Gear dynamic response analysis and calculation method, device, equipment and medium

Abstract

The invention discloses a gear dynamic response analysis and calculation method and device, equipment and a medium. The method comprises the steps that S1, excitation frequency which does not generate a beat vibration phenomenon is screened out from inherent frequencies, obtained through modal calculation, transient dynamics calculation and verification, of a gear to serve as final excitation frequency; s2, determining the number of partial teeth loaded by the gear according to the overlap ratio of the gear, and carrying out analog loading instead of full-tooth analog loading by utilizing the final excitation frequency and the determined number of partial teeth to obtain an excitation load curve; s3, determining a corresponding gear damping ratio according to the material characteristics of the aviation gear; and S4, performing dynamic response solution according to the final excitation frequency, the excitation load curve and the gear damping ratio to obtain a dynamic response result of the target position. According to the method, the calculation precision of the real dynamic response of the gear in the damping state is improved; the gear meshing loading process is simulated through cyclic loading on a small number of gear teeth, and the simulation efficiency and computer memory consumption are remarkably improved.

Description

Technical Field

[0001] This application relates to the field of aero-engine gear technology, and in particular to a method, apparatus, equipment and medium for dynamic response analysis and calculation of gears. Background Technology

[0002] Aero engines operate at high speeds over a wide range, making it difficult to completely avoid designing gears to resonate at all engine operating speeds. While gear modal analysis can calculate the resonant frequency and speed, it cannot determine the actual dynamic stress at the resonant speed, thus failing to accurately assess the risk of resonant failure at that speed. Currently, to verify whether gears will experience resonant failure, dynamic stress measurement tests are often conducted on the gears during engine testing or in component testing equipment.

[0003] Currently, gear design can only provide modal analysis results and the operating speed at the resonant speed point within the working range. It's difficult to accurately predict the vibration response of the gear at the resonant speed point. The reliability of the gear can only be determined by measuring dynamic stress in its physical state after machining. However, testing through experiments has several drawbacks: 1) Testing and experimentation are costly and have a time lag. Once it is found that the dynamic stress of the gear is too high at the resonance speed point, the gear structure needs to be adjusted. Sometimes, major adjustments to the gear structure parameters are required to reduce the dynamic stress, and the adjustment process is often a continuous trial and error process. 2) Sufficient space is required to install the testing equipment during the testing process. Therefore, not all gears can be used for dynamic stress measurement. Engines need to be modified for testing, which will also increase the processing cost and delay the research progress. Summary of the Invention

[0004] This application provides a method for analyzing and calculating the dynamic response of gears, which solves the technical problems of high testing and experimentation costs, lag, limited applicability, and delays in scientific research progress in existing technologies.

[0005] This application is achieved through the following solution: A method for analyzing and calculating the dynamic response of gears, comprising the following steps: S1. Select the excitation frequency that does not produce beat vibration from the gear natural frequencies obtained by modal calculation, transient dynamics calculation and verification as the final excitation frequency; S2. Determine the number of teeth of the gear to be loaded based on the overlap ratio of the gears, and use the final excitation frequency and the determined number of teeth of the gear to perform simulated loading instead of full-tooth simulated loading to obtain the excitation load curve. S3. Determine the appropriate gear damping ratio based on the material properties of the aircraft gears; S4. Solve the dynamic response based on the final excitation frequency, excitation load curve and gear damping ratio to obtain the dynamic response result at the target position.

[0006] Further, step S1 specifically includes the following steps: S11. Perform modal calculations on the gears; S12. Select the natural frequency of a certain mode within the working range. ; S13. Perform transient dynamics calculations, adding the frequency during the calculation. The excitation is a sinusoidal function, and the damping is defined as 0; S14. Based on the beat vibration results given by transient dynamics calculation, calculate the excitation frequency at which beat vibration will not occur. : ; Among them, the shooting frequency Based on the beat response calculation results: ,in The period of the shot can be obtained directly by reading the response result; S15. Perform transient dynamic calculation verification. During the calculation verification, add an excitation frequency of... The excitation frequency is determined by applying a sinusoidal function excitation with zero damping. If the response no longer exhibits beat vibration and increases continuously with time, then the excitation frequency is determined accordingly. This is the final excitation frequency.

[0007] Furthermore, step S2 specifically includes the following steps: S21. Determine the number of teeth of the gear under load based on the gear overlap ratio ε. S22. Simulate the alternating meshing of partially paired gears during operation based on the number of teeth Z0 of the loaded gear and the final excitation frequency to obtain the excitation load curve.

[0008] Preferably, in step S21, determining the number of teeth of the gear under load based on the gear overlap ratio ε specifically involves: Z0 = [ε] + 1; Where [ε] represents the degree of overlap ε, which is rounded down to the nearest integer and the decimal part is discarded.

[0009] Further, in step S22, when the overlap ratio 1 < ε < 2, the obtained excitation load curve is a trapezoidal wave. The amplitude of the flat top of the trapezoidal wave is determined according to the actual load on the gear, including alternating single-pair meshing areas and double-pair meshing areas, wherein: Gear meshing cycle: ; Duration of engagement zone for a single pair of teeth: ; Duration of double-pair tooth engagement zone: .

[0010] Further, in step S22, when the overlap ratio ε=2, the obtained excitation load curve changes from a trapezoidal wave to a triangular wave. The peak amplitude of the triangular wave is determined according to the actual load on the gear, and the peak time of the excitation load curve is shortened to 0. It includes alternating single-pair meshing areas and double-pair meshing areas, wherein: Gear meshing cycle: ; Duration of engagement zone for a single pair of teeth: ; Duration of double-pair tooth engagement zone: .

[0011] Further, in step S22, when the overlap ratio 2 < ε < 3, the obtained excitation load curve is a trapezoidal wave. The amplitude of the flat top of the trapezoidal wave is determined according to the actual load on the gear, including alternating double-pair meshing areas and triple-pair meshing areas, wherein: Gear meshing cycle: ; Duration of double-pair tooth engagement zone: t 2 = (3 - ε ) T ; Duration of the three pairs of teeth in the meshing zone: t 3=( ε -2) T .

[0012] This application also provides a gear dynamic response analysis and calculation device, including: The excitation frequency determination module is used to select the excitation frequency that does not produce beat vibration as the final excitation frequency from the gear natural frequencies obtained by modal calculation, transient dynamics calculation and verification. The excitation load curve determination module is used to determine the number of teeth of the gear that are partially loaded based on the gear overlap ratio, and to obtain the excitation load curve by using the final excitation frequency and the determined number of teeth of the gear that are partially loaded to perform simulated loading instead of full-tooth simulated loading. The damping ratio determination module is used to determine the corresponding gear damping ratio based on the material properties of the aircraft gears. The dynamic response solution module is used to solve the dynamic response based on the final excitation frequency, excitation load curve and gear damping ratio, and obtain the dynamic response result at the target position.

[0013] This application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and running on the processor, wherein the processor executes the computer program to implement the steps of the gear dynamic response analysis and calculation method.

[0014] This application also provides a storage medium including a stored program that, when the program is executed, controls the device where the storage medium is located to perform the steps of the gear dynamic response analysis and calculation method.

[0015] Compared with the prior art, this application has the following advantages: 1. The focus of this application is on the preprocessing of gear dynamic response calculation. Specifically, based on the beat vibration theory, a method for calculating the beat frequency is created by combining gear modal and transient dynamic calculations. This method can accurately calculate the beat frequency of the gear, effectively eliminating the difference between the gear's natural frequency and the gear's excitation frequency, thereby improving the calculation accuracy of the gear's real dynamic response under damped conditions. 2. This application creates a gear loading method that simulates the gear meshing loading process by cyclically loading a small number of gear teeth. Compared with the full-tooth cyclic loading according to the real situation, this method can greatly reduce the amount of calculation and significantly improve the simulation efficiency and computer memory consumption.

[0016] In addition to the purposes, features, and advantages described above, this application has other purposes, features, and advantages. A further detailed description of this application will be provided below with reference to the figures. Attached Figure Description

[0017] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[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, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort, wherein: Figure 1 This is a schematic flowchart of a preferred embodiment of the gear dynamic response analysis and calculation method of this application; Figure 2 This is a schematic diagram of a preferred embodiment of the present application; Figure 3This is a schematic diagram of the gear loading curve and single and double tooth meshing regions of a preferred embodiment of this application (ε=1.7); Figure 4 This is a schematic diagram of the gear loading curve and the meshing regions of two and three pairs of teeth according to a preferred embodiment of this application (ε=2.3); Figure 5 This is a schematic diagram of a gear dynamic response analysis and calculation device module according to a preferred embodiment of this application; Figure 6 This is a schematic block diagram of an electronic device according to a preferred embodiment of this application; Figure 7 This is an internal structural diagram of a computer device according to a preferred embodiment of this application. Detailed Implementation

[0019] It should be understood that the specific embodiments described herein are merely illustrative of the technical solutions of this application and are not intended to limit this application.

[0020] To better understand the technical solution of this application, a detailed description will be provided below in conjunction with the accompanying drawings and specific implementation methods.

[0021] It should be noted that the executing entity in this embodiment can be a computing service device with data processing, network communication, and program execution functions, such as a tablet computer, personal computer, or mobile phone, or a gear dynamic response analysis computing device capable of performing the above functions. The following description uses a gear dynamic response analysis computing device as the executing entity to illustrate this embodiment and the subsequent embodiments.

[0022] like Figure 1 As shown, a preferred embodiment of this application provides a method for analyzing and calculating the dynamic response of a gear, including the following steps: S1. Select the excitation frequency that does not produce beat vibration from the gear natural frequencies obtained by modal calculation, transient dynamics calculation and verification as the final excitation frequency; S2. Determine the number of teeth of the gear to be loaded based on the overlap ratio of the gears, and use the final excitation frequency and the determined number of teeth of the gear to perform simulated loading instead of full-tooth simulated loading to obtain the excitation load curve. S3. Determine the corresponding gear damping ratio based on the material properties of the aircraft gear. For aircraft gears, the material is generally steel. Although the damping ratios of different gear structures are different, they are generally in the range of 0.06%-0.12%. Therefore, the value can be selected within this range based on engineering experience. S4. Based on the final excitation frequency, excitation load curve and gear damping ratio, perform dynamic response calculation (dynamic response calculation can be performed using currently mature commercial software) to obtain the dynamic response results at the target position.

[0023] Compared with the prior art, this embodiment has the following advantages: 1. The focus of this embodiment is on the preprocessing of gear dynamic response calculation. Specifically, based on beat vibration theory, a method for calculating beat frequency is created by combining gear modal and transient dynamic calculations. This method can accurately calculate the beat frequency of the gear, effectively eliminating the difference between the gear's natural frequency and the gear's excitation frequency, thereby improving the calculation accuracy of the gear's real dynamic response under damped conditions. 2. This embodiment creates a gear loading method that simulates the gear meshing loading process by cyclically loading a small number of gear teeth. Compared with the full-tooth cyclic loading according to the real situation, this method can greatly reduce the amount of calculation and significantly improve the simulation efficiency and computer memory consumption.

[0024] Preferably, step S1 specifically includes the following steps: S11. Perform modal calculations on the gears; S12. Select the natural frequency of a certain mode within the working range. ; S13. Perform transient dynamics calculations, adding the frequency during the calculation. The excitation is a sinusoidal function, and the damping is defined as 0; S14. Based on the beat vibration results given by transient dynamics calculation, calculate the excitation frequency at which beat vibration will not occur. : ; Among them, the shooting frequency Based on the beat response calculation results (see...) Figure 2 ): ,in The period of the shot can be obtained directly by reading the response result; S15. Perform transient dynamic calculation verification. During the calculation verification, add an excitation frequency of... The excitation frequency is determined by applying a sinusoidal function excitation with zero damping. If the response no longer exhibits beat vibration and increases continuously with time, then the excitation frequency is determined accordingly. This is the final excitation frequency.

[0025] Simulation analysis of gear dynamic stress typically employs transient dynamics methods. However, when calculating the dynamic response, if the excitation frequency is very close to the gear's resonant frequency, beat vibration can occur, causing periodic fluctuations in the gear's dynamic stress. This effect is particularly pronounced in low-damped systems (damping ratio ≤ 0.2%). Consequently, the obtained dynamic stress results may differ significantly from the actual results. Therefore, it is crucial that the excitation frequency closely matches the gear's natural frequency.

[0026] When solving for the transient response of gears, the direct integration method is often used. This method often leads to a difference between the natural frequencies of the model and those obtained from modal calculations. If the natural frequencies obtained from modal calculations are used directly, beat vibrations will occur when calculating the gear response, resulting in significant deviations in the calculation results. Therefore, this embodiment calculates the gear's natural frequencies without beat vibrations before calculating the transient dynamics. By accurately calculating the gear's beat frequencies, the difference between the gear's natural frequencies and the gear's excitation frequencies is effectively eliminated, thereby improving the calculation accuracy of the gear's true dynamic response under damped conditions.

[0027] Preferably, step S2 specifically includes the following steps: S21. Determine the number of teeth in the loaded portion of the gear based on the gear overlap ratio ε: Z0 = [ε] + 1; Where [ε] represents the degree of overlap ε, which is rounded down to the nearest integer and the decimal part is discarded; S22. Simulate the alternating meshing of partially paired gears during operation based on the number of teeth Z0 of the loaded gear and the final excitation frequency to obtain the excitation load curve.

[0028] During gear meshing, the number of teeth involved in meshing changes over time, and the meshing position also changes. It is impossible to accurately simulate the actual meshing situation. Therefore, it is necessary to perform equivalence. In this embodiment, the number of teeth loaded on the gear is determined according to the overlap ratio ε of the gear, Z0 = [ε] + 1, where [ε] represents the overlap ratio ε. The integer part is taken directly, and the decimal part is discarded. This embodiment only uses a portion of the teeth to simulate the alternating meshing of different pairs of gears during the working process, which will greatly improve the simulation calculation efficiency.

[0029] Preferably, in step S22, when the overlap ratio 1 < ε < 2, taking ε = 1.7 as an example, the obtained excitation load curve is a trapezoidal wave. The amplitude of the flat top of the trapezoidal wave is determined according to the actual load on the gear, including alternating single-pair meshing areas and double-pair meshing areas, wherein: Gear meshing cycle: ; Duration of engagement zone for a single pair of teeth: ; Duration of double-pair tooth engagement zone: .

[0030] This embodiment takes an overlap ratio of 1.7 as an example, and loads are applied to two adjacent gear teeth. The loading curves of the two gear teeth are shown below. Figure 3As shown (the amplitude in the figure represents the magnitude of the gear pair meshing force). This embodiment uses only two teeth to simulate the alternating single and double meshing during gear operation, which greatly improves the simulation calculation efficiency. If a gear has 31 teeth, and the load is calculated after the gear rotates 10 revolutions, in real working conditions, each gear is loaded. During simulation, even gears without load would be loaded, albeit with a load of 0, requiring calculation. This significantly increases the computational load and computer memory consumption. This embodiment uses only two teeth to achieve this full-tooth loading substitution, thus greatly reducing the computational load. The gear load is assumed to be a trapezoidal wave (a trapezoidal wave is a relatively ideal load curve, which can be further optimized based on the actual meshing load, but has little impact on the response result, and the optimized curve is also applicable to the method of this embodiment). The peak amplitude of the trapezoidal wave is determined based on the actual gear load.

[0031] Preferably, in step S22, when the overlap ratio ε=2, similar to the case of 1<ε<2, the obtained excitation load curve changes from a trapezoidal wave to a triangular wave. The peak amplitude of the triangular wave is determined according to the actual load on the gear, and the peak time of the excitation load curve is shortened to 0. It includes alternating single-pair meshing areas and double-pair meshing areas, wherein: Gear meshing cycle: ; Duration of engagement zone for a single pair of teeth: ; Duration of double-pair tooth engagement zone: .

[0032] Preferably, in step S22, when the overlap ratio 2 < ε < 3, similar to the case of 1 < ε < 2, the obtained excitation load curve is a trapezoidal wave. The amplitude of the flat top of the trapezoidal wave is determined according to the actual load on the gear, including alternating double-pair meshing areas and triple-pair meshing areas, wherein: Gear meshing cycle: ; Duration of double-pair tooth engagement zone: t 2 = (3 - ε ) T ; Duration of the three pairs of teeth in the meshing zone: t 3=( ε -2) T .

[0033] Taking ε=2.3 as an example, the loading curve is as follows: Figure 4As shown in the figure, (1,2), (1,3), and (2,3) represent gears under load as (tooth 1, tooth 2), (tooth 1, tooth 3), and (tooth 2, tooth 3), respectively. The case of ε≥3 can be deduced by analogy.

[0034] like Figure 5 As shown, another preferred embodiment of this application also provides a gear dynamic response analysis and calculation device, including: The excitation frequency determination module is used to select the excitation frequency that does not produce beat vibration as the final excitation frequency from the gear natural frequencies obtained by modal calculation, transient dynamics calculation and verification. The excitation load curve determination module is used to determine the number of teeth of the gear that are partially loaded based on the gear overlap ratio, and to obtain the excitation load curve by using the final excitation frequency and the determined number of teeth of the gear that are partially loaded to perform simulated loading instead of full-tooth simulated loading. The damping ratio determination module is used to determine the corresponding gear damping ratio based on the material properties of the aircraft gears. The dynamic response solution module is used to solve the dynamic response based on the final excitation frequency, excitation load curve and gear damping ratio, and obtain the dynamic response result at the target position.

[0035] The gear dynamic response analysis and calculation device provided in this embodiment adopts the gear dynamic response analysis and calculation method in the above embodiments, solving the technical problems of high testing and experimentation costs, lag, limited applicability, and delays in scientific research progress in existing technologies. Compared with the prior art, the beneficial effects of the gear dynamic response analysis and calculation device provided in this embodiment are the same as those of the gear dynamic response analysis and calculation method provided in the above embodiments, and other technical features in the gear dynamic response analysis and calculation device are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0036] like Figure 6 As shown, a preferred embodiment of this embodiment also 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 computer program, it implements the steps of the gear dynamic response analysis and calculation method in the above embodiment.

[0037] This embodiment provides an electronic device that employs the gear dynamic response analysis and calculation method described in the above embodiments, solving the technical problems of high testing and experimental costs, lag, limited applicability, and delays in scientific research progress in existing technologies. Compared with the prior art, the beneficial effects of the electronic device provided in this embodiment are the same as those of the gear dynamic response analysis and calculation method provided in the above embodiments, and other technical features of the electronic device are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0038] like Figure 7 As shown, a preferred embodiment of this invention also provides a computer device, which may be a terminal or a liveness detection server, and its internal structure diagram may be as follows. Figure 7 As shown, the computer device includes a processor, memory, and a network interface connected via a system bus. The processor provides computational and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs stored in the non-volatile storage media. The network interface is used to communicate with other external computer devices via a network connection. When the computer program is executed by the processor, it implements the steps of the aforementioned gear dynamic response analysis and calculation method.

[0039] Those skilled in the art will understand that Figure 7 The structure shown is merely a block diagram of a portion of the structure related to the solution of this embodiment, and does not constitute a limitation on the computer device to which the solution of this embodiment is applied. The specific computer device may include more or fewer components than shown in the figure, or combine certain components, or have different component arrangements.

[0040] The computer equipment provided in this application employs the gear dynamic response analysis and calculation method described in the above embodiments, solving the technical problems of high testing and experimental costs, lag, limited applicability, and delays in scientific research progress in existing technologies. Compared with the prior art, the beneficial effects of the computer equipment provided in this embodiment are the same as those of the gear dynamic response analysis and calculation method provided in the above embodiments, and other technical features in the electronic device are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0041] A preferred embodiment of this example also provides a storage medium, which includes a stored program that, when the program is executed, controls the device where the storage medium is located to perform the steps of the gear dynamic response analysis and calculation method described in the above embodiment.

[0042] This application has been successfully used in the dynamic simulation design of gears for a certain aero-engine, and the calculation results are reliable and can meet the engine's requirements for accessory transmission components.

[0043] It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and although a logical order is shown in the flowchart, in some cases the steps shown or described may be executed in a different order than that shown here.

[0044] If the functions described in this embodiment are implemented as software functional units and sold or used as independent products, they can be stored in one or more computing device-readable storage media. Based on this understanding, the parts of this embodiment that contribute to the prior art or the technical solution can be embodied in the form of a software product. This software product is stored in a storage medium and includes several instructions to cause a computing device (which may be a personal computer, server, mobile computing device, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this embodiment. The aforementioned storage media include: USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.

[0045] Those skilled in the art will understand that embodiments of this example can be provided as methods, systems, or computer program products. Therefore, this example can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this example can take 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.) containing computer-usable program code. The solutions in this example can be implemented using various computer languages, such as the object-oriented programming language C++ and the embedded programming language C.

[0046] This embodiment is described with reference to flowchart illustrations and / or block diagrams of the method, apparatus (system), and computer program product according to this embodiment. It should be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0047] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0048] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0049] This embodiment also provides a computer program product, including a computer program that, when executed by a processor, implements the steps of the gear dynamic response analysis and calculation method described above.

[0050] The computer program product provided in this embodiment solves the technical problems of high testing and experimentation costs, delays, limited applicability, and slowdowns in scientific research in existing technologies. Compared with the prior art, the beneficial effects of the computer program product provided in this embodiment are the same as those of the gear dynamic response analysis and calculation method provided in the above embodiments, and will not be repeated here.

[0051] Although preferred embodiments of this embodiment have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this embodiment.

[0052] Obviously, those skilled in the art can make various modifications and variations to this embodiment without departing from the spirit and scope of this embodiment. Therefore, if these modifications and variations of this embodiment fall within the scope of the claims of this embodiment and their equivalents, this embodiment is also intended to include these modifications and variations.

Claims

1. A method of gear dynamic response analysis calculation, characterized by, The method comprises the steps of: S1, screening out an excitation frequency not causing beat vibration from gear inherent frequencies obtained through modal calculation, transient dynamics calculation and verification as a final excitation frequency; S2, determining partial teeth of gear loading according to a contact ratio of the gear, and obtaining an excitation load curve by using the final excitation frequency and the determined partial teeth of gear loading to perform simulation loading instead of full-tooth simulation loading; S3, determining a corresponding gear damping ratio according to material characteristics of the aviation gear; S4, performing dynamic response solving according to the final excitation frequency, the excitation load curve and the gear damping ratio to obtain a dynamic response result of a target position.

2. The gear dynamic response analysis calculation method according to claim 1, characterized by, The step S1 specifically comprises the steps of: S11, performing modal calculation on the gear; S12, selecting the natural frequency of a certain order modal in the working range ; S13, transient kinetic calculation is performed, when calculating, add the sinusoidal function excitation with frequency of 0.1 Hz, and define the damping as 0; S14. Calculate the exciting frequency that does not produce beat vibration according to the beat vibration result given by the transient dynamics calculation : ； wherein the beat frequency From the beat vibration response calculation results, it is concluded that: wherein represents the period of the beat, which is directly obtained by reading the response results. S15, carry out transient dynamic calculation verification, in the calculation verification, add the sinusoidal function excitation with the exciting frequency of 0. If the response result no longer exists beat phenomenon, and the response increases with time, then the exciting frequency is determined as the final exciting frequency.

3. The gear dynamic response analysis calculation method according to claim 1, characterized by, The step S2 specifically comprises the steps of: S21, determining partial teeth of gear loading according to a contact ratio of the gear; S22, performing simulation on a partial pair meshing alternation in a gear working process according to the partial teeth of gear loading and the final excitation frequency to obtain an excitation load curve.

4. The gear dynamic response analysis calculation method according to claim 3, characterized by, In the step S21, the determination of the partial teeth of gear loading according to the contact ratio of the gear is specifically as follows: Z0=[ε]+1; Wherein, [ε] represents rounding of the contact ratio ε, directly taking an integer part and discarding a decimal part.

5. The gear dynamic response analysis calculation method according to claim 4, characterized by, In the step S22, when the contact ratio is 1<ε<2, the obtained excitation load curve is a trapezoidal wave, a flat-top amplitude of the trapezoidal wave is determined according to actual load of the gear, and the excitation load curve includes alternately appearing single pair tooth meshing area and double pair tooth meshing area, wherein: Gear tooth meshing period: ； Single pair tooth meshing area duration: ； Double pair tooth meshing area duration: 。 6. The gear dynamic response analysis calculation method according to claim 4, characterized by, In the step S22, when the contact ratio is ε=2, the obtained excitation load curve changes from the trapezoidal wave to a triangular wave, a flat-top amplitude of the triangular wave is determined according to actual load of the gear, a flat-top time of the excitation load curve is shortened to 0, and the excitation load curve includes alternately appearing single pair tooth meshing area and double pair tooth meshing area, wherein: Gear tooth meshing period: ； Single pair tooth meshing area duration: ； Double pair tooth meshing area duration: 。 7. The gear dynamic response analysis calculation method according to claim 4, characterized by, In the step S22, when the contact ratio is 2<ε<3, the obtained excitation load curve is a trapezoidal wave, a flat-top amplitude of the trapezoidal wave is determined according to actual load of the gear, and the excitation load curve includes alternately appearing double pair tooth meshing area and triple pair tooth meshing area, wherein: Gear tooth meshing period: ； Double pair tooth meshing area duration: t 2=(3- ε ) T ； Triple pair tooth meshing area duration: t 3=( ε -2) T 。 8. A gear dynamic response analysis computing device, characterized by, The method comprises: An excitation frequency determination module, configured to screen out an excitation frequency not causing beat vibration from gear inherent frequencies obtained through modal calculation, transient dynamics calculation and verification as a final excitation frequency; An excitation load curve determination module, configured to determine partial teeth of gear loading according to a contact ratio of the gear, and obtain an excitation load curve by using the final excitation frequency and the determined partial teeth of gear loading to perform simulation loading instead of full-tooth simulation loading; A damping ratio determination module, configured to determine a corresponding gear damping ratio according to material characteristics of the aviation gear; A dynamic response solving module, configured to perform dynamic response solving according to the final excitation frequency, the excitation load curve and the gear damping ratio to obtain a dynamic response result of a target position.

9. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, The processor executes the computer program to realize the steps of the gear dynamic response analysis calculation method in any one of claims 1 to 7.

10. A storage medium, the storage medium comprising a stored program, characterized in that, The program controls the device in which the storage medium is located to execute the steps of the gear dynamic response analysis calculation method according to any one of claims 1 to 7 when the program is running.

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