Simulation method for manufacturing rocket engine jet pipe through inner wall and outer wall integrated forming scheme based on ABAQUS

Abstract

The invention relates to a simulation method for manufacturing a rocket engine jet pipe through an inner and outer wall integrated forming scheme based on ABAQUS. The method specifically comprises the steps that ABAQUS simulation pretreatment is conducted; aBAQUS simulation solution is carried out; and ABAQUS simulation post-processing is carried out. According to the ABAQUS-based simulation method for manufacturing the rocket engine jet pipe through the inner wall and outer wall integrated forming scheme, the relation between geometric parameters, material parameters and manufacturing process parameters of the jet pipe and the performance of the jet pipe is effectively established; the optimized parameter combination is obtained by adjusting different numerical values of all parameters, the problem of cost and process limitation in the actual manufacturing process is solved, the method is a new idea for obtaining optimized parameters, and the method has important significance on selection of actual parameters and is suitable for popularization and application. The relation between geometric parameters, material parameters and manufacturing process parameters of the spray pipe and the performance of the spray pipe is effectively established, and the structural strength and the overall performance of the spray pipe can be remarkably improved by accurately controlling and optimizing the parameters.

Description

Technical Field

[0001] This invention relates to the field of spinning finite element simulation technology, specifically a simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated molding scheme for inner and outer walls. Background Technology

[0002] As a key component in the aerospace field, the performance of rocket engine nozzles directly affects the thrust and efficiency of rockets.

[0003] Traditional manufacturing methods often suffer from high costs and complex processes. Therefore, it is necessary to establish a parameterized three-dimensional geometric constraint simulation model of nozzle oscillation through simulation methods. During nozzle design, actuator stroke curve data can be directly generated to verify rocket flight control algorithms, such as the rocket engine nozzle oscillation simulation analysis method and system disclosed in Chinese Patent 202010256153.8.

[0004] ABAQUS, a powerful finite element analysis software, can accurately simulate the mechanical behavior of nozzles under complex working conditions. The integrated molding scheme of the inner and outer walls helps improve the structural strength and overall performance of the nozzle. However, in practical applications, this simulation method needs to be validated in conjunction with specific material properties and manufacturing processes to ensure the accuracy and reliability of the simulation results. Furthermore, how to further optimize simulation parameters, improve computational efficiency, and reduce costs are also important issues that need to be addressed in current research.

[0005] Using ABAQUS finite element software for billet spinning analysis can save costs and improve the accuracy of optimization parameters. Therefore, a simulation method is needed to correlate spinning-related process parameters with rocket engine nozzle forming. Summary of the Invention

[0006] To address the shortcomings of existing technologies, this invention provides a simulation method for manufacturing rocket engine nozzles using an integrated molding scheme for inner and outer walls based on ABAQUS, solving the problems of cumbersome optimization parameters, high cost, and inaccuracy in existing technologies.

[0007] To achieve the above objectives, the present invention provides the following technical solution: a simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated inner and outer wall molding scheme, specifically implemented according to the following steps:

[0008] Step 1: Perform ABAQUS simulation preprocessing;

[0009] Step 2: Perform ABAQUS simulation and solve the problem;

[0010] Step 3: Perform ABAQUS simulation post-processing.

[0011] As a preferred technical solution of the present invention, the ABAQUS simulation preprocessing in step 1 is specifically performed as follows:

[0012] Step 1.1, Model sketch drawing: Draw the sketch of the inner wall blank, forming tooling and strong rotating wheel. The angle between the blank and the mold axis is 20°, the angle between the mold hypotenuse and the axis is 10°, and the radius of the strong rotating wheel is 80mm.

[0013] Step 1.2, 3D model creation: Create a 3D part including a blank, two spinning wheels and a mold. The blank thickness is 5mm. Determine the part type.

[0014] Step 1.3, Material Property Definition: The material is 304 stainless steel, with a density of 7.93 g / cm³. 3 Melting point is 1400℃; mechanical properties include tensile strength of 1000MPa, yield strength of 205MPa, and elongation of 40%. The material property definition also includes a strain hardening model, using the Johnson-Cook constitutive equation to describe the mechanical behavior of the material at high strain rates.

[0015] Step 1.4, Section Creation: Select the section type, and determine the section integration and integration rules;

[0016] Step 1.5, Section Assignment: Assign section to the component blank;

[0017] Step 1.6, Mesh System Construction: Global seeding is performed for the four components: billet, mold, and left and right strong spinning wheels. Seeding is also performed on the edges. The meshing type is selected, and finally the meshing is completed.

[0018] Step 1.7, Component Assembly: Assemble the four components according to the sketch: blank, mold, and left and right strong spinning wheels. The outer edge of the strong spinning wheel is 3mm from the surface of the mold, and the thickness of the blank after strong spinning is 2mm.

[0019] Specifically, in step 1.3, the material property definition also includes a strain hardening model, which uses the Johnson-Cook constitutive equation to describe the mechanical behavior of the material at high strain rates.

[0020] As a preferred technical solution of the present invention, the ABAQUS simulation solution process in step 2 is specifically performed as follows:

[0021] Step 2.1, Adding an Analysis Unit: Add an analysis unit type, and set the analysis unit increment and quality scaling;

[0022] Step 2.2, Field Output Settings: Edit the field output options for the overall assembly model to output field variables such as stress, strain, displacement / velocity / acceleration, action / reaction force, contact, volume / thickness / coordinates;

[0023] Step 2.3, Interaction Settings: Add 'Surface-to-Surface Contact (Explicit)' interaction to the outer surface of the mold and the inner surface of the billet, and the outer surfaces of the left and right strong spinning wheels and the outer surface of the billet. Select 'Penalty Contact Method' as the formula for all mechanical constraints. Select the slip formula. The improved penalty function contact algorithm includes dynamically adjusting the penalty stiffness according to the contact pressure to balance convergence and penetration.

[0024] Step 2.4, Adding contact conditions: Add the 'Tangential Behavior' contact attribute, select the 'Penalty' friction formula, set the directionality to isotropic, and set the friction coefficient;

[0025] Step 2.5, Add constraint conditions: bind the blank to the mold mating surface;

[0026] Step 2.6, Add boundary conditions: Add loads to the four components: billet, mold, and left and right strong spinning wheels. Select the load type and set the load coordinates.

[0027] As a preferred technical solution of the present invention, in step 3, the ABAQUS simulation post-processing is specifically performed as follows: a visual cloud map is obtained through job analysis, and the cloud map is adjusted for intensity analysis.

[0028] As a preferred technical solution of the present invention, step 3 includes:

[0029] Step 3.1, Multi-field Coupling Analysis: Simultaneously analyze the stress field, strain field, and temperature field;

[0030] Step 3.2, Parameter sensitivity analysis: Evaluate the degree of influence of each process parameter on molding quality. The parameter sensitivity analysis adopts the analysis of variance (ANOVA) method to quantify the influence weight of each parameter on molding quality.

[0031] Step 3.3, Optimize parameter output: Output the optimal combination of process parameters.

[0032] As a preferred technical solution of the present invention, the simulation method is applicable to the spin forming simulation of other high-strength metal materials, including titanium alloys and nickel-based high-temperature alloys.

[0033] Compared with the prior art, the technical solution of this application has the following beneficial effects:

[0034] This invention discloses a simulation method for manufacturing rocket engine nozzles using an ABAQUS-based integrated molding scheme for inner and outer walls. This method effectively establishes the relationship between the nozzle's geometric parameters, material parameters, manufacturing process parameters, and nozzle performance. By adjusting different values ​​of each parameter to obtain an optimized parameter combination, it solves the cost and process limitations in the actual manufacturing process. This is a new approach to obtaining optimized parameters and is of great significance for the selection of actual parameters. Attached Figure Description

[0035] Figure 1 This is a finite element simulation flowchart of a simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated molding scheme for inner and outer walls, according to the present invention.

[0036] Figure 2 This is a sketch of all the components of a simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated molding scheme for inner and outer walls, according to the present invention.

[0037] Figure 3 This is a three-dimensional diagram and coordinate system diagram of the assembly relationship between the components of a simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated molding scheme for inner and outer walls, according to the present invention.

[0038] Figure 4 This is a mesh generation diagram of a simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated molding scheme for inner and outer walls, according to the present invention.

[0039] Figure 5 This is a visualization of the simulation results cloud map of the simulation method for manufacturing rocket engine nozzles based on ABAQUS through an integrated molding scheme of inner and outer walls according to the present invention.

[0040] Figure 6 This is a visualization cloud map of the initial state of the simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated molding scheme for inner and outer walls, according to the present invention.

[0041] Figure 7 This is a visualization cloud map of the operational completion status of a simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated molding scheme for inner and outer walls, and it is also a Mises stress distribution cloud map.

[0042] Figure 8 This is the Max. In-Plane Principal stress distribution cloud map of the simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated molding scheme for inner and outer walls, as described in this invention.

[0043] Figure 9 This is a Tresca stress distribution cloud map of a simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated molding scheme for inner and outer walls, according to the present invention.

[0044] Figure 10 This is a pressure distribution cloud map of a simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated molding scheme for inner and outer walls, according to the present invention. Detailed Implementation

[0045] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0046] This invention discloses a finite element analysis method for simulating the manufacture of rocket engine nozzles using an integrated inner and outer wall molding scheme based on ABAQUS. Figure 1 As shown, please follow these steps:

[0047] Step 1, the ABAQUS simulation preprocessing stage, is implemented according to the following steps:

[0048] Step 1.1, Model sketch drawing: as follows Figure 2 As shown, draw a sketch of the inner wall blank, forming tooling and strong rotating wheel. The angle between the blank and the mold axis is 20°, the angle between the mold hypotenuse and the axis is 10°, and the radius of the strong rotating wheel is 80mm.

[0049] Step 1.2, 3D model creation: Create a 3D part including a blank, two powerful spinning wheels and a mold. The blank thickness is 5mm. Determine the part type. The mold and the two left and right powerful spinning wheels are all 3D discrete rigid bodies. The basic feature is selected as solid, while the blank is a 3D variable shell.

[0050] Step 1.3, Material Property Definition: Create a material in the Material Manager of the Properties module. The material is 304 stainless steel, with a chemical property and a density of 7.93 g / cm³. 3 Melting point is 1400℃; mechanical properties: tensile strength is 1000MPa, yield strength is 205MPa, elongation is 40%;

[0051] Step 1.4, Section Creation: Select the section type for the component blank, homogeneous continuous shell, determine the section integral as "analysis", the thickness integral rule as Simpson, and the shell thickness value as 5mm;

[0052] Step 1.5, Section Assignment: Assign a section to the component blank, select the section-1 created in Step 1.4, select 'From Section' for the thickness, and define the shell offset as the mid-surface;

[0053] Step 1.6, Grid System Construction: (e.g.) Figure 3 As shown, global seeding is performed on four components: billet, mold, and left and right strong rotating wheels. The global approximate size is 2000mm. Seeding is performed on the edges. The meshing type is selected as tetrahedron, and the mesh size is accurate to 1mm. Finally, the meshing is completed.

[0054] Step 1.7, Component Assembly: (e.g.) Figure 4 As shown in the sketch, the blank, mold, and left and right strong spinning wheels are assembled. The upper bottom surface of the mold is in contact with the lower bottom surface of the blank. The axis of the strong spinning wheels is parallel to the side of the mold. The outer edge of the strong spinning wheels is 3mm away from the surface of the mold. The thickness of the blank is 2mm after strong spinning.

[0055] Step 2, the ABAQUS simulation and solution process, is implemented according to the following steps:

[0056] Step 2.1, Add Analysis Unit: Add an analysis unit of type 'Dynamic, Display', analysis unit increment type is automatic, stable increment step estimation is global, maximum time increment step is unlimited, mass scaling target is semi-automatic mass scaling, application area is the entire model, scaling is performed at the beginning of the analysis unit, scaling factor is 1e5, linear volume viscosity parameter is 0.06, and quadratic volume viscosity parameter is 1.2;

[0057] Step 2.2, Field Output Settings: Edit the field output options for the overall assembly model. The field output scope is the entire model, the frequency is a uniform time interval of 100, and the output includes stress, strain, displacement / velocity / acceleration, action / reaction force, contact, volume / thickness / coordinates.

[0058] Step 2.3, Interaction Settings: Add 'Surface-to-Surface Contact (Explicit)' interaction to the outer surface of the mold and the inner surface of the blank, and the outer surfaces of the left and right strong spinning wheels and the outer surface of the blank. Select 'Penalty Contact Mode' as the formula for all mechanical constraints, and the slip formula is finite slip.

[0059] Step 2.4, Add contact conditions: Add the 'Tangential Behavior' contact attribute, select the 'Penalty' friction formula, set the directionality to isotropic, and the friction coefficient to 0.01;

[0060] Step 2.5, add constraints: bind the blank and mold mating surfaces, discretize the surface as 'surface-to-surface', use the calculated default values ​​for positional tolerances, and bind rotational degrees of freedom (if applicable);

[0061] Step 2.6, Adding Boundary Conditions: Add loads to the four components: billet, mold, and left and right powerful spinning wheels. Add a 'velocity / angular velocity' boundary condition to the mold and billet as a whole, with a rotational angular velocity of 1.0 radians / time. Add 'velocity / angular velocity' boundary conditions to the left and right powerful spinning wheels and the billet separately, with a rotational angular velocity of -5.0 radians / time, opposite to the mold's rotation direction. The left and right powerful spinning wheels move downwards along the axial direction at a speed of 0.5. The method for creating local coordinate axes can be seen in Step 1.7. Figure 4 As shown.

[0062] Step 3, the ABAQUS simulation post-processing stage, is implemented according to the following steps: Create a job in the job module, with the job type being full analysis, the run mode being background, the ABAQUS / Explicit precision being 'both - only constraints', and the node variable output precision being full. Submit the job, and the results will be displayed in the visualization module. Plot a contour plot on the deformation graph, with the animation option being time history, to obtain the following... Figure 5 The results shown also include the following steps:

[0063] Step 3.1, Multi-field Coupling Analysis: Simultaneously analyze the stress field, strain field, and temperature field;

[0064] Step 3.2, Parameter sensitivity analysis: Evaluate the degree of influence of each process parameter on molding quality. The parameter sensitivity analysis adopts the analysis of variance (ANOVA) method to quantify the influence weight of each parameter on molding quality.

[0065] Step 3.3, Optimize parameter output: Output the optimal combination of process parameters.

[0066] During the simulated processing, such as Figure 5 As shown, the initial and final states of the process are as follows: Figure 6 , 7 As shown in the diagram. The visualization module displays a cloud map showing the completed processing state, as shown below. Figure 7 As shown, Mises stress is used to measure the strength of a material under three-dimensional stress. It can effectively predict the yield behavior of materials and is an important indicator for evaluating the plastic deformation and strength of materials; for example... Figure 8 As shown, the Max. In-Plane Principal stress display shows the distribution of the maximum principal stress in the plane, which can intuitively reflect the stress situation of the material in the plane and is of great significance for evaluating the tensile and compressive properties of the material; for example Figure 9 As shown, Tresca stress, based on the maximum shear stress theory, is suitable for evaluating the yield behavior of materials under low-speed and low-temperature conditions, and can intuitively reflect the distribution of the maximum shear stress in the material; such as Figure 10 As shown, the Pressure display shows the distribution of pressure, which can intuitively reflect the stress situation of the material under pressure, and is of great significance for evaluating the compressive strength of the material.

[0067] Analysis of the stress cloud diagrams from the finite element simulation results reveals that the maximum values ​​of Mises stress, Max. In-Plane Principal stress, Tresca stress, and Pressure stress at various locations within the model do not exceed the tensile strength of 304 stainless steel, which is 1000 MPa. This indicates that under the applied load conditions, all parts of the model remain within the material's elastic range, without plastic deformation or failure. Therefore, it can be concluded that the finite element simulation meets the allowable stress standard, and the safety and reliability of the model during design and manufacturing have been effectively verified.

[0068] Example 1: Simulation of Spin Forming of 304 Stainless Steel Rocket Engine Nozzle

[0069] 1. Model establishment and parameter settings: The axial angle between the billet and the mold is set to 20°, the axial angle between the mold's inclined side and the mold is set to 10°, the radius of the strength wheel is set to 80mm, and the billet thickness is set to 5mm.

[0070] The material used is 304 stainless steel, and the parameters are set as follows: density 7.93 g / cm³. 3 Tensile strength 1000MPa, yield strength 205MPa, elongation 40%, elastic modulus 193GPa, Poisson's ratio 0.29, coefficient of thermal expansion 17.2×10 -6 / ℃, thermal conductivity 16.2W / (m·K).

[0071] 2. Mesh generation: Adaptive meshing technology is adopted, with a global seed size of 2mm and local refinement to 0.5mm in key contact areas.

[0072] Mesh type: tetrahedral element.

[0073] 3. Contact condition settings: friction coefficient 0.01 (dynamic adjustment range 0.005-0.02), improved penalty function method for contact algorithm, contact stiffness scaling factor 0.1.

[0074] 4. Boundary conditions: mold rotation speed 1.0 radians / time, strength wheel rotation speed 5.0 radians / time (direction opposite to mold), strength wheel axial feed speed 0.5 mm / time.

[0075] 5. Simulation results analysis: The maximum Mises stress is 358 MPa (lower than the material yield strength), the maximum deformation is 2.3 mm, the maximum temperature rise is 85℃, and the calculation time is 8 hours (20% shorter than the traditional method).

[0076] Example 2: Verification of Process Parameter Optimization

[0077] 1. Parameter sensitivity analysis: A full factorial experimental design was used.

[0078] Parameters to be examined: mold rotation speed, strength wheel rotation speed, and friction coefficient.

[0079] Analysis indicators: molding quality, residual stress, and calculation efficiency.

[0080] 2. Optimal parameter combination: mold rotation speed 0.9 radians / time, strength wheel rotation speed 4.8 radians / time, friction coefficient 0.008.

[0081] 3. Optimization results: Molding quality improved by 15%, residual stress reduced by 12%, and calculation efficiency improved by 25%.

[0082] Example 3: Verification with different materials

[0083] 1. Applications of titanium alloy (Ti-6Al-4V)

[0084] Material parameter adjustment: density 4.43 g / cm³ 3 Its yield strength is 880 MPa and its thermal conductivity is 6.7 W / (m·K).

[0085] Process parameter optimization: mold rotation speed 1.1 radians / time, strength wheel rotation speed 5.2 radians / time.

[0086] Molding effect: Maximum Mises stress 820MPa, temperature rise 120℃.

[0087] 2. Applications of nickel-based superalloys (Inconel 718)

[0088] Material parameter adjustment: density 8.19 g / cm³ 3 Yield strength: 1030 MPa, thermal conductivity: 11.4 W / (m·K).

[0089] Process parameter optimization: mold rotation speed 0.8 radians / time, strength wheel rotation speed 4.5 radians / time.

[0090] Molding effect: Maximum Mises stress 980MPa, temperature rise 150℃.

[0091] This invention discloses a simulation method for manufacturing rocket engine nozzles using an ABAQUS-based integrated molding scheme for both inner and outer walls. This method effectively establishes the relationship between the nozzle's geometric parameters, material parameters, manufacturing process parameters, and nozzle performance. Through precise control and optimization of these parameters, the structural strength and overall performance of the nozzle can be significantly improved, thereby better meeting the stringent requirements of rocket engines in actual operation.

[0092] Specifically, this invention comprehensively analyzes the distribution of key physical quantities such as stress, strain, and displacement during the nozzle manufacturing process by performing detailed pre-simulation processing, simulation solving, and post-simulation processing in ABAQUS. These analytical results provide important theoretical basis for optimizing nozzle design and manufacturing processes, and contribute to further improving nozzle quality and reliability.

[0093] In addition, this invention also solves the problems of high cost and complex process in traditional manufacturing methods. Through simulation optimization, it reduces unnecessary experiments and errors, thereby reducing R&D costs and time costs.

[0094] Therefore, this invention is not only a new approach to obtaining optimized parameters, but also has important guiding significance for the selection of actual parameters, providing a more scientific and efficient method for the manufacture of rocket engine nozzles.

[0095] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0096] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A simulation method for manufacturing rocket engine nozzles using an ABAQUS-based integrated molding scheme for inner and outer walls, characterized in that, The specific steps are as follows: Step 1: Perform ABAQUS simulation preprocessing; Step 2: Perform ABAQUS simulation and solve the problem; Step 3: Perform ABAQUS simulation post-processing.

2. The simulation method for manufacturing rocket engine nozzles using an integrated inner and outer wall molding scheme based on ABAQUS according to claim 1, characterized in that, In step 1, the ABAQUS simulation preprocessing is performed as follows: Step 1.1, Model sketch drawing: Draw the sketch of the inner wall blank, forming tooling and strong rotating wheel. The angle between the blank and the mold axis is 20°, the angle between the mold hypotenuse and the axis is 10°, and the radius of the strong rotating wheel is 80mm. Step 1.2, 3D model creation: Create a 3D part including a blank, two spinning wheels and a mold. The blank thickness is 5mm. Determine the part type. Step 1.3, Material Property Definition: The material is 304 stainless steel, with a density of 7.93 g / cm³. 3 Melting point is 1400℃; mechanical properties: tensile strength is 1000MPa, yield strength is 205MPa, elongation is 40%; Step 1.4, Section Creation: Select the section type, and determine the section integration and integration rules; Step 1.5, Section Assignment: Assign section to the component blank; Step 1.6, Mesh System Construction: Global seeding is performed for the four components: billet, mold, and left and right strong spinning wheels. Seeding is also performed on the edges. The meshing type is selected, and finally the meshing is completed. Step 1.7, Component Assembly: Assemble the four components as shown in the sketch: blank, mold, and left and right strong spinning wheels. The outer edge of the strong spinning wheel is 3mm from the surface of the mold, and the thickness of the blank after strong spinning is 2mm.

3. The simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated inner and outer wall molding scheme, as described in claim 2, is characterized in that... In step 1.3, the material property definition also includes a strain hardening model, which uses the Johnson-Cook constitutive equation to describe the mechanical behavior of the material at high strain rates.

4. The simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated inner and outer wall molding scheme, as described in claim 1, is characterized in that... In step 2, the ABAQUS simulation solution process is performed as follows: Step 2.1, Adding an Analysis Unit: Add an analysis unit type, and set the analysis unit increment and quality scaling; Step 2.2, Field Output Settings: Edit the field output options for the overall assembly model to output field variables such as stress, strain, displacement / velocity / acceleration, action / reaction force, contact, volume / thickness / coordinates; Step 2.3, Interaction Settings: Add 'Surface-to-Surface Contact (Explicit)' interaction to the outer surface of the mold and the inner surface of the blank, and the outer surfaces of the left and right strong rotating wheels and the outer surface of the blank. Select 'Penalty Contact Method' as the formula for all mechanical constraints, and select the slip formula. Step 2.4, Adding contact conditions: Add the 'Tangential Behavior' contact attribute, select the 'Penalty' friction formula, set the directionality to isotropic, and set the friction coefficient; Step 2.5, Add constraint conditions: bind the blank to the mold mating surface; Step 2.6, Add boundary conditions: Add loads to the four components: billet, mold, and left and right strong spinning wheels. Select the load type and set the load coordinates.

5. The simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated inner and outer wall molding scheme, as described in claim 4, is characterized in that... In step 2.3, the improved penalty function contact algorithm includes dynamically adjusting the penalty stiffness based on the contact pressure to balance convergence and penetration.

6. The simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated inner and outer wall molding scheme, as described in claim 1, is characterized in that... In step 3, the ABAQUS simulation post-processing is performed as follows: a visual cloud map is obtained through job analysis, and the cloud map is adjusted for intensity analysis.

7. The simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated inner and outer wall molding scheme, as described in claim 1, is characterized in that... Step 3 includes: Step 3.1, Multi-field Coupling Analysis: Simultaneously analyze the stress field, strain field, and temperature field; Step 3.2, Parameter Sensitivity Analysis: Evaluate the degree of influence of each process parameter on molding quality; Step 3.3, Optimize parameter output: Output the optimal combination of process parameters.

8. The simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated inner and outer wall molding scheme, as described in claim 7, is characterized in that... In step 3.2, the parameter sensitivity analysis uses analysis of variance (ANOVA) to quantify the influence weight of each parameter on the molding quality.

9. The simulation method for manufacturing rocket engine nozzles based on ABAQUS using an integrated inner and outer wall molding scheme, as described in claim 1, is characterized in that... The simulation method is applicable to the spin forming simulation of other high-strength metallic materials, including titanium alloys and nickel-based superalloys.

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