area between the R-corner area of ​​the support block and the R-corner area of ​​the cylinder should not exceed 30% of the area of ​​the R-corner area of ​​the cylinder, ensuring that the R-zone surface measurement is accessible. After rotating 90°, only the precision positioning pin 8 is needed to fix the target component 1 onto the support block 9. No requirements are placed on the clamping posture or measurement coordinate system.

[0052] S20: The least squares method is used to fit the center of the reference hole on surfaces A, B and C in the first and second states, and the measurement coordinate system is obtained.

[0053] In the specific implementation process, the least squares method is used to iteratively fit the center of the aperture of the reference hole 5 under two clamping postures, unifying the measurement reference for the two clamping postures. The reference error is within ±0.1mm, thereby obtaining the measurement coordinate system. Furthermore, the transformation matrix of the measurement reference under the 90° clamping posture relative to the measurement coordinate system under the 0° clamping posture can be obtained through iterative fitting, thereby converting and obtaining the measurement coordinate system under the 90° clamping posture.

[0054] S30: The least squares method is used to fit the blank profiles of surfaces A and B in the first and second states and the center of the reference hole on them to obtain the machining coordinate offset value in the first state; wherein, the blank profiles of surfaces A and B in the second state are measured in the measurement coordinate system.

[0055] In the specific implementation process, the blank surfaces of surfaces A, B, and D of the cylinder are measured using a measuring machine under the measurement coordinate system established in the aforementioned steps. The blank surfaces of surfaces A and B, measured repeatedly under two clamping postures, and the center of the orifice of the reference hole 5 are subjected to least squares iterative fitting. Based on the principle of minimizing the solid dimension of the part by the machining allowance, the machining coordinate X, Y, and Z offset values ​​are optimized and determined; that is, the least squares method is used to fit the blank surfaces of surfaces A and B and the center of the orifice of the reference hole in the first and second states to obtain the machining coordinate offset values ​​in the first state, including:

[0056] Based on the principle of the minimum solid part being enveloped by the machining allowance, the least squares method is used to fit the blank surfaces of surfaces A and B in the first and second states and the center of the reference hole on them to obtain the machining coordinate offset value in the first state.

[0057] Furthermore, the transformation matrix of the measurement reference under the 0° clamping posture relative to the measurement coordinate system under the 90° clamping posture can be obtained through iterative fitting, thereby converting and obtaining the offset value of the measurement coordinate system under the 0° clamping posture.

[0058] S40: If the machining coordinate offset value in the first state is verified to be correct, perform the first machining on surface A, surface B and surface C, install the reference block in the machined surface area and measure its three-dimensional reference.

[0059] In the specific implementation process, the clamping posture is restored to the first state, and the coordinate system is re-established. The center of the hole of the reference hole 5 is measured on the machine and the posture is adjusted to ensure the consistency between the clamping state and the reference hole 5, with the measurement error within 0.1mm. After verifying that the machining coordinate offset value in the first state is correct, milling of the A, B, and C surfaces, fabrication of assembly positioning holes, and end contour trimming are carried out. After completing the machining of the first surface, several reference blocks 10 are installed around the cylinder, as shown in the attached figure. Figure 4 As shown, the X, Y, and Z-axis reference blocks are used for measurement, ensuring they are installed in their theoretical positions with a measurement deviation within ±0.1mm. The reference blocks are distributed on the machined ruled surface area along the length of the cylinder, with an effective positioning area ≤0.02m². 2 The fitting gap should be ≤0.05mm. The number of reference blocks for a single section is generally 2-3, and their distribution space should encompass the entire composite cylindrical component. Furthermore, four reference block mounting holes 11 are provided on the bottom surface of the reference block 10. The hole diameter and hole position are consistent with the assembly positioning holes opened on the cylinder, which facilitates the precise installation of parts and cylinder. The three references are: the reference surface 12 of the reference block in the X direction, and the references in the Y and Z directions are the hole position Y value and Z value of the reference block process hole 13. The hole diameter is generally Φ12H9, and the hole position accuracy is ±0.1mm.

[0060] In one embodiment, before verifying that the machining coordinate offset value in the first state is correct, the method further includes:

[0061] Based on the blank profiles of surfaces A, B, and C and the magnitude of the machining coordinate offset values ​​in the first state, the correctness of the machining coordinate offset values ​​is verified.

[0062] Verify whether the target area exists on the blank surface of surface C, and adjust the machining program of the first machining step based on the verification results.

[0063] In the specific implementation process, based on the determined machining coordinate deviation values, the blank surfaces of surfaces A and B are re-measured on the machine to verify the correctness of the coordinate system offset values. The blank surface of surface C is also re-measured on the machine to verify whether there are under-milled or over-milled areas, i.e., the target area, and the machining program is adjusted accordingly. Specifically: the principle for judging the correctness of the coordinate offset values ​​is: the measured deviation values ​​of the blank surfaces of surfaces A and B are ≤ the fitting error values ​​in the aforementioned steps; the principle for judging under-milling of the blank surface of surface C is: the measured value of the blank surface of surface C minus the theoretical value < 0, and... If the amount exceeds the machining compensation, the solution is to add shims for compensation during the rear assembly. The criterion for determining whether the C-side blank surface has been over-milled is: measured value of C-side blank surface - theoretical value > 0. If the machining compensation is greater than the allowable amount, the solution is to perform adaptive normal lifting machining while ensuring the minimum thickness and strength of the cylinder. Where P... xi P yi P zi P represents the measured X, Y, and Z coordinate values ​​of the blank profile. xj P yj P zj These are the theoretical X, Y, and Z coordinate values ​​of the blank profile.

[0064] S50: The least squares method is used to fit the three-dimensional reference of the reference block measured in the third state and the first state to obtain the machining coordinate offset value in the third state; wherein, the third state is positioned by the reference hole on the C surface, and the third state is the target component rotated 180 degrees in the first state.

[0065] In the specific implementation process, the clamping is performed according to the initial clamping method, and a coordinate system is established. The three-dimensional reference of the machine-re-measured reference block 9 is then rotated 180 degrees and the reference is re-measured, as shown in the attached figure. Figure 5 As shown, the least squares method is used to iteratively fit the three-dimensional reference of the reference block 9 under two clamping postures to determine the offset values ​​of machining coordinates X, Y, and Z.

[0066] S60: If the machining coordinate offset value in the third state is verified to be correct, perform the second machining on surfaces A, B, and D.

[0067] In the specific implementation process, the verification of correctness mentioned in this step is the same as that in the aforementioned embodiment, that is: before verifying that the machining coordinate offset value in the third state is correct, the method further includes:

[0068] Verify whether the target area exists on the blank surface of surface D, and adjust the machining program for the second machining step based on the verification results.

[0069] The accuracy of the coordinate system offset values ​​was verified by machine re-measuring the blank surfaces of cylinder surfaces A, B, and D. The presence of under-milled or over-milled areas on the blank surface of cylinder surface D was verified, and the machining program was adjusted accordingly. Milling of the blank surfaces of target component 1 cylinder surfaces A, B, and D, fabrication of assembly positioning holes, and end contour trimming were carried out, thereby achieving precise CNC machining of all surfaces of the overall composite cylinder.

[0070] In this embodiment, the reference is transferred by installation and positioning in the first state, and then the reference is measured. The reference transformation is achieved by fitting the reference remeasurement results in the second state. The machining coordinate offset value is obtained in the obtained measurement coordinate system. Then, the system is restored to the first state. If the machining coordinate offset value is verified to be correct, the first machining is performed, the reference block is installed, and the three-dimensional reference is measured. Then, the reference transformation is achieved again by fitting the reference remeasurement results in the third state. Finally, if the machining coordinate offset value is verified to be correct, the second machining is performed to achieve precise CNC machining of all surfaces of the overall cylindrical component.

[0071] As attached Figure 6 As shown in the attached document Figure 6 The present application will be further described below with reference to the embodiments shown:

[0072] Step 1 reference transfer is performed in the 0° clamping position. A series of pins are used to roughly position and clamp the part with the DA hole. A coordinate system is established according to the tooling process hole and ZO plane, and the reference hole is numerically controlled.

[0073] Perform the reference measurement in step 2 under the 0° clamping posture, and use the measuring machine to measure the center of the reference hole opening in the coordinate system of step 1.

[0074] In step 3, the cylinder is rotated 90° and the reference is remeasured under the 90° clamping posture. The cylinder is rotated 90° counterclockwise, and the part is positioned and clamped by the reference hole using the positioning pin. The center of the reference hole opening is measured using a measuring machine in any coordinate system.

[0075] Perform the datum transformation in step 4 under the 90° clamping posture, fit the center of the datum hole opening under the two clamping postures, and inversely obtain the measurement coordinate system under the 90° clamping posture.

[0076] In step 5, the reference offset is performed under the 90° clamping posture. The blank surfaces of the cylinder A, B, and C surfaces are measured in the inverse coordinate system. The blank surfaces of the A and B surfaces and the center of the reference hole are fitted by the coincident measurements under the two clamping postures. The machining coordinate offset value of the 0° clamping state is optimized and determined according to the minimum envelope principle.

[0077] Step 6, clamping posture restoration, is performed in the 0° clamping posture. The cylinder is flattened to 0°. By measuring the center of the reference hole and adjusting the posture, the deviation of the hole center measurement is ensured to be within 0.1mm. The clamping posture is then restored to 0°.

[0078] Perform the benchmark verification in step 7 under the 0° clamping posture, input the coordinate offset value in step 5, re-measure the blank surface of cylinder A, B, and C on the machine, verify the correctness of the coordinate deviation value, measure the blank surface of cylinder C on the machine, determine the under-milled and over-milled areas, and adjust the machining program accordingly.

[0079] In the 0° clamping position, perform step 8, the first surface machining, i.e., the new datum design. Carry out surface milling, assembly positioning hole making and contour cutting of the CNC machining reachable area of ​​surfaces A, B, and C. Install datum blocks in the machined surface area and measure the X / Y / Z three-axis datums to ensure the installation accuracy is within ±0.1mm.

[0080] In step 9, the cylinder is rotated 180° under the 180° clamping posture. The cylinder is rotated 180°, and the parts are positioned and clamped using positioning pins and datum holes. A coordinate system is established according to the tooling process holes and ZO plane. The three-dimensional datum of the datum block is re-measured on the machine.

[0081] Step 10 datum transformation is performed under the 180° clamping posture. The three-dimensional datum of the datum block under the two clamping postures is fitted, and the machining coordinate offset value of the 180° clamping state is optimized and determined according to the minimum envelope principle.

[0082] Perform benchmark verification in step 11 under 180° clamping posture, input the coordinate offset value in step 10, re-measure the blank surface of cylinder A and B on the machine, verify the correctness of the coordinate offset value, measure the blank surface of cylinder D on the machine, determine the under-milled and over-milled areas, and adjust the machining program accordingly.

[0083] Step 12, the second surface machining, is performed in a 180° clamping position. This involves milling the surfaces of surfaces A, B, and D, creating assembly positioning holes, and trimming the contours to achieve precise CNC machining of all feature parts.

[0084] Based on the same inventive concept as in the foregoing embodiments, embodiments of this application also provide a cylindrical component, which is obtained by the integral composite cylindrical component processing method provided in the embodiments of this application.

[0085] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or system that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or system. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or system that includes that element.

[0086] The sequence numbers of the embodiments in this application are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0087] The above description is only a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A method for processing integral composite cylindrical components, characterized in that, Includes the following steps: The blank surfaces of the target component on surfaces A, B, and C in a first state, and the centers of the reference holes on those surfaces, are obtained. The centers of the reference holes on surfaces A, B, and C in a second state are also obtained. In the first state, the target component is coarsely positioned using the DA hole. In the second state, the target component is positioned using the reference holes on surface C. The second state is achieved by rotating the target component 90 degrees from its first state position. The reference holes are evenly distributed on surfaces A, B, and C, and are not located in the radius (R) corner region of the target component. In the second state, the target component is mounted using multiple support blocks distributed along the length of the target component, with the overlap between the radius (R) corner regions of the support blocks and the radius (R) corner regions of the target component not exceeding 30%. The least squares method is used to fit the center of the reference hole on surface A, surface B and surface C in the first state and the second state, and the measurement coordinate system is obtained. The least squares method is used to fit the blank surfaces of surface A and surface B, and the center of the reference hole on them, in the first and second states to obtain the machining coordinate offset value in the first state. Specifically, this includes: according to the principle of the machining allowance enveloping the minimum solid of the part, the least squares method is used to fit the blank surfaces of surface A and surface B, and the center of the reference hole on them, in the first and second states to obtain the machining coordinate offset value in the first state; wherein, the blank surfaces of surface A and surface B in the second state are measured in the measurement coordinate system. If the machining coordinate offset value in the first state is verified to be correct, the first machining is performed on the A surface, the B surface and the C surface. A reference block is installed in the machined surface area and its three-dimensional reference is measured. The least squares method is used to fit the three-dimensional reference of the reference block measured in the third state and the first state to obtain the machining coordinate offset value in the third state; wherein, the third state is positioned by the reference hole on the C surface, and the third state is the target component rotated 180 degrees in the first state. If the machining coordinate offset value in the third state is verified to be correct, the second machining is performed on surface A, surface B, and surface D.

2. The method for processing integral composite cylindrical components according to claim 1, characterized in that, Before verifying that the machining coordinate offset value in the first state is correct, the method further includes: Based on the blank profiles of surface A, surface B, and surface C, and the magnitude of the machining coordinate offset values ​​in the first state, the correctness of the machining coordinate offset values ​​is verified.

3. The method for processing integral composite cylindrical components according to claim 1, characterized in that, Before verifying that the machining coordinate offset value in the first state is correct, the method further includes: Verify whether the blank surface of surface C has a target area, and adjust the processing program of the first processing according to the verification result.

4. The method for processing integral composite cylindrical components according to claim 1, characterized in that, Before verifying that the machining coordinate offset value in the third state is correct, the method further includes: Verify whether the target area exists on the blank surface of surface D, and adjust the processing program of the second processing according to the verification result.

5. The method for processing integral composite cylindrical components according to claim 1, characterized in that, Before obtaining the blank profiles of surfaces A, B, and C of the target component in its first state and the center of the orifice of the reference hole thereon, the method further includes: Positioned by the DA hole, the target component is fixed on the milling fixture using a series of coarse positioning pins, so that the target component is in the first state.

6. The method for processing integral composite cylindrical components according to claim 5, characterized in that, The method further includes positioning the target component using the DA hole and fixing it to the milling fixture using coarse positioning pins, so that after the target component is in the first state, the method also includes: In the first state, the target component is rotated 90 degrees and positioned using the reference hole on the C-surface. The target component is then fixed to the support block using a precision positioning pin.

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