Damping Ring Vibration Reduction Design Method for Aeronautical Gears, Electronic Equipment and Storage Medium

Abstract

The present application discloses a damping ring vibration reduction design method, an electronic device and a storage medium for aviation gears. The method includes the steps of: S1. obtaining the resonance speed point of the gear through modal analysis of the gear; S2. calculating and simulating the true vibration stress σ1 of the gear web in the state without the damping ring installed for the resonance speed point; S3. identifying the dangerous vibration mode according to the allowable stress value σ0 of the gear material; S4. preliminarily designing the damping ring for the dangerous vibration mode; S5. calculating the true vibration stress σ2 in the state with the damping ring installed according to the equivalent damping ratio of the damping ring; S6. evaluating the applicability and vibration reduction effect of the damping ring according to the allowable stress value σ0 and the true vibration stress σ2 in the state with the damping ring installed. If σ2 meets the design requirements, the design is completed. Otherwise, steps S4 to S6 are repeated until the damping ring meets the design requirements. The present application meets the design cycle requirements and the forward design requirements of the engine.

Description

Technical Field

[0001] This application relates to the technical field of damping rings, and in particular, to a vibration damping design method, device, and storage medium for damping rings used in aviation gears. Background Technique

[0002] Aviation engine gears often have multiple resonance speeds within the operating speed range. It is almost impossible to optimize the gear structure to adjust all resonance points outside the operating speed range. Therefore, new vibration damping means need to be adopted, such as adding a damping ring to the gear for vibration damping.

[0003] In the prior art, when designing a damping ring, a damping ring is initially designed, and then a dynamic stress test is carried out to verify the vibration damping effect, and iteration is performed to obtain the final damping ring. It cannot be evaluated during the design stage. This method is time-consuming and costly, and it is difficult to meet the design cycle requirements and forward design requirements of the engine. Summary of the Invention

[0004] This application provides a vibration damping design method for a damping ring used in an aviation gear on the one hand, so as to solve the technical problems that the existing damping ring design method cannot be evaluated during the design stage, is time-consuming, costly, and difficult to meet the design cycle requirements and forward design requirements of the engine.

[0005] A vibration damping design method for a damping ring used in an aviation gear includes the steps of:

[0006] S1. Obtain the resonance speed points of the gear by performing modal analysis on the gear;

[0007] S2. Calculate and simulate the true vibration stress σ of the gear web in the state without installing the damping ring for the resonance speed points 1 ;

[0008] S3. Identify the dangerous vibration modes according to the allowable stress value σ of the gear material 0 , and the dangerous vibration mode is the vibration type corresponding to when σ 1 ≥σ 0 ;

[0009] S4. For the dangerous vibration mode, initially design a damping ring for vibration damping;

[0010] S5. Calculate the true vibration stress σ of the state with the damping ring according to the equivalent damping ratio of the initially designed damping ring 2 ;

[0011] S6. Evaluate the applicability and vibration damping effect of the initially designed damping ring according to the allowable stress value σ of the gear material 0 , the true vibration stress σ of the state with the damping ring 2 . If σ 2If the design requirements are met, the design is completed; otherwise, steps S4 to S6 are repeated until the damping ring meets the design requirements.

[0012] Further, the specific steps of step S2 include:

[0013] S21. According to the gear modal analysis results, extract the modal parameters of the reference points in the gear web, including the modal displacement A modal and the modal stress σ modal , where the reference point is the point with the maximum modal stress σ modal in each order of mode;

[0014] S22. Import the web in the gear finite element calculation model into the dynamics simulation software, and construct a rigid-flexible coupling dynamics model in the dynamic stress software with the gear tooth ring and the gear shaft as rigid models and the gear web as a flexible model. Then, use the dynamics simulation software to obtain the modal participation factors, where the modal participation factors represent the contribution of each order of mode to the response;

[0015] S23. Use the dynamics simulation software to obtain the vibration displacement output response at different resonance speeds, and then calculate the true vibration amplitude A in different modes according to the modal participation factors;

[0016] S24. Based on the mapping relationship between the true vibration stress σ 1 , the true vibration amplitude A, and the modal stress σ modal , and the modal displacement A modal in the state without installing the damping ring:

[0017]

[0018] Calculate the true vibration stress σ 1 of the gear in the state without installing the damping ring.

[0019] Further, the specific steps of step S5 include:

[0020] S51. Calculate the equivalent damping ratio of the preliminarily designed damping ring;

[0021] S52. Calculate the true vibration stress σ 2 in the state with the damping ring according to the equivalent damping ratio.

[0022] Further, the specific steps of S51 include:

[0023] S511. Calculate the energy ΔW consumed by the damping ring within one vibration cycle of the gear and the true vibration energy W of the gear respectively;

[0024] S512. Calculate the equivalent damping ratio of the preliminarily designed damping ring based on the energy ΔW consumed by the damping ring within one vibration cycle of the gear and the true vibration energy W of the gear:

[0025]

[0026] Further, the step S511 specifically includes the following steps:

[0027] S5111. During the axial vibration process, according to the inconsistency of the relative motion speed between the gear and the damping ring, integrate and solve the relative displacement caused by the speed inconsistency within one vibration cycle to calculate the axial vibration friction energy consumption.

[0028] S5112. During the radial vibration process, according to the inconsistency of the deformation amount of the joint surface between the gear and the damping ring, integrate and solve the relative displacement caused by the deformation inconsistency within one vibration cycle to calculate the radial vibration friction energy consumption.

[0029] S5113. Sum up the axial vibration friction energy consumption and the radial vibration friction energy consumption to solve the total friction energy consumption of the damping ring in two directions, and obtain the energy ΔW consumed by the damping ring within one vibration cycle of the gear.

[0030] Further, the step S511 specifically includes the following steps:

[0031] S5111. Use finite element calculation software to calculate the modal vibration stress σ at the location with the maximum stress of the gear modal , the modal vibration amplitude A at the damping ring installation groove modal , and the modal vibration energy W of the entire gear modal ;

[0032] S5112. According to the proportional relationship among σ modal , A modal , W modal , and the true vibration amplitude A under the corresponding mode, obtain the true vibration energy W of the gear:

[0033]

[0034] Further, in the step S52, the true vibration stress σ in the state with the damping ring 2 is calculated by the following formula:

[0035]

[0036] Among them, 0.08% represents the structural damping ratio of the gear itself without the damping ring, which is obtained from the results of the dynamic stress measurement test.

[0037] Further, in the step S6, the meeting the design requirements specifically means that the following two conditions must be met:

[0038] Condition 1: σ 2 ≤σ 0 ;

[0039] Condition 2: The equivalent damping ratio within the range of σ 2 ±20Mp is above 0.2%.

[0040] On the other hand, the present application also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the steps of the damping ring vibration reduction design method for aviation gears are implemented.

[0041] On the other hand, the present application also provides a storage medium. The storage medium includes a stored program. When the program runs, it controls the device where the storage medium is located to execute the steps of the damping ring vibration reduction design method for aviation gears.

[0042] Compared with the prior art, the present application has the following beneficial effects:

[0043] The present application realizes the identification of dangerous vibration modes through modal analysis and calculation, so as to evaluate whether it is necessary to adopt a damping ring for vibration reduction. At the same time, after the damping ring is preliminarily designed for the dangerous vibration mode, the true vibration stress in the state with the damping ring can be calculated by using the equivalent damping ratio of the preliminarily designed damping ring, so that the gear vibration stress can be calculated accordingly at the design stage, and the applicability and vibration reduction effect of the preliminarily designed damping ring can be evaluated. It is not necessary to complete the optimization design of the damping ring by iterating according to the vibration reduction effect of actual tests as in the prior art, thereby reducing the time and cost of the optimization design of the damping ring, and meeting the design cycle requirements and forward design requirements of the engine.

[0044] In addition to the purposes, features, and advantages described above, the present application has other purposes, features, and advantages. The following will refer to the accompanying drawings for a further detailed description of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] The accompanying drawings constituting a part of the present application are used to provide a further understanding of the present application. The schematic embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation to the present application. In the drawings:

[0046] Figure 1 is a schematic flow chart of the damping ring vibration reduction design method for aviation gears in a preferred embodiment of the present application;

[0047] Figure 2 is a schematic block diagram of the entity of the electronic device in a preferred embodiment of the present application;

[0048] Figure 3 is the internal structure diagram of the computer device of the preferred embodiment of the present application; Detailed implementation manners

[0049] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments may be combined with each other. The present application will be described in detail below with reference to the drawings and in conjunction with the embodiments.

[0050] Refer to Figure 1 , the preferred embodiment of the present application provides a damping ring vibration reduction design method for an aviation gear, including the steps of:

[0051] S1. Obtain the resonance speed point of the gear by performing modal analysis on the gear;

[0052] S2. Calculate and simulate the true vibration stress σ of the gear web in the state without installing the damping ring for the resonance speed point 1 ;

[0053] S3. Identify the dangerous vibration mode according to the allowable stress value σ of the gear material 0 , and the dangerous vibration mode is the vibration type corresponding to when σ 1 ≥σ 0 ;

[0054] S4. For the dangerous vibration mode, preliminarily design a damping ring for vibration reduction;

[0055] S5. Calculate the true vibration stress σ in the state with the damping ring according to the equivalent damping ratio of the preliminarily designed damping ring 2 ;

[0056] S6. Evaluate the applicability and vibration reduction effect of the preliminarily designed damping ring according to the allowable stress value σ of the gear material 0 , the true vibration stress σ in the state with the damping ring 2 . If σ 2 meets the design requirements, the design is completed; otherwise, repeat steps S4 to S6 until the damping ring meets the design requirements.

[0057] In this embodiment, the identification of dangerous vibration modes is achieved through modal analysis and calculation, so as to evaluate whether it is necessary to adopt a damping ring for vibration reduction. At the same time, after the damping ring is preliminarily designed for the dangerous vibration mode, the equivalent damping ratio of the preliminarily designed damping ring can be used to calculate the true vibration stress in the state with the damping ring, so that the gear vibration stress can be calculated accordingly at the design stage, evaluate the applicability and vibration reduction effect of the preliminarily designed damping ring, and start to optimize the structural parameters of the damping ring, without the need to iteratively complete the optimized design of the damping ring according to the actual test of the vibration reduction effect as in the prior art, thus reducing the time and cost of the optimized design of the damping ring, meeting the design cycle requirements and forward design requirements of the engine.

[0058] In a preferred embodiment of the present application, the step S2 specifically includes the steps:

[0059] S21. According to the gear modal analysis results, extract the modal parameters of the reference points in the gear web, including the modal displacement A modal and the modal stress σ modal , and the reference point is the point with the maximum modal stress σ modal in each order of mode;

[0060] S22. Import the web of the gear finite element calculation model into the dynamic simulation software, and construct a rigid-flexible coupling dynamic model in the dynamic stress software with the gear tooth ring and the gear shaft as rigid models and the gear web as a flexible model. Then, use the dynamic simulation software to obtain the modal participation factor, where the modal participation factor is the contribution amount of each order of mode to the response;

[0061] S23. Use the dynamic simulation software to obtain the vibration displacement output response at different resonance speeds, and then calculate the true vibration amplitude A in different modes according to the modal participation factor;

[0062] S24. Based on the mapping relationship between the true vibration stress σ 1 , the true vibration amplitude A and the modal stress σ modal , and the modal displacement A modal in the state without installing the damping ring:

[0063]

[0064] Calculate the true vibration stress σ 1 of the gear in the state without installing the damping ring.

[0065] In a preferred embodiment of the present application, in step S4, when initially designing a corresponding damping ring for vibration reduction for a dangerous vibration mode, it includes the installation position and outer diameter size of the damping ring. Among them, for a damping ring with a rectangular cross-section, its initial design parameters include the axial width and radial thickness. For a damping ring with a circular cross-section, its initial design parameter includes the cross-sectional diameter. The material of the damping ring is selected as stainless steel.

[0066] In a preferred embodiment of the present application, step S5 specifically includes the steps of:

[0067] S51. Calculate the equivalent damping ratio of the initially designed damping ring;

[0068] S52. Calculate the true vibration stress σ in the state with the damping ring according to the equivalent damping ratio 2 .

[0069] In a preferred embodiment of the present application, S51 specifically includes the steps of:

[0070] S511. Calculate the energy ΔW consumed by the damping ring within one vibration cycle of the gear and the true vibration energy W of the gear respectively;

[0071] S512. Calculate the equivalent damping ratio of the initially designed damping ring according to the energy ΔW consumed by the damping ring within one vibration cycle of the gear and the true vibration energy W of the gear:

[0072]

[0073] According to existing research, aeroengine gears are prone to traveling wave resonance and early fatigue failure. The damping ring can reduce the vibration amplitude during gear resonance and reduce the risk of resonance failure.

[0074] There are two main directions of traveling wave resonance of the gear, one is radial vibration and the other is axial vibration. And in the two directions, the working principle of the damping ring is different. Therefore, the methods for calculating the energy consumption of the damping ring in the two directions are different.

[0075] For the quality of the vibration reduction effect of the damping ring, in this embodiment, the energy consumed by the damping ring within one vibration cycle of the gear and the true vibration energy W of the gear can be calculated first, and then through formula (2), it is converted into the corresponding equivalent damping ratio ζ d .

[0076] In a preferred embodiment of the present application, step S511 specifically includes the steps of:

[0077] S5111. During axial vibration, according to the inconsistency of the relative motion speed between the gear and the damping ring, integrate and solve the relative displacement caused by the speed inconsistency within one vibration cycle to calculate the axial vibration friction energy consumption;

[0078] S5112. During the radial vibration process, according to the inconsistent deformation amounts of the joint surface between the gear and the damping ring, the relative displacement caused by the inconsistent deformation is integrated and solved within one vibration cycle to calculate the radial vibration frictional energy consumption.

[0079] S5113. Sum up the axial vibration frictional energy consumption and the radial vibration frictional energy consumption to solve the total frictional energy consumption in two directions of the damping ring, and obtain the energy ΔW consumed by the damping ring within one vibration cycle of the gear. ΔW is a function of σ 1 .

[0080] In a preferred embodiment of the present application, the step S511 specifically includes the steps:

[0081] S5111. Use finite element calculation software to calculate the modal vibration stress σ modal at the location with the maximum stress of the gear, the modal vibration amplitude A modal at the damping ring installation groove, and the modal vibration energy W modal of the entire gear;

[0082] S5112. Obtain the true vibration energy W of the gear according to the proportional relationship between σ modal , A modal , W modal and the true vibration amplitude A in the corresponding mode:

[0083]

[0084] According to formulas (1) and (3), it can be known that W is also a function of σ 1 .

[0085] In a preferred embodiment of the present application, in the step S52, the true vibration stress σ 2 in the state with the damping ring is calculated by the following formula:

[0086]

[0087] Among them, 0.08% represents the structural damping ratio of the gear itself without the damping ring, which is obtained from the dynamic stress measurement test results. It should be noted that since σ 2 is the true vibration stress in the state of the gear with the damping ring, that is, the true vibration stress after vibration reduction, and the true vibration stress σ 1 of the gear in the state without the installed damping ring should satisfy formula (4). At the same time, σ 1 can also be obtained through computational simulation. Therefore, σ 2 can be calculated according to formula (4).

[0088] In a preferred embodiment of the present application, in step S6, the satisfaction of the design requirements specifically means that the following two conditions must be met:

[0089] Condition 1: σ 2 ≤σ 0 ;

[0090] Condition 2: The equivalent damping ratio within the range of σ 2 ±20Mp is above 0.2%.

[0091] In this embodiment, when evaluating the applicability and vibration reduction effect of the preliminarily designed damping ring based on the allowable stress value σ 0 of the gear material and the true vibration stress σ 2 in the state with a damping ring, the above two conditions must be met. Among them, the purpose of meeting Condition 1 is to ensure that the true vibration stress σ 2 in the state with a damping ring does not exceed the allowable stress value σ 0 of the gear material, thereby ensuring the safe operation of the gear. The purpose of meeting Condition 2 is to ensure that the damping ring can provide a sufficient damping ratio when the gear resonates. Above 0.2% means that the damping ratio is good. As for ±20Mp, it is to prevent errors, so a range is given, and good damping can be provided within this range.

[0092] As Figure 2 shown, a preferred embodiment of the present application further provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, the steps of the damping ring vibration reduction design method for aviation gears in the above embodiment are implemented.

[0093] As Figure 3 shown, a preferred embodiment of the present application further provides a computer device. This computer device can be a terminal or a living body detection server, and its internal structure diagram can be as Figure 3 shown. This computer device includes a processor, a memory, and a network interface connected through a system bus. Among them, the processor of this computer device is used to provide computing and control capabilities. The memory of this computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of this computer device is used to communicate with other external computer devices through a network connection. When the computer program is executed by the processor, the steps of the above damping ring vibration reduction design method for aviation gears are implemented.

[0094] Those skilled in the art can understand, Figure 3The structure shown is only a block diagram of some structures related to the solution of this application, and does not constitute a limitation on the computer device to which the solution of this application is applied. Specifically, the computer device may include more or fewer components than those shown in the figure, or combine some components, or have different component arrangements.

[0095] A preferred embodiment of the present application also provides a storage medium. The storage medium includes a stored program that controls the device where the storage medium is located to execute the steps of the damping ring vibration reduction design method for aviation gears in the above embodiment when the program runs.

[0096] It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. And although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in a different order than here.

[0097] If the functions of the method in this embodiment are implemented in the form of software function units and sold or used as independent products, they can be stored in one or more computer-readable storage media that can be read by a computing device. Based on such an understanding, the part of the present application embodiment that contributes to the prior art or part of this technical solution can be embodied in the form of a software product. The software product is stored in a storage medium and includes several instructions to enable a computing device (which may be a personal computer, a server, a mobile computing device or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of the present application. The foregoing storage media include: USB flash drives, mobile hard disks, read-only memories (ROM, Read-Only Memory), random access memories (RAM, Random Access Memory), magnetic disks or optical discs and other various media that can store program codes.

[0098] Those skilled in the art should understand that the embodiments of the present application can be provided as a method, a system, or a computer program product. Therefore, the present application can adopt the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware aspects. Moreover, the present application can adopt the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) that contain computer-usable program codes. The solutions in the embodiments of the present application can be implemented in various computer languages. For example, object-oriented programming languages such as Java and interpreted scripting languages such as JavaScript.

[0099] This application is described with reference to the flowcharts and / or block diagrams of methods, apparatuses (systems), and computer program products according to embodiments of the present application. It should be understood that each flow and / or block in the flowchart and / or block diagram can be implemented by computer program instructions, as well as the combination of flows and / or blocks in the flowchart and / or block diagram. These computer program instructions can be provided to the processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing devices to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing devices generate a device for implementing the functions specified in one or more of the flows Figure 1 one or more flows and / or blocks Figure 1 or a plurality of blocks.

[0100] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer-readable memory generate a manufactured article including an instruction device, and the instruction device implements the functions specified in one or more of the flows Figure 1 one or more flows and / or blocks Figure 1 or a plurality of blocks.

[0101] These computer program instructions can also be loaded onto a computer or other programmable data processing device, so that a series of operation steps are executed on the computer or other programmable device to generate a computer-implemented process. Thus, the instructions executed on the computer or other programmable device provide steps for implementing the functions specified in one or more of the flows Figure 1 one or more flows and / or blocks Figure 1 or a plurality of blocks.

[0102] Although the preferred embodiments of the present application have been described, those skilled in the art can make additional changes and modifications once they know the basic creative concepts. Therefore, the appended claims are intended to be construed as including the preferred embodiments and all changes and modifications falling within the scope of the present application.

[0103] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalent technologies, the present application is also intended to include these changes and modifications.

Claims

1. A damping ring vibration reduction design method for an aviation gear, characterized in that, it includes the steps: S1. Obtain the resonance speed point of the gear through modal analysis of the gear; S2. Calculate and simulate the true vibration stress σ of the gear web in the state without the damping ring installed at the resonance speed point 1 ; S3. Identify the dangerous vibration mode according to the allowable stress value σ of the gear material 0 wherein the dangerous vibration mode is the vibration type corresponding to 1 σ ≥ σ 0 ; S4. For the dangerous vibration mode, preliminarily design a damping ring for vibration reduction; S5. Calculate the true vibration stress σ in the state with a damping ring according to the equivalent damping ratio ζ of the preliminarily designed damping ring d Specifically, it includes the steps of: 2 calculating the true vibration stress σ in the state with a damping ring S51. Calculate the equivalent damping ratio ζ of the damping ring in the preliminary design d ; S52. Calculate the true vibration stress σ in the state of the damped ring according to the equivalent damping ratio 2 : wherein, 0.08% represents the structural damping ratio of the gear itself without a damping ring, which is obtained from the results of the dynamic stress measurement test; S6. According to the allowable stress value σ of the gear material 0 and the true vibration stress σ under the state with a damping ring 2 evaluate the applicability of the preliminarily designed damping ring and the vibration reduction effect. If σ 2 meets the design requirements, the design is completed; otherwise, after optimizing the structural parameters of the damping ring, repeat steps S4 to S6 until the damping ring meets the design requirements. The so-called meeting the design requirements specifically means that the following two conditions must be met: Condition 1: σ 2 ≤ σ 0 ; Condition 2: σ 2 The equivalent damping ratio within the range of ±20Mp is above 0.2%.

2. The damping ring vibration reduction design method for an aviation gear according to claim 1, characterized in that, the step S2 specifically includes the steps: S21. According to the gear modal analysis results, extract the modal parameters of the reference points in the gear web plate, including the modal displacement A modal and the modal stress σ modal , where the reference point is the point with the maximum modal stress σ modal in each order of mode; S22. Import the web of the gear finite element calculation model into the dynamics simulation software, and construct a rigid-flexible coupling dynamics model in the dynamic stress software with the gear tooth ring and the gear shaft as rigid models and the gear web as a flexible model, and then use the dynamics simulation software to obtain the modal participation factor, where the modal participation factor represents the contribution amount of each order of the modal to the response; S23. Use the dynamics simulation software to obtain the vibration displacement output response at different resonance speeds, and then calculate the true vibration amplitude A in different modes according to the modal participation factor; S24. Mapping relationship between the true vibration stress σ 1 under the state without installing a damping ring, the true vibration amplitude A, and the modal stress σ modal , and the modal displacement A modal : Calculate the true vibration stress σ of the gear in the state without the damping ring installed 1 .

3. The damping ring vibration reduction design method for an aviation gear according to claim 1, characterized in that, the S51 specifically includes the steps: S511. Calculate the energy ΔW consumed by the damping ring within one vibration cycle of the gear and the true vibration energy W of the gear respectively; S512. Calculate the equivalent damping ratio of the preliminarily designed damping ring according to the energy ΔW consumed by the damping ring within one vibration cycle of the gear and the true vibration energy W of the gear; 4. The damping ring vibration reduction design method for an aviation gear according to claim 3, characterized in that, the step S511 specifically includes the steps: S5111. During the axial vibration process, according to the inconsistency of the relative movement speed between the gear and the damping ring, integrate and solve the relative displacement caused by the speed inconsistency within one vibration cycle to calculate the axial vibration friction energy consumption; S5112. During the radial vibration process, according to the inconsistency of the deformation amount of the joint surface between the gear and the damping ring, integrate and solve the relative displacement caused by the deformation inconsistency within one vibration cycle to calculate the radial vibration friction energy consumption; S5113. Sum the axial vibration friction energy consumption and the radial vibration friction energy consumption, and solve the total sum of the friction energy consumption in two directions of the damping ring to obtain the energy ΔW consumed by the damping ring within one vibration cycle of the gear.

5. The damping ring vibration reduction design method for an aviation gear according to claim 3, characterized in that, the step S511 specifically includes the steps: S5111. Calculate the modal vibration stress σ at the location with the maximum stress of the gear using finite element calculation software modal . Calculate the modal vibration amplitude A at the damping ring installation groove modal , and calculate the modal vibration energy W of the entire gear modal ; S5112. Obtained according to the ratio relationship between σ modal , A modal , W modal and the true vibration amplitude A in the corresponding mode, the true vibration energy W of the gear is obtained:

6. An electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, when the processor executes the computer program, it implements the steps of the damping ring vibration reduction design method for an aviation gear according to any one of claims 1 to 5.

7. A storage medium, the storage medium includes a stored program, characterized in that, when the program runs, it controls the device where the storage medium is located to execute the steps of the damping ring vibration reduction design method for an aviation gear according to any one of claims 1 to 5.

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