Method and device for determining dynamic load and aeroengine

Abstract

The application provides a dynamic load determination method, comprising: obtaining test data, the test data being determined based on a dynamic test of a structure model corresponding to an application structure; obtaining simulation data, the simulation data being determined through simulation calculation based on a simulation model corresponding to the structure model; fitting the test data and the simulation data into quadratic expressions about vibration frequencies respectively, and determining a linear relationship between the test data and the simulation data; and determining a dynamic load of the application structure based on simulation strain data of the application structure and the linear relationship.

Description

Technical Field

[0001] This invention relates to the field of aero-engine testing, and in particular to a method, apparatus, and aero-engine for determining dynamic loads. Background Technology

[0002] In rotating machinery, bearings are key structures connecting the rotor and stator, playing a crucial role in transferring the rotor's vibrational loads to the stator. To continuously improve the thrust-to-weight ratio of aero-engines, rotors have consistently adhered to a lightweight, high-load design philosophy, which places even more stringent demands on the structural design of bearings.

[0003] Real-time acquisition of vibration loads at the bearing is a highly effective means of monitoring the bearing's operating condition and a key step in preventing bearing damage. Vibration loads at the bearing can be divided into axial loads and radial loads. Under operating conditions, the radial load at the bearing exhibits dynamic characteristics. For example, due to the unbalanced force generated by the residual unbalance on the rotor, the radial load will rotate with the rotor.

[0004] Currently, the radial load at the bearing is often estimated using data from static calibration. However, this method ignores the dynamic characteristics of the radial load, and the estimated radial load is not accurate enough. Summary of the Invention

[0005] The purpose of this invention is at least to provide a method, apparatus, and aero-engine for determining dynamic loads, which can more accurately obtain the radial load borne by the engine rotor bearing during operation.

[0006] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.

[0007] One embodiment of the present invention provides a method for determining dynamic loads. The method includes acquiring experimental data, which is determined by dynamic testing based on a structural model corresponding to the applied structure; acquiring simulation data, which is determined by simulation calculation based on a simulation model corresponding to the structural model; fitting the experimental data and simulation data into quadratic expressions about the vibration frequency to determine the linear relationship between the experimental data and the simulation data; and determining the dynamic loads of the applied structure based on the simulated strain data of the applied structure and the linear relationship.

[0008] In some embodiments, the structural model is consistent with the structure of the application structure.

[0009] In some embodiments, the simulated strain data of the applied structure is obtained through the overall dynamic model of the applied structure.

[0010] In some embodiments, the dynamic test includes: placing a strain sensor on the force transmission path of the structural model; applying a test load with a vibration frequency varying within a target frequency range at the corresponding position on the structural model; and obtaining test data from the strain sensor.

[0011] In some embodiments, when the structural model has a resonant frequency within the target frequency range, a frequency within the target frequency range that is less than the resonant frequency is used as the segmented frequency, and the experimental data corresponding to the frequencies on both sides of the segmented frequency are fitted in segments.

[0012] In some embodiments, the determination method further includes: conducting a static test on the structural model and calibrating the quadratic expression of the test data; the static test includes: setting a strain sensor on the force transmission path of the structural model; applying a static load with a vibration frequency of zero at the corresponding position on the structural model; the strain sensor measuring the static data; and comparing the constant term in the quadratic expression of the static data and the test data.

[0013] One embodiment of the present invention provides a dynamic load determination device, which is used to perform the dynamic load determination method described above. The determination device includes a memory and a processor; the memory is used to store linear relationships; the processor is used to acquire simulated strain data and linear relationships to determine the dynamic load of the applied structure.

[0014] In some embodiments, the memory is used to store the overall dynamic model corresponding to the application structure; the processor is used to calculate and obtain simulation strain data through the overall dynamic model.

[0015] One embodiment of the present invention also provides an aero-engine, including the above-described dynamic load determination device, which is used to determine the radial load of the rotor support structure.

[0016] The present invention relates to a method for determining dynamic loads. This method establishes a linear relationship between simulated and experimental data, or more specifically, a linear relationship between simulated strain data and actual strain data, by conducting experiments based on a structural model beforehand. Since there is a certain discrepancy between simulated strain data and the actual strain data of the applied structure, improving the accuracy of the determined load requires improving the accuracy of the determined strain data. The method of the present invention does not directly use simulated strain data as the actual strain data. Instead, it determines the strain data by analyzing the linear relationship between simulated strain data and actual strain data, thereby improving the accuracy of the determined strain data. Attached Figure Description

[0017] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related properties or features may have the same or similar reference numerals. Wherein:

[0018] Figure 1 This is a flowchart illustrating a dynamic load determination method according to some embodiments;

[0019] Figure 2 This is a flowchart of a dynamic test based on some embodiments;

[0020] Figure 3 This is a dynamic test schematic diagram of the elastic support structure shown in some embodiments;

[0021] Figure 4A This is a comparison chart of experimental data and simulation data based on some embodiments;

[0022] Figure 4B This is a comparison chart of the results after fitting experimental data and simulation data according to some embodiments;

[0023] Figure 5 It is a graph showing the change of coefficient A1 with frequency according to some embodiments;

[0024] Figure 6 It is a graph showing the change of coefficient A2 with frequency according to some embodiments. Detailed Implementation

[0025] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0026] It should be understood that the terms “system,” “device,” “unit,” and / or “module” used herein are one method of distinguishing different components, elements, parts, sections, or assemblies at different levels. However, if other words can achieve the same purpose, they may be replaced by other expressions.

[0027] Flowcharts are used in this specification to illustrate the operations performed by the system according to embodiments of this specification. 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.

[0028] like Figure 1As shown in the embodiments of this specification, a method 100 for determining dynamic load is proposed, including steps 110-140.

[0029] Step 110: Obtain experimental data. The experimental data is determined by dynamic experiments based on the structural model corresponding to the application structure.

[0030] The structural model is a scaled-down model of the applied structure. In some embodiments, the structural model is a scaled-down model of the applied structure. The applied structure refers to the research object of this invention, that is, the specific structure bearing the dynamic load obtained by this invention. During the experimental phase, the applied structure is scaled down to a structural model. The experimental data actually measured on the structural model can be used to characterize the real dynamic load borne by the applied structure, so as to subsequently determine the relationship between the dynamic load borne by the applied structure and the strain data obtained from simulation calculations. In some embodiments, the applied structure described in this specification includes a rotor support structure, such as a squirrel-cage elastic support structure, a bearing housing, etc. In the working state, the rotor support structure bears the vibration load from the rotor, and due to the residual unbalance on the rotor, an unbalanced force is generated, causing the radial load of the rotor support structure to exhibit a rotational tendency as the rotor rotates, making the radial load of the rotor support structure a dynamic load.

[0031] In some embodiments, the structural model can be consistent with the applied structure or a simplified model of the applied structure. When determining the simplified model of the applied structure, the force direction and force transmission path of the structural model must be consistent with the applied structure. In some embodiments, the constraints of the structural model are consistent with the applied structure, and the constraints include the installation fixing position and installation conditions, etc.

[0032] In some embodiments, such as Figure 2 As shown, the dynamic test includes steps 111-113.

[0033] Step 111: Set up strain sensors on the force transmission path of the structural model.

[0034] During the experimental phase, strain sensors are installed on the structural model to obtain experimental data. These strain sensors are used to sense the strain on the structural model. For example, the strain sensors can be displacement sensors or strain gauges. In some embodiments, strain sensors are installed along the force transmission path of the structural model, and strain gauges or displacement sensors are installed to obtain the deformation and displacement of key structural locations under load excitation. For example, strain sensors are installed on the cage bars of a squirrel-cage elastic support structure. Another example is that strain sensors are installed on the conical wall of a bearing housing. In some embodiments, since the applied structure bears the circumferential excitation of the rotor, the applied structure experiences strain in the circumferential direction around the rotor. Accordingly, multiple strain sensors can be evenly distributed around the circumferential direction of the rotor on the structural model to detect the strain at various points in the circumferential direction of the structural model.

[0035] Step 112: Apply a test load with a vibration frequency varying within the target frequency range to the corresponding position on the structural model.

[0036] In this design, the corresponding position on the structural model corresponds to the stress position on the applied structure. When the corresponding stress position on the structural model is unreachable, the corresponding position on the structural model is determined to be the position closest to the stress position. The target frequency range of the test load's vibration frequency is determined based on the vibration frequency range of the dynamic load on the applied structure. In some embodiments, the direction of the test load applied at the corresponding position on the structural model is consistent with the force direction of the applied structure. The following uses an elastically supported structure as an example to illustrate the determination of the strain sensor position, constraint conditions, stress position, and force direction of the structural model.

[0037] In operation, the elastic support structure is subjected to circumferential excitation from the rotor. The force transmission path of the elastic support structure is the cage bars, and the strain can be measured at the location of the cage bars. Figure 3 The image shown is half of a cross-section taken along the diameter of the structural model of the corresponding elastic support structure. Figure 3 The constraints, force locations, and force directions of the structural model shown are consistent with those used in applications with elastic supports. Specifically, Figure 3The structural model shown has its end 31 fixed. A test load is applied to the inner annular surface 32, away from the end 31, with the direction of the test load perpendicular to the inner annular surface 32. A strain sensor 33 is disposed on a cage bar 34 located between the end 31 and the inner annular surface 32. In some embodiments, the detection direction of the strain sensor 33 is aligned with the length extension direction of the cage bar 34, allowing for more accurate detection of the strain magnitude. The detection direction of the strain sensor 33 refers to the deformation direction of its sensing element. For example, when the sensing element is a strain gauge, the strain gauge is arranged in the same direction as the length extension direction of the cage bar 34. The deformation of the cage bar 34 causes deformation of the strain gauge, and the strain sensor 33 can detect the deformation of the cage bar 34 based on the magnitude of the strain gauge deformation. In some embodiments, the elastic support structure bears the circumferential excitation of the rotor. The elastic support structure has multiple cage bars 34 in the circumferential direction around the rotor, and all of these cage bars 34 exhibit strain. Correspondingly, strain sensors are disposed at each of the multiple cage bars 34 in the circumferential direction of the structural model to detect the strain of each cage bar 34.

[0038] Step 113: The strain sensor measures the test data.

[0039] The vibration frequency of the test load can be adjusted within the target frequency range. The structural model responds to changes in the vibration frequency of the test load by producing different strains. Strain sensors detect the strain of the structural model as test data. In some embodiments, the maximum value of the data measured by multiple strain sensors in the circumferential direction of the structural model is taken as the test data to design the application structure within the maximum safety range, thereby protecting the structural safety of the application structure to the greatest extent.

[0040] Step 120: Obtain simulation data. The simulation data is determined through simulation calculation based on the simulation model corresponding to the structural model.

[0041] In some embodiments, the simulation model includes a physical model established based on the structural model. Load data with the same vibration frequency as the test load is input; the vibration frequency of the load data is adjustable within a target frequency range. Simulation data is output through simulation calculations using the physical model.

[0042] Step 130: Fit the experimental data and simulation data into quadratic equations about the vibration frequency to determine the linear relationship between the experimental data and the simulation data.

[0043] The experimental data obtained in step 110 and the simulation data obtained in step 120 are actually frequency-dependent structural strain data. Since structural strain is mainly controlled by the structural stiffness, the structural dynamic stiffness K... S =K-MΩ 2 +jD(1-λ)Ω, where K is the static stiffness of the structure, Ω is the vibration frequency, and MΩ is the static stiffness of the structure. 2Let jD(1-λ)Ω be the mass stiffness and jD(1-λ)Ω be the damping stiffness. Based on the structural dynamic stiffness K... S The expression can determine K S The equation is a quadratic expression with vibration frequency as the variable. The coefficients of the quadratic term are mainly determined by the structural mass, the coefficients of the linear term are mainly determined by the structural damping, and the constant term is mainly controlled by the structural static stiffness.

[0044] Based on the characteristics of the steady-state solution of forced vibration in a linear system, experimental and simulation data can be fitted as quadratic equations with respect to the vibration frequency. The fitted quadratic equations of the experimental and simulation data are then mapped one-to-one according to the vibration frequency to explore the relationship between the experimental and simulation data at the same vibration frequency. In some embodiments, to facilitate establishing a correlation between the experimental and simulation data, normalization with respect to the applied experimental load can be performed on both the experimental and simulation data before fitting.

[0045] The quadratic expressions of the fitted experimental and simulation data with respect to frequency are as follows:

[0046] S T =t1·f 2 +t2·f+t3;

[0047] S S =s1·f 2 +s2·f+s3;

[0048] Among them, S T S represents the result of normalizing the experimental data with respect to the experimental load. S The result is the result of normalizing the simulation data with respect to the test load, where f is the vibration frequency; t1, t2, t3, s1, s2, s3 are constants.

[0049] In some embodiments, to ensure the accuracy and stability of the experimental data, static tests are conducted, and the static data obtained from the static tests is used to verify the experimental data. Static tests include setting strain sensors along the force transmission path of the structural model; applying a static load with a vibration frequency of zero at the corresponding position on the structural model; and measuring static data using the strain sensors. Further details regarding static tests are similar to those of the dynamic tests described in step 110 and will not be repeated here. The static data obtained from the static tests is essentially frequency-dependent structural strain data. The structural strain in the static tests is primarily controlled by the structural static stiffness K. Therefore, the static data obtained from the static tests should be the same as or close to the constant term in the quadratic equation fitted to the experimental data. By comparing the constant term in the quadratic equation fitted to the static data and the experimental data, the accuracy and stability of the experimental data can be verified. If, at the same vibration frequency, the constant terms of the static data and the experimental data are not the same or close, the experimental data can be re-measured at that vibration frequency, or the constant term of the experimental data can be replaced with the static data, thereby ensuring the accuracy and stability of the experimental data.

[0050] Some embodiments in this specification establish a linear relationship between experimental and simulation data by fitting experimental and simulation data into quadratic expressions with respect to the vibration frequency.

[0051] like Figure 4A and Figure 4B As shown, Figure 4A , Figure 4B The horizontal axis represents the vibration frequency, and the vertical axis represents the strain. Figure 4A The dashed curve 41 in the figure represents the experimental data (or experimental value) curve. Figure 4B The dashed curve 42 in the figure is the result curve after fitting the experimental data (or called experimental fitting). The trend of the result curve 42 after fitting the experimental data with the vibration frequency is consistent with the trend of the experimental data curve 41 with the vibration frequency. The result curve 42 after fitting the experimental data can characterize the experimental data curve 41. Figure 4A The solid curve 43 in the figure represents the simulation data (or calculated value) curve. Figure 4BThe solid curve 44 in the figure represents the result curve after fitting (or calculating) the simulation data. The trend of the result curve 44 with vibration frequency is consistent with the trend of the simulation data curve 43 with vibration frequency. The result curve 44 can characterize the simulation data curve 43. Moreover, comparing curves 41 and 43, there is a discrepancy between the trends of the simulation data and the experimental data, indicating that the simulation data cannot completely and accurately reflect the actual load borne by the structural model. By determining the linear relationship between the simulation data and the experimental data based on the fitting results of the experimental data and the fitting results of the simulation data, it is easier to find the accurate linear relationship between the two. Under the premise of having simulation data but not being able to measure and know the load, combining the simulation data with the linear relationship can lead to the experimental data, that is, the real load.

[0052] In some embodiments, determining the linear relationship between simulation data and experimental data specifically includes:

[0053] S T =t1·f 2 +t2·f+t3 and S S =s1·f 2 Data correlation analysis was performed using +s2·f+s3, based on the structural dynamic stiffness K. S The expression for the quadratic term coefficient is mainly determined by the structural mass. The difference between the simulation and experimental masses is small. The relationship between the simulation data and the experimental data can be fitted using a linear function. The fitted relationship between the simulation data and the experimental data is as follows:

[0054] S T =A·S s +B;

[0055] Where A and B are constants, A is the coefficient of the linear term, which is related to the frequency, and B is related to the static data. Since the relationship between the fitted simulation data and the experimental data is a linear function, there is a linear relationship between the simulation data and the experimental data.

[0056] See also Figure 4A As shown in Figure B, the structural model exhibits a resonant frequency within the target frequency range, approximately 350Hz. Experimental data fluctuate drastically near this resonant frequency. To reduce error, a piecewise fitting approach can be employed. A frequency within the target frequency range, but lower than the resonant frequency, is designated as the piecewise frequency. For example, Figure 4A The segmented frequencies in Figure B can be determined to be within the range of 250Hz-300Hz. The experimental data corresponding to the frequencies on both sides of the segmented frequency will be fitted piecewise. The frequencies on both sides of the segmented frequency refer to frequencies within the target frequency range that are lower than the segmented frequency and frequencies within the target frequency range that are higher than the segmented frequency.

[0057] To facilitate the determination of the relationship between simulation and experimental data, the simulation data corresponding to frequencies on both sides of the segmented frequency are piecewise fitted. The relationship between simulation and experimental data is determined on both sides of the segmented frequency, and the data at the segmented frequency can be arbitrarily included in the fit before or after the segmented frequency. Since the coefficient A of the first term in the relationship between simulation and experimental data is frequency-dependent, the coefficient A of the first term in the relationship between simulation and experimental data on both sides of the segmented frequency is represented as A1 and A2, respectively. Taking a segmented frequency of 260Hz as an example, the curve of coefficient A1 in the relationship between simulation and experimental data as a function of frequency in the range before 260Hz, i.e., frequencies less than 260Hz, is shown below. Figure 5 As shown, in the range beyond 260Hz, i.e., frequencies greater than 260Hz, the curve of coefficient A2 in the relationship between simulation data and experimental data as a function of frequency is as follows: Figure 6 As shown. Before and after the resonance frequency, due to the resonance effect of the structural model, the coefficient A of the first term in the relationship between simulation and experimental data changes drastically near the resonance frequency. To reduce the error of A, piecewise fitting is performed based on piecewise frequencies to determine the coefficients A of the first term before and after the piecewise frequencies, namely A1 and A2, as shown. Figure 5 As shown, A1 and A2 determined by piecewise fitting are indeed in different ranges, with obvious differences, indicating that piecewise fitting is necessary.

[0058] Therefore, when the structural model has a resonant frequency within the target frequency range, a frequency within the target frequency range that is less than the resonant frequency will be used as the segment frequency. The experimental data corresponding to the frequencies on both sides of the segment frequency will be fitted piecewise to improve the accuracy of the fitting results.

[0059] Step 140: Based on the simulation strain data and linear relationship of the applied structure, determine the dynamic load of the applied structure.

[0060] The linear relationship between simulation data and experimental data can be inferred to be applicable to actual application structures. The simulation strain data W for the actual application structure is then determined. s Simulated strain data W s Simulation data S of the structural model S Correspondingly, and based on the linear relationship determined in step 130, the strain data W of the applied structure can be derived. T Strain data W of the applied structure T Experimental data S of structural model T Correspondingly.

[0061] Because there is a certain gap between simulated strain data and the actual strain data of the applied structure, it is necessary to improve the accuracy of the determined strain data in order to improve the accuracy of the determined load. By conducting preliminary experiments to determine the linear relationship between simulated and experimental data, the simulated strain data of the applied structure is determined. Instead of directly using the simulated strain data as the actual strain data, the actual strain data is determined through the linear relationship between simulated and actual strain data, thus improving the accuracy of the determined strain data.

[0062] In some embodiments, the simulated strain data of the applied structure is obtained through the overall dynamic model corresponding to the applied structure, wherein the overall dynamic model is a physical model. Based on the result S of the test data normalized with respect to the test load determined in step 130... T From this, we can derive the dynamic load F on the overall application structure as a function of frequency under operating conditions as follows:

[0063] F = W T / S T .

[0064] Secondly, some embodiments of this specification provide a dynamic load determination device, which includes a memory and a processor.

[0065] The memory is used to store data and / or instructions. For example, the memory stores instructions or programs that can be invoked by a processor. As another example, the memory stores processing data output by the processor. In some embodiments, the memory is used to store the experimental data obtained in step 110 and the simulation data obtained in step 110. In some embodiments, the memory is used to store the linear relationship between the simulation data output by the processor and the experimental data. In some embodiments, the memory is used to directly store the linear relationship between the simulation data and the experimental data described in the above embodiments, wherein the linear relationship is determined in advance by steps 110-130, which can be executed by a separately configured processing device. In some embodiments, the memory includes one or more storage components, each of which can be a separate device or part of another device. In some embodiments, the memory is implemented on a cloud platform.

[0066] The processor processes data and / or information from at least one component in the dynamic load determination device or an external data source. For example, the processor acquires and processes instructions, programs, and linear relationship data stored in memory via a network. In some embodiments, the processor acquires experimental data and simulation data stored in memory, runs a preset calculation program to determine the linear relationship between the simulation data and the experimental data, and outputs the linear relationship to memory. In some embodiments, the processor acquires a whole-machine dynamics model stored in memory, controls the operation of the whole-machine dynamics model, and acquires simulation application data output by the whole-machine dynamics model. In some embodiments, the processor acquires linear relationships stored in memory, processes the linear relationships and simulation application data, and determines the dynamic load on the application structure. In some embodiments, the processor is local or remote. In some embodiments, the processing device is implemented on a cloud platform.

[0067] Furthermore, this specification also provides an aero-engine including the dynamic load determination device described in the above embodiments, used to determine the radial load on the rotor support structure. The rotor support structure is subjected to circumferential excitation by the rotor. Because the rotor is rotating, the radial load applied to the rotor support structure by the rotor also exhibits a rotational state as the rotor rotates. Therefore, the radial load borne by the rotor support structure is a dynamic load with a rotational tendency.

[0068] In some embodiments, the aero-engine uses a dynamic load determination device to monitor the radial load on the rotor bearing during engine operation online. In some embodiments, the aero-engine includes an alarm, which is communicatively connected to a processor included in the dynamic load determination device. After determining the dynamic load of the bearing, the processor compares the dynamic load with a preset load threshold. If the dynamic load exceeds the load threshold, the processor activates the alarm. In some embodiments, the load threshold may be determined by prior testing and pre-stored in the memory included in the dynamic load determination device.

[0069] The basic concepts have been described above. It is clear that the detailed disclosure above is merely illustrative and does not constitute a limitation of this specification, especially for those skilled in the art. Furthermore, unless expressly stated in the claims, the order of elements and sequences, the use of numbers and letters, or other names in this specification are not intended to limit the order of the processes and methods described herein. Although various examples of currently considered useful embodiments of the invention have been discussed in the foregoing disclosure, it should be understood that such details are for illustrative purposes only, and the appended claims are not limited to the disclosed embodiments. Rather, the claims are intended to cover all modifications and equivalent combinations that conform to the substance and scope of the embodiments described herein.

Claims

1. A method for determining dynamic loads, characterized in that, The determination method includes: Acquire experimental data, which is determined through dynamic experiments based on the structural model corresponding to the application structure. Acquire simulation data, which is determined through simulation calculations based on the simulation model corresponding to the structural model; The experimental data and the simulation data are respectively fitted into quadratic equations with respect to the vibration frequency to determine the linear relationship between the experimental data and the simulation data; Based on the simulated strain data of the application structure and the linear relationship, the dynamic load of the application structure is determined.

2. The method for determining dynamic load according to claim 1, characterized in that, The structural model is consistent with the structure of the application structure.

3. The method for determining dynamic load according to claim 1, characterized in that, The simulated strain data of the application structure is obtained through the overall dynamic model corresponding to the application structure.

4. The method for determining dynamic load according to claim 1, characterized in that, The dynamic test includes: Strain sensors are installed along the force transmission path of the structural model; A test load with a vibration frequency varying within the target frequency range is applied at the corresponding position on the structural model; The strain sensor measures the test data.

5. The method for determining dynamic load according to claim 4, characterized in that, When the structural model has a resonant frequency within the target frequency range, a frequency within the target frequency range that is less than the resonant frequency is taken as a segmented frequency, and the experimental data corresponding to the frequencies on both sides of the segmented frequency are fitted in segments.

6. The method for determining dynamic load according to claim 1, characterized in that, The determination method further includes: Static tests were conducted on the structural model to calibrate the quadratic equation. The static test includes: Strain sensors are installed along the force transmission path of the structural model; A static load with a vibration frequency of zero is applied at the corresponding position on the structural model; The strain sensor measures static data; Compare the constant term in the quadratic expression of the static data with that of the experimental data.

7. A device for determining dynamic loads, characterized in that, The determining device is used to execute the dynamic load determining method according to claim 1, and the determining device includes a memory and a processor; The memory is used to store the linear relationship; The processor is used to acquire the simulated strain data and the linear relationship to determine the dynamic load of the applied structure.

8. The dynamic load determination device according to claim 7, characterized in that, The memory is used to store the overall dynamics model corresponding to the application structure; The processor is used to calculate the simulated strain data through the overall dynamic model.

9. An aircraft engine, characterized in that, The device includes the dynamic load determination device according to any one of claims 7 to 8, the device being used to determine the radial load on the rotor support structure.

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