A design method and system of a propeller shaft spline relief groove simulation piece

Abstract

The application discloses a design method and system of a propeller shaft spline tool withdrawal groove simulation piece, and relates to the technical field of aero-engine testing. The method comprises the following steps: obtaining the dangerous point position of an actual propeller shaft spline tool withdrawal groove, thereby initially constructing a simulation piece, obtaining the size parameter of the simulation piece, and applying high and low cycle loads to the simulation piece to obtain corresponding stress tensors; the Mises stress of the dangerous point position of the simulation piece is calculated through an equivalent Mises stress formula; the size parameter and the Mises stress gradient expression are input into an optimization platform together with the Mises stress gradient expression of the dangerous point of the actual propeller shaft spline tool withdrawal groove; the first size parameter is optimized through an optimization algorithm, and an optimized propeller shaft spline tool withdrawal groove simulation piece is generated, so that the accuracy of the generated propeller shaft spline tool withdrawal groove simulation piece is ensured, and the generation efficiency is improved.

Description

Technical Field

[0001] This invention relates to the field of aero-engine testing technology, and in particular to a design method and system for a propeller shaft spline relief groove simulation component. Background Technology

[0002] As a critical component for transmitting torque and bearing complex loads, the structural integrity of the aero-engine propeller shaft directly affects the safety of the engine and even the entire aircraft. In actual operation, the propeller shaft not only bears high-cycle fatigue loads from the turbine shaft and propeller, but also low-cycle fatigue loads caused by starting, stopping, and maneuvering flight conditions. Through numerous tests and simulations, it has been verified that the spline relief groove on the propeller shaft, due to its abrupt geometric changes, is prone to significant stress concentration, becoming a common source of combined high- and low-cycle fatigue failure. Therefore, accurate fatigue performance assessment and life prediction for this area are crucial. To effectively evaluate material properties, manufacturing quality, and design reliability during the R&D phase, and to reduce the high costs associated with full-scale testing, it is typically necessary to design and manufacture simulants capable of simulating the stress states of critical areas in real components for bench testing.

[0003] Existing designs for aero-engine propeller shaft simulators have significant limitations, failing to accurately reflect the fatigue characteristics of real propeller shaft components and support reliable life prediction. The core issues are twofold: firstly, most simulator designs cannot fully replicate the complex boundary conditions and service load spectrum of a real propeller shaft in an engine; secondly, the design process relies on empirically simplified models and repeated trial and error, resulting in low efficiency. For example, to reconcile geometric similarity and stress field equivalence, it is often necessary to manually adjust the simulator structure multiple times, leading to a lack of sufficient experimental verification for the life prediction model.

[0004] To address the aforementioned challenges, improving the efficiency and accuracy of the design of propeller shaft spline relief groove simulators is a technical problem that urgently needs to be solved in this field. Summary of the Invention

[0005] To address the aforementioned technical problems, the purpose of this application is to provide a design method and system for a propeller shaft spline relief groove simulation component, which improves the efficiency and accuracy of the design of the propeller shaft spline relief groove simulation component and makes the stress gradient distribution of the designed propeller shaft spline relief groove simulation component more similar to that of the real propeller shaft.

[0006] To achieve the above objectives, this application provides a design method and system for a propeller shaft spline relief groove simulation component.

[0007] The above-mentioned objective of this application is achieved through the following technical solution: A design method for a propeller shaft spline relief groove simulation component includes: The location of the dangerous point in the actual propeller shaft spline relief groove is obtained, and the feature vector is obtained through feature extraction. Based on the aforementioned feature vectors and simulation design criteria, a preliminary simulation of the propeller shaft spline tool retraction was constructed, and the first dimensional parameters of the critical point location of the simulation were obtained. Based on the propeller spline retraction simulation component, the corresponding stress tensor is obtained by applying corresponding high and low cycle loads respectively. The stress tensor is used to calculate the Mises stress at the critical point of the propeller spline retraction simulation part using the equivalent Mises stress formula, and the Mises stress gradient is obtained by gradient normalization. After inputting the first size parameter, the Mises stress gradient representation, and the Mises stress gradient representation of the actual propeller shaft spline relief groove dangerous point into the optimization platform, the first size parameter is optimized by the optimization algorithm to obtain the optimized second size parameter; Based on the second dimensional parameter, the initially constructed propeller shaft spline relief groove simulation part is modified to generate an optimized propeller shaft spline relief groove simulation part.

[0008] Preferably, the location of the critical point of the actual propeller shaft spline relief groove is obtained, and a feature vector is obtained through feature extraction, including: The material parameters of the propeller shaft spline relief groove are obtained, and the stress distribution parameters of the propeller shaft spline relief groove are obtained by performing finite element simulation analysis in a three-dimensional model. Based on the stress distribution parameters of the propeller shaft spline relief groove, the location of the critical point of the propeller shaft spline relief groove is determined by stress calculation; The feature vector of the danger point location is obtained by extracting features from the location of the danger point.

[0009] Preferably, the design criteria for the simulated component include: The principles of geometric similarity, load equivalence, and stress gradient equivalence.

[0010] Preferably, the dimensional parameters include: Notch depth, tilt angle, and fillet radius.

[0011] Preferably, the stress tensor includes: The normal stress tensor and shear stress tensor under low-cycle loading; The normal stress tensor and shear stress tensor under high cycle load.

[0012] Preferably, the equivalent Mises stress formula is as follows: ; Where, σ e Equivalent Mises stress; S 11 S 22and S 33 These are the normal stress tensors along the X-axis, Y-axis, and Z-axis, respectively. S 12 S 13 and S 23 These are the shear stress tensors perpendicular to the X-axis and parallel to the Y-axis, perpendicular to the X-axis and parallel to the Z-axis, and perpendicular to the Y-axis and parallel to the Z-axis, respectively.

[0013] Preferably, the optimization platform is the iSight optimization platform.

[0014] Preferably, the optimization algorithm includes: Sequential quadratic programming and / or multi-island genetic algorithm.

[0015] Preferably, the first dimension parameter is optimized using an optimization algorithm to obtain the optimized second dimension parameter, specifically as follows: After optimizing the first dimension parameter using an optimization algorithm, the fitting error between the re-obtained Mises stress gradient representation and the stress gradient representation at the critical point of the actual propeller shaft spline relief groove is within a preset range, and finally the optimized second dimension parameter is obtained.

[0016] A design system for a propeller shaft spline relief groove simulation component includes: The feature extraction module is used to obtain the location of the dangerous point of the actual propeller shaft spline relief groove, and obtain the feature vector through feature extraction; The parameter acquisition module is used to initially construct a propeller shaft spline retraction simulation component based on the feature vector and the simulation component design criteria, and to obtain the first dimensional parameters of the critical point location of the propeller shaft spline retraction simulation component. The stress tensor acquisition module is used to obtain the corresponding stress tensor based on the propeller shaft spline retraction simulation component by applying corresponding high and low cycle loads respectively. The gradient representation module is used to calculate the Mises stress at the critical point location of the propeller spline retraction simulation part based on the stress tensor using the equivalent Mises stress formula, and obtain the Mises stress gradient representation through gradient normalization. The optimization module is used to input the first size parameter, the Mises stress gradient representation and the Mises stress gradient representation of the actual propeller shaft spline relief groove dangerous point position into the optimization platform, and then optimize the first size parameter through the optimization algorithm to obtain the optimized second size parameter; The modification module is used to modify the initially constructed propeller shaft spline relief groove simulation part according to the second dimension parameter, and generate an optimized propeller shaft spline relief groove simulation part.

[0017] This application first extracts the feature vectors of the actual critical points of the propeller shaft through simulation analysis, thereby establishing a preliminary propeller shaft simulation component. Then, based on the stress tensor in the obtained feature vectors, the stress gradient representation of the propeller shaft simulation component calculated by the equivalent stress formula is input into an optimization platform along with the actual propeller shaft stress gradient. The optimization platform continuously modifies the generated stress gradient representation of the propeller shaft simulation component, and the platform enables the modification of the dimensional parameters of the propeller shaft simulation component and the testing of the results, thereby obtaining the final dimensional parameters of the propeller shaft simulation component. This ensures accuracy while improving the generation efficiency of the propeller shaft simulation component. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a flowchart illustrating the design method of a propeller shaft spline relief groove simulation component according to an embodiment of this application. Figure 2 This is a structural diagram of a design system for a propeller shaft spline relief groove simulation component in an embodiment of this application. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0021] Furthermore, the technical features in the various embodiments or individual embodiments provided in this application can be arbitrarily combined with each other to form a feasible technical solution. Such combination is not constrained by the order of steps and / or the structural composition mode, but must be based on the ability of those skilled in the art to implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0022] In the embodiments provided in this application, it should be understood that the disclosed methods and systems can be implemented in other ways. The system embodiments described below are merely illustrative. For example, the division of units and modules is only a logical functional division, and in actual implementation, there may be other division methods, such as: multiple units or modules can be combined, or integrated into another system, or some features can be ignored or not executed. In addition, the coupling or direct coupling communication connection between the various components shown or discussed can be through some interfaces, indirect coupling or communication connection of devices or modules, and can be electrical, mechanical or other forms.

[0023] In addition, each functional unit in the various embodiments of this application can be integrated into a single processor, or each unit can be a separate device, or two or more units can be integrated into a single device; each functional unit in the various embodiments of this application can be implemented in hardware or in the form of hardware plus software functional units.

[0024] Those skilled in the art will understand that all or part of the steps of the following method embodiments can be implemented by program instructions and related hardware. The aforementioned program instructions can be stored in a computer-readable storage medium. When the program instructions are executed, they perform the steps of the following method embodiments. The aforementioned storage medium includes various media capable of storing program code, such as mobile storage devices, read-only memory (ROM), magnetic disks, or optical disks.

[0025] It should be understood that the use of terms such as "system," "device," "unit," and / or "module" in this application is merely one method of distinguishing different components, elements, parts, sections, or assemblies at different levels. However, if other terms can achieve the same purpose, they may be replaced by other expressions.

[0026] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "a plurality of" or "several" means two or more, unless otherwise explicitly specified.

[0027] It should be noted that the structures, proportions, sizes, etc., shown in the accompanying drawings of this specification are only for the purpose of assisting those skilled in the art in understanding and reading the content disclosed in the specification, and are not intended to limit the conditions under which this application can be implemented. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in the proportions, or adjustments to the size should still fall within the scope of the technical content disclosed in this application, provided that they do not affect the effects and purposes that this application can produce.

[0028] If a flowchart is used in this application, it is used to illustrate the operations performed by the system according to embodiments of this application. It should be understood that the preceding or following operations are not necessarily performed in exact order. Instead, the steps can be processed in reverse order or simultaneously. Furthermore, other operations can be added to these processes, or one or more steps can be removed from them.

[0029] It should also be noted that, in this document, terms such as "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that an article or device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such an article or device. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the article or device that includes the aforementioned element.

[0030] The implementation method of this application is written in a progressive manner.

[0031] like Figure 1 As shown, a design method for a propeller shaft spline relief groove simulation component includes: Step S1: Obtain the location of the dangerous point of the actual propeller shaft spline relief groove, and obtain the feature vector through feature extraction; Step S2: Based on the feature vector and the design criteria of the simulation part, a propeller shaft spline retraction simulation part is initially constructed to obtain the first dimensional parameters of the dangerous point location of the propeller shaft spline retraction simulation part; Specifically, based on the design criteria of the simulation component and the extracted feature vectors, the construction of the propeller shaft spline retraction simulation component was initially completed. This included designing a thin-walled circular tube structure based on the actual propeller shaft spline retraction component. The dimensions of the clamping section and transition section must meet the thin-walled circular tube dimensions of the tensile and torsion test standards. The notch was initially designed as an asymmetric V-shaped annular groove based on the geometric characteristics of the spline retraction groove. The left side was relatively gentle with a larger rounded corner, while the right side was relatively steep with a smaller rounded corner.

[0032] Step S3: Based on the propeller shaft spline retraction simulation part, obtain the corresponding stress tensor by applying the corresponding high and low cycle loads respectively; Specifically, the high-cycle load of the propeller shaft is taken as the axial load, and the low-cycle load is taken as the shear load. In the simulation calculation, the load is applied in steps to obtain the stress tensor applied in each step, and each tensor is a vector in the same direction.

[0033] Step S4: Calculate the Mises stress at the critical point of the propeller shaft spline retraction simulation part using the equivalent Mises stress formula, and obtain the Mises stress gradient representation by gradient normalization. Since the load size is not considered for optimization during the iSight calculation, because the load size does not affect the stress gradient, all subsequent stress gradient values ​​are divided by the maximum Mises stress of the load calculated based on the stress value of the load with the maximum Mises stress, and normalized with the maximum Mises stress as 1 as the benchmark.

[0034] The Mises stress gradient representation is obtained by normalizing the calculated results through gradient normalization.

[0035] Step S5: Input the first dimension parameter, the Mises stress gradient representation and the Mises stress gradient representation of the actual propeller shaft spline relief groove dangerous point into the optimization platform, and then optimize the first dimension parameter through the optimization algorithm to obtain the optimized second dimension parameter; Specifically, after inputting the first size parameter, the Mises stress gradient representation, and the stress gradient representation of the actual propeller shaft spline relief groove critical point into the optimization platform, the Mises stress gradient representation is first used as input, the applied load is high cycle for tension and compression and low cycle for torsion, and the same gradient normalization process as in step S4 is performed. Then, the goodness of fit (i.e., similarity, which can be calculated by using an algorithm) between the normalized Mises stress gradient representation and the normalized Mises stress gradient representation of the actual propeller shaft spline relief groove critical point is calculated to obtain the calculated goodness of fit result. An optimization platform is built based on the calculated goodness-of-fit results and other data. When the goodness-of-fit result is lower than a preset value, the first size parameter is optimized using an optimization algorithm. The stress tensor is then recalculated through the optimization platform. Based on the equivalent Mises stress formula, the optimized Mises stress gradient representation is finally obtained. The goodness-of-fit of the optimized Mises stress gradient representation is compared with the Mises stress gradient representation of the critical point of the propeller shaft spline relief groove. The above optimization process is repeated until the final goodness-of-fit is lower than a preset threshold (the threshold can be set to ±5%). At this point, the optimization of the first size parameter is stopped, and the second size parameter is obtained.

[0036] Step S6: Modify the initially constructed propeller shaft spline relief groove simulation part according to the second dimension parameters to generate the optimized propeller shaft spline relief groove simulation part.

[0037] Specifically, based on the obtained second dimension parameters, the dimension parameters of the propeller spline retraction simulation component constructed in step S2 are modified to obtain the final propeller spline retraction simulation component.

[0038] In some embodiments, the location of the critical point of the actual propeller shaft spline relief groove is obtained, and a feature vector is obtained through feature extraction, including: The material parameters of the propeller shaft spline relief groove are obtained, and the stress distribution parameters of the propeller shaft spline relief groove are obtained by performing finite element simulation analysis in a three-dimensional model. Based on the stress distribution parameters of the propeller shaft spline relief groove, the location of the critical point of the propeller shaft spline relief groove is determined by stress calculation; By extracting features from the locations of the dangerous points, feature vectors for the locations of the dangerous points are obtained.

[0039] Specifically, the material parameters of the spline relief groove of the aero-engine propeller shaft are obtained and imported into a three-dimensional model. Based on the high and low cycle combined fatigue loads that the propeller shaft spline relief groove is subjected to under actual working conditions, the propeller shaft is simulated and analyzed using Abaqus simulation software. The stress distribution of the propeller shaft spline relief groove is obtained through analysis. By applying the maximum value of the Mises stress of the propeller shaft under high and low cycle loads, the location of the critical point of the propeller shaft spline relief groove is determined. Feature extraction is performed on the location of the danger point to obtain the feature vector of the danger point location. The feature vector includes the geometric features and dimensional parameters of the propeller shaft spline relief groove.

[0040] Simulation analysis was used to determine the location of the critical point of the spline relief groove in the actual aero-engine propeller shaft, laying a data foundation for the initial generation of the subsequent propeller shaft simulation component.

[0041] In some embodiments, the design guidelines for the simulation component include: The principles of geometric similarity, load equivalence, and stress gradient equivalence.

[0042] In some embodiments, the dimensional parameters include: Notch depth, tilt angle, and fillet radius.

[0043] In some embodiments, the stress tensor includes: The normal stress tensor and shear stress tensor under low-cycle loading; The normal stress tensor and shear stress tensor under high cycle load.

[0044] In some embodiments, the equivalent Mises stress formula is specifically: ; Where, σ e Equivalent Mises stress; S11 S 22 and S 33 These are the normal stress tensors along the X-axis, Y-axis, and Z-axis, respectively. S 12 S 13 and S 23 These are the shear stress tensors perpendicular to the X-axis and parallel to the Y-axis, perpendicular to the X-axis and parallel to the Z-axis, and perpendicular to the Y-axis and parallel to the Z-axis, respectively.

[0045] In other embodiments, the platform is optimized, specifically the iSight optimized platform.

[0046] In other embodiments, the optimization algorithm includes: Sequential quadratic programming and / or multi-island genetic algorithm.

[0047] In some embodiments, the first dimension parameter is optimized using an optimization algorithm to obtain the optimized second dimension parameter, specifically as follows: After optimizing the first dimension parameter using an optimization algorithm, the fitting error between the newly obtained Mises stress gradient representation and the stress gradient representation at the critical point of the actual propeller shaft spline relief groove is within a preset range, and finally the optimized second dimension parameter is obtained.

[0048] By ensuring that the fitting error between the two is below a preset range, the dimensional parameters of the propeller shaft simulation part are more consistent with the actual propeller shaft spline relief groove, thereby improving the accuracy of the design.

[0049] like Figure 2 As shown, a design system for a propeller shaft spline relief groove simulation component includes: The feature extraction module 101 is used to obtain the location of the dangerous point of the actual propeller shaft spline relief groove and obtain the feature vector through feature extraction. The parameter acquisition module 102 is used to initially construct a propeller shaft spline tool retraction simulation part based on the feature vector and the simulation part design criteria, thereby obtaining the first dimensional parameters of the critical point location of the propeller shaft spline tool retraction simulation part. The stress tensor acquisition module 103 is used to obtain the corresponding stress tensor based on the propeller shaft spline retraction simulation part by applying corresponding high and low cycle loads respectively. The gradient representation module 104 is used to calculate the Mises stress at the critical point of the propeller spline retraction simulation part based on the stress tensor and the equivalent Mises stress formula, and obtain the Mises stress gradient representation through gradient normalization. The optimization module 105 is used to input the first dimension parameter, the Mises stress gradient representation and the Mises stress gradient representation of the actual propeller shaft spline relief groove dangerous point position into the optimization platform, and then optimize the first dimension parameter through the optimization algorithm to obtain the optimized second dimension parameter; Modification module 106 is used to modify the initially constructed propeller shaft spline relief groove simulation part according to the second dimension parameters, and generate an optimized propeller shaft spline relief groove simulation part.

[0050] This application first extracts the feature vectors of the actual critical points of the propeller shaft through simulation analysis, thereby establishing a preliminary propeller shaft simulation component. Then, based on the stress tensor in the obtained feature vectors, the stress gradient representation of the propeller shaft simulation component calculated by the equivalent stress formula is input into an optimization platform along with the actual propeller shaft stress gradient. The optimization platform continuously modifies the generated stress gradient representation of the propeller shaft simulation component, and the platform enables the modification of the dimensional parameters of the propeller shaft simulation component and the testing of the results, thereby obtaining the final dimensional parameters of the propeller shaft simulation component. This approach improves the generation efficiency of the propeller shaft simulation component while ensuring accuracy.

[0051] The sequence numbers of the embodiments in this application are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0052] In the above embodiments of this application, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0053] The above description of the disclosed embodiments enables those skilled in the art to make or use this application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this application. Therefore, this application is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A design method for a propeller shaft spline relief groove simulation component, characterized in that, include: The location of the critical point of the actual propeller shaft spline relief groove is obtained, and features are extracted. The vector, wherein the feature vector includes: the geometric features and dimensional parameters of the propeller shaft spline relief groove; the dimensional parameters include: notch depth, tilt angle and fillet radius; Based on the eigenvectors and the design criteria for the simulated component, a simulated component of the propeller shaft spline relief groove is initially constructed, and the first dimensional parameters of the critical point location of the simulated component of the propeller shaft spline relief groove are obtained. The design criteria for the simulated component include: geometric similarity principle, load equivalence principle and stress gradient equivalence principle. Based on the propeller shaft spline relief groove simulation component, the corresponding stress tensor is obtained by applying high and low cyclic loads respectively. The stress tensor is used to calculate the Mises stress at the critical point of the propeller shaft spline relief groove simulation part using the equivalent Mises stress formula, and the Mises stress gradient is obtained by gradient normalization. After inputting the first size parameter, the Mises stress gradient representation, and the Mises stress gradient representation of the actual propeller shaft spline relief groove dangerous point into the optimization platform, the first size parameter is optimized by the optimization algorithm to obtain the optimized second size parameter; Based on the second dimensional parameter, the initially constructed propeller shaft spline relief groove simulation part is modified to generate an optimized propeller shaft spline relief groove simulation part.

2. The design method for the propeller shaft spline relief groove simulation component according to claim 1, characterized in that, The location of the critical point in the actual propeller shaft spline relief groove is obtained, and the feature vector is obtained through feature extraction, including: The material parameters of the propeller shaft spline relief groove are obtained, and the stress distribution parameters of the propeller shaft spline relief groove are obtained by performing finite element simulation analysis in a three-dimensional model. Based on the stress distribution parameters of the propeller shaft spline relief groove, the location of the critical point of the propeller shaft spline relief groove is determined by stress calculation; The feature vector of the danger point location is obtained by extracting features from the location of the danger point.

3. The design method for the propeller shaft spline relief groove simulation component according to claim 1, characterized in that, The stress tensor includes: The normal stress tensor and shear stress tensor under low-cycle loading; The normal stress tensor and shear stress tensor under high cycle load.

4. The design method for the propeller shaft spline relief groove simulation component according to claim 1, characterized in that, The equivalent Mises stress formula is as follows: ； Where, σ e Equivalent Mises stress; S 11 S 22 and S 33 These are the normal stress tensors along the X-axis, Y-axis, and Z-axis, respectively. S 12 S 13 and S 23 These are the shear stress tensors perpendicular to the X-axis and parallel to the Y-axis, perpendicular to the X-axis and parallel to the Z-axis, and perpendicular to the Y-axis and parallel to the Z-axis, respectively.

5. The design method for the propeller shaft spline relief groove simulation component according to claim 1, characterized in that, The optimization platform is specifically the iSight optimization platform.

6. The design method for the propeller shaft spline relief groove simulation component according to claim 1, characterized in that, The optimization algorithm includes: Sequential quadratic programming and / or multi-island genetic algorithm.

7. The design method for the propeller shaft spline relief groove simulation component according to claim 1, characterized in that, The first dimension parameter is optimized using an optimization algorithm to obtain the optimized second dimension parameter, specifically: After optimizing the first dimension parameter using an optimization algorithm, the fitting error between the re-obtained Mises stress gradient representation and the stress gradient representation at the critical point of the actual propeller shaft spline relief groove is within a preset range, and finally the optimized second dimension parameter is obtained.

8. A design system for a propeller shaft spline relief groove simulation component, characterized in that, include: The feature extraction module is used to obtain the location of the critical point of the actual propeller shaft spline relief groove, and to obtain features through feature extraction. The vector, wherein the feature vector includes: the geometric features and dimensional parameters of the propeller shaft spline relief groove; the dimensional parameters include: notch depth, tilt angle and fillet radius; The parameter acquisition module is used to initially construct a propeller shaft spline retraction simulation part based on the feature vector and the simulation part design criteria, and obtain the first dimensional parameters of the critical point location of the propeller shaft spline retraction simulation part, wherein: the simulation part design criteria include: geometric similarity principle, load equivalence principle and stress gradient equivalence principle; The stress tensor acquisition module is used to obtain the corresponding stress tensor based on the propeller shaft spline retraction simulation component by applying corresponding high and low cycle loads respectively. The gradient representation module is used to calculate the Mises stress at the critical point location of the propeller spline retraction simulation part based on the stress tensor using the equivalent Mises stress formula, and obtain the Mises stress gradient representation through gradient normalization. The optimization module is used to input the first size parameter, the Mises stress gradient representation and the Mises stress gradient representation of the actual propeller shaft spline relief groove dangerous point position into the optimization platform, and then optimize the first size parameter through the optimization algorithm to obtain the optimized second size parameter; The modification module is used to modify the initially constructed propeller shaft spline relief groove simulation part according to the second dimension parameter, and generate an optimized propeller shaft spline relief groove simulation part.

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