System and method for detecting rotation intensity of runner plate of airplane blade

Abstract

The invention discloses a system and method for detecting the rotation strength of an aircraft blade runner plate, and relates to the technical field of mechanical detection, and the system comprises a static balance and dynamic balance test module which carries out the static balance test and dynamic balance test of the aircraft blade runner plate; the static balance control module compares the static balance state data before and after the installation of the stress piece, and adjusts the installation of the stress piece according to the comparison result; the dynamic balance control module compares the dynamic balance state data before and after the installation of the stress piece, adjusts the installation of the stress piece according to the comparison result, and judges the correlation between each component of the vibration signal and the vibration signal before the installation of the stress piece; and the rotation intensity detection module is used for removing components which are weakly related to the vibration signals before the stress sheet is installed, obtaining new vibration signals after reconstruction, and detecting the rotation intensity through the new vibration signals, so that the interference of the mass of the sensor on the accuracy of a rotation intensity detection result is reduced, and the overall detection precision is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of mechanical detection, and in particular to a system and method for detecting the rotational strength of a blade flow channel plate of an aircraft. Background Art

[0002] In the aviation industry, aircraft blade runner plates are key components of aircraft engines. Their rotational strength directly affects the performance, stability and safety of the engine. Aircraft blade runner plates need to withstand extremely high centrifugal forces and airflow impacts during operation. Therefore, the strength and stability of their structure are crucial. However, due to the influence of factors such as manufacturing process, material properties and operating environment, aircraft blade runner plates may experience defects such as fatigue and cracks during long-term use, which in turn cause problems such as increased vibration and decreased rotational strength. This will not only reduce the working efficiency of the engine, but may also pose a serious threat to flight safety.

[0003] Traditional methods for testing the rotational strength of aircraft blade runner plates mainly rely on static testing and dynamic testing. Static testing evaluates the structural strength of blade runner plates by measuring the stress distribution and deformation of the blade runner plates in a static state. However, this method cannot fully simulate the dynamic environment of the blade runner plates in actual work, so the test results have certain limitations. Dynamic testing evaluates the rotational strength by simulating the working conditions of the blade runner plates in a rotating state and measuring their vibration frequency, amplitude and other parameters.

[0004] In addition, traditional detection methods mainly rely on strain measurement lines and other means, and measure by directly placing sensors such as strain gauges in the area to be tested. However, the sensor itself has a certain quality. This quality factor will affect the static balance and dynamic balance of the blade flow plate during the detection process, resulting in a decrease in the accuracy of the rotational strength test results. Summary of the invention

[0005] 1. Technical issues to be resolved In view of the deficiencies in the prior art, the present invention provides a system and method for detecting the rotational strength of an aircraft blade flow channel plate. By performing static and dynamic balance tests on the aircraft blade flow channel plate and making adjustments, the vibration signal is decomposed, and components weakly correlated with the vibration signal before the stress sheet is installed are removed. After reconstruction, a new vibration signal is obtained, and the rotational strength is detected by the new vibration signal, thereby reducing the interference of the sensor's own mass on the accuracy of the rotational strength detection result, thereby improving the overall detection accuracy.

[0006] (II) Technical solution To achieve the above objectives, the present invention is implemented through the following technical solutions: A system for detecting the rotation strength of a flow channel plate of an aircraft blade, comprising: Static balance and dynamic balance test module, which performs static balance test and dynamic balance test on the aircraft blade flow channel plate without installing sensors, and records static balance state data and dynamic balance state data; The static balance control module uses finite element analysis software to mesh the aircraft blade flow channel plate, determine the final mesh density, install stress sheets at the mesh intersections, and perform static balance tests. The static balance state data before and after the installation of the stress sheets are compared, and the installation of the stress sheets is adjusted according to the comparison results. The dynamic balance control module performs a dynamic balance test, compares the dynamic balance status data before and after the stress sheet is installed, adjusts the installation of the stress sheet according to the comparison result, performs a dynamic balance test on the adjusted aircraft blade flow channel plate again, extracts the vibration signal, decomposes the vibration signal into several IMF components and a residual signal, and determines the correlation between each IMF component and the vibration signal before the stress sheet is installed; The rotation strength detection module installs the aircraft blade flow channel plate to the rotation strength detection equipment, collects vibration signals in real time, decomposes and reconstructs the vibration signals to obtain new vibration signals, extracts the amplitude and vibration frequency from the new vibration signals, and issues an early warning if the current amplitude exceeds the amplitude threshold or the vibration frequency exceeds the vibration frequency threshold.

[0007] Furthermore, the geometric center position is determined according to the shape of the aircraft blade flow channel plate, the aircraft blade flow channel plate is placed on a test bench, the geometric center of the aircraft blade flow channel plate is clamped using a point contact fixture, and a three-axis level is placed on the plane of the aircraft blade flow channel plate to record the static balance state data of the aircraft blade flow channel plate, including the inclination angles in the X, Y, and Z directions; the aircraft blade flow channel plate is fixed on a dynamic balancing test device to rotate the aircraft blade flow channel plate at a fixed speed, and the dynamic balance state data during the rotation process is recorded, including the vibration signal, vibration frequency, amplitude, and phase.

[0008] Furthermore, the final mesh density is determined, including: According to the geometric shape of the aircraft blade flow plate, finite element analysis software is used to perform preliminary mesh division, set the initial mesh density and analysis parameters, and the analysis parameters include material properties, boundary conditions, and loads; use the initial mesh density and analysis parameters to perform finite element analysis, record the analysis results, including the displacement, stress, and strain of the mesh intersections, adjust the mesh density, including increasing or decreasing the mesh density in fixed increments, use the adjusted mesh density to perform finite element analysis, and record the analysis results.

[0009] Furthermore, the analysis results under different mesh densities are compared, and the changes in the analysis results, including displacement error and stress error, are calculated. If the change in the analysis results no longer changes or is less than a preset change threshold as the mesh density increases or decreases, the mesh is considered to have converged, and the mesh density at this time is used as the final mesh density.

[0010] Furthermore, the static balance state data before and after the installation of the stress gauge are compared, and the installation of the stress gauge is adjusted according to the comparison result, including: A tilt angle deviation threshold is set in advance, and the static balance state data before and after the installation of the stress sheet are compared. The tilt angle changes in the X, Y, and Z directions are calculated respectively. If the tilt angle change in any of the X, Y, and Z directions is greater than or equal to the tilt angle deviation threshold, the installation position of the stress sheet is adjusted or the number of stress sheets is adjusted until the tilt angle change in any of the X, Y, and Z directions is less than the tilt angle deviation threshold.

[0011] Furthermore, the dynamic balance state data before and after the stress gauge is installed is compared, and the installation of the stress gauge is adjusted according to the comparison result, including: The dynamic balance deviation thresholds corresponding to the dynamic balance status data are set respectively, including the thresholds corresponding to the vibration frequency, amplitude and phase, and the dynamic balance status data before and after the installation of the stress sheet are compared. If the change in any dynamic balance status data is greater than or equal to the dynamic balance deviation threshold, the installation position of the stress sheet is adjusted or the number of stress sheets is adjusted until the change in any dynamic balance status data is less than the dynamic balance deviation threshold.

[0012] Furthermore, the vibration signal is decomposed into several IMF components and a residual signal. The specific decomposition steps are as follows: S1: Add Gaussian white noise with a mean of 0 to the original vibration signal N times to construct N noisy signal sequences: ,in, represents the i-th noisy signal sequence, represents the original vibration signal, represents the noise added for the i-th time; S2: Perform EMD decomposition on each noisy signal sequence to obtain several IMF components; S3: Take an overall average of the first-order IMF components of all noisy signal sequences to obtain the first-order IMF components decomposed by CEEMDAN: ,in, represents the averaged first-order IMF component, represents the first-order IMF component of the i-th noisy signal sequence, and N represents the number of times noise is added; S4: Calculate the residual signal after removing the j-th order IMF component: ,in, represents the residual signal after removing the j-th order IMF component, represents the j-th order IMF component; S5: Add Gaussian white noise to the residual signal again and perform EMD decomposition to obtain new IMF components; S6: perform overall averaging on the newly obtained IMF components to obtain the j+1th order IMF components decomposed by CEEMDAN; S7: Use the residual signal as the new original signal and repeat the above S4 to S6 until the residual signal becomes a monotonic function and cannot be further decomposed.

[0013] Furthermore, the correlation between each IMF component and the vibration signal before the stress sheet is installed is determined, including: For each IMF component, calculate the correlation coefficient between it and the vibration signal before the stress gauge is installed: ; in, represents the correlation coefficient between the kth IMF component and the vibration signal before the stress gauge is installed, represents the kth IMF component, Indicates the vibration signal before installing the stress gauge. and Respectively and The average value of , t represents the time point, and T represents the number of time points; Set the correlation coefficient threshold. If the current IMF component is greater than or equal to the correlation coefficient threshold, it is judged that the component is strongly correlated with the vibration signal before the stress sheet is installed. If the current IMF component is less than the correlation coefficient threshold, it is judged that the component is weakly correlated with the vibration signal before the stress sheet is installed.

[0014] Furthermore, the vibration signal is decomposed and reconstructed to obtain a new vibration signal, including: The vibration signal is decomposed using the CEEMDAN algorithm. The vibration signal is decomposed into several IMF components and a residual signal. The IMF components that are weakly correlated with the vibration signal before the stress sheet is installed are removed, and the remaining IMF components are reconstructed to obtain a new vibration signal: , where h(x) represents the new vibration signal, represents the qth residual IMF component.

[0015] A method for detecting the rotation strength of a flow channel plate of an aircraft blade comprises the following steps: Step 1: Without installing the sensor, perform static balance test and dynamic balance test on the aircraft blade flow channel plate, and record the static balance state data and dynamic balance state data; Step 2: Use finite element analysis software to mesh the aircraft blade flow channel plate, determine the final mesh density, install stress sheets at the mesh intersections, and perform static balance tests. Compare the static balance state data before and after the installation of the stress sheets, and adjust the installation of the stress sheets according to the comparison results. Step 3: Perform a dynamic balance test, compare the dynamic balance status data before and after the stress sheet is installed, adjust the installation of the stress sheet according to the comparison result, perform a dynamic balance test on the adjusted aircraft blade flow channel plate again, extract the vibration signal, decompose the vibration signal into several IMF components and a residual signal, and determine the correlation between each IMF component and the vibration signal before the stress sheet is installed; Step 4: Install the aircraft blade flow channel plate to the rotation strength detection equipment, collect vibration signals in real time, decompose and reconstruct the vibration signals to obtain new vibration signals, extract the amplitude and vibration frequency from the new vibration signals, and issue an early warning if the current amplitude exceeds the amplitude threshold or the vibration frequency exceeds the vibration frequency threshold.

[0016] (III) Beneficial effects The present invention provides a system and method for detecting the rotation strength of a blade flow channel plate of an aircraft, which has the following beneficial effects: (1) By performing static and dynamic balancing tests without installing the sensor, the influence of the sensor's own mass on the balance state of the blade runner plate can be eliminated, thereby more accurately evaluating the rotational strength of the blade runner plate, avoiding the error caused by sensor mass in traditional detection methods, and improving the accuracy of the detection results.

[0017] (2) By using finite element analysis software to mesh the aircraft blade runner plate and determine the final mesh density, the stress distribution of the blade runner plate can be accurately simulated. By installing stress gauges at the intersection of the grids, the stress changes of the blade runner plate during rotation can be more accurately measured, thereby improving the accuracy of rotational strength detection. By comparing the static balance state data before and after the installation of the stress gauges and adjusting the installation position and number of the stress gauges based on the comparison results, it can be ensured that the stress gauges can accurately measure the stress changes without affecting the static balance state of the blade runner plate.

[0018] (3) By comparing the vibration signals before and after the installation of the stress gauge and decomposing the vibration signals into IMF components and residual signals, the influence of the stress gauge on the vibration characteristics of the blade flow plate can be analyzed more accurately. This helps to reduce the interference of the sensor's own mass on the accuracy of the rotational strength test results, thereby improving the overall detection accuracy.

[0019] (4) By first performing CEEMDAN decomposition on the vibration signal, then removing the IMF components that are weakly correlated with the vibration signal before the stress sheet is installed, and reconstructing the remaining IMF components, a new vibration signal that is purer and closer to the actual vibration state of the blade flow plate can be obtained. This helps to more accurately extract the amplitude and vibration frequency, thereby improving the accuracy of rotational strength detection. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the structure of the aircraft blade flow channel plate rotation strength detection system of the present invention; Figure 2 The present invention is a schematic diagram of the steps of the method for detecting the rotational strength of a blade flow channel plate of an aircraft. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0022] See also Figure 1 The present invention provides a rotation strength detection system for an aircraft blade flow channel plate, comprising: a static balance and dynamic balance test module, a static balance control module, a dynamic balance control module and a rotation strength detection module; wherein, Static balance and dynamic balance test module, which performs static balance test and dynamic balance test on the aircraft blade flow channel plate without installing sensors, and records static balance state data and dynamic balance state data; Without installing sensors, perform a static balance test on the aircraft blade runner plate, determine the geometric center position according to the shape of the aircraft blade runner plate, place the aircraft blade runner plate on the test bench, use a point contact fixture to clamp the geometric center of the aircraft blade runner plate, ensure that the aircraft blade runner plate is not subjected to any additional stress or deformation when it is stationary, use a three-axis level to place it on the plane of the aircraft blade runner plate, ensure that it is in close contact with the aircraft blade runner plate, and record the static balance state data of the aircraft blade runner plate, including the tilt angles in the three directions of X, Y, and Z; Without installing sensors, perform a dynamic balancing test on the aircraft blade flow plate, fix the aircraft blade flow plate on a dynamic balancing test device, such as a dynamic balancing machine, ensure that the fixing method is stable and does not cause additional stress or deformation to the aircraft blade flow plate, set parameters such as rotation speed and measurement accuracy, start the balancing test device, rotate the aircraft blade flow plate at a fixed speed, and record the dynamic balancing state data during the rotation process, including but not limited to vibration signals, vibration frequency, amplitude and phase, etc.; It should be noted that the geometric center position refers to the center point of the aircraft blade runner plate in physical shape. This point is usually relative to the shape and size of the blade runner plate. The purpose of determining the geometric center is to ensure that the aircraft blade runner plate can be evenly stressed during the static balance test and avoid measurement errors caused by unbalanced clamping methods. By measuring the size of the aircraft blade runner plate, the geometric center position is determined using geometric methods (such as calculating the center of mass) or special software; The point contact fixture is designed to apply only a small clamping force to the geometric center of the aircraft blade runner plate during the test to avoid additional stress or deformation of the blade runner plate. The fixture should be designed to ensure that the contact area with the aircraft blade runner plate is as small as possible, and the clamping force should be stable enough to keep the position of the aircraft blade runner plate unchanged when it is stationary; By performing static and dynamic balancing tests without installing the sensor, the influence of the sensor's own mass on the balance state of the blade channel plate can be eliminated, thereby more accurately evaluating the rotational strength of the blade channel plate, avoiding errors caused by sensor mass in traditional detection methods, and improving the accuracy of the detection results.

[0023] The static balance control module uses finite element analysis software to mesh the aircraft blade flow channel plate, determine the final mesh density, install stress sheets at the mesh intersections, and perform static balance tests. The static balance state data before and after the installation of the stress sheets are compared, and the installation of the stress sheets is adjusted according to the comparison results. According to the geometric shape of the aircraft blade flow plate, use finite element analysis software (such as ANSYS, Abaqus, etc.) to perform preliminary mesh division, set an initial mesh density, and configure the material properties, boundary conditions, loads and other analysis parameters required by the finite element analysis software; Perform finite element analysis using the initial mesh density and analysis parameters, record the analysis results, including displacements, stresses, and strains at mesh intersections, adjust the mesh density, including increasing the mesh density by fixed increments (i.e., decreasing the mesh size) or decreasing the mesh density (i.e., increasing the mesh size), perform finite element analysis using the adjusted mesh density, and record the analysis results; Compare the analysis results under different mesh densities and calculate the changes in the analysis results, including displacement errors and stress errors: , where Δμ represents the displacement error, represents the displacement analysis result before adjustment, represents the adjusted displacement analysis results, , where Δσ represents the stress error, represents the stress analysis results before adjustment, represents the adjusted stress analysis results; If the change in the analysis result no longer changes or is less than the preset change threshold as the mesh density increases or decreases, the mesh is considered to have converged, and the mesh density at this time is taken as the final mesh density; It should be noted that the setting of the change threshold should ensure the accuracy of the analysis. If the threshold is set too high, it may lead to insufficient mesh density and fail to accurately capture the details of the stress distribution; if the threshold is set too low, it may increase unnecessary calculations and reduce analysis efficiency. A change threshold can be initially set, and the setting of the change threshold can be gradually optimized through multiple tests and adjustments. This method is also applicable to the thresholds set later. Mark the installation point of the stress sheet at the intersection of the grid lines, fix the stress sheet on the installation point, perform a static balance test on the aircraft blade flow channel plate after the stress sheet is installed, and record the static balance state data after the stress sheet is installed, including the tilt angles in the three directions of X, Y, and Z; Preset the tilt angle deviation threshold, compare the static balance data before and after the stress sheet is installed, and calculate the tilt angle changes in the X, Y, and Z directions respectively. ,in, represents the change in tilt angle, Indicates the tilt angle before installing the stress piece. Indicates the tilt angle after the stress piece is installed. If the tilt angle change in any of the three directions X, Y, and Z is greater than or equal to the tilt angle deviation threshold, the installation position of the stress piece is adjusted or the number of stress pieces is adjusted until the tilt angle change in any of the three directions X, Y, and Z is less than the tilt angle deviation threshold; By using finite element analysis software to mesh the aircraft blade runner plate and determine the final mesh density, the stress distribution of the blade runner plate can be accurately simulated. Installing stress gauges at the intersection of the grids can more accurately measure the stress changes of the blade runner plate during rotation, thereby improving the accuracy of rotational strength detection. By comparing the static balance state data before and after the installation of the stress gauges and adjusting the installation position and number of the stress gauges based on the comparison results, it can be ensured that the stress gauges can accurately measure stress changes without affecting the static balance state of the blade runner plate.

[0024] The dynamic balance control module performs a dynamic balance test, compares the dynamic balance status data before and after the stress sheet is installed, adjusts the installation of the stress sheet according to the comparison result, performs a dynamic balance test on the adjusted aircraft blade flow channel plate again, extracts the vibration signal, decomposes the vibration signal into several IMF components and a residual signal, and determines the correlation between each IMF component and the vibration signal before the stress sheet is installed; After completing the static balance control, perform a dynamic balance test on the aircraft blade flow channel plate after installing the stress plate, fix the aircraft blade flow channel plate on the dynamic balance test equipment again, ensure that the fixing method is consistent with the previous one, avoid additional stress or deformation, set the same parameters such as rotation speed and measurement accuracy, start the balance test equipment, rotate the aircraft blade flow channel plate at a fixed speed, and record the dynamic balance state data during the rotation process, including but not limited to vibration frequency, amplitude and phase, etc.; The dynamic balance deviation thresholds corresponding to the dynamic balance state data are respectively set, including thresholds corresponding to the vibration frequency, amplitude and phase, etc., and the dynamic balance state data before and after the installation of the stress sheet are compared. If the change amount of any dynamic balance state data is greater than or equal to the dynamic balance deviation threshold, the installation position of the stress sheet is adjusted or the number of stress sheets is adjusted until the change amount of any dynamic balance state data is less than the dynamic balance deviation threshold; The aircraft blade runner plate after static and dynamic balancing is tested again to extract the vibration signal. The extracted vibration signal is decomposed using CEEMDAN to obtain several IMF components and a residual signal. The specific decomposition steps are as follows: S1: Preprocess the original vibration signal, such as denoising, filtering, etc., add Gaussian white noise with a mean of 0 to the original vibration signal N times, and construct N noisy signal sequences: ,in, represents the i-th noisy signal sequence, represents the original vibration signal, represents the noise added for the i-th time; S2: Perform EMD decomposition on each noisy signal sequence to obtain several IMF components; S3: Take an overall average of the first-order IMF components of all noisy signal sequences to obtain the first-order IMF components decomposed by CEEMDAN: ,in, represents the averaged first-order IMF component, represents the first-order IMF component of the i-th noisy signal sequence, and N represents the number of times noise is added; S4: Calculate the residual signal after removing the j-th order IMF component: ,in, represents the residual signal after removing the j-th order IMF component, represents the j-th order IMF component; S5: Add Gaussian white noise to the residual signal again and perform EMD decomposition to obtain new IMF components; S6: perform overall averaging on the newly obtained IMF components to obtain the j+1th order IMF components decomposed by CEEMDAN; S7: Take the residual signal as the new original signal and repeat the above S4 to S6 until the residual signal is a monotonic function and cannot be further decomposed; After the above steps, several IMF components and a final residual signal are obtained; For each IMF component, calculate the correlation coefficient between it and the vibration signal before the stress gauge is installed: ; in, represents the correlation coefficient between the kth IMF component and the vibration signal before the stress gauge is installed, represents the kth IMF component, Indicates the vibration signal before installing the stress gauge. and Respectively and The average value of , t represents the time point, and T represents the number of time points; Set the correlation coefficient threshold. If the current IMF component is greater than or equal to the correlation coefficient threshold, it is judged that the component is strongly correlated with the vibration signal before the stress plate is installed. If the current IMF component is less than the correlation coefficient threshold, it is judged that the component is weakly correlated with the vibration signal before the stress plate is installed. By comparing the vibration signals before and after the installation of the stress sheet and decomposing the vibration signals into IMF components and residual signals, the influence of the stress sheet on the vibration characteristics of the blade flow plate can be analyzed more accurately, which helps to reduce the interference of the sensor's own mass on the accuracy of the rotational strength test results, thereby improving the overall detection accuracy.

[0025] The rotation strength detection module installs the aircraft blade flow channel plate to the rotation strength detection equipment, collects vibration signals in real time, decomposes and reconstructs the vibration signals to obtain new vibration signals, extracts the amplitude and vibration frequency from the new vibration signals, and issues an early warning if the current amplitude exceeds the amplitude threshold or the vibration frequency exceeds the vibration frequency threshold.

[0026] The aircraft blade flow channel plate is installed on the rotation strength testing device, and the rotation strength testing device is started to rotate the aircraft blade flow channel plate at a predetermined speed. During the rotation process, a sensor is used to collect vibration signals in real time; The vibration signal is decomposed using the CEEMDAN algorithm. The vibration signal is decomposed into several IMF components and a residual signal. The IMF components that are weakly correlated with the vibration signal before the stress sheet is installed are removed, and the remaining IMF components are reconstructed to obtain a new vibration signal: , where h(x) represents the new vibration signal, represents the qth residual IMF component; Extract the amplitude and vibration frequency from the new vibration signal, pre-set the amplitude threshold and vibration frequency threshold, if the current amplitude exceeds the amplitude threshold or the vibration frequency exceeds the vibration frequency threshold, it is judged that the rotation intensity of the current aircraft blade flow channel plate may be too high, there is a potential safety risk, and an early warning is issued, otherwise, no processing is performed; By first performing CEEMDAN decomposition on the vibration signal, then removing the IMF components weakly correlated with the vibration signal before installing the stress sheet, and reconstructing the remaining IMF components, a new vibration signal that is purer and closer to the actual vibration state of the blade flow plate can be obtained, which helps to more accurately extract the amplitude and vibration frequency, thereby improving the accuracy of rotation strength detection.

[0027] See also Figure 2 The present invention also provides a method for detecting the rotation strength of a blade flow channel plate of an aircraft, comprising the following steps: Step 1: Without installing the sensor, perform static balance test and dynamic balance test on the aircraft blade flow channel plate, and record the static balance state data and dynamic balance state data; Step 2: Use finite element analysis software to mesh the aircraft blade flow channel plate, determine the final mesh density, install stress sheets at the mesh intersections, and perform static balance tests. Compare the static balance state data before and after the installation of the stress sheets, and adjust the installation of the stress sheets according to the comparison results. Step 3: Perform a dynamic balance test, compare the dynamic balance status data before and after the stress sheet is installed, adjust the installation of the stress sheet according to the comparison result, perform a dynamic balance test on the adjusted aircraft blade flow channel plate again, extract the vibration signal, decompose the vibration signal into several IMF components and a residual signal, and determine the correlation between each IMF component and the vibration signal before the stress sheet is installed; Step 4: Install the aircraft blade flow channel plate to the rotation strength detection equipment, collect vibration signals in real time, decompose and reconstruct the vibration signals to obtain new vibration signals, extract the amplitude and vibration frequency from the new vibration signals, and issue an early warning if the current amplitude exceeds the amplitude threshold or the vibration frequency exceeds the vibration frequency threshold.

[0028] In the application, the several formulas involved are all calculated by removing dimensions and taking their numerical values. The formula is a formula of the most recent real situation obtained by collecting a large amount of data and performing software simulation. The coefficients in the formula are set by technicians in this field according to actual conditions.

[0029] The above embodiments may be implemented in whole or in part by software, hardware, firmware or any other combination thereof. When implemented by software, the above embodiments may be implemented in whole or in part in the form of a computer program product. A person of ordinary skill in the art may appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein may be implemented in combination with electronic hardware, computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution.

[0030] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, and may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0031] The above description is only a specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application.

Claims

1. A system for detecting the rotational strength of a blade runner plate of an aircraft, characterized in that: include: Static balance and dynamic balance test module, which performs static balance test and dynamic balance test on the aircraft blade flow channel plate without installing sensors, and records static balance state data and dynamic balance state data; The static balance control module uses finite element analysis software to mesh the aircraft blade flow channel plate, determine the final mesh density, install stress sheets at the mesh intersections, and perform static balance tests. The static balance state data before and after the installation of the stress sheets are compared, and the installation of the stress sheets is adjusted according to the comparison results. The dynamic balance control module performs a dynamic balance test, compares the dynamic balance status data before and after the stress sheet is installed, adjusts the installation of the stress sheet according to the comparison result, performs a dynamic balance test on the adjusted aircraft blade flow channel plate again, extracts the vibration signal, decomposes the vibration signal into several IMF components and a residual signal, and determines the correlation between each IMF component and the vibration signal before the stress sheet is installed; The rotation strength detection module installs the aircraft blade flow channel plate to the rotation strength detection equipment, collects vibration signals in real time, decomposes and reconstructs the vibration signals to obtain new vibration signals, extracts the amplitude and vibration frequency from the new vibration signals, and issues an early warning if the current amplitude exceeds the amplitude threshold or the vibration frequency exceeds the vibration frequency threshold.

2. The system for detecting the rotational strength of a flow channel plate of an aircraft blade according to claim 1, characterized in that: Determine the geometric center position according to the shape of the aircraft blade runner plate, place the aircraft blade runner plate on the test bench, clamp the geometric center of the aircraft blade runner plate with a point contact fixture, place a three-axis level on the plane of the aircraft blade runner plate, and record the static balance state data of the aircraft blade runner plate, including the tilt angles in the three directions of X, Y, and Z; Fix the aircraft blade flow channel plate on the dynamic balancing test equipment, rotate the aircraft blade flow channel plate at a fixed speed, and record the dynamic balancing state data during the rotation process, including vibration signal, vibration frequency, amplitude and phase.

3. The system for detecting the rotational strength of a flow channel plate of an aircraft blade according to claim 1, characterized in that: Determine the final mesh density, including: According to the geometric shape of the aircraft blade flow plate, finite element analysis software is used to perform preliminary mesh division, set the initial mesh density and analysis parameters, and the analysis parameters include material properties, boundary conditions, and loads; use the initial mesh density and analysis parameters to perform finite element analysis, record the analysis results, including the displacement, stress, and strain of the mesh intersections, adjust the mesh density, including increasing or decreasing the mesh density in fixed increments, use the adjusted mesh density to perform finite element analysis, and record the analysis results.

4. The system for detecting the rotational strength of a flow channel plate of an aircraft blade according to claim 3, characterized in that: Compare the analysis results under different mesh densities, and calculate the changes in the analysis results, including displacement error and stress error. If the change in the analysis results no longer changes or is less than the preset change threshold as the mesh density increases or decreases, the mesh is considered to have converged, and the mesh density at this time is used as the final mesh density.

5. The system for detecting the rotational strength of a flow channel plate of an aircraft blade according to claim 1, characterized in that: Compare the static balance data before and after the installation of the stress gauge, and adjust the installation of the stress gauge according to the comparison results, including: A tilt angle deviation threshold is set in advance, and the static balance state data before and after the installation of the stress sheet are compared. The tilt angle changes in the X, Y, and Z directions are calculated respectively. If the tilt angle change in any of the X, Y, and Z directions is greater than or equal to the tilt angle deviation threshold, the installation position of the stress sheet is adjusted or the number of stress sheets is adjusted until the tilt angle change in any of the X, Y, and Z directions is less than the tilt angle deviation threshold.

6. The system for detecting the rotational strength of a flow channel plate of an aircraft blade according to claim 1, characterized in that: Compare the dynamic balance data before and after the installation of the stress gauge, and adjust the installation of the stress gauge according to the comparison results, including: The dynamic balance deviation thresholds corresponding to the dynamic balance status data are set respectively, including the thresholds corresponding to the vibration frequency, amplitude and phase, and the dynamic balance status data before and after the installation of the stress sheet are compared. If the change in any dynamic balance status data is greater than or equal to the dynamic balance deviation threshold, the installation position of the stress sheet is adjusted or the number of stress sheets is adjusted until the change in any dynamic balance status data is less than the dynamic balance deviation threshold.

7. The system for detecting the rotational strength of a flow channel plate of an aircraft blade according to claim 6, characterized in that: The vibration signal is decomposed into several IMF components and a residual signal. The specific decomposition steps are as follows: S1: Add Gaussian white noise with a mean of 0 to the original vibration signal N times to construct N noisy signal sequences: ,in, represents the i-th noisy signal sequence, represents the original vibration signal, represents the noise added for the i-th time; S2: Perform EMD decomposition on each noisy signal sequence to obtain several IMF components; S3: Take an overall average of the first-order IMF components of all noisy signal sequences to obtain the first-order IMF components decomposed by CEEMDAN: ,in, represents the averaged first-order IMF component, represents the first-order IMF component of the i-th noisy signal sequence, and N represents the number of times noise is added; S4: Calculate the residual signal after removing the j-th order IMF component: ,in, represents the residual signal after removing the j-th order IMF component, represents the j-th order IMF component; S5: Add Gaussian white noise to the residual signal again and perform EMD decomposition to obtain new IMF components; S6: perform overall averaging on the newly obtained IMF components to obtain the j+1th order IMF components decomposed by CEEMDAN; S7: Use the residual signal as the new original signal and repeat the above S4 to S6 until the residual signal becomes a monotonic function and cannot be further decomposed.

8. The system for detecting the rotational strength of a flow channel plate of an aircraft blade according to claim 7, characterized in that: Determine the correlation between each IMF component and the vibration signal before installing the stress gauge, including: For each IMF component, calculate the correlation coefficient between it and the vibration signal before the stress gauge is installed: ； in, represents the correlation coefficient between the kth IMF component and the vibration signal before the stress gauge is installed, represents the kth IMF component, Indicates the vibration signal before installing the stress gauge. and Respectively and The average value of , t represents the time point, and T represents the number of time points; Set the correlation coefficient threshold. If the current IMF component is greater than or equal to the correlation coefficient threshold, it is judged that the component is strongly correlated with the vibration signal before the stress sheet is installed. If the current IMF component is less than the correlation coefficient threshold, it is judged that the component is weakly correlated with the vibration signal before the stress sheet is installed.

9. The system for detecting the rotational strength of a flow channel plate of an aircraft blade according to claim 1, characterized in that: The vibration signal is decomposed and reconstructed to obtain a new vibration signal, including: The vibration signal is decomposed using the CEEMDAN algorithm. The vibration signal is decomposed into several IMF components and a residual signal. The IMF components that are weakly correlated with the vibration signal before the stress sheet is installed are removed, and the remaining IMF components are reconstructed to obtain a new vibration signal: , where h(x) represents the new vibration signal, represents the qth residual IMF component.

10. A method for detecting the rotation strength of a blade runner plate of an aircraft, using the system described in any one of claims 1 to 9, characterized in that: The following steps are involved: Step 1: Without installing the sensor, perform static balance test and dynamic balance test on the aircraft blade flow channel plate, and record the static balance state data and dynamic balance state data; Step 2: Use finite element analysis software to mesh the aircraft blade flow channel plate, determine the final mesh density, install stress sheets at the mesh intersections, and perform static balance tests. Compare the static balance state data before and after the installation of the stress sheets, and adjust the installation of the stress sheets according to the comparison results. Step 3: Perform a dynamic balance test, compare the dynamic balance status data before and after the stress sheet is installed, adjust the installation of the stress sheet according to the comparison result, perform a dynamic balance test on the adjusted aircraft blade flow channel plate again, extract the vibration signal, decompose the vibration signal into several IMF components and a residual signal, and determine the correlation between each IMF component and the vibration signal before the stress sheet is installed; Step 4: Install the aircraft blade flow channel plate to the rotation strength detection equipment, collect vibration signals in real time, decompose and reconstruct the vibration signals to obtain new vibration signals, extract the amplitude and vibration frequency from the new vibration signals, and issue an early warning if the current amplitude exceeds the amplitude threshold or the vibration frequency exceeds the vibration frequency threshold.

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