Processing method of horizontal tail fixed wing wallboard part

Abstract

The invention belongs to the technical field of aviation sheet metal forming, and relates to a machining method of a horizontal tail fixed wing wallboard part. The combined forming machining method of the horizontal tail fixed wing wall plate part solves a series of problems that a traditional horizontal tail fixed wing wall plate forming method is single, low in appearance curved surface precision and poor in continuity, ribs are unstable and fractured, and residual stress rebounds. Precise manufacturing of integral panel parts of the horizontal tail fixed wing with the characteristics of unequal-distance ribs, unequal-height ribs, crossed ribs and the like is achieved. The combined machining method can also be used for manufacturing complex sheet metal integral wall plate aeronautical parts with wall plates of different thicknesses, different materials and different rib heights. The invention relates to manufacturing of complex aluminum alloy wall plate aeronautical parts with different rib heights, wall plates with different thicknesses, different aluminum alloy materials and different rib heights.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation sheet metal forming and relates to a processing method for a horizontal tail fixed wing wall panel part. Background Art

[0002] Aircraft wall panels are basic components of the fuselage structure. Their manufacturing accuracy and surface quality directly affect the shape accuracy and aerodynamic performance of the whole aircraft. Wall panel parts play a vital role in aircraft. Due to the large size, low rigidity, complex structure, double curvature of the shape, large amount of machining and cutting, multiple processes are required to complete the manufacturing. In the current Chinese aviation industry, aluminum alloy integral wall panel flat blanks are directly cut from a whole piece of pre-stretched aluminum alloy thick plate. Its ribs and skin are an integral structure with the advantages of high strength, light weight and long service life. However, due to the complex rib structure of the integral wall panel, it is difficult to form, especially for large-sized high-rib and complex curvature integral wall panels. Traditional forming methods have their own defects. For example, roll forming and gate pressure forming are easy to damage the wall panel structure, causing instability and fracture of the ribs; creep aging forming requires large tank press equipment, which has high production costs.

[0003] This paper proposes a manufacturing method for an integral horizontal tail fixed wing wall panel. First, the aluminum alloy thick plate is formed to the target curvature by shot peening, and then the required high-rib structure is processed by high-speed milling technology. In view of the rebound of the plate, residual stress distribution, and wall panel rebound caused by residual stress release during the removal process after high-speed milling of the aluminum alloy thick plate, shot peening is used for shape correction. The shot peening forming method can effectively solve the forming problem of integral wall panels with high ribs, complex curvatures and structures. The shot peening forming method has the advantages of low cost, no need for forming molds, extended fatigue life, and short production preparation cycle.

[0004] As the machinery manufacturing industry is undergoing a transformation towards intelligent manufacturing, there are higher demands on the appearance accuracy and service life of the aircraft's integral wall panel components. The traditional single processing method can no longer meet the performance requirements, and new combined processing methods are urgently needed to iterate, optimize and improve the integral horizontal tail fixed-wing wall panel manufacturing technology. Summary of the invention

[0005] The present invention aims to solve a series of problems of the traditional horizontal tail fixed wing wall panel forming method, such as single method, low surface accuracy, poor continuity, rib instability and fracture, and residual stress rebound. A combined forming method of horizontal tail fixed wing wall panel parts is proposed, which realizes the precise manufacturing of horizontal tail fixed wing integral wall panel parts with features such as unequally spaced ribs, unequally high ribs, and crossed ribs. This combined processing method can also be used to manufacture complex sheet metal integral wall panel aviation parts with unequal thickness panels, different materials, and different rib heights. Taking a typical horizontal tail fixed wing integral wall panel part as an example, its processing process is as followsFigure 3 shown.

[0006] The technical solution of the present invention is as follows:

[0007] The processing method of the horizontal tail fixed wing wall panel parts is composed of shot peening, high-speed cutting and shot peening. Shot peening is a special process for aircraft sheet metal processing that uses high-speed spherical projectiles to spray the surface layer to cause plastic deformation. High-speed cutting is a metal processing method used in CNC machine tools. The cutting force is transmitted to the surface of the workpiece through a high-speed rotating tool to quickly remove excess material on the workpiece to achieve the purpose of manufacturing precision parts. Shot peening is a method of impacting the surface of metal parts with high-speed moving projectiles. This impact causes plastic deformation of the metal surface and forms a cold hardening layer, also known as a surface strengthening layer. This surface strengthening layer can significantly improve the fatigue resistance and corrosion resistance of the material. The manufacturing process of the horizontal tail fixed wing wall panel does not rely on mold assistance. Due to the large number of deformation factors caused by high-speed milling, there are many uncertain factors. Shot peening can repair the deformation and form a stress layer. Whether the fixed wing wall panel after shot peening can meet the requirements of the aircraft part digital model or drawing requires a set of inspection fixtures to locate and detect the accuracy of the part shape.

[0008] The tooling designed by this combined method is a set of inspection fixture positioning detection devices, thereby obtaining an inspection fixture positioning detection device that is convenient, fast, accurately positioned, and has full-surface detection of shape accuracy. The inspection fixture positioning detection device includes: a frame assembly, a "latch"-shaped piece, a foot pad, a rectangular steel plate, an inspection bracket assembly, a square bracket, an L-profile, a screw, a lower inspection card plate, an upper inspection card plate, a Φ6 threaded locating pin, an M5 handle nut with a recess, a Φ10 threaded locating pin, an M8 handle nut with a recess, a tool ball assembly, a cylindrical pin, a screw, and a positioning plate.

[0009] The frame assembly is a support frame structure that supports the horizontal tail fixed wing wall panel. The total length is 100mm longer than the horizontal tail fixed wing wall panel, the total width is 60mm wider than the horizontal tail fixed wing wall panel, and the total height is generally 100-120mm. It is made of 20 square steels of different lengths welded into 5 "latch"-shaped pieces, and 8 square steels of the same length are horizontally connected to the 5 "latch"-shaped pieces by welding. The frame assembly has a total of 10 support legs, and each support leg is welded with a 20×20mm 2The foot pads are used to connect and fix with the ground plane; two identical rectangular steel plates are screwed on the top of the frame assembly through tool ball assemblies, cylindrical pins, and screws to fix the inspection bracket assembly. The inspection bracket assembly includes a square bracket, L-profiles, and screws. Among them, 11 square brackets are assigned different numbers and are distributed on the fixed axis of the frame assembly according to the cross-sectional shape of the horizontal tail fixed wing wall panel. Each square bracket is screwed and fixed to the rectangular steel plate through two L-profiles and 16 screws. The length of the square bracket is determined according to the width of the horizontal tail fixed wing wall panel, and the height of the square bracket is fine-tuned by 10 to 15 mm according to the curvature of the horizontal tail fixed wing wall panel. Positioning holes of Φ6.2 and Φ10.2 are drilled on the square bracket. The number and position of the positioning holes are consistent with the positioning holes on the lower inspection card plate. The lower inspection card is composed of 11 steel plates of different sizes and shapes, and the numbers corresponding to the square brackets are set respectively. The upper end face of the lower inspection card and the contact surface of the horizontal tail fixed wing wall plate are tightly wrapped with a special protective cloth to prevent bumps and scratches when contacting with parts. The curve of the upper end face is consistent with the cross-sectional arc selected by the part shape. The lower inspection card is connected to the square bracket through positioning holes. The number of positioning holes depends on the length of the lower inspection card, generally 3 to 5. The aperture of the positioning holes on both sides is Φ10.2, and the aperture of the positioning hole in the middle is Φ6.2. The center positions of the positioning holes are not on the same line as far as possible, and the spacing is evenly distributed. After the lower inspection card and the square bracket are inserted into the Φ6.2 or Φ10.2 positioning holes with Φ6 threaded positioning pins or Φ10 threaded positioning pins according to the corresponding numbers, the lower inspection card is tightened with a sunken M5 handle nut or a sunken M8 handle nut to firmly position it on the square bracket point to point. Among them, the Φ6 threaded positioning pin with a sunken M5 handle nut and the Φ10 threaded positioning pin with a sunken M8 handle nut are connected to the corresponding square bracket with a wire rope to ensure that they can play a positioning and clamping role. The upper inspection card is used to detect the internal shape of the horizontal tail fixed wing wall panel parts. It is used in conjunction with the lower inspection card. The lower end face of the upper inspection card and the contact surface with the internal shape of the horizontal tail fixed wing wall panel are tightly wrapped with a special protective cloth to prevent bumps and scratches when in contact with the parts. The curve of the lower end face is consistent with the curvature of the cross section selected for the internal shape of the part. The positioning plate is used for point-to-point positioning of the horizontal tail fixed wing wall panel parts placed on the inspection tooling.

[0010] Beneficial effects of the present invention:

[0011] The combined forming processing method of the horizontal tail fixed wing wall panel parts solves a series of problems such as the single forming method of the traditional horizontal tail fixed wing wall panel, low surface accuracy, poor continuity, instability and fracture of ribs, and residual stress rebound. It realizes the precise manufacturing of the horizontal tail fixed wing integral wall panel parts with features such as unequally spaced ribs, unequally high ribs, and crossed ribs. This combined processing method can also be used to manufacture complex sheet metal integral wall panel aviation parts with unequal thickness panels, different materials, and different rib heights. The manufacturing of complex aluminum alloy wall panel aviation parts with unequal thickness panels, different aluminum alloy materials, and different rib heights. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is a front view of the inspection fixture positioning detection tooling of the present invention;

[0013] Figure 2 This is an axonometric diagram of the inspection fixture positioning detection tooling of the present invention;

[0014] Figure 3 This is a typical process flow chart for the processing of integral wall panels of horizontal tail fixed wing parts.

[0015] In the figure: 1 frame assembly; 2 "latch" shaped part; 3 foot pad; 4 rectangular steel plate; 5 inspection bracket assembly; 6 square bracket; 7 L profile; 8 screws; 9 lower inspection card plate; 10 upper inspection card plate; 11 Φ6 threaded locating pin; 12 M5 handle nut with recess; 13 Φ10 threaded locating pin; 14 M8 handle nut with recess; 15 tool ball assembly; 16 cylindrical pin; 17 screws; 18 locating plate.

[0016] Specific implementation method

[0017] According to the processing process of the horizontal tail fixed wing wall panel parts, a typical 7B04 T74 aluminum alloy integral wall panel part is selected as an example. The implementation steps of the combined forming method are as follows:

[0018] Step 1: Check the surface quality of the wall panels. Check whether the wall panels and process documents are complete, check the surface condition of the materials, and do not allow visible cracks, splits, scratches, delamination, non-metallic inclusions, bubbles, corrosion spots and other surface defects on the material surface.

[0019] Step 2: Check the equipment status. According to the maximum cutting length in the linear material arrangement, select the shearing machine, which requires the shearing machine model, i.e. the blade length is greater than the maximum cutting length; check the equipment, which requires the equipment to be in good condition, within the maintenance cycle, and with the protective measures and signs intact.

[0020] Step 3: Straight-line cutting. Start the equipment and adjust the distance between the rear baffle of the shearing machine and the cutting edge of the lower shear according to the width of the strip to be cut. According to the straight-line cutting and discharging plan, feed the sheet in the length or width direction, and require that the edge of one end of the sheet fed into the shearing machine press against the rear baffle of the shearing machine. Step on the shearing machine switch, the presser foot moves down until it presses on the sheet, and then the upper shear moves down and crosses with the lower shear. After completing a shearing, the upper shear and the presser foot move up and return to the initial position. Execute the requirements for the limit deviation of the cutting size and shape according to the requirements of the process documents.

[0021] Step 4: Check the shot peening equipment. Check that the equipment is in good condition and connect the voltage stabilizer; drain the water in the pressure storage tank and filter and connect the air source; turn on the air dryer and use a mirror to check the air cleanliness to ensure that the air is dry and clean; start the CNC system, check the various performances of the machine tool through the CNC system self-check function, and confirm whether the current projectile type meets the requirements of the process regulations. If not, replace the projectile; run the machine tool for 5 to 10 minutes, check the machine tool operation and projectile circulation; visually check whether there are cracks in the nozzle, and use a stop gauge to check the wear of the inner wall of the nozzle. The wear of the nozzle diameter in use should not exceed 5% of the nominal inner diameter of the nozzle.

[0022] Step 5: Take the ASH280 shot sample. The shot sample is selected from the nozzle in the machine tool. The specific operation method is as follows: first, empty the shot sampling barrel and place it on the workbench in the machine tool; then move the nozzle above the barrel mouth, aim the nozzle at the sampling barrel and keep it at least 100mm high; finally, run the machine tool so that the nozzle sprays the shot into the barrel, turn off the machine tool, take out the sampling barrel, and select the shot for inspection.

[0023] Step 6: Screen the shape of the projectile. Spread the corresponding model of the taken projectiles on a 0.25 (ASH280) square inch plane. The projectiles are arranged neatly and no overlap is allowed. Visual inspection and combined with ASH280 using a minimum 10x magnifying glass inspection method to screen out unqualified projectiles and deformed projectiles. The projectile inspection cycle is controlled when the cumulative work of shot peening reaches 40 hours or when new projectiles are added.

[0024] Step 7: Screen the shot size. Select the standard test sieve according to the shot model, randomly sample 100 grams of shot in the shot barrel, screen on the rotary vibrator, ASH280 screen for 5min±5S, check whether the sieve on the sieve meets the requirements. If the shot size screening is unqualified, the automatic shot peening machine should increase the number of shot cycles until the screening is qualified. The shot size and crushing rate inspection is carried out jointly by the operator and the inspector. The shot inspection cycle is controlled when the shot peening forming has accumulated work for 40h or when new shots are added.

[0025] Step 8: Check the cleanliness of the projectile. The projectile should be dry, free of rust, oil, metal chips and other contaminants. The inspection method is to use 0.1Mpa air pressure to spray a straight, clean aluminum plate (the material, state and thickness of the aluminum plate are not limited) at a distance of 100-120mm for 1 minute. After spraying, cover the aluminum plate with a layer of water film and check whether the water film is broken. If it is broken, it means that the projectile is oily. The inspection is carried out by the operator and the inspector.

[0026] Step 9: Clean the surface of the parts. Use the cleaning agent required by the technical specifications to manually clean the surface of the parts.

[0027] Step 10: Select the shot peening area. Select the shot peening area based on the curvature structure characteristics of the part and the initial deformation state, use the strip shot peening method, and determine the shot peening path.

[0028] Step 11: Protect the non-forming area of ​​the part. In order to prevent the parts from being sprayed by the projectiles and the non-forming area from deformation, in combination with step 11, the non-peening path and non-peening area analyzed in advance are protected on the surface of the part using P-68 tape. The tolerance of the protection area should comply with the drawings and process regulations. If not specified, the tolerance of the protection area is 0 to +3mm.

[0029] Step 12: Shot peening. Nozzle selection: Usually a single nozzle is selected for shot peening; Shot peening angle: When 90° shot peening can be achieved, the shot peening angle is selected to be 90°; Machine tool speed: When other process parameters can be adjusted, the machine tool feed speed is selected to be the maximum; Air pressure: Select the appropriate air pressure according to the part material, thickness, and bending radius of different areas; Shot flow rate: Usually a smaller shot flow rate is selected, generally not exceeding 8kg / min; Shot diameter size: The shot diameter size characterizes the ultimate capacity of shot peening, and ASH280 (0.028 inches) is generally selected; Shot peening distance: The distance mainly affects the strip width and can be selected according to the size of the shot peening area. The material of the part being formed is 7B04-T74, the material thickness is 4.0 mm, and the shot peening forming process parameters are: number of nozzles 1, shot peening angle 90°, machine speed 4000-6000 mm / min, air pressure 0.1 MPa-0.3 MPa, shot flow rate 8 kg / min, shot diameter size 0.028 inches, and shot peening distance 400 mm.

[0030] Step 13: High-speed cutting. Establish a coordinate system and mill the semi-finished product's right-angle edges, depressions, corners, and holes according to the CNC program.

[0031] Step 14: Check the status of semi-finished products. Check the surface quality of semi-finished products. The surface of semi-finished products should be free of oil stains, rust, bumps, pits and scratches; check the curvature and deformation of semi-finished products. The semi-finished products should not have any bulging or loose edges.

[0032] Step 15: Shot peening. To accurately measure the shot peening intensity, the Almen test piece should be fixed on the fixture and simulate the relevant area of ​​the workpiece as much as possible. A full saturation curve is generated at each Almen test piece position, and the process of measuring the shot peening intensity and measuring the coverage of the required area should be verifiable. To measure the coverage rate, the part can be processed in a short cycle and the coverage is checked at a minimum magnification of ×10. By repeating this procedure, 100% coverage is gradually achieved as a basis for verification. According to the actual needs of deformation after high-speed cutting of the integral wall panel, the position and intensity of shot peening shaping are determined. If the local bending degree of the part after shot peening exceeds the requirements of the drawing, reverse shot peening shaping is required; the process parameters and shot peening trajectory of shot peening shaping are selected according to actual needs, but generally the shaping air pressure should be lower than the shot peening shaping air pressure in its area, and the process parameter value of shot peening shaping should be as small as possible. The process parameter value will cause the thinner parts to sway. In order to avoid too large a shot peening area during shaping, use P-68 model tape for local protection when necessary.

Claims

1. A test fixture positioning detection device, characterized in that: It comprises a frame assembly (1), a "latch"-shaped member (2), a foot pad (3), a rectangular steel plate (4), an inspection bracket assembly (5), a square bracket (6), an L-shaped material (7), a screw (8), a lower inspection card plate (9), an upper inspection card plate (10), a Φ6 threaded positioning pin (11), an M5 handle nut with a depression (12), a Φ10 threaded positioning pin (13), an M8 handle nut with a depression (14), a tool ball assembly (15), a cylindrical pin (16), a screw (17), and a positioning plate (18); 20 square steels of different lengths are welded into five "latch"-shaped pieces (2), and eight square steels of the same length are welded to connect the five "latch"-shaped pieces (2) transversely; the frame assembly (1) has a total of 10 support legs, and a 20×20mm thick steel sheet is welded underneath each support leg. 2 The frame assembly (1) is provided with two identical rectangular steel plates (4) screwed to the upper side thereof by means of a tool ball assembly (15), a cylindrical pin (16) and a screw (17) for fixing the inspection bracket assembly (5); the inspection bracket assembly (5) includes a square bracket (6), an L-shaped material (7) and a screw (8); The 11 square brackets (6) are respectively provided with different numbers and are distributed on the fixed axis of the frame assembly (1) according to the cross-sectional conditions of the horizontal tail fixed wing wall panel. Each square bracket (6) is screwed and fixed to the rectangular steel plate (4) through two L-shaped materials (7) and 16 screws (8). The length of the square bracket (6) is determined according to the width of the horizontal tail fixed wing wall panel. The height of the square bracket (6) is finely adjusted by 10 to 15 mm according to the curvature of the horizontal tail fixed wing wall panel. Positioning holes of Φ6.2 and Φ10.2 are drilled on the square bracket (6). The number and position of the positioning holes are consistent with the positioning holes on the lower inspection card plate (9); The lower inspection card plate (9) is composed of 11 steel plates of different sizes and shapes, each of which is numbered one by one with the square bracket (6). The upper end surface of the lower inspection card plate (9) and the contact surface of the horizontal tail fixed wing wall plate are tightly wrapped with a special protective cloth to prevent bumps and scratches when in contact with the parts. The curve of the upper end surface is consistent with the curvature of the cross section selected from the part shape. The lower inspection card plate (9) is connected to the square bracket (6) through positioning holes. The number of positioning holes depends on the length of the lower inspection card plate (9), generally 3 to 5. The aperture of the positioning holes on both sides is Φ10.2, and the aperture of the middle positioning hole is Φ6.

2. The center positions of the positioning holes are not on the same line as much as possible, and the spacing is evenly distributed. After the lower inspection card plate (9) and the square bracket (6) are inserted into the Φ6.2 or Φ10.2 positioning holes using Φ6 threaded positioning pins (11) or Φ10 threaded positioning pins (13) according to the corresponding numbers, the lower inspection card plate (9) is screwed tight using a recessed M5 handle nut (12) or a recessed M8 handle nut (14) to securely position the lower inspection card plate (9) point to point on the square bracket (6); The Φ6 threaded positioning pin (11), the M5 handle nut with a depression (12), the Φ10 threaded positioning pin (13) and the M8 handle nut with a depression (14) are connected to the corresponding square bracket (6) using a steel wire rope.

2. A test fixture positioning detection device as claimed in claim 1, characterized in that: The total length of the frame assembly (1) is 100 mm longer than the length of the horizontal tail fixed wing wall panel, the total width is 60 mm longer than the width of the horizontal tail fixed wing wall panel, and the total height is 100-120 mm.

3. A test fixture positioning detection device as claimed in claim 1 or 2, characterized in that: The upper inspection card plate (10) is used to detect the internal shape of the horizontal tail fixed wing wall panel parts, and is used in conjunction with the lower inspection card plate (9). The lower end surface of the upper inspection card plate (10) and the contact surface with the internal shape of the horizontal tail fixed wing wall panel are tightly wrapped with a special protective cloth to prevent bumps and scratches when contacting the parts. The curve of the lower end surface is consistent with the curvature of the cross section selected for the internal shape of the parts.

4. A test fixture positioning detection device as claimed in claim 1 or 2, characterized in that: The positioning plate (18) is used for point-to-point positioning of the horizontal tail fixed wing wall panel parts placed on the detection tooling.

5. The inspection fixture positioning detection device according to claim 3, characterized in that: The positioning plate (18) is used for point-to-point positioning of the horizontal tail fixed wing wall panel parts placed on the detection tooling.

6. A method for processing a horizontal tail fixed wing panel part, characterized in that: Here are the steps: Step 1: Check the surface quality of the siding; Step 2: Check the device status; Step 3: Cutting in a straight line; start the equipment and adjust the distance between the rear baffle of the shearing machine and the lower shearing edge according to the width of the strip to be cut; Step 4: Check the shot peening equipment; Step 5: Take samples of ASH280 projectiles; Step 6: Screen the shape of the projectiles; spread the corresponding models of the taken projectiles on a plane of 0.25 (ASH280) square inches, and arrange the projectiles neatly without overlapping; visual inspection and combined with ASH280 using a minimum 10x magnifying glass inspection method to screen out unqualified projectiles and deformed projectiles; the projectile inspection cycle is controlled when the cumulative work of shot peening reaches 40 hours or when new projectiles are added; Step 7: Screen the shot size; select the standard test sieve according to the shot model, randomly sample 100 grams of shot in the shot barrel, screen on the rotary vibrator, ASH280 screen for 5min±5S, check whether the sieve on the sieve meets the requirements. If the shot size screening is unqualified, the automatic shot peening machine should increase the number of shot cycles until the screening is qualified; the shot size and crushing rate inspection is carried out jointly by the operator and the inspector; the shot inspection cycle is controlled when the shot peening forming has accumulated work for 40h or new shots are added; Step 8: Check the cleanliness of the projectile; Step 9: Clean the surface of parts; Step 10: Select the shot peening area; Step 11: Protect the non-forming area of ​​the part; In order to prevent the part from being sprayed with shot and the non-forming area from being deformed; Combined with step 11, the pre-analyzed non-shot peening path and non-shot peening area are protected on the surface of the part using P-68 tape. The tolerance of the protection area should comply with the drawings and process regulations. If not specified, the tolerance of the protection area is 0 to +3mm; Step 12: Shot peening; Step 13: High-speed cutting; establish a coordinate system and mill the right-angle edges, depressions, corners, and holes of semi-finished products according to the CNC program; Step 14: Check the status of semi-finished products; check the surface quality of semi-finished products. The surface of semi-finished products should be free of oil stains, rust, bumps, pits and scratches; Step 15: Shot peening.

7. The method for processing the horizontal tail fixed wing panel parts according to claim 6, characterized in that: The fourth step: Check the shot peening equipment, the specific operation is as follows: Check that the equipment is in good condition and connect the voltage-stabilized power supply; release the accumulated water in the pressure storage tank and filter, and connect the air source; turn on the air dryer and use a mirror to check the air cleanliness to ensure that the air is dry and clean; start the CNC system, check the various performance of the machine tool through the CNC system self-check function, and confirm whether the current projectile type is consistent with the requirements of the process regulations. If not, replace the projectile; run the machine tool for 5 to 10 minutes, check the machine tool operation and projectile circulation; visually check whether there is crack in the nozzle, and use a stop gauge to check the wear of the inner wall of the nozzle. The wear of the nozzle diameter in use should not exceed 5% of the nominal inner diameter of the nozzle.

8. The method for processing the horizontal tail fixed wing panel parts according to claim 6, characterized in that: The twelfth step: shot peening, the specific operation is as follows: Nozzle selection: Usually a single nozzle is selected for shot peening; Shot peening angle: When 90° shot peening can be achieved, the shot peening angle is selected to be 90°; Machine tool speed: When other process parameters can be adjusted, the machine tool feed speed is selected to be the maximum; Air pressure: Select the appropriate air pressure according to the part material, thickness, and bending radius in different areas; Shot flow rate: usually choose a smaller shot flow rate, not exceeding 8kg / min; shot diameter size: the shot diameter size characterizes the ultimate capacity of shot peening, and ASH280 is selected; the part material being formed is 7B04-T74, the material thickness is 4.0㎜, and the shot peening process parameters are: number of nozzles 1, shot peening angle 90°, machine speed 4000~6000mm / min, air pressure 0.1mpa~0.3mpa, shot flow rate 8kg / min, shot diameter size 0.028 inches, and shot peening distance 400mm.

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