Spinning forming method for perfect circle aircraft engine lip

Abstract

The invention discloses a spinning forming method for a perfect circle aircraft engine lip, and belongs to the technical field of spinning forming. The spinning forming method comprises the following steps: S1, designing a spinning process; S2, designing a spinning blank: respectively designing blank sizes required by an inner side wall and an outer side wall according to a product structure; S3, designing a spinning process: S3.1, designing a spinning roller attack angle and a spinning roller shape, S3.2, designing a spinning roller gap, S3.3, designing a spinning track, S3.4, producing a spinning program, S3.5, designing spinning parameters, S4, spinning forming, and S5, machining a part. According to the method, the defects of a die spinning process can be overcome, the material performance of the aircraft engine lip is improved through the machining mode of overall spinning forming of the plate, the problem that microdefects are generated in a welding seam in a traditional split welding mode is solved, and the welding quality of the aircraft engine lip is improved through multi-pass spinning forming and control over the motion trail of a spinning roller in the spinning process. And the temperature in the spinning process is controlled, so that the spinning forming stability is improved, and the product machining precision is also improved.

Description

Technical Field

[0001] The invention relates to the technical field of spin forming, and more specifically to a spin forming method for a perfect circular aircraft engine lip. Background Art

[0002] During the flight, the lip of the aircraft engine is affected by high-speed and high-pressure airflow, and the engine lip is in an ultra-high-intensity complex load working environment for a long time. Therefore, there are high requirements for the dimensional accuracy and product performance of the aircraft engine lip parts. Due to the large diameter of the aircraft engine lip, the traditional lip forming process is either achieved through the split-welding process or through large-tonnage stamping through large-scale special molds.

[0003] First of all, the traditional split-flap welding method is prone to produce microscopic defects in the weld, which is not conducive to improving the overall performance. Reducing the welding process of the lip or realizing the overall forming of the lip is conducive to improving the overall performance, which is very important for the safety of the aircraft. In addition, in order to prevent the material from wrinkling and rupture due to exceeding the stamping limit, the use of stamping often requires multiple sets of molds for stamping. The stamping mold requires upper and lower concave and convex dies, and the mold cost investment is too high. In view of this, we propose a method for spinning the round aircraft engine lip. Summary of the invention

[0004] The object of the present invention is to provide a method for spinning a perfect circular aircraft engine lip to solve the problems raised in the above background technology:

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] A method for spinning a perfect circular aircraft engine lip, comprising the following steps:

[0007] S1. Design of spinning process: Design a set of spinning molds for spinning processing. Two-step spinning. First, use the mold to spin the outer wall, and leave a clamping position for spinning. After the outer wall is spun, use a fixed fixture to clamp the outer circle position and spin the inner wall.

[0008] S2. Design the spinning blank: Design the blank size required for the inner wall and the outer wall according to the product structure. The volume of the outer wall is V 外 , the volume of the inner wall is V 内 , the total volume is V 产品 ; Among them, the designed blank thickness is T 0 , the design blank outer diameter is φ 外 , the inner diameter of the blank is designed to be φ 内 ;

[0009] S3. Design the spinning process: S3.1 Design the spinning wheel attack angle and spinning wheel morphology, S3.2 Design the spinning wheel gap, S3.3 Design the spinning trajectory, S3.4 Production spinning program, S3.5 Design the spinning parameters;

[0010] Designing the rotor attack angle and rotor morphology includes:

[0011] S3.1.1 Design the outer wall spinning wheel attack angle and wheel shape: The outer wall spinning attack angle is set to 45°, the forming fillet radius of the wheel shape is R, and the fillet radius in the product forming structure is R A The round aircraft engine lip product is a thin-walled part with a forming fillet radius of R≤16. A ≤T 0 , two types of rollers need to be designed. One roller has a radius R designed according to the initial material thickness and part thickness for spinning. The other roller is a shaping roller with a radius R≤R A , during spinning, replace the shaping wheel to complete the final forming of the part;

[0012] S3.1.2 Design the inner wall spinning wheel attack angle and wheel shape: The inner wall spinning needs to design an inner spinning tool bar, the spinning wheel attack angle is 10°-20°, the spinning wheel shape is set to a double cone spinning wheel, and the wheel fillet radius R is the same as the outer wall forming spinning wheel;

[0013] S4, spinning: including S4.1 spinning of the outer wall and S4.2 spinning of the inner wall;

[0014] S5. Machined parts: After the blank is spun, the clamping position is removed by machining, and sampling, testing and flaw detection are carried out according to the requirements of the finished product.

[0015] Preferably, designing the spinning blank comprises the following steps:

[0016] S2.1 The blank is designed as a sheet material, and the thinning rate of multi-pass ordinary spinning is 30%-40%. The thickness T is determined according to the product requirements. 1 The blank thickness is obtained, and the designed blank thickness is T 0 ;

[0017] S2.2 Design the outer diameter of the blank to be φ 外 According to the principle of constant volume during spinning, the volume of the outer wall of the product is V 外 To ensure that the spinning product has a margin, the blank volume corresponding to the outer wall of the product is designed to be 1.2 times the V 外 , then we can get:

[0018]

[0019] S2.3 Design the inner diameter of the blank to be φ 内According to the principle of constant volume during spinning, the volume of the inner wall of the product is V 内 In order to ensure that the spinning product has a margin, the V is designed to be 1.2 times the volume of the blank on the inner wall of the product. 内 , the diameter of the boundary between the inner and outer walls of the product is φ A , then we can get:

[0020]

[0021] During spinning, a clamping position needs to be left on the outer wall. If the clamping length is set to L, the final blank size is the outer diameter φ 外 +2L, inner diameter φ 内 , wall thickness T 0 .

[0022] Preferably, in S3.2, the spinning gap is designed as follows: the spinning gap is set to 0.8-1.0 times the wall thickness of the original product.

[0023] Preferably, S3.3 designing the spinning trajectory includes: S3.3.1 designing the outer wall spinning wheel motion trajectory and S3.3.2 designing the inner wall spinning wheel motion trajectory, and the specific steps in step S3.3.1 and step S3.3.2 are as follows:

[0024] a. Design the shape and quantity of the wheel track: The wheel motion track is an arc line, and the number of tracks is designed according to the length of the part;

[0025] b. Initial spinning process: Use a single-pass forward spinning trajectory to make the material undergo initial deformation;

[0026] c. Pre-deformation process: designed as two passes, so that the material has a tendency to tilt in the deformation direction;

[0027] d. Subsequent forming spinning design: design multiple forming tracks in the form of "forward-forward-return" so that the material fits the part surface after deformation;

[0028] e. Final forming trajectory design: Use the "forward-forward" spinning trajectory to gradually shape the material into parts, that is, complete the trajectory design of the outer wall spinning deformation.

[0029] Preferably, S3.4 production spinning program includes: after supplementing auxiliary lines such as feed and retract, generating numerical control program code on the programming software, and performing simulation detection on the generated code.

[0030] Preferably, in S3.5, in the design of spinning parameters: the spinning temperature, machine tool speed, and spinning wheel feed parameters need to be designed during the spinning process, a heating device is used to heat the blank before spinning, and a heating device is used to supplement heat to the spinning position during the spinning process;

[0031] Preferably, S4.1 spinning the outer side wall comprises the following steps:

[0032] S4.1.1 Fix the blank on the spinning machine;

[0033] S4.1.2 Use a heating device to heat and turn on a thermal monitoring device;

[0034] S4.1.3 After the temperature reaches the set index, start the machine tool and run the spinning trajectory, while keeping the deformation temperature constant during the deformation process;

[0035] S4.1.4 After spinning is completed, remove the parts.

[0036] Preferably, S4.2 spinning the inner side wall comprises the following steps:

[0037] S4.2.1 Fix the product with the outer side wall of the spinning process on the spinning machine;

[0038] S4.2.2 Use a heating device to heat the spinning position and turn on the thermal monitoring device;

[0039] S4.2.3 After the temperature reaches the set index, start the machine tool and run the spinning trajectory, while keeping the deformation temperature constant during the deformation process;

[0040] S4.2.4 After spinning is completed, remove the parts.

[0041] Compared with the prior art, the present invention has the following beneficial effects:

[0042] The present invention can overcome the shortcomings of the die spinning process and provide an effective advanced forming method for various types of perfect circular aircraft engine lip parts. By using the processing method of integrally spinning the sheet material, the material properties of the aircraft engine lip are improved, and the problem of microscopic defects in the weld caused by the traditional split-flap welding method is solved. Through multiple passes of spinning, the motion trajectory of the spinning wheel during the spinning process is controlled, and the temperature during the spinning process is controlled, which improves the stability of the spinning process and the processing accuracy of the product. Compared with stamping, the use of the spinning processing method greatly reduces the cost investment of mold tooling, saves the manufacturing cost and preparation cycle of the mold, shortens the processing cycle, and improves the applicability and flexibility of the spinning process. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 This is a schematic diagram of the structure of the perfect circular aircraft engine lip product of the present invention;

[0044] Figure 2 It is a schematic diagram of the spinning of the outer wall of the perfect circular aircraft engine lip of the present invention;

[0045] Figure 3It is a schematic diagram of the inner side wall spinning of the perfect circular aircraft engine lip of the present invention.

[0046] Explanation of the numbers in the figure: 1. mold; 2. blank; 3. rotating wheel; 4. tail top; 5. heating device; 6. temperature measuring device; 7. clamping tooling. DETAILED DESCRIPTION

[0047] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0048] Example:

[0049] See also Figure 1-3 A method for spinning a perfect circular aircraft engine lip is provided. The overall process route is: designing a spinning process → designing a spinning blank → designing a spinning process → spinning forming → machining, which specifically includes the following steps:

[0050] Step S1, designing a spinning process: designing a set of spinning molds for spinning processing, two-step spinning, first use the mold to spin the outer wall, spin to leave a clamping position, after the outer wall is spun into shape, use a fixed fixture to clamp the outer circle position, and spin the inner wall.

[0051] Step S2, designing the spinning blank: designing the blank size required for the inner wall and the outer wall according to the product structure, and the volume of the outer wall is V 外 , the volume of the inner wall is V 内 , the total volume is V 产品 ; Among them, the designed blank thickness is T 0 , the design blank outer diameter is φ 外 , the inner diameter of the blank is designed to be φ 内 .

[0052] like Figure 1 As shown, the diameter at the vertex A of the perfect circular aircraft lip product is recorded as φA, that is, the product is divided into two parts, the inner wall and the outer wall, from φA, and the diameter at the outer edge B of the perfect circular aircraft lip product is recorded as φB, where the height between A and B is recorded as H.

[0053] Specifically, designing a spinning blank includes the following steps:

[0054] S2.1 The blank is designed as a sheet material, and the thinning rate of multi-pass ordinary spinning is 30%-40%. The thickness T is determined according to the product requirements. 1 The blank thickness is obtained, and the designed blank thickness is T 0 ;

[0055] S2.2 Design the outer diameter of the blank to be φ 外 According to the principle of constant volume during spinning, the volume of the outer wall of the product is V外 In order to ensure the spin processing product has a margin, the design of the corresponding product outer wall blank volume is 1.2 times the V 外 , the diameter of the boundary between the inner and outer walls of the product is φ A , then we can get:

[0056]

[0057] S2.3 Design the inner diameter of the blank to be φ 内 According to the principle of constant volume during spinning, the volume of the inner wall of the product is V 内 In order to ensure the margin of the spinning product, the V is designed to be 1.2 times the volume of the blank on the inner wall of the product. 内 , then we can get:

[0058]

[0059] During spinning, a clamping position needs to be left on the outer wall. If the clamping length is set to L, the final blank size is the outer diameter φ 外 +2L, inner diameter φ 内 , wall thickness T 0 The outer diameter φ is obtained by laser cutting or water jet cutting. 外 +2L, inner diameter φ 内 , wall thickness T 0 Spinning blank.

[0060] Step S3, designing the spinning process: S3.1 designing the spinning wheel attack angle and spinning wheel morphology, S3.2 designing the spinning wheel gap, S3.3 designing the spinning trajectory, S3.4 producing the spinning program, S3.5 designing the spinning parameters.

[0061] Specifically, S3.1 designs the rotor attack angle and rotor morphology including:

[0062] S3.1.1 Design the outer wall spinning wheel attack angle and wheel shape: The outer wall spinning attack angle is set to 45°, the forming fillet radius of the wheel shape is R, and the fillet radius in the product forming structure is R A The round aircraft engine lip product is a thin-walled part with a forming fillet radius of R≤16. A ≤T 0 , two types of rollers need to be designed. One roller has a radius R designed according to the initial material thickness and part thickness for spinning. The other roller is a shaping roller with a radius R≤R ADuring spinning, the shaping roller is replaced to complete the final forming of the part; the roller attack angle and roller morphology are designed: the roller is the main tool for applying deformation force, and the roller can passively rotate synchronously with the blank under the action of friction. The roller is selected according to different deformation conditions, mainly deformation temperature. Under high temperature conditions, the material of the forming roller should be selected from materials with red hardness, such as W18Cr4V, H13, etc.

[0063] S3.1.2 Design the inner wall spinning wheel attack angle and wheel shape: The inner wall spinning needs to design an inner spinning tool bar, the spinning wheel attack angle is 10°-20°, the spinning wheel shape is set to a double cone spinning wheel, and the wheel fillet radius R is the same as the outer wall forming spinning wheel;

[0064] S3.2 Design of the spinner gap: Draw the spinner gap line according to the part shape, first set the spinning gap line, which is the shortest distance between the spinner and the spinning mold. The spinning gap is set to 0.8-1.0 times the wall thickness of the original product. If it is set to 1.0 times, that is, T 1 , and then carry out process design and adjustment according to the thickness of the first piece.

[0065] S3.3 Design of spinning trajectory includes: S3.3.1 Design of outer wall spinning wheel motion trajectory and S3.3.2 Design of inner wall spinning wheel motion trajectory. The spinning wheel motion trajectory can control the material deformation during the spinning process and is the intermediate configuration of each spinning process. During the spinning deformation process, there is both a reduction in material thickness and a change in shape. It cannot be formed in one pass and needs to be gradually formed in multiple passes.

[0066] The specific steps in step S3.3.1 and step S3.3.2 are as follows:

[0067] a. Design the shape and quantity of the wheel track: The wheel motion track is an arc line, and the number of tracks is designed according to the length of the part;

[0068] b. Initial spinning process: a single-pass forward spinning trajectory is used to make the material undergo preliminary deformation in preparation for the subsequent pre-deformation and forming stages;

[0069] c. Pre-deformation process: designed as two passes, so that the material has a tendency to tilt in the deformation direction;

[0070] d. Subsequent forming spinning design: design multiple forming tracks in the form of "forward-forward-return" so that the material fits the part surface after deformation; the "forward-forward-return" cycle track, that is, the spinning wheel first performs forward spinning, then performs forward spinning for the second time, the direction and position are slightly adjusted, and finally the return spinning is performed. This form of track can more effectively control the deformation process of the material;

[0071] e. Final forming trajectory design: Use the "forward-forward" spinning trajectory to gradually shape the material into parts, that is, complete the trajectory design of the outer wall spinning deformation.

[0072] Exemplarily, the motion trajectory of the outer wall spinning wheel is designed: the motion trajectory of the spinning wheel is designed to be an arc line, and the number of trajectories is designed according to the length of the part. In the initial spinning process, a single-pass forward spinning trajectory is adopted, numbered 1-2, which is 2 passes, and the material is pre-deformed so that the material has a tendency to tilt in the deformation direction. The subsequent design of the forming spinning trajectory is a multi-group forming trajectory, and the trajectory form is "forward-forward-return", which is designed here as 10 groups of trajectories, numbered 3-12. After deformation, the material has basically fit the part surface. Then use the "forward-forward" spinning trajectory to gradually shape the material into a part. In this way, the trajectory design of the outer wall spinning deformation is completed. The number of spinning trajectories can be adjusted according to the material deformation effect during the spinning process and the dimensional accuracy of the first piece after spinning.

[0073] Design the motion trajectory of the inner wall spinning wheel: Design the motion trajectory of the spinning wheel as an arc line, design the number of trajectories according to the length of the part, use a single-pass forward spinning trajectory in the initial spinning process, design it as 2 passes, and pre-deform the material. The subsequent design of the forming spinning trajectory is a multi-group forming trajectory, and the trajectory form is "forward-forward-return", and the number of trajectories can be designed according to the length of the part. Finally, use the "forward-forward" spinning trajectory to gradually form the material into a part. The number of spinning trajectories can be adjusted according to the material deformation effect during the spinning process and the dimensional accuracy of the first piece after spinning.

[0074] S3.4 The production spinning program includes: after adding auxiliary lines such as feed and retract, generating NC program code on the programming software, and performing simulation detection on the generated code.

[0075] S3.5 designs spinning parameters: during the spinning process, it is necessary to design the spinning temperature, machine tool speed, and wheel feed parameters. The spinning temperature is related to the material. The high temperature state can reduce the material deformation resistance and improve the material fluidity. Before spinning, a heating device is used to heat the blank. During the spinning process, a heating device is used to supplement the heat at the spinning position. According to the diameter of the part, the machine tool speed for diameters below two meters is 20-50rev / min, and the feed speed is maintained at 40-150mm / min. The larger the diameter, the lower the speed and the slower the feed speed, and the contact line speed of the deformed part is kept constant.

[0076] Step S4, spinning: including S4.1 spinning the outer wall and S4.2 spinning the inner wall;

[0077] Specifically, S4.1 spinning the outer side wall includes the following steps:

[0078] S4.1.1 Fix the blank on the spinning machine;

[0079] S4.1.2 Use a heating device to heat and turn on a thermal monitoring device;

[0080] S4.1.3 After the temperature reaches the set index, start the machine tool and run the spinning trajectory, while keeping the deformation temperature constant during the deformation process;

[0081] S4.1.4 After spinning is completed, remove the parts.

[0082] In this application, S4.2 spinning the inner side wall includes the following steps:

[0083] S4.2.1 Fix the product with the outer side wall of the spinning process on the spinning machine;

[0084] S4.2.2 Use a heating device to heat the spinning position and turn on the thermal monitoring device;

[0085] S4.2.3 After the temperature reaches the set index, start the machine tool and run the spinning trajectory, while keeping the deformation temperature constant during the deformation process;

[0086] S4.2.4 After spinning is completed, remove the parts.

[0087] Step S5, machining parts: After the blank is spun, the clamping position is removed by machining, and sampling, testing and flaw detection are performed according to the requirements of the finished product.

[0088] like Figure 2 The figure shows the spinning of the outer wall of the engine lip. During the spinning process, the main shaft drives the mold 1 and the tail top 4 to rotate, and the rotating wheel 3 rotates passively driven by the friction force. The rotating wheel 3 moves according to the drawn motion trajectory to roll the material into shape. A temperature measuring device 6 is designed to measure the temperature of the deformation position during the deformation process. After the heating device 5 is heated, the temperature measuring device 6 starts to record the spinning temperature and feeds it back to the heating system. The system compares the heating temperature with the set temperature and makes dynamic adjustments to ensure that the spinning deformation temperature is always at a constant temperature. At the same time, the rotating wheel 3 moves according to the CNC program. By controlling the heating and the spinning forming process, the part structure is formed to obtain the outer wall spinning forming product.

[0089] like Figure 3The figure shows the spinning of the inner wall of the engine lip. The outer wall spinning-formed product is obtained by spinning the outer wall. The product is fixed on the mold 1 by the clamping tool 7. During the spinning process, the main shaft drives the mold 1 to rotate, and the rotating wheel 3 rotates passively driven by the friction force. The rotating wheel 3 moves according to the drawn motion trajectory to roll the material into shape. A temperature measuring device 6 is designed to measure the temperature of the deformation position during the deformation process. After the heating device 5 is heated, the temperature measuring device 6 starts to record the spinning temperature and feeds it back to the heating system. The system compares the heating temperature with the set temperature and makes dynamic adjustments to ensure that the spinning deformation temperature is always at a constant temperature. At the same time, the rotating wheel 3 moves according to the CNC program to complete the product spinning.

[0090] The present invention provides a method for the spin forming of various types of aircraft engine lips, and is particularly suitable for the spin forming of perfect circular aircraft engine lips. The processing method of integral sheet metal spin forming improves the material properties of the aircraft engine lip, solves the problem of microscopic defects in the weld caused by the traditional split-flap welding method, and controls the motion trajectory of the spinning wheel during the spinning process through multiple spin forming passes. The temperature during the spinning process is controlled, thereby improving the stability of the spin forming and the processing accuracy of the product. Compared with stamping, the use of the spinning processing method greatly reduces the cost investment of mold tooling, saves the manufacturing cost and preparation cycle of the mold. It is not only suitable for the spin forming of perfect circular aircraft engine lips, but also has applicability to other types of large-diameter rotating body parts.

[0091] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. The above embodiments and descriptions are only preferred examples of the present invention and are not intended to limit the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A method for spinning a perfect circular aircraft engine lip, characterized in that: The steps include: S1. Design of spinning process: Design a set of spinning molds for spinning processing. Two-step spinning. First, use the mold to spin the outer wall, and leave a clamping position for spinning. After the outer wall is spun, use a fixed fixture to clamp the outer circle position and spin the inner wall. S2. Design the spinning blank: Design the blank size required for the inner wall and the outer wall according to the product structure. The volume of the outer wall is V 外 , the volume of the inner wall is V 内 , the total volume is V 产品 ; Among them, the designed billet thickness is T0, and the designed billet outer diameter is φ 外 , the inner diameter of the blank is designed to be φ 内 ; S3. Design the spinning process: S3.1 Design the spinning wheel attack angle and spinning wheel morphology, S3.2 Design the spinning wheel gap, S3.3 Design the spinning trajectory, S3.4 Production spinning program, S3.5 Design the spinning parameters; Designing the rotor attack angle and rotor morphology includes: S3.1.1 Design the outer wall spinning wheel attack angle and wheel shape: The outer wall spinning attack angle is set to 45°, the forming fillet radius of the wheel shape is R, and the fillet radius in the product forming structure is R A The round aircraft engine lip product is a thin-walled part with a forming fillet radius of R≤16. A ≤T0, two types of rollers need to be designed. One roller is designed with a roller corner radius R according to the initial material thickness and part thickness for spinning. The other roller is a shaping roller with a designed roller corner radius R≤R A , during spinning, replace the shaping wheel to complete the final forming of the part; S3.1.2 Design the inner wall spinning wheel attack angle and wheel shape: The inner wall spinning needs to design an inner spinning tool bar, the spinning wheel attack angle is 10°-20°, the spinning wheel shape is set to a double cone spinning wheel, and the wheel fillet radius R is the same as the outer wall forming spinning wheel; S4, spinning: including S4.1 spinning of the outer wall and S4.2 spinning of the inner wall; S5. Machined parts: After the blank is spun, the clamping position is removed by machining, and sampling, testing and flaw detection are carried out according to the requirements of the finished product.

2. A method for spinning a perfect circular aircraft engine lip according to claim 1, characterized in that: Designing a spinning blank includes the following steps: S2.1 The blank is designed as a sheet material, and the thinning rate of multi-pass ordinary spinning is 30%-40%. The blank thickness is obtained according to the product required thickness T1, and the designed blank thickness is T0; S2.2 Design the outer diameter of the blank to be φ 外 According to the principle of constant volume during spinning, the volume of the outer wall of the product is V 外 To ensure that the spinning product has a margin, the blank volume corresponding to the outer wall of the product is designed to be 1.2 times the V 外 , the diameter of the boundary between the inner and outer walls of the product is φ A , then we can get: S2.3 Design the inner diameter of the blank to be φ 内 According to the principle of constant volume during spinning, the volume of the inner wall of the product is V 内 In order to ensure that the spinning product has a margin, the V is designed to be 1.2 times the volume of the blank on the inner wall of the product. 内 , then we can get: During spinning, a clamping position needs to be left on the outer wall. If the clamping length is set to L, the final blank size is the outer diameter φ 外 +2L, inner diameter φ 内 , wall thickness T0.

3. A method for spinning a perfect circular aircraft engine lip according to claim 1, characterized in that: S3.2 Design of the spinning wheel gap: The spinning gap is set to 0.8-1.0 times the wall thickness of the original product.

4. A method for spinning a perfect circular aircraft engine lip according to claim 3, characterized in that: S3.3 Designing the spinning trajectory includes: S3.3.1 Designing the outer wall spinning wheel motion trajectory and S3.3.2 Designing the inner wall spinning wheel motion trajectory. The specific steps in step S3.3.1 and step S3.3.2 are as follows: a. Design the shape and quantity of the wheel track: The wheel motion track is an arc line, and the number of tracks is designed according to the length of the part; b. Initial spinning process: Use a single-pass forward spinning trajectory to make the material undergo initial deformation; c. Pre-deformation process: designed as two passes, so that the material has a tendency to tilt in the deformation direction; d. Subsequent forming spinning design: design multiple forming tracks in the form of "forward-forward-return" so that the material fits the part surface after deformation; e. Final forming trajectory design: Use the "forward-forward" spinning trajectory to gradually shape the material into parts, that is, complete the trajectory design of the outer wall spinning deformation.

5. A method for spinning a perfect circular aircraft engine lip according to claim 4, characterized in that: S3.4 The production spinning program includes: after adding auxiliary lines such as feed and retract, generating NC program code on the programming software, and performing simulation detection on the generated code.

6. A method for spinning a perfect circular aircraft engine lip according to claim 5, characterized in that: S3.5 Design of spinning parameters: During the spinning process, it is necessary to design the spinning temperature, machine speed, and spinning wheel feed parameters. A heating device is used to heat the blank before spinning, and a heating device is used to supplement heat at the spinning position during the spinning process.

7. A method for spinning a perfect circular aircraft engine lip according to claim 1, characterized in that: S4.1 Spinning the outer wall includes the following steps: S4.1.1 Fix the blank on the spinning machine; S4.1.2 Use a heating device to heat and turn on a thermal monitoring device; S4.1.3 After the temperature reaches the set index, start the machine tool and run the spinning trajectory, while keeping the deformation temperature constant during the deformation process; S4.1.4 After spinning is completed, remove the parts.

8. A method for spinning a perfect circular aircraft engine lip according to claim 7, characterized in that: S4.2 Spinning the inner wall includes the following steps: S4.2.1 Fix the product with the outer side wall of the spinning process on the spinning machine; S4.2.2 Use a heating device to heat the spinning position and turn on the thermal monitoring device; S4.2.3 After the temperature reaches the set index, start the machine tool and run the spinning trajectory, while keeping the deformation temperature constant during the deformation process; S4.2.4 After spinning is completed, remove the parts.

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