Size control method for TA1 aviation container spinning part with large diameter of 300mm
By accurately designing the spinning trajectory and adopting two-wheel synchronous multi-pass high-temperature hot spinning forming process, the problem of reduced dimensional consistency in TA1 aviation container spinning parts in large-scale production is solved, achieving high-quality and rapid forming effect.
Patent Information
- Application Number
- CN202311748044.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-12-19
- Publication Date
- 2025-06-20
AI Technical Summary
During the mass production process of existing TA1 aviation container spinning parts, the size consistency of aviation containers is reduced due to the reduction of mold dimensional accuracy, and there are problems such as complicated processing steps, low production efficiency, high manufacturing costs, large environmental pollution, and difficult product quality to ensure.
By accurately designing and controlling the spinning trajectory, two-wheel synchronous multi-pass high-temperature hot spin forming process is adopted, combining high-temperature general rotation and shear spinning to gradually form the shape of the ball table and the corresponding wall thickness dimensions, improving the forming quality and dimensional accuracy of aviation containers.
The rapid and high-quality forming of TA1 aviation container spinning parts with a large diameter Ø300mm is achieved. The tolerance of the same annular wall thickness is ≤0.1mm, and the actual measured wall thickness tolerance is ≤0.05mm, which significantly improves the dimensional accuracy and forming quality of the product.
Smart Images
Figure CN120169926A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to a method for controlling the dimensions of a spun part of a TA1 aviation container, and particularly to a method for controlling the dimensions of a spun part of a TA1 aviation container with a large diameter of Ø300 mm, belonging to the field of material processing technology. Background Art
[0002] In China, the deep drawing process is widely used to produce spun parts of TA1 aviation containers. To produce aviation container parts with different shapes and wall thicknesses, corresponding molds and supporting temperature control equipment need to be prepared. Due to the extremely high requirements for precision and consistency and strict temperature control in the production of aviation containers, the dimensions of aviation container parts are basically ensured by the supporting molds, and the batch size is very large. Once there are deviations, a large number of defective products will be caused.
[0003] When TA1 is used as the raw material for domestic aviation containers, the deep drawing process is relatively complex, with relatively high design precision requirements for molds and machine tools. The heating temperature affects the internal tissue structure of the formed product. There are many stamping processing procedures, and friction continuously occurs between the material and the mold during mass production. After producing a certain number of aviation containers, the dimensional consistency of the aviation containers decreases due to the reduction of the dimensional accuracy of the molds. In domestic manufacturing of TA1 aviation containers, a large number of equipment are used and a large number of molds need to be replaced. There are many disadvantages such as redundant processing procedures, low production efficiency, high manufacturing cost, large environmental pollution, and difficulty in ensuring product quality. Summary of the Invention
[0004] The purpose of the present invention is to overcome the deficiencies of the prior art and provide a method for controlling the dimensions of a spun part of a TA1 aviation container with a large diameter of Ø300 mm. By precisely designing and controlling the spinning trajectory, precisely designing the process parameters of the spinning process plan, and adopting a two-round synchronous multi-pass high-temperature hot spinning forming process, the high-temperature universal spinning and shear spinning of the aviation container are combined to gradually form a spherical table shape and the corresponding wall thickness dimensions, improving the forming quality and dimensional accuracy of the aviation container. The circumferential wall thickness tolerance of the spun part of the TA1 aviation container with a large diameter of Ø300 mm is ≤0.1 mm, and the measured circumferential wall thickness tolerance of the spun part of the aviation container is ≤0.05 mm.
[0005] The purpose of the present invention is realized through the following technical solutions: (1) Determine the spinning forming trajectory of the TA1 aviation container Design the multi-pass high-temperature universal spinning forming trajectory of the aviation container according to the material characteristics of the aviation container and the spinning forming process. To reduce the influence of the cold work reaction generated by alloy structural steel after spinning on plastic spinning forming, a negative deviation drawing deformation coefficient is adopted for the design of the spinning trajectory in each pass, as shown in formula (1): d if =m i D 0i (1) where d if is the diameter of the i-th conventional spinning forming, and D 0i is the blank diameter required for the i-th spinning, and m i is the drawing deformation coefficient, and its value range is 0.60 - 0.90.
[0006] Formula (1) is only applicable to the design of multi-pass high-temperature conventional spinning forming trajectories.
[0007] In order to ensure the forming quality and dimensional accuracy of the aerospace container and improve the dimensional consistency of the spun parts of the aerospace container, a high-temperature hot spinning process is adopted. In order to ensure the product quality in mass production, molybdenum disulfide liquid is used to lubricate the spinning contact position between the spinning wheel and the blank to reduce the surface damage of the spinning wheel.
[0008] (2) Design the spinning forming process parameters of TA1 aerospace container Taking the small diameter of the spherical table of the aerospace container as the benchmark, the wall thickness dimension of the container gradually decreases with the increase of the spherical table height. According to the requirements of the wall thickness change of the aerospace container, multi-pass high-temperature hot spinning plastic forming is carried out on the plate-shaped blank. Two spinning wheels synchronously carry out multi-pass high-temperature die-less conventional spinning combined with one-time high-temperature die-fitting shear spinning process to form in one step, ensuring the forming quality and dimensional accuracy of the TA1 aerospace container and reducing the processing procedures and material losses.
[0009] In the step (2) described above, the forming trajectory of the aerospace container is designed for two spinning wheels synchronously according to the wall thickness dimension requirements at different heights. The working fillet radius r of the spinning wheel ρ is designed as shown in Formula (2): r ρ =(2 - 4)t0 (2) where t0 is the wall thickness of the plate-shaped blank of the aerospace container.
[0010] In the step (2) described above, in order to ensure the forming dimensional accuracy of the aerospace container and balance the influence of the spinning force on the surface quality of the spun aerospace container, the center line of each spinning wheel forms an angle of ≤15° with the central axis of the aerospace container. When working continuously, the rotation speed of the aerospace container matches the servo feed speed of the spinning wheel, ensuring that no cracking, peeling, process instability and other phenomena occur during the multi-pass high-temperature hot spinning plastic forming of the TA1 aerospace container with a large diameter of Ø300mm. When spinning, the rotation speed of the aerospace container is 30r / min - 70r / min, the synchronous closed-loop control feed speed range of the two spinning wheels is 0.4 - 0.8mm / r, the core die is preheated to 200°C, and the workpiece temperature is ensured to be 800°C - 850°C during spinning forming. The plastic deformation generated after the two spinning wheels synchronously carry out high-temperature hot spinning is the final forming dimension of the aerospace container.
[0011] (3) Prepare the plate-shaped blank of TA1 aerospace container Prepare the plate-shaped blank of TA1 aerospace container according to the principle of volume invariance.
[0012] (4) Clamp and fix the TA1 aircraft container plate blank designed and prepared in step (3), determine the forming trajectory according to step (1), and perform the spinning forming process set in step (2) until the TA1 aircraft container plate blank is formed into a TA1 aircraft container spinning part with a large diameter of Ø300 mm.
[0013] (5) Unload the TA1 aircraft container spinning part with a large diameter of Ø300 mm after spinning in step (4), and turn and remove the excess material head of the aircraft container according to the workpiece height requirement.
[0014] The present invention has the following beneficial effects compared with the prior art: Aiming at the problems of controlling the forming quality and dimensional accuracy of the TA1 aircraft container spinning part with a large diameter of Ø300 mm, the present invention combines the cold work hardening characteristics of the material with negative deviation, precisely designs and controls the forming trajectory, which helps to ensure the dimensional accuracy of the TA1 aircraft container spinning part with a large diameter of Ø300 mm during the multi-pass hot spinning plastic forming process; through the precise design and control of the two-round synchronous multi-pass hot spinning plastic forming trajectory, the TA1 aircraft container spinning part with a large diameter of Ø300 mm is reduced in diameter and conforms to the mold, which is beneficial to ensuring the forming quality of the TA1 aircraft container spinning part with a large diameter of Ø300 mm; through the two-round synchronous multi-pass hot spinning plastic forming process, the forming process is reduced, and the rapid and high-quality forming of the TA1 aircraft container spinning part with a large diameter of Ø300 mm is realized.
[0015] The present invention relates to a method for controlling the dimensions of a TA1 aircraft container spinning part with a large diameter of Ø300 mm. By precisely designing the forming trajectory, the precise distribution and control of the reduction amounts of the two wheels during the two-round synchronous multi-pass hot spinning plastic forming process are realized. The obtained TA1 aircraft container spinning part with a large diameter of Ø300 mm has good forming quality and forming accuracy. The circumferential wall thickness tolerance of the TA1 aircraft container spinning part with a large diameter of Ø300 mm is ≤0.1 mm, and the measured circumferential wall thickness tolerance of the aircraft container spinning part is ≤0.05 mm. Description of the Drawings
[0016] Figure 1 Schematic diagram of the TA1 aircraft container spinning part with a large diameter of Ø300 mm in the embodiment of the present invention; Figure 2 Schematic diagram of the multi-pass plastic forming process trajectory in the embodiment of the present invention; Embodiment
[0017] The following further details the present invention with reference to the drawings and specific embodiments, so as to more clearly understand the purpose and technical solution of the present invention.
[0018] A method for controlling the dimensions of a spun TA1 aviation container with a large diameter of Ø300 mm, the method comprising the following steps: (1) Determine the spinning forming trajectory of the TA1 aviation container Design the multi-pass plastic spinning forming trajectory of the aviation container according to the material characteristics of the aviation container and the spinning forming process. In order to reduce the influence of the cold working reaction generated by the alloy structural steel after spinning on the plastic spinning forming, the negative deviation drawing deformation coefficient is adopted for the design of each pass spinning trajectory, as shown in formula (3): d if =m i D 0i (3) In the formula, d if is the diameter of the i-th conventional spinning forming, D 0i is the blank diameter required for the i-th spinning, m i is the drawing deformation coefficient, and the value range is 0.60 - 0.90.
[0019] Formula (3) is only applicable to the design of the multi-pass high-temperature conventional spinning forming trajectory.
[0020] In order to ensure the forming quality and dimensional accuracy of the aviation container and improve the dimensional consistency of the spun parts of the aviation container, the high-temperature hot spinning process is adopted. In order to ensure the product quality of mass production, liquid molybdenum disulfide is used to lubricate the spinning contact position between the spinning wheel and the blank to reduce the surface damage of the spinning wheel.
[0021] (2) Design the spinning forming process parameters of the TA1 aviation container The aviation container is based on the small diameter of the spherical table. As the height of the spherical table increases, the wall thickness dimension of the container gradually decreases. According to the requirements of the wall thickness change of the aviation container, the plate-shaped blank is subjected to multi-pass high-temperature hot spinning plastic forming. Two spinning wheels are synchronously formed by multi-pass high-temperature die-less conventional spinning combined with one-time high-temperature die-fitting shear spinning process, ensuring the forming quality and dimensional accuracy of the TA1 aviation container, and reducing the processing procedures and material losses.
[0022] In the step (2) described above, the forming trajectory of the aviation container is designed for two spinning wheels synchronously according to the wall thickness dimensions required at different heights. The working fillet radius r of the spinning wheel ρ is designed as shown in formula (4): r ρ =(2~4)t0 (4) In the formula, t0 is the wall thickness of the plate-shaped blank of the aviation container.
[0023] In step (2), to ensure the forming dimensional accuracy of the aviation container and balance the influence of the spinning pressure on the surface quality of the spun aviation container, the center line of each spinning wheel is arranged at an angle of ≤15° with the central axis of the aviation container. When working continuously, the rotational speed of the aviation container is matched with the servo feed speed of the spinning wheel, ensuring that no cracking, peeling, or process instability occurs during the multi-pass hot spinning plastic forming of the TA1 aviation container spinning part with a large diameter of Ø300 mm. During spinning, the rotational speed of the aviation container is 30 r / min to 70 r / min, the synchronous closed-loop control feed speed range of the two spinning wheels is 0.4 to 0.8 mm / r, the core mold is preheated to 200 °C, and the workpiece temperature is ensured to be between 800 °C and 850 °C during spinning. The plastic deformation generated after the two spinning wheels perform synchronous hot spinning is the final forming size of the aviation container.
[0024] (3) Prepare the plate-shaped blank 2 of the TA1 aviation container Prepare the plate-shaped blank 2 of the TA1 aviation container according to the principle of constant volume.
[0025] (4) Clamp and fix the plate-shaped blank 2 of the TA1 aviation container prepared in step (3) on the positioning shaft 1, determine the forming trajectory according to step (1), and execute the spinning forming process set in step (2) until the plate-shaped blank of the TA1 aviation container is formed into a TA1 aviation container spinning part with a large diameter of Ø300 mm.
[0026] (5) Unload the TA1 aviation container spinning part 3 with a large diameter of Ø300 mm after spinning in step (4), and turn and remove the excess material head of the aviation container according to the workpiece height requirement.
[0027] Implementation case: In this implementation case, the inner diameter of the large end of the TA1 aviation container spinning part 3 with a large diameter of Ø300 mm is Ø300 mm, the total height of the workpiece is ≥150 mm, and the wall thickness of the TA1 aviation container spinning part 3 with a large diameter of Ø300 mm gradually thins with the change of the spherical table height. The wall thickness dimensions are shown in Table 1: Table 1 Workpiece wall thickness dimensions Height from the bottom (mm) 30 50 100 150 Wall thickness (mm) 7.81 6.4 5.25 5.25 Trend of wall thickness change Gradually thinning Gradually thinning Gradually thinning Dimensions are consistent Step (1) Determine the spinning forming trajectory of the TA1 aviation container 3 Design the multi-pass hot spinning plastic forming trajectory of the aviation container according to the material characteristics of the aviation container and the spinning forming process. To reduce the influence of the cold working reaction generated after spinning of the TA1 aviation container on plastic spinning forming, the drawing deformation coefficient with a large negative deviation is adopted for the design of each spinning trajectory, as shown in formula (5): d if = m i D 0i (5) In the formula, d ifis the diameter of the i-th conventional spinning forming, D 0i is the blank diameter required for the i-th spinning, m i is the drawing deformation coefficient, and its value range is 0.60 - 0.90.
[0028] TA1 material has a better rigid extension property. The bottom diameter of the small end of the TA1 aviation container 3 is smaller. Compared with the large port diameter, the blank sheet diameter and the spherical table depth are relatively large. The wall thickness of the spherical table changes greatly with a central angle of 30° - 70° based on the spherical center. When there is no mandrel in multiple passes of conventional spinning, the force is large and elastic deformation is likely to occur. Using negative deviation, according to formula (5), two spinning wheels are designed to synchronously perform multiple passes of high-temperature non-mold conventional spinning combined with a single high-temperature mold-fitting shear spinning process. The plastic deformation amount of the material between the forming trajectories is shown in Table 2: Table 2 Design Trajectories of Multiple Passes Height from the bottom h (mm) Starting rotation point 5.3 30 50 100 150 Radius R of the clockwise arc at the end point Drawing deformation coefficient m 0.8 0.6 0.6 0.6 0.6 0.6 <![CDATA[Track ① Design plastic deformation amount t i (mm)]]> 9.9 7.81 6.4 / / 230 <![CDATA[Track ② Design plastic deformation amount t i (mm)]]> / / 6.4 5.25 / 230 <![CDATA[Track ③ Design plastic deformation amount t i (mm)]]> / / / 5.25 / 230 <![CDATA[Track ④ Design Plastic Deformation Amount t i (mm)]]> 9.9 7.81 6.4 5.25 5.25 / In order to ensure the forming quality and dimensional accuracy of the aviation container and improve the dimensional consistency of the spun parts of the aviation container, a high-temperature hot spinning process is adopted. In order to ensure the product quality of mass production, liquid molybdenum disulfide is used to lubricate the spinning contact position between the spinning wheel and the blank to reduce the surface damage of the spinning wheel.
[0029] Step (2) Design the spinning forming process parameters of the TA1 aviation container Based on the small diameter of the spherical table of the aviation container, as the height of the spherical table increases, the wall thickness dimension of the container gradually decreases. According to the requirements of the wall thickness change of the aviation container, the plate-shaped blank is plastically formed by multiple passes of high-temperature hot spinning. Two spinning wheels synchronously perform multiple passes of high-temperature non-mold conventional spinning combined with a single high-temperature mold-fitting shear spinning process to form in one step, ensuring the forming quality and dimensional accuracy of the TA1 aviation container and reducing the processing procedures and material losses. In the said step (2), the forming trajectory of the aviation container is designed for two spinning wheels synchronously according to the wall thickness dimension requirements at different heights. The working fillet radius r of the spinning wheel ρ is designed as shown in formula (6): r ρ =(2 - 4)t0 (6) In the formula, t0 is the wall thickness of the plate-shaped blank of the aviation container.
[0030] In step (2), to ensure the forming dimensional accuracy of the aviation container and balance the influence of the spinning pressure on the surface quality of the spun aviation container, the center line of each spinning wheel is arranged at an angle of ≤15° with the central axis of the aviation container. When working continuously, the rotational speed of the aviation container matches the servo feed speed of the spinning wheel, ensuring that no cracking, peeling, or process instability occurs during the multi-pass hot spinning plastic forming of the TA1 aviation container spinning part with a large diameter of Ø300 mm. During spinning, the rotational speed of the aviation container is 30 r / min to 70 r / min, the synchronous closed-loop control feed speed range of the two spinning wheels is 0.4 to 0.8 mm / r, the core mold is preheated to 200 °C, and the workpiece temperature is ensured to be between 800 °C and 850 °C during spinning. The plastic deformation generated after the two spinning wheels perform synchronous hot spinning is the final forming size of the aviation container.
[0031] Step (3): Prepare the plate-shaped blank 2 of the TA1 aviation container Prepare the plate-shaped blank 2 of the TA1 aviation container according to the principle of constant volume.
[0032] Step (4): Clamp and fix the plate-shaped blank 2 of the TA1 aviation container prepared in step (3) on the positioning shaft 1, and according to the forming trajectory designed in step (1), execute the spinning forming process set in step (2) until the plate-shaped blank of the TA1 aviation container is formed into a TA1 aviation container spinning part 3 with a large diameter of Ø300 mm.
[0033] Step (5): Unload the TA1 aviation container spinning part 3 with a large diameter of Ø300 mm after spinning in step (4), and turn and remove the excess stock of the aviation container according to the workpiece height requirement. The height after processing is 150 mm.
[0034] Aiming at the problems of controlling the forming quality and dimensional accuracy of the TA1 aviation container spinning part with a large diameter of Ø300 mm, the present invention combines the cold work hardening characteristics of the material with increasing the drawing deformation coefficient by a large negative deviation, precisely designs and controls the forming trajectory, which helps to ensure the dimensional accuracy of the TA1 aviation container spinning part with a large diameter of Ø300 mm during the multi-pass hot spinning plastic forming process; through the precise design and control of the synchronous hot spinning trajectory of the two wheels, the blank die-fitting rate of the TA1 aviation container spinning part with a large diameter of Ø300 mm is improved, which is beneficial to ensuring the forming quality of the TA1 aviation container spinning part with a large diameter of Ø300 mm; through the combined one-time forming process of synchronous high-temperature conventional spinning and shear spinning of the two wheels, the forming process is reduced, and the rapid high-quality forming of the TA1 aviation container spinning part with a large diameter of Ø300 mm is realized. The obtained TA1 aviation container spinning part with a large diameter of Ø300 mm has good forming quality and forming accuracy. The circumferential wall thickness tolerance of the TA1 aviation container spinning part with a large diameter of Ø300 mm is ≤0.1 mm, and the measured circumferential wall thickness tolerance of the aviation container spinning part is ≤0.05 mm.
[0035] The content not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.
[0036] Although the present invention has been disclosed above with the preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions in the specification of the present invention without departing from the spirit and scope of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.
Claims
1. A method for controlling the dimensions of a spun TA1 aerospace container with a large diameter of Ø300 mm, characterized in that, It includes the following steps: S1. Design the spinning forming trajectory of the TA1 aviation container; S2. Design the spinning forming process parameters of the TA1 aviation container; S3. Prepare the blank of the TA1 aviation container; S4. Clamp and fix the blank of the TA1 aviation container, determine the forming trajectory according to S1, execute the spinning forming process set in S2, and perform multi-pass hot spinning plastic forming on the blank of the TA1 aviation container to obtain the spun part of the TA1 aviation container; S5. Unload the spun part of the TA1 aviation container after spinning, and turn and remove the excess stock head of the spun part of the aviation container according to the required height.
2. The forming method according to claim 1, characterized in that: The forming trajectory of the spun part of the aviation container is multi-pass hot spinning plastic forming. Specifically, the TA1 aviation container is in the shape of a spherical table. Based on the bottom surface of the small diameter of the TA1 aviation container mold, it is formed by a multi-pass hot non-mold conventional spinning combined with a single-pass hot mold-fitting shear spinning process.
3. The forming method according to claim 1, characterized in that: Two-wheel synchronous hot spinning forming is adopted. When the aviation container is spun, the two spinning wheels are symmetrically distributed on both sides of the central axis of the aviation container to ensure the balance of the spinning force. The sum of the plastic deformation angles of the two spinning wheels under multi-pass conventional spinning is less than the included angle between the tangent of the spherical zone of the aviation container and the starting point of spinning.
4. The forming method according to claim 1, characterized in that: The following method is adopted for the multi-pass conventional spinning forming process trajectory of the spun part of the aviation container: Wherein, is the diameter of the i-th conventional spinning forming, is the blank diameter required for the i-th spinning, is the drawing deformation coefficient, and its value range is 0.60 to 0.
90.
5. The forming method according to claim 1, characterized in that: The hot shear spinning forming trajectory of the aviation container is accurately designed according to the wall thickness dimension requirements of the spun parts corresponding to different heights. The two spinning wheels are symmetric on both sides of the central axis of the aviation container and synchronously complete the relative spinning trajectory. The plastic deformation generated after the spinning wheels perform hot shear mold-fitting spinning is the final forming dimension of the aviation container.
6. The forming method according to claim 1, characterized in that: Radius of working fillet of the roller The design is as shown in the formula: In the formula, is the wall thickness of the aviation container blank.
7. The forming method according to claim 1, characterized in that: To ensure the forming dimension accuracy of the aviation container and balance the influence of the spinning force on the surface quality of the spun aviation container, the center line of each spinning wheel is arranged at an angle of ≤15° with the central axis of the aviation container. When working continuously, the rotational speed of the aviation container matches the servo feed speed of the spinning wheel to ensure that no cracking, peeling, process instability and other phenomena occur during the multi-pass non-mold spinning forming of the spun part of the TA1 aviation container. When spinning, the rotational speed of the aviation container is 30 r / min to 70 r / min, and the synchronous closed-loop control feed speed range of the two spinning wheels is 0.4 to 0.8 mm / r.
8. A method for controlling the dimensions of a spun TA1 aerospace container with a large diameter of Ø300 mm, characterized in that, Control the dimensions of the spun part of the TA1 aviation container by using the control method described in any one of claims 1 to 7.