Method for controlling shot peening strengthening deformation of titanium alloy vertical fin joint of aircraft
By using finite element simulation and support process optimization, the problem of uneven deformation during the shot peening process of titanium alloy parts was solved, and precise shot peening control of titanium alloy joints was achieved, improving part quality and assembly accuracy and meeting the high precision requirements of aerospace manufacturing.
Patent Information
- Application Number
- CN202511285800.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-10
- Publication Date
- 2025-12-09
AI Technical Summary
In the shot peening process of aircraft titanium alloy parts, there is a problem of part deformation caused by uneven deformation, which affects the assembly accuracy and safety. Moreover, there is a lack of experience in optimizing shot peening process parameters in China, making it difficult to meet the stable batch production requirements of high-precision aerospace structural parts.
Deformation analysis was performed using Abaqus finite element-discrete element coupled simulation technology. Shot peening reinforcement support tooling was designed. By optimizing the differentiated strength parameters and support process, combined with rubber pad support, precise shot peening reinforcement deformation control of titanium alloy joints was achieved. By combining 7075 aluminum alloy tooling and rubber pads, the formation of deformation area and plastic deformation layer was controlled.
It effectively reduced the deformation of titanium alloy joints during shot peening, improved part quality, increased processing efficiency and assembly accuracy, and met the high precision requirements of aerospace manufacturing.
Smart Images
Figure CN121093705A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to a method for controlling deformation during shot peening of aircraft titanium alloy vertical tail joints, specifically belonging to the field of shot peening strengthening technology for aircraft machined parts. Background Technology
[0002] In aircraft design, shot peening is frequently used for titanium alloy parts to improve the fatigue performance of the metal. Shot peening introduces residual compressive stress into the titanium alloy parts through shot impact, refining the internal grains and significantly improving the fatigue and corrosion resistance of titanium alloys. Common surface strengthening methods in the aerospace field include surface shot peening, surface rolling, and surface nitriding. Among these, shot peening has been widely used in aerospace manufacturing due to its low manufacturing cost, relatively simple process, easy control, and obvious effects. However, the shot peening process induces uneven deformation inside and outside the parts, causing deformation of the part shape. This deformation will lead to gaps and delamination during aircraft assembly. Compared with foreign aerospace fields, China's aerospace industry started late and is still in its early stages of development. Insufficient processing experience results in severe deformation after shot peening, and the lack of experience in controlling this deformation seriously restricts the development of the aerospace manufacturing field.
[0003] The vertical tail joint of the domestically produced C919 large passenger aircraft, as a core load-bearing connection component between the vertical tail and the fuselage, must withstand complex and variable aerodynamic loads and high-frequency structural vibrations during long-term high-altitude flight. Its design requirements simultaneously meet high specific strength, lightweight, and life-cycle durability indicators. Its unique technical characteristics are concentrated in the synergistic innovation of the titanium alloy material system and shot peening process. Shot peening uses a high-speed projectile stream to controllably impact the titanium alloy surface, introducing a residual compressive stress field into the material surface, improving the material's fatigue resistance by 30% to 50%. This process has become a key surface strengthening technology in the manufacture of aerospace structural components. However, the non-uniformity of projectile energy transfer during shot peening can easily lead to zero fatigue. The three-dimensional deformation of the component leads to local dimensional deviations exceeding 1mm in complex curved surface joints. This deformation poses a risk of interlayer delamination during the docking of the vertical tail and fuselage sections. Compared to the shot peening deformation compensation database and closed-loop control system already established by internationally advanced aerospace manufacturing companies, China still has shortcomings in this field, such as insufficient experience in optimizing process parameters, which restricts the stable mass production of high-precision aerospace structural components. If the C919 vertical tail joint is not shot peened, the titanium alloy surface will lack the protective effect of the residual compressive stress layer. Under cyclic loading, the microcrack initiation life will be shortened by 60% to 70%, failing to meet the stringent requirements for structural durability and safety in airworthiness standards, posing a potential threat to flight safety.
[0004] Traditional shot peening methods in the aerospace manufacturing industry rely solely on the precision control of the shot peening equipment itself. Parts prone to damage during shot peening require subsequent correction and rework. Process design schemes and auxiliary tooling are rarely used, resulting in low first-pass yield and low rework efficiency, severely hindering quality improvement and technological development. Traditional shot peening uses single shot peening parameters, requiring frequent manual adjustments for easily deformable structural parts, leading to poor controllability.
[0005] The aircraft titanium alloy connector addressed in this application is manufactured using the machining mold described in Chinese Patent Application No. 2025108274898, "A Three-Axis Machining Mold for an Aircraft Hyperbolic Connector Part." The vertical tail connector structure comprises a hyperbolic irregular base plate, a bottom boss, sidewalls perpendicular to the bottom boss, four transverse ribs of different sizes on the inner side, two longitudinal ribs, and four mutually perpendicular nut holes. The four recessed areas on the bottom surface of the hyperbolic irregular base plate are used to connect to the composite material panel of the aircraft's vertical tail fin. Summary of the Invention
[0006] This invention, through a method of "design analysis - process optimization - auxiliary support," derives feasible means to control the deformation impact of shot peening on aircraft titanium alloy joints. It can accurately predict and control the deformation of such titanium alloy structures after shot peening, forming a complete design and control system for shot peening processes. Therefore, it has significant theoretical and engineering application value.
[0007] The purpose of this invention is to provide a method for controlling the deformation of the titanium alloy vertical tail joint of an aircraft after shot peening. Shot peening results in severe deformation, insufficient control experience, low processing efficiency, difficulty in assembling deformed parts, and easy functional failure.
[0008] To achieve the above objectives, this invention provides a method for controlling deformation during shot peening of an aircraft titanium alloy vertical tail joint. Specifically, it consists of the following five steps:
[0009] 1) Based on Abaqus finite element-discrete element (FEM-DEM) coupled simulation technology, shot peening deformation analysis was conducted on titanium alloy joint parts. The simulation model used 0.25mm diameter cast steel shot as the discrete phase, impacting the three-dimensional geometric model (CAD model) of the part perpendicularly with an initial velocity of 12mm / s. A dynamic coupled solver captured the interaction between the material surface and the shot particles, quantitatively evaluating the deformation evolution trend and the deformation amount in key areas. In terms of modeling strategy, the titanium alloy joint parts were meshed using hexahedral linear reduced integral elements, and a local refinement technique was used to balance computational accuracy and solution efficiency. The shot particle group was defined as an analytical rigid body to reduce the computational complexity of nonlinear contact, thus deriving the deformation area and deformation amount.
[0010] 2) Based on the structural characteristics of the part, a shot peening reinforcement support fixture was designed. The support surface was designed in the non-deformable area, while the deformable area was suspended. The support surface was selected from the non-deformable area of the part with high rigidity and low risk of stress concentration to avoid obstructing the shot peening path. The suspended deformable area ensured that the area to be reinforced was completely unsupported by the fixture. The fixture material was selected as 7075 aluminum alloy to ensure rigidity without damaging the part. A 5mm gap was maintained between the support surface and the deformable area to ensure no stress interference. The support fixture was connected to the part using industrial double-sided tape to ensure that the part did not move during shot peening. The fixture had a groove and a cylinder to mate with the vertical ribs on the part's contact surface. The groove size was 1mm larger than the vertical rib to ensure complete engagement between the part and the fixture. The inner cavity on the reverse side of the fixture was a 10mm thick cavity to reduce the weight of the fixture and facilitate installation.
[0011] 3) Based on the predictive analysis results of the deformation trend of the parts, the high deformation risk area is precisely processed by the directional shot peening strengthening process. The plastic deformation generated by the high-speed impact of the shot constructs a gradient residual compressive stress field on the surface of the parts. This stress field forms a vector superposition effect with the original deformation tensile stress field, which causes the parts to produce controllable reverse pre-deformation and simultaneously form a surface hardening layer. The work hardening effect induced by shot peening increases the surface hardness of the material by 30%. The synergistic effect of stress field reconstruction and material performance enhancement increases the critical value of plastic deformation of the parts under service load by more than 35%, effectively inhibiting the continuous development of the original deformation trend and ultimately achieving long-term maintenance of the geometric accuracy stability of the parts.
[0012] 4) Based on numerical simulation analysis of the deformation field, a dual-sided synergistic shot peening strengthening process is implemented using differentiated strength parameters. On the forward-facing surface, a parameter of 0.224 mmA (Almen strength) is selected according to the principal vector direction of the deformation trend. High-energy shot impacts form a plastic deformation layer with a depth of 0.30 mm on the surface, with this high-amplitude compressive stress serving as the main deformation driving force. On the reverse-facing surface, a compensating shot peening process is implemented using a parameter of 0.162 mmA, generating a shallow plastic deformation zone of 0.20 mm. Through the vector superposition effect of the residual compressive stress gradients on both sides, combined with the difference in bending stiffness caused by the depth difference of the plastic deformation layer, the reverse deformation is further driven.
[0013] 5) Based on the structural characteristics of the part and addressing the deformation suppression requirements in the stepped area, a rubber support pad with the same thickness as the step and a three-dimensional contour perfectly matching the part's surface is used. The microscopic peak meshing effect between the support pad and the step's contact surface achieves uniform stress distribution. This solution significantly reduces the maximum plastic deformation in the stepped area from 0.30 mm in the free state to 0.10 mm, effectively suppressing deformation in the stepped area.
[0014] Specifically, according to one aspect of this application, a method for controlling deformation during shot peening of an aircraft titanium alloy vertical tail joint is provided, comprising the following steps:
[0015] A support fixture is used to assemble the machined parts of the aircraft titanium alloy vertical tail connector with the support fixture, and then shot peening is performed to obtain the shot peening-strengthened aircraft titanium alloy vertical tail connector.
[0016] The support fixture consists of baffle 5, support block 6, support block 7, support block 8, support block 9, and mandrel 10;
[0017] The support blocks 6, 7, 8, and 9 are designed based on the internal cavity structure features of the machined part of the aircraft titanium alloy vertical tail connector. The support surfaces of the support blocks 6, 7, 8, and 9 are designed in the rigid structural area of the machined part of the aircraft titanium alloy vertical tail connector, while the easily deformable areas of the machined part of the aircraft titanium alloy vertical tail connector are suspended, ensuring that the areas that need to be reinforced are completely free of tooling support.
[0018] The support fixture is made of 7075 aluminum alloy, which ensures rigidity without damaging the machined parts of the aircraft's titanium alloy vertical tail connector.
[0019] The support surfaces of the support blocks 6, 7, 8, and 9 are connected to the contact surfaces of the machined parts of the aircraft titanium alloy vertical tail connector using industrial double-sided tape to ensure that the machined parts of the aircraft titanium alloy vertical tail connector do not move during shot peening.
[0020] The baffle 5 is an aluminum alloy plate with a thickness of 20mm, and a boss is provided on the upper surface. The shape of the boss is consistent with the shape of the boss on the bottom surface of the machined part of the aircraft titanium alloy vertical tail connector.
[0021] The chamfer on the long side of the contact surface between the baffle 5 and the machined part of the aircraft titanium alloy vertical tail connector is R5mm, and the chamfer on the short side is R15mm.
[0022] The baffle 5 has three φ10.5mm mounting holes for connecting support block 6, support block 8, and support block 9.
[0023] The support blocks 6, 7, 8, and 9 are divided into upper and lower parts. The upper part is used to support the machined parts of the aircraft titanium alloy vertical tail connector. The structural dimensions are based on the internal cavity design of the machined parts of the aircraft titanium alloy vertical tail connector. The lower part is a plane. They are fitted together with a 0mm gap. The support block 7 does not have assembly holes and is positioned by the friction of the support blocks 6 and 7.
[0024] The support block 6 is used to support the inner cavity area 11 of the machined part of the aircraft titanium alloy vertical tail connector. Its shape conforms to the outer vertical rib and outer contour of the machined part of the aircraft titanium alloy vertical tail connector. The allowance is 0mm to prevent shot peening during the shot peening process.
[0025] The support block 6 has a φ10.5mm mounting hole on its side for connecting the baffle 5;
[0026] The support block 7 is used to support the middle area 12 of the two transverse ribs of the machined part of the aircraft titanium alloy vertical tail connector, and the mating surface structure is consistent with that of the machined part of the aircraft titanium alloy vertical tail connector.
[0027] The support block 8 is used to support the middle area 13 of the two horizontal ribs on the other side of the machined part of the aircraft titanium alloy vertical tail connector, and the mating surface structure is consistent with that of the machined part of the aircraft titanium alloy vertical tail connector.
[0028] One end of the support block 8 is provided with a mandrel hole for installing the mandrel 10 to position the nut hole of the machining part of the aircraft titanium alloy vertical tail connector.
[0029] The support block 8 has a φ10.5mm mounting hole on its side for connecting the baffle 5;
[0030] The support block 9 is used to support the inner cavity area 14 of the machined part of the aircraft titanium alloy vertical tail connector. Its shape conforms to the outer vertical rib and outer contour of the machined part of the aircraft titanium alloy vertical tail connector. The margin is 0mm to prevent shot peening during the shot peening process.
[0031] The support block 9 has a φ10.5mm mounting hole on its side for connecting the baffle 5.
[0032] The mandrel 10 is a cylindrical mandrel with a diameter of φ32.6mm. A bolt hole is provided in the middle of the mandrel 10. The mandrel 10 is installed on the support block 9 and is used to position the nut hole of the machined part of the aircraft titanium alloy vertical tail connector perpendicular to the bottom surface.
[0033] The shot peening process prioritizes the deformation trend direction of the machined part of the aircraft titanium alloy vertical tail connector, causing the machined part of the aircraft titanium alloy vertical tail connector to deform and harden preferentially in the opposite direction, thereby weakening the deformation trend. At this time, the shot peening intensity is 0.224 mmA on the front and 0.162 mmA on the back. The intensity difference method is used to deform in the opposite direction of the deformation trend.
[0034] The deformation trend and the amount of deformation required for shot peening were obtained in advance through finite element deformation analysis.
[0035] To control deformation in the stepped area of the machined titanium alloy vertical tail connector for aircraft, an industrial rubber pad with the same thickness as the step and the same shape as the part structure is used for support. The elastic deformation of the rubber pad absorbs the impact energy of shot peening, and its geometric adaptability is used to achieve precise local support, thereby effectively suppressing excessive deformation in the stepped area.
[0036] The beneficial effects of this invention are as follows:
[0037] The advantages of this application are as follows: This invention adopts a method for controlling deformation after shot peening of aircraft titanium alloy joints. Through the process design scheme of "finite element deformation analysis - differential strength processing - non-deformation area support fixture", the deformation of aircraft titanium alloy joints after shot peening is effectively reduced, the quality of parts is greatly improved, and valuable experience is provided for aerospace parts manufacturing technology. Attached Figure Description
[0038] Figure 1 Process flow diagram;
[0039] Figure 2 Schematic diagram of machining parts and support tooling assembly for aircraft titanium alloy vertical tail joint;
[0040] Figure 3 Exploded view of the supporting tooling;
[0041] Figure 4 Schematic diagram of a machined titanium alloy vertical tail connector for an aircraft.
[0042] Among them, 1 is the machined part of the aircraft titanium alloy vertical tail connector, 2 is the support tooling, 3 is the deformation area, 4 is the working surface, 5 is the baffle, 6 is the support block, 7 is the support block, 8 is the support block, 9 is the support block, 10 is the mandrel, 11 is the inner cavity area, 12 is the intermediate area, 13 is the intermediate area, and 14 is the inner cavity area. Detailed Implementation
[0043] The present application is described in detail below with reference to the embodiments, but the present application is not limited to these embodiments.
[0044] Example 1
[0045] like Figure 1-2 As shown, a method for controlling deformation during shot peening of aircraft titanium alloy joints includes:
[0046] Step 1: Using Abaqus finite element-discrete element (FEM-DEM) coupled simulation technology, deformation analysis was performed on titanium alloy joint part 1 after shot peening. The deformation area and deformation amount of the titanium alloy part were determined.
[0047] Step 2: Based on the deformation area 3 and trend analysis, design and manufacture shot peening reinforcement support fixture 2 to determine the front side of shot peening reinforcement.
[0048] The support fixture consists of baffle 5, support block 6, support block 7, support block 8, support block 9, and mandrel 10;
[0049] The support blocks 6, 7, 8, and 9 are designed based on the internal cavity structure features of the machined part of the aircraft titanium alloy vertical tail connector. The support surfaces of the support blocks 6, 7, 8, and 9 are designed in the rigid structural area of the machined part of the aircraft titanium alloy vertical tail connector, while the easily deformable areas of the machined part of the aircraft titanium alloy vertical tail connector are suspended, ensuring that the areas that need to be reinforced are completely free of tooling support.
[0050] The support fixture is made of 7075 aluminum alloy, which ensures rigidity without damaging the machined parts of the aircraft's titanium alloy vertical tail connector.
[0051] The support surfaces of the support blocks 6, 7, 8, and 9 are connected to the contact surfaces of the machined parts of the aircraft titanium alloy vertical tail connector using industrial double-sided tape to ensure that the machined parts of the aircraft titanium alloy vertical tail connector do not move during shot peening.
[0052] The baffle 5 is an aluminum alloy plate with a thickness of 20mm, and a boss is provided on the upper surface. The shape of the boss is consistent with the shape of the boss on the bottom surface of the machined part of the aircraft titanium alloy vertical tail connector.
[0053] The chamfer on the long side of the contact surface between the baffle 5 and the machined part of the aircraft titanium alloy vertical tail connector is R5mm, and the chamfer on the short side is R15mm.
[0054] The baffle 5 has three φ10.5mm mounting holes for connecting support block 6, support block 8, and support block 9.
[0055] The support blocks 6, 7, 8, and 9 are divided into upper and lower parts. The upper part is used to support the machined parts of the aircraft titanium alloy vertical tail connector. The structural dimensions are based on the internal cavity design of the machined parts of the aircraft titanium alloy vertical tail connector. The lower part is a plane. They are fitted together with a 0mm gap. The support block 7 does not have assembly holes and is positioned by the friction of the support blocks 6 and 7.
[0056] The support block 6 is used to support the inner cavity area 11 of the machined part of the aircraft titanium alloy vertical tail connector. Its shape conforms to the outer vertical rib and outer contour of the machined part of the aircraft titanium alloy vertical tail connector. The allowance is 0mm to prevent shot peening during the shot peening process.
[0057] The support block 6 has a φ10.5mm mounting hole on its side for connecting the baffle 5;
[0058] The support block 7 is used to support the middle area 12 of the two transverse ribs of the machined part of the aircraft titanium alloy vertical tail connector, and the mating surface structure is consistent with that of the machined part of the aircraft titanium alloy vertical tail connector.
[0059] The support block 8 is used to support the middle area 13 of the two horizontal ribs on the other side of the machined part of the aircraft titanium alloy vertical tail connector, and the mating surface structure is consistent with that of the machined part of the aircraft titanium alloy vertical tail connector.
[0060] One end of the support block 8 is provided with a mandrel hole for installing the mandrel 10 to position the nut hole of the machining part of the aircraft titanium alloy vertical tail connector.
[0061] The support block 8 has a φ10.5mm mounting hole on its side for connecting the baffle 5;
[0062] The support block 9 is used to support the inner cavity area 14 of the machined part of the aircraft titanium alloy vertical tail connector. Its shape conforms to the outer vertical rib and outer contour of the machined part of the aircraft titanium alloy vertical tail connector. The margin is 0mm to prevent shot peening during the shot peening process.
[0063] The support block 9 has a φ10.5mm mounting hole on its side for connecting the baffle 5.
[0064] The mandrel 10 is a cylindrical mandrel with a diameter of φ32.6mm. A bolt hole is provided in the middle of the mandrel 10. The mandrel 10 is installed on the support block 9 and is used to position the nut hole of the machined part of the aircraft titanium alloy vertical tail connector perpendicular to the bottom surface.
[0065] Step 3: Install the shot peening reinforcement support fixture 2 on the working platform of the shot peening machine, and fix the position of the shot peening reinforcement support fixture 2 through the positioning holes of the platform using a universal positioning block.
[0066] Step 4: Use general industrial double-sided tape to attach the reverse side of the titanium alloy connector part 1 to the working surface 4 of the shot peening reinforcement support fixture 2. Use no less than 4 pieces of double-sided tape, each piece being no less than 20×40mm. After attaching, check the stability of the titanium alloy connector part 1 and the shot peening reinforcement support fixture 2.
[0067] Step 5: When blasting the front side, adjust the parameters of the shot peening equipment and set the fitting intensity to 0.224 mmA to complete the front shot peening.
[0068] Step Six: When spraying the reverse side, do not use tooling. Based on the thickness of the front step and the outer contour dimensions of the deformation area, manufacture a rubber support pad of the same thickness and shape. Attach the rubber support pad to the front deformation area of the titanium alloy joint part 1 using industrial double-sided tape.
[0069] Step 7: Place the titanium alloy connector part 1 flat on the working platform of the shot peening machine, and use a universal positioning block to fix the titanium alloy connector part 1 through the positioning holes of the platform to ensure stability.
[0070] Step 8: When blasting the reverse side, adjust the parameters of the shot peening equipment and set the fitting intensity to 0.162mmA to complete the reverse side shot peening.
[0071] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any modifications or substitutions made by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.
Claims
1. A method for controlling deformation during shot peening of an aircraft titanium alloy vertical tail joint, characterized in that, Includes the following steps: A support fixture is used to assemble the machined parts of the aircraft titanium alloy vertical tail connector with the support fixture, and then shot peening is performed to obtain the shot peening-strengthened aircraft titanium alloy vertical tail connector. The support fixture consists of a baffle (5), a support block (6), a support block (7), a support block (8), a support block (9), and a mandrel (10); The support blocks (6), (7), (8), and (9) are designed based on the internal cavity structure features of the machined part of the aircraft titanium alloy vertical tail connector. The support surfaces of the support blocks (6), (7), (8), and (9) are designed in the rigid structure area of the machined part of the aircraft titanium alloy vertical tail connector. The easily deformable areas of the machined part of the aircraft titanium alloy vertical tail connector are suspended, ensuring that the areas that need to be strengthened are completely free of tooling support.
2. The method for controlling deformation strengthening of aircraft titanium alloy vertical tail joint by shot peening according to claim 1, characterized in that, The support fixture is made of 7075 aluminum alloy, which ensures rigidity without damaging the machined parts of the aircraft's titanium alloy vertical tail connector. The support surfaces of the support blocks (6), (7), (8), and (9) are connected to the contact surfaces of the machined parts of the aircraft titanium alloy vertical tail connector using industrial double-sided tape to ensure that the machined parts of the aircraft titanium alloy vertical tail connector do not move during the shot peening process.
3. The method for controlling deformation strengthening of aircraft titanium alloy vertical tail joint by shot peening according to claim 2, characterized in that, The baffle (5) is an aluminum alloy plate with a thickness of 20mm, and a boss is provided on the upper surface. The shape of the boss is consistent with the shape of the boss on the bottom surface of the machined part of the titanium alloy vertical tail connector of the aircraft. The chamfer on the long side of the contact surface between the baffle (5) and the machined part of the titanium alloy vertical tail connector of the aircraft is R5mm, and the chamfer on the short side is R15mm. The baffle (5) has three φ10.5mm mounting holes for connecting the support block (6), support block (8), and support block (9).
4. The method for controlling deformation strengthening of aircraft titanium alloy vertical tail joint by shot peening according to claim 3, characterized in that, The support blocks (6), (7), (8), and (9) are divided into upper and lower parts. The upper part is used to support the machined parts of the aircraft titanium alloy vertical tail connector. The structural dimensions are based on the internal cavity design of the machined parts of the aircraft titanium alloy vertical tail connector. The lower part is a plane. They are fitted together with a 0mm gap. The support block (7) does not have assembly holes and is positioned by the friction of the support blocks (6) and (7).
5. The method for controlling deformation strengthening of aircraft titanium alloy vertical tail joint by shot peening according to claim 4, characterized in that, The support block (6) is used to support the inner cavity area (11) of the machined part of the aircraft titanium alloy vertical tail connector. Its shape conforms to the outer vertical rib and outer contour of the machined part of the aircraft titanium alloy vertical tail connector. The allowance is 0mm to prevent shot peening during the shot peening process. The support block (6) has a φ10.5mm mounting hole on its side for connecting the baffle (5); The support block (7) is used to support the middle area (12) of the two transverse ribs of the machined part of the aircraft titanium alloy vertical tail connector, and the mating surface structure is consistent with that of the machined part of the aircraft titanium alloy vertical tail connector. The support block (8) is used to support the middle area (13) of the two horizontal ribs on the other side of the machined part of the aircraft titanium alloy vertical tail connector, and the mating surface structure is consistent with that of the machined part of the aircraft titanium alloy vertical tail connector. The support block (8) has a mandrel hole at one end for installing the mandrel (10) to position the nut hole of the machined part of the aircraft titanium alloy vertical tail connector. The support block (8) has a φ10.5mm mounting hole on its side for connecting the baffle (5); The support block (9) is used to support the inner cavity area (14) of the machined part of the aircraft titanium alloy vertical tail connector. Its shape conforms to the outer vertical rib and outer contour of the machined part of the aircraft titanium alloy vertical tail connector. The allowance is 0mm to prevent shot peening during the shot peening process. The support block (9) has a φ10.5mm mounting hole on its side for connecting the baffle (5).
6. The method for controlling deformation strengthening of aircraft titanium alloy vertical tail joint by shot peening according to claim 5, characterized in that, The core rod (10) is a cylindrical core rod with a diameter of φ32.6mm. A bolt hole is provided in the middle of the core rod (10). The core rod (10) is installed on the support block (9) and the support block (9) is used to position the nut hole of the machined part of the aircraft titanium alloy vertical tail connector perpendicular to the bottom surface.
7. The method for controlling deformation strengthening of aircraft titanium alloy vertical tail joint by shot peening according to claim 1, characterized in that, The shot peening process prioritizes the deformation trend direction of the machined part of the aircraft titanium alloy vertical tail connector, causing the machined part of the aircraft titanium alloy vertical tail connector to deform and harden preferentially in the opposite direction, thereby weakening the deformation trend. At this time, the shot peening intensity is 0.224 mmA on the front and 0.162 mmA on the back. The intensity difference method is used to deform in the opposite direction of the deformation trend. The deformation trend and the amount of deformation required for shot peening were obtained in advance through finite element deformation analysis.
8. The method for controlling deformation strengthening of aircraft titanium alloy vertical tail joint by shot peening according to claim 1, characterized in that, To control deformation in the stepped area of the machined titanium alloy vertical tail connector for aircraft, an industrial rubber pad with the same thickness as the step and the same shape as the part structure is used for support. The elastic deformation of the rubber pad absorbs the impact energy of shot peening, and its geometric adaptability is used to achieve precise local support, thereby effectively suppressing excessive deformation in the stepped area.