Comprehensive performance test method for undercarriage maintenance

Abstract

The invention relates to the technical field of undercarriage performance testing, in particular to a comprehensive performance testing method for undercarriage maintenance. The method comprises the following steps: performing static test on supporting structure areas of the undercarriage to obtain the health influence degree of each supporting structure area on the undercarriage; carrying out dynamic simulation test on the cushioning structure areas of the undercarriage to obtain the structural damage degree under each cushioning structure area; and finally, the comprehensive performance of the undercarriage is obtained by combining the structural damage degree of each cushioning structure area and the health influence degree of the supporting structure area on the undercarriage. Each cushioning structure area of the undercarriage can be monitored, and the purpose of evaluating the overall comprehensive performance of the undercarriage is achieved in combination with monitoring of a supporting structure area during static testing.

Description

Technical Field

[0001] The invention relates to the technical field of landing gear performance testing, and in particular to a comprehensive performance testing method for landing gear maintenance. Background Art

[0002] The comprehensive performance testing method for landing gear maintenance, with its comprehensiveness, accuracy and systematicness, has brought significant advantages to the field of aviation maintenance. It not only improves the safety of aircraft and extends the service life of landing gear, but also improves the quality and efficiency of maintenance, enhances fault prediction capabilities, and optimizes resource allocation.

[0003] The landing gear of an aircraft is a key component that withstands extreme shocks, vibrations, and loads, and its performance is directly related to the safety and flight stability of the aircraft. In the current routine monitoring and maintenance process, the single parts on the landing gear are mainly monitored, but there is currently no good evaluation solution for the damage assessment of the internal structure of the material during repeated use. However, when the material is subjected to repeated dynamic effects such as loads, shocks, and vibrations, material fatigue and stress concentration will affect the safety during flight, so the performance evaluation of the aircraft landing gear is crucial.

[0004] When the performance of the landing gear is currently tested, a simulation model is usually established to directly monitor the entire landing gear. However, it is difficult to determine the comprehensive performance of the landing gear through a single structural analysis of the landing gear. Summary of the invention

[0005] In order to solve the technical problem that the comprehensive performance of the landing gear cannot be determined by a single structural analysis of the landing gear, resulting in low accuracy in the performance evaluation of the landing gear, the purpose of the present invention is to provide a comprehensive performance testing method for landing gear maintenance, and the technical solution adopted is as follows: In a first aspect, an embodiment of the present invention provides a comprehensive performance testing method for landing gear maintenance, the method comprising: Obtain stress, displacement and vibration signals of the supporting structure area and the shock absorbing structure area of ​​the landing gear; Determine the degree of influence of each support structure area on the health of the landing gear based on the change amplitude, stress magnitude and total stress magnitude of each support structure area in the static test of the landing gear under different loads; Perform multiple ground taxiing simulations on the landing gear respectively, and determine the absorption ratio of the low-frequency vibration signal of each shock-absorbing structure area according to the displacement during the ground taxiing simulation; obtain the load size corresponding to the shock-absorbing structure area according to the vibration signal and the absorption ratio, and determine the load deviation degree corresponding to the shock-absorbing structure area of ​​the landing gear; correct the load deviation degree in combination with the vibration signal and the stress change, and obtain the structural damage degree of each shock-absorbing structure area; The comprehensive performance of the landing gear is obtained by combining the structural damage degree of each shock absorbing structure area and the health impact degree of the supporting structure area on the landing gear.

[0006] Preferably, determining the degree of influence of each support structure area on the health of the landing gear according to the change amplitude, stress magnitude and total stress magnitude of the landing gear support structure of each support structure area in the static test of the landing gear under different loads includes: Under static testing, analyze the changes in stress data of the landing gear support structure area under different loads to determine the degree of stress deviation; The degree of influence of each supporting structure area on the landing gear health is determined by combining the stress deviation degree, stress magnitude and total stress magnitude of the landing gear supporting structure of each supporting structure area under different loads.

[0007] Preferably, the analyzing, under static testing, changes in stress data of the supporting structure area of ​​the landing gear under different loads to determine the degree of stress deviation comprises: Calculate the slope of the stress curve consisting of the stresses at each load for each support structure area of ​​the landing gear as a single amplitude of change; Calculate the average of the single change amplitudes corresponding to all supporting structure areas of the landing gear under the same load as the overall change amplitude; The difference between the single variation amplitude and the overall variation amplitude is taken as the stress deviation degree of the supporting structure area of ​​the landing gear under each load.

[0008] Preferably, determining the degree of influence of each support structure area on the health of the landing gear according to the change amplitude, stress magnitude and total stress magnitude of the landing gear support structure of each support structure area of ​​the landing gear under different loads in the static test stress comprises: Calculate the average value of stress deviation degrees of different supporting structure areas of the landing gear under the same load as the stress deviation average value; Calculate the difference between the stress deviation degree of each supporting structure area of ​​the landing gear under the current load and the stress deviation average value corresponding to the same load as the overall deviation of each supporting structure area under the current load; Calculate the ratio of the stress magnitude of each supporting structure area of ​​the landing gear under the current load to the total stress magnitude of all supporting structures of the landing gear under the current load, as the stress proportion of each supporting structure area under the current load; The product of the overall deviation and the stress proportion of each supporting structure area under the current load is used as the individual influence of each supporting structure area on the landing gear under the current load; The sum of the individual influence of each supporting structure area on the landing gear under all loads is calculated as the health influence degree of each supporting structure area on the landing gear.

[0009] Preferably, the performing of multiple ground taxiing simulations on the landing gear and determining the absorption ratio of the low-frequency vibration signal of each shock-absorbing structure area according to the displacement during the ground taxiing simulation comprises: For any number of ground sliding simulations, the displacement size collected by each displacement monitoring device during the ground sliding simulation is obtained, the displacement size is converted into a frequency domain signal by Fourier transform, the sum of the energy of the frequency domain signal at different frequencies is calculated as the bandwidth energy, and the sum of the bandwidth energies of all displacement monitoring devices corresponding to the current shock absorbing structure area during the ground sliding simulation is used as the energy absorption of the shock absorbing structure area; The energy absorption of the shock absorbing structure area is used as the numerator, the low-frequency vibration signal in the vibration signal is used as the denominator, and the ratio formed by the numerator and the denominator is used as the fractional simulation absorption ratio of the low-frequency vibration signal in the current shock absorbing structure area; The absorption ratio of each shock-absorbing structure area obtained by multiple ground sliding simulations is averaged to obtain the absorption ratio of each shock-absorbing structure area.

[0010] Preferably, obtaining the load size corresponding to the shock absorbing structure area according to the vibration signal and the absorption ratio, and determining the load deviation degree corresponding to the shock absorbing structure area of ​​the landing gear includes: Obtain the vibration signal after removing the low-frequency vibration signal, calculate the product value of the magnitude of the vibration signal after removing the low-frequency vibration signal and the absorption ratio of the low-frequency vibration signal, as the first product; take the difference between the stress magnitude at the current acquisition moment and the first product as the load magnitude of the corresponding shock-absorbing structure area, recorded as the structural area load; Obtain the average value of the load magnitudes corresponding to all the seismic buffer structure regions at the current acquisition time as the regional load average; For any shock absorbing structure area of ​​the landing gear, the difference between the structural area load at the current collection moment and the average load of the area is used as the numerator, and the average load of the area is used as the denominator to obtain the load deviation degree of the load size corresponding to the shock absorbing structure area of ​​the landing gear at the current collection moment.

[0011] Preferably, the load deviation degree is corrected in combination with the vibration signal and the stress change to obtain the structural damage degree of each shock absorbing structure area, including: According to the vibration signal and the stress change, a correction coefficient of the load deviation degree is determined; in combination with the correction coefficient, the load deviation degree is corrected to obtain the structural damage degree in each shock-absorbing structure area.

[0012] Preferably, determining the correction coefficient of the load deviation degree according to the vibration signal and the stress change includes: Obtain the slope value and standard deviation of the vibration signal corresponding to each shock absorbing structure area; The product of the slope value of the vibration signal, the standard deviation of the vibration signal and the mean value of the stress is normalized, and the normalized result value is used as the correction coefficient of the load deviation degree.

[0013] Preferably, the load deviation degree is corrected in combination with the correction coefficient to obtain the structural damage degree in each shock absorbing structure area, including: Performing negative correlation mapping on the correction coefficient to obtain a target correction coefficient; For any collection time, the product of load deviation degree and target correction coefficient is calculated as the degree of foundation structure loss; The normalized value of the mean value of the basic structure loss degree at all acquisition moments is taken as the structural damage degree.

[0014] Preferably, the comprehensive performance of the landing gear is obtained by combining the structural damage degree of each shock absorbing structure area and the health impact degree of the supporting structure area on the landing gear, including: For any landing gear, the mean value of the structural damage degree of all shock-absorbing structure areas is multiplied by the mean value of the health impact degree of all supporting structure areas on the landing gear, and the resulting value is used as the comprehensive damage value; the comprehensive damage value is negatively correlated and mapped to obtain the comprehensive performance of the landing gear.

[0015] In a second aspect, a comprehensive performance test system for landing gear maintenance is provided, the system comprising the following modules: A data acquisition module is used to obtain stress, displacement and vibration signals of the support structure area and the shock absorbing structure area of ​​the landing gear; A static analysis module is used to determine the degree of influence of each support structure area on the health of the landing gear based on the change amplitude, stress magnitude and total stress magnitude of each support structure area of ​​the landing gear under static tests under different loads; The dynamic analysis module is used to perform multiple ground taxiing simulations on the landing gear, and determine the absorption ratio of the low-frequency vibration signal of each shock-absorbing structure area according to the displacement during the ground taxiing simulation; obtain the load size corresponding to the shock-absorbing structure area according to the vibration signal and the absorption ratio, and determine the load deviation degree corresponding to the shock-absorbing structure area of ​​the landing gear; and correct the load deviation degree in combination with the vibration signal and the stress change to obtain the structural damage degree of each shock-absorbing structure area; The performance evaluation module is used to obtain the comprehensive performance of the landing gear by combining the structural damage degree of each shock absorbing structure area and the health impact degree of the supporting structure area on the landing gear.

[0016] In a third aspect, an embodiment of the present invention provides an electronic device, including a memory and a processor, wherein the memory stores executable code, and when the processor executes the executable code, various possible embodiments of the first aspect are implemented.

[0017] In a fourth aspect, an embodiment of the present invention provides a computer program product, which includes: a computer program code, which, when executed on a computer, enables the computer to execute the method in the first aspect or any possible implementation of the first aspect.

[0018] In a fifth aspect, an embodiment of the present invention provides a computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, enables the computer to execute various possible implementations of the first aspect.

[0019] The embodiments of the present invention have at least the following beneficial effects: The present invention relates to the technical field of landing gear performance testing. Firstly, in view of the problems arising during the maintenance of aircraft landing gear, especially the problem that the internal structure of the landing gear is complex and the fatigue degree of a single structural material is difficult to monitor, the present invention mainly adopts two methods: static load testing and dynamic simulation testing. In the static testing stage, the present invention collects and analyzes stress data of each supporting structure area to evaluate the influence of a single supporting structure area on the overall damage of the landing gear. In the dynamic testing stage, the present invention first analyzes the absorption and distribution of vibrations by each shock-absorbing structure area based on the vibration data during the taxiing process. Subsequently, during the take-off and landing process, by monitoring the load change and the vibration change, the data after the vibration is eliminated is used to realize the reverse thrust load size, and the damage degree of the corresponding shock-absorbing structure area is evaluated according to the deviation of the load. Through this dynamic simulation monitoring process, the present invention can monitor each shock-absorbing structure area of ​​the landing gear, and then combined with the monitoring of the supporting structure area during the static test, the purpose of evaluating the overall comprehensive performance of the landing gear is achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions and advantages in the embodiments of the present invention or the prior art, the drawings required for use in the embodiments or the prior art descriptions are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 A method flow chart of a comprehensive performance testing method for landing gear maintenance provided by one embodiment of the present invention; Figure 2 A system block diagram of a comprehensive performance testing system for landing gear maintenance provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0022] In order to further explain the technical means and effects adopted by the present invention to achieve the predetermined purpose of the invention, the following is a detailed description of the comprehensive performance testing method for landing gear maintenance proposed in accordance with the present invention, its specific implementation method, structure, characteristics and effects, in combination with the accompanying drawings and preferred embodiments.

[0023] In the following description, different "one embodiment" or "another embodiment" do not necessarily refer to the same embodiment. In addition, specific features, structures or characteristics in one or more embodiments may be combined in any suitable form.

[0024] Among them, in the description of the embodiments of the present invention, unless otherwise specified, " / " means or, for example, A / B can mean A or B: "and / or" in the text is only a way to describe the association relationship of associated objects, indicating that there can be three relationships, for example, A and / or B can mean: A exists alone, A and B exist at the same time, and B exists alone. In addition, in the description of the embodiments of the present invention, "multiple" refers to two or more than two.

[0025] In the following, the terms "first" and "second" are used for descriptive purposes only and are not to be understood as suggesting or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features.

[0026] Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.

[0027] The embodiments of the present invention are described below in conjunction with the accompanying drawings. Those skilled in the art will appreciate that, with the development of technology and the emergence of new scenarios, the technical solutions provided by the embodiments of the present invention are also applicable to similar technical problems.

[0028] A specific scheme of a comprehensive performance testing method for landing gear maintenance provided by the present invention is described in detail below with reference to the accompanying drawings.

[0029] See also Figure 1 , which shows a flowchart of a comprehensive performance testing method for landing gear maintenance provided by an embodiment of the present invention, the method comprising the following steps: Step S100, obtaining stress, displacement and vibration signals of the support structure area and the shock absorbing structure area of ​​the landing gear.

[0030] Build the environments required for static and dynamic testing of the landing gear respectively, and collect monitoring data during the testing process.

[0031] In order to evaluate the comprehensive performance of the corresponding materials in the current aircraft landing gear maintenance process, the embodiment of the present invention adopts a combined evaluation method of static testing and dynamic testing to evaluate the damage performance of the landing gear materials. The static monitoring is mainly used to evaluate the stress and deformation of the landing gear under the maximum design load, and the dynamic monitoring is mainly to evaluate the performance of the landing gear in actual working conditions by simulating the vibration and impact during the aircraft takeoff, landing and taxiing.

[0032] Regarding static test design, specifically: (1) Static load application: Based on the design specifications and operating conditions of the landing gear, a gradually increasing static load is applied to simulate the maximum load conditions during actual use.

[0033] (2) Monitor the deformation of the landing gear by gradually applying load.

[0034] (3) Static load is applied in stages: from 50%, 75%, 100% to 125% or 150% until the maximum design load. Real-time data of each sensor needs to be recorded at each step.

[0035] The sensors include strain sensors, displacement sensors and vibration sensors. Among them, strain sensors are installed at important load-bearing points such as the undercarriage bracket, hinge point, and connection point between the wheel group and the support frame to collect strain data, and then the mutual conversion between strain data and stress data is realized through Hooke's law to obtain the stress in different structural areas. Displacement sensors are installed on the bracket, main pillar, wheel group and the telescopic part of the hydraulic system to collect displacement data in the shock-absorbing structure area. Among them, vibration sensors are used for dynamic monitoring design. It should be noted that strain sensors can be installed only in the support structure area, and strain sensors, displacement sensors and vibration sensors can be installed in the shock-absorbing structure area; strain sensors, displacement sensors and vibration sensors can also be installed in both the support structure area and the shock-absorbing structure area.

[0036] The collected signals are collected through data acquisition (DAQ) to collect sensor data, and the collected data is processed by signal conditioning equipment and transmitted to the computer for analysis. Among them, DAQ refers to the automatic collection of non-electrical or electrical signals from analog and digital units such as sensors and other devices under test, and sending them to the host computer for analysis and processing.

[0037] Regarding dynamic monitoring design, specifically: (1) Simulating landing impact: The vibration platform is used to simulate the impact force during the aircraft landing process, especially the instantaneous reaction of the landing gear under the action of gravity.

[0038] (2) Simulated ground taxiing: By simulating the continuous vibration during taxiing, the landing gear's ability to adapt to uneven ground during taxiing is examined.

[0039] (3) Simulated takeoff process: Monitor the vibration and shock absorption feedback of the landing gear by gradually releasing the load on the landing gear. The vibration sensor is installed in the shock absorption area. The installation positions of the remaining strain sensors and displacement sensors are the same as those of the static test. The signal acquisition device is the same as that of the static test.

[0040] Step S200, determining the degree of influence of each support structure area on the health of the landing gear according to the change amplitude, stress magnitude and total stress magnitude of each support structure area in the static test of the landing gear under different loads and the total stress magnitude of the landing gear support structure.

[0041] When conducting a comprehensive performance evaluation of an aircraft landing gear, the strength and stress characteristics of its material structure cannot be fully understood by a single disassembly test analysis. Therefore, the embodiments of the present invention currently mainly use static test methods to evaluate the relationship between stress and position changes of the internal structure of the landing gear under different loads, and combine dynamic test methods to further analyze the stress and position changes in the device structure with load under the influence of simulated actual operating environments and external factors, so as to complete a comprehensive evaluation of the landing gear structure.

[0042] The health impact of a single structural area of ​​the landing gear under static test conditions on the health of the landing gear is evaluated based on the static test results.

[0043] During the static test, strain sensors and displacement sensors are installed on the key support structure area of ​​the aircraft landing gear. During the test, the external static load is continuously increased from low to high, and the speed and position of its application remain unchanged. The data are collected and recorded starting from 50% load, and each increase of 25% is regarded as a load change node. It can also be understood as increasing the load size from 50% as a step length of 25%.

[0044] The monitoring data of the strain sensors under each supporting structure area are extracted along with the change of load. Among them, the monitoring data of the strain sensors is stress.

[0045] First, from the stress aspect, the influence of each supporting structure area on the health of the landing gear is determined based on the change amplitude, stress magnitude and total stress magnitude of each supporting structure area in the static test of the landing gear under different loads.

[0046] The strain detection data installed under each current support structure area, if the current support structure area has a greater impact on the health of the aircraft landing gear, the support structure area will show a greater response and fluctuation as the load changes; at the same time, when its load is constant, the greater the stress borne by the support structure area, the greater the impact of the support structure area on the health of the landing gear.

[0047] Obtain a stress curve composed of stress data under the i-th load under the p-th support structure area; calculate the slope of the stress curve composed of stress under each load for each support structure area of ​​the landing gear as a single variation amplitude. It should be noted that each support structure area has a corresponding single variation amplitude under each load. For example, if there are N support structure areas and MI loads, the corresponding landing gear will have a total of N×MI single variation amplitudes.

[0048] Taking the case of the pth support structure area under the i-th load as an example, under static testing, calculate the average slope of each point in the stress curve of the pth support structure area of ​​the current landing gear under the i-th load, and record it as the single change amplitude of the pth support structure area under the i-th load .

[0049] Calculate the average of the single change amplitudes corresponding to all supporting structural areas of the landing gear under the same load as the overall change amplitude ; The difference between the single change amplitude and the overall change amplitude corresponding to each support structure area under each load is taken as the stress deviation degree of each support structure area of ​​the landing gear under each load. For example, taking the case of the pth support structure area under the i-th load as an example, the single change amplitude of the pth support structure area under the i-th load is taken as The overall change The difference between the pth support structure area and the i-th load is used as the stress deviation degree of the p-th support structure area under the i-th load That is, the calculation formula for the degree of stress deviation is: , when the stress deviation is greater, it means that there is a greater change in stress under the current corresponding load stage.

[0050] For the stress data on the current single supporting structure area, when the stress size shared by the single supporting structure area on the various structural areas of the entire landing gear is larger, the stress change response speed of the corresponding structural area is faster during the corresponding load change process, and the stress change that the current structural area needs to bear is larger, and the impact of the problem with the structure on the overall aircraft landing gear is higher.

[0051] Therefore, further, combined with the stress deviation degree, stress magnitude and total stress magnitude of each support structure area of ​​the landing gear under different loads, the degree of influence of each support structure area on the health of the landing gear is determined, specifically: Calculate the average value of stress deviation degrees of different supporting structure areas of the landing gear under the same load as the stress deviation average value; The difference between the stress deviation degree of each supporting structure area of ​​the landing gear under the current load and the average stress deviation corresponding to the same load is calculated as the overall deviation of each supporting structure area under the current load; wherein, the overall deviation of the supporting structure area under the current load reflects the difference in stress fluctuation between the currently analyzed supporting structure area and other supporting structure areas. When the overall deviation is larger, the corresponding current support structure area has a higher sensitivity to stress changes.

[0052] Calculate the ratio of the stress magnitude of each supporting structure area of ​​the landing gear under the current load to the total stress magnitude of all supporting structures of the landing gear under the current load, as the stress ratio of each supporting structure area under the current load; The product of the overall deviation and the stress proportion of each supporting structure area under the current load is used as the individual influence of each supporting structure area on the landing gear under the current load; The sum of the individual influence of each supporting structure area on the landing gear under all loads is calculated as the health influence degree of each supporting structure area on the landing gear.

[0053] In some embodiments, taking the pth support structure area and the i-th load as the current load as an example, the degree of influence of the pth support structure area on the health of the landing gear is The calculation formula is: ; Where norm is the linear normalization function; MI is the number of loads; is the stress deviation degree of the pth supporting structure area under the i-th load; is the average value of the stress deviation of different supporting structure areas of the landing gear under the i-th load, that is, the average value of the stress deviation of the landing gear under the i-th load; is the stress magnitude of the pth support structure area under the i-th load; is the total stress magnitude of all supporting structures of the landing gear under the i-th load; is the stress proportion of the pth supporting structure area under the i-th load; is the overall deflection of the pth support structure area under the i-th load; is the individual influence of the pth supporting structure area on the landing gear under the ith load.

[0054] Step S300, performing multiple ground taxiing simulations on the landing gear, and determining the absorption ratio of the low-frequency vibration signal of each shock-absorbing structure area according to the displacement during the ground taxiing simulation; obtaining the load size corresponding to the shock-absorbing structure area according to the vibration signal and the absorption ratio, and determining the load deviation degree corresponding to the shock-absorbing structure area of ​​the landing gear; correcting the load deviation degree in combination with the vibration signal and the stress change, and obtaining the structural damage degree of each shock-absorbing structure area.

[0055] During the dynamic test, the aircraft landing gear will simulate three stages: landing impact, ground taxiing, and takeoff. In this dynamic test process, in addition to collecting stress data from strain sensors and displacement data from displacement sensors, vibration signals collected by vibration sensors are also included. When the landing gear is affected by vibration, the displacement signal monitored in the shock absorbing structure area and the stress signal monitored in the supporting structure area will be affected by the vibration and change.

[0056] At the same time, there is a corresponding relationship between the degree of fluctuation of each structural area and the vibration frequency; during low-frequency vibration, the shock-absorbing structure can absorb more energy, thereby reducing the impact on the supporting structure area; while during high-frequency vibration, energy absorption becomes relatively difficult, resulting in more energy being transferred to the supporting structure area.

[0057] First, based on the test phase of the aircraft simulating ground taxiing, the vibration signals of different frequency bands, the energy absorption effect of the shock-absorbing structure, and the capacity distribution of each supporting structure area are analyzed.

[0058] During the test phase of simulated ground taxiing, the load on the landing gear of the aircraft is stable, and the fluctuations of its stress signal and displacement signal are the impact of the current vibration signal on it. The vibration signal is adjusted by adjusting the bumpiness of the simulated taxiing road surface during the aircraft's simulated ground taxiing phase. The energy absorption effect of the current shock-absorbing structure area is evaluated by monitoring the displacement and stress fluctuations of each monitoring position under different vibration signals.

[0059] The ground taxiing simulation of the landing gear is performed on v simulated road surfaces respectively, and the stress signal and displacement signal of each structural area in the corresponding simulation process are collected respectively, as well as the vibration signal monitored by the current equipment.

[0060] Firstly, the vibration signal during a single ground sliding simulation is analyzed, and the low-frequency vibration signal and the high-frequency vibration signal of the current vibration signal are extracted using a low-pass filter and a high-pass filter.

[0061] For high-frequency vibration signals, their fluctuation amplitude is small and the frequency is high, and the absorption efficiency of their shock-absorbing devices is poor. Therefore, their high-frequency vibration signals directly act on the current supporting structure. For low-frequency vibration signals, their fluctuation amplitude is large and the frequency is low. The shock-absorbing devices can better absorb the fluctuations of low-frequency vibration signals.

[0062] For any number of ground taxiing simulations, obtain the displacement size collected by each displacement monitoring device during the ground taxiing simulation, perform Fourier transform on the displacement size and convert it into a frequency domain signal, calculate the sum of the energy of the frequency domain signal at different frequencies as the bandwidth energy, and take the sum of the bandwidth energies of all displacement monitoring devices corresponding to the current shock-absorbing structure area during the ground taxiing simulation as the energy absorption of the shock-absorbing structure area. It should be noted that each ground taxiing simulation will have its own corresponding energy absorption in the shock-absorbing structure area. It should be noted that different shock-absorbing structure areas have their own corresponding displacement monitoring devices, and the number of shock-absorbing structure areas corresponding to the specific aircraft landing gear needs to refer to the aircraft landing gear model. It should be noted that the displacement monitoring device in the embodiment of the present invention is a displacement sensor.

[0063] For example, for the monitoring signal corresponding to any shock-absorbing structure area during the v-th ground sliding simulation, the monitoring signal is a displacement signal. The signals of each displacement monitoring device in the current shock-absorbing structure area are extracted to obtain the displacement size collected by each displacement monitoring device, and then the displacement size is converted into a frequency domain signal by Fourier transform. The sum of the energy of the frequency domain signal at different frequencies is calculated as the bandwidth energy, and then the bandwidth energy of each displacement monitoring device is determined; the energy absorbed by the current shock-absorbing structure area is obtained by accumulating and summing the bandwidth energies of the corresponding multiple displacement monitoring devices. The energy absorption of the current shock-absorbing structure area for the v-th ground sliding simulation is recorded as .

[0064] Get the magnitude of the low-frequency vibration signal in the vibration signal of the pth shock-absorbing structure area in the vth ground sliding simulation When there are multiple vibration sensors in a shock-absorbing structure area, the magnitude of the low-frequency vibration signal in the vibration signal is It is the sum of multiple low-frequency vibration signals in a shock-absorbing structure area.

[0065] For any ground sliding simulation, the energy absorption of the shock-absorbing device is used as the numerator, and the low-frequency vibration signal in the vibration signal is used as the denominator. The ratio formed by the numerator and the denominator is used as the fractional simulation absorption ratio of the low-frequency vibration signal in the current shock-absorbing structure area.

[0066] Taking the vth ground sliding simulation as an example, the fractional simulation absorption ratio corresponding to the pth shock-absorbing structure area in the vth ground sliding simulation is for: ;in, The energy absorption corresponding to the p-th shock-absorbing structure area for the v-th ground sliding simulation; is the low-frequency vibration signal corresponding to the p-th shock-absorbing structure area of ​​the v-th ground sliding simulation. It should be noted that each ground sliding simulation has its own corresponding fractional simulation absorption ratio.

[0067] The absorption ratio of each shock-absorbing structure area obtained by multiple ground sliding simulations is averaged to obtain the absorption ratio of each shock-absorbing structure area.

[0068] After determining the absorption ratio of each shock-absorbing structure area, the vibration signal on the shock-absorbing structure area is subjected to low-frequency denoising to obtain monitoring data after low-frequency denoising; based on the monitoring data after low-frequency denoising and the absorption ratio, the corresponding load size is obtained to determine the load deviation degree of the load size corresponding to each shock-absorbing structure area of ​​the landing gear.

[0069] Through its take-off and landing simulation test phase, the damage extent of its individual structural areas during the impact changes is evaluated.

[0070] For the landing gear of an aircraft, during the dynamic simulation, the vibration signal response of the landing gear itself changes during the take-off and landing phases, and its load also changes significantly. When there is internal material damage in a single support structure area or a shock absorbing structure area of ​​the aircraft landing gear, after the stress monitoring data and displacement monitoring data of the corresponding structure are processed according to the vibration response of the monitored vibration signal, stress concentration or displacement concentration will occur in the damaged area, resulting in abnormal deviations in the monitoring data.

[0071] During the dynamic simulation phase of takeoff and landing, the vibration signal on the landing gear of the current aircraft is collected, and the current low-frequency vibration signal is extracted.

[0072] For the monitoring data on a single supporting structure area and its shock absorbing structure area, the response size of the corresponding low-frequency vibration signal on the corresponding structure is subtracted from the monitoring data of a single collected data point to obtain the vibration signal after removing the low-frequency vibration signal.

[0073] For the pth shock-absorbing structure area on the aircraft landing gear, if there is no damage in the current shock-absorbing structure area, the vibration data of the current shock-absorbing structure area after removing the influence of the vibration signal can directly reflect the current load size and the corresponding load change. However, when the internal material of a single shock-absorbing structure area is damaged, the load size and load change reflected by the monitored data fluctuation curve will deviate.

[0074] According to the vibration signal and absorption ratio of the pth shock-absorbing structural area on the aircraft landing gear, the load size corresponding to the structural area is determined, specifically: Obtain the vibration signal after removing the low-frequency vibration signal, calculate the product of the size of the vibration signal after removing the low-frequency vibration signal and the absorption ratio of the low-frequency vibration signal, and use it as the first product; take the difference between the stress size at the current acquisition moment and the first product as the load size of the corresponding shock-absorbing structure area, and record it as the structural area load.

[0075] Taking the pth damping structure area at the tth moment as an example, the corresponding structural area load is The calculation formula is: ;in, is the stress magnitude at the current moment t; is the magnitude of the vibration signal after removing the low-frequency vibration signal corresponding to the p-th shock-absorbing structure area at the t-th moment; is the absorption ratio corresponding to the pth shock-absorbing structure area at the tth moment.

[0076] Furthermore, the load deviation degree of the load size corresponding to each shock absorbing structure area of ​​the landing gear is determined.

[0077] Obtain the average value of the load magnitudes corresponding to all the seismic buffer structure regions at the current acquisition time as the regional load average; For any shock absorbing structure area of ​​the landing gear, the difference between the structural area load at the current collection moment and the average load of the area is used as the numerator, and the average load of the area is used as the denominator to obtain the load deviation degree of the load size corresponding to the shock absorbing structure area of ​​the landing gear at the current collection moment.

[0078] In some embodiments, taking the pth shock absorbing structure area as an example, the load deviation degree at the tth moment is The calculation formula is: ;in, is the structural area load of the pth seismic buffer structure area at the tth moment; is the regional load mean at the tth moment.

[0079] Furthermore, the load deviation degree is corrected in combination with the vibration signal and stress change to obtain the structural damage degree in each shock absorbing structure area. More specifically: according to the vibration signal and stress change, a correction coefficient of the load deviation degree is determined; in combination with the correction coefficient, the load deviation degree is corrected to obtain the structural damage degree in each shock absorbing structure area.

[0080] To analyze the load deviation degree of the shock absorbing structure of the landing gear at a single moment, it is necessary to analyze according to the amplitude of the vibration signal at the current acquisition moment, the slope average of the vibration signal values ​​at each acquisition point, and the stress change of the corresponding landing gear structure. When the amplitude of the vibration signal is larger, the slope fluctuation of the vibration signal is larger, and the stress change degree of the landing gear is higher, the correction parameter of the deviation degree of the load monitored at that location is used.

[0081] Specifically, the correction coefficient of the load deviation is determined according to the vibration signal and stress changes. Specifically: the slope value and standard deviation of the vibration signal corresponding to each shock absorbing structure area are obtained; the product of the slope value of the vibration signal, the standard deviation of the vibration signal and the mean value of the stress is normalized, and the normalized result value is used as the correction coefficient of the load deviation.

[0082] In some embodiments, taking the pth shock absorbing structure area at the tth moment as an example, the correction coefficient of the load deviation degree of the pth shock absorbing structure area at the tth moment is The calculation formula is: ; Among them, norm is the normalization function; is the slope of the vibration signal of the p-th shock absorbing structure area before the t-th moment; is the standard deviation of the vibration signal of the p-th shock absorbing structure area before the t-th moment; is the mean value of the stress in the pth seismic buffer structure area before the tth moment.

[0083] The standard deviation of the vibration signal of the shock absorbing structure area reflects the vibration amplitude of the shock absorbing structure area at the current position; the mean value of the stress magnitude of the shock absorbing structure area reflects the stress change of the shock absorbing structure.

[0084] Furthermore, the load deviation degree of the shock absorbing structure area of ​​the landing gear is corrected in combination with the correction coefficient of the load deviation degree, and the structural damage degree of each shock absorbing structure area is obtained, specifically: The correction coefficient of the load deviation degree is negatively mapped to obtain the target correction coefficient; since the correction coefficient is a normalized value, in the embodiment of the present invention, the correction coefficient can be subtracted from the constant 1 to achieve negative correlation mapping of the correction coefficient. The average value of the load deviation degree at different acquisition times is calculated as the degree of infrastructure loss. The normalized value of the average value of the infrastructure loss degree at all acquisition times is used as the degree of structural damage.

[0085] In some embodiments, taking the pth shock absorbing structure area as an example, the structural damage degree of the pth shock absorbing structure area is The calculation formula is: ; Wherein, MT is the number of monitoring time points during the simulated takeoff and landing process; is the target correction coefficient of the load deviation degree of the p-th seismic buffer structure area at the t-th moment; is the load deviation degree of the load magnitude at the tth moment in the pth seismic buffer structure area; is the correction coefficient of the load deviation degree of the pth seismic buffer structure area at the tth moment; is the degree of foundation structure loss in the p-th seismic buffer structure area at the t-th moment.

[0086] When there is damage in the shock-absorbing structure area, there will be a large deviation in the load size at the corresponding moment in the simulation monitoring results. The damage degree of the corresponding single shock-absorbing structure area can be obtained by analyzing the load deviation in the entire time period.

[0087] Step S400, combining the structural damage degree of each shock absorbing structure area and the health impact degree of the supporting structure area on the landing gear, to obtain the comprehensive performance of the landing gear.

[0088] Finally, for a single landing gear of the aircraft, static load tests and dynamic simulation tests are performed to obtain the degree of structural damage in the shock-absorbing structure area of ​​a single landing gear and the degree of impact of the supporting structure area on the health of the landing gear. The overall comprehensive performance of the aircraft landing gear is determined by combining the characteristics of the shock-absorbing structure area and the supporting structure area corresponding to each landing gear.

[0089] For any landing gear, the mean value of the structural damage degree of all shock-absorbing structure areas is multiplied by the mean value of the health impact degree of all supporting structure areas on the landing gear, and the resulting value is taken as the comprehensive damage value.

[0090] The comprehensive damage value is negatively correlated to obtain the comprehensive performance of the landing gear.

[0091] In some embodiments, the overall performance of the landing gear The calculation formula is: ; in, is the average value of the structural damage degree of all shock absorbing structural areas of the landing gear; It is the average of the health impact of all supporting structure areas of the landing gear on the landing gear; is the comprehensive damage value.

[0092] Among them, the comprehensive damage value reflects the overall damage of the aircraft landing gear. The larger the value of the comprehensive damage value, the more serious the structural damage of the current landing gear.

[0093] According to the obtained comprehensive performance evaluation structure and the degree of damage on each structure of the aircraft landing gear, the area with abnormal damage can be inspected and maintained in a targeted manner. When the comprehensive performance of the landing gear is greater than the preset normal threshold, that is, QL>0.95 in the embodiment of the present invention, it is determined that the current aircraft landing gear has passed the inspection and can be installed and used; otherwise, it is determined that the current aircraft landing gear has failed the inspection. In the embodiment of the present invention, the value of the preset normal threshold is 0.95, and in other embodiments, it can be adjusted by the implementer according to the actual situation.

[0094] See also Figure 2 , which shows a system block diagram of a comprehensive performance test system for landing gear maintenance provided by an embodiment of the present invention, the system includes the following modules: A data acquisition module is used to obtain stress, displacement and vibration signals of the support structure area and the shock absorbing structure area of ​​the landing gear; A static analysis module is used to determine the degree of influence of each support structure area on the health of the landing gear based on the change amplitude, stress magnitude and total stress magnitude of each support structure area of ​​the landing gear under static tests under different loads; The dynamic analysis module is used to perform multiple ground taxiing simulations on the landing gear, and determine the absorption ratio of the low-frequency vibration signal of each shock-absorbing structure area according to the displacement during the ground taxiing simulation; obtain the load size corresponding to the shock-absorbing structure area according to the vibration signal and the absorption ratio, and determine the load deviation degree corresponding to the shock-absorbing structure area of ​​the landing gear; and correct the load deviation degree in combination with the vibration signal and the stress change to obtain the structural damage degree of each shock-absorbing structure area; The performance evaluation module is used to obtain the comprehensive performance of the landing gear by combining the structural damage degree of each shock absorbing structure area and the health impact degree of the supporting structure area on the landing gear.

[0095] Optionally, the transmission medium may be a wired link, such as but not limited to coaxial cable, optical fiber, and digital subscriber line, or a wireless link, such as but not limited to Wireless Fidelity (WIFI), Bluetooth, and mobile device network.

[0096] It should be noted that the device provided in the above embodiment is only illustrated by the division of the above functional modules. In actual applications, the above functions can be assigned to different functional modules as needed, that is, the internal structure of the computer device can be divided into different functional modules to complete all or part of the functions described above.

[0097] A schematic diagram of the structure of a computer device provided in an embodiment of the present invention. Exemplarily, the computer device includes: a memory, a processor, and a computer program stored in the memory and running on the processor, wherein when the processor executes the computer program, the computer device can execute any of the above-mentioned comprehensive performance test methods for landing gear maintenance.

[0098] In addition, an embodiment of the present invention also protects a device, which may include a memory and a processor, wherein the memory stores executable program code, and the processor is used to call and execute the executable program code to perform a comprehensive performance testing method for landing gear maintenance provided by an embodiment of the present invention.

[0099] The embodiment of the present invention can divide the functional modules of the device according to the above method example. For example, each functional module can be corresponded, or two or more functions can be integrated into one processing module. The above integrated module can be implemented in the form of hardware. It should be noted that the division of modules in this embodiment is schematic and is only a logical function division. There may be other division methods in actual implementation.

[0100] In the case of dividing each module according to each function, the device may also include a signal uploading module, a determining module, an adjusting module, etc. It should be noted that all relevant contents of each step involved in the above method embodiment can be referred to the functional description of the corresponding functional module, which will not be repeated here.

[0101] It should be understood that the device provided in the embodiment of the present invention is used to execute the above-mentioned comprehensive performance testing method for landing gear maintenance, and thus can achieve the same effect as the above-mentioned implementation method.

[0102] In the case of an integrated unit, the device may include a processing module and a storage module. When the device is applied to a device, the processing module may be used to control and manage the actions of the device. The storage module may be used to support the device to execute mutual program codes, etc. The processing module may be a processor or a controller, which may implement or execute various exemplary logic blocks, modules and circuits described in conjunction with the disclosure of the present invention. The processor may also be a combination that implements a computing function, such as a combination of one or more microprocessors, a combination of digital signal processing (DSP) and a microprocessor, etc. The storage module may be a memory.

[0103] In addition, the device provided in the embodiment of the present invention may specifically be a chip, a component or a module, and the chip may include a connected processor and a memory; wherein the memory is used to store instructions, and when the processor calls and executes the instructions, the chip can execute a comprehensive performance testing method for landing gear maintenance provided in the above embodiment.

[0104] An embodiment of the present invention also provides a computer-readable storage medium, in which a computer program code is stored. When the computer program code is executed on a computer, the computer executes the above-mentioned related method steps to implement a comprehensive performance testing method for landing gear maintenance provided in the above embodiment.

[0105] An embodiment of the present invention further provides a computer program product. When the computer program product is run on a computer, the computer is enabled to execute the above-mentioned related steps to implement a comprehensive performance testing method for landing gear maintenance provided in the above embodiment.

[0106] Among them, the device, computer-readable storage medium, computer program product or chip provided in the embodiments of the present invention are all used to execute the corresponding methods provided above. Therefore, the beneficial effects that can be achieved can refer to the beneficial effects in the corresponding methods provided above, and will not be repeated here. Through the description of the above implementation methods, technicians in the relevant field can understand that for the convenience and simplicity of description, only the division of the above-mentioned functional modules is used as an example. In actual applications, the above-mentioned functions can be assigned to different functional modules as needed, that is, the internal structure of the device is divided into different functional modules to complete all or part of the functions described above. In the embodiments provided by the present invention, it should be understood that the disclosed devices and methods can be implemented in other ways.

[0107] The device embodiments described above are merely illustrative. For example, the division of modules or units is only a logical function division. There may be other divisions in actual implementation. For example, multiple units or components may be combined or integrated into another device, or some features may be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed may be through some interfaces, indirect coupling or communication connection of devices or units, which may be electrical, mechanical or other forms.

[0108] It should also be noted that, in this article, the terms "include", "comprises" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or terminal device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or terminal device. In the absence of further restrictions, the elements defined by the sentence "comprises a ..." do not exclude the existence of other identical elements in the process, method, article or terminal device including the elements.

[0109] It should be noted that the sequence of the above embodiments of the present invention is for description only and does not represent the advantages and disadvantages of the embodiments. The processes depicted in the accompanying drawings do not necessarily require the specific order or continuous order shown to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0110] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referenced to each other, and each embodiment focuses on the differences from other embodiments.

[0111] The above contents are only specific implementation modes of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be covered within the protection scope of the present invention.

Claims

1. A comprehensive performance test method for landing gear maintenance, characterized in that: The method comprises the following steps: Obtain stress, displacement and vibration signals of the supporting structure area and the shock absorbing structure area of ​​the landing gear; Determine the degree of influence of each support structure area on the health of the landing gear based on the change amplitude, stress magnitude and total stress magnitude of each support structure area in the static test of the landing gear under different loads; Perform multiple ground taxiing simulations on the landing gear respectively, and determine the absorption ratio of the low-frequency vibration signal of each shock-absorbing structure area according to the displacement during the ground taxiing simulation; obtain the load size corresponding to the shock-absorbing structure area according to the vibration signal and the absorption ratio, and determine the load deviation degree corresponding to the shock-absorbing structure area of ​​the landing gear; correct the load deviation degree in combination with the vibration signal and the stress change, and obtain the structural damage degree of each shock-absorbing structure area; The comprehensive performance of the landing gear is obtained by combining the structural damage degree of each shock absorbing structure area and the health impact degree of the supporting structure area on the landing gear.

2. A comprehensive performance testing method for landing gear maintenance according to claim 1, characterized in that: Determining the degree of influence of each support structure area on the health of the landing gear according to the change amplitude, stress magnitude and total stress magnitude of the landing gear support structure of each support structure area in the static test of the landing gear under different loads includes: Under static testing, analyze the changes in stress data of the landing gear support structure area under different loads to determine the degree of stress deviation; The degree of influence of each supporting structure area on the landing gear health is determined by combining the stress deviation degree, stress magnitude and total stress magnitude of the landing gear supporting structure of each supporting structure area under different loads.

3. A comprehensive performance testing method for landing gear maintenance according to claim 2, characterized in that: In the static test, the stress data changes of the supporting structure area of ​​the landing gear under different loads are analyzed to determine the degree of stress deviation, including: Calculate the slope of the stress curve consisting of the stresses at each load for each support structure area of ​​the landing gear as a single amplitude of change; Calculate the average of the single change amplitudes corresponding to all supporting structure areas of the landing gear under the same load as the overall change amplitude; The difference between the single variation amplitude and the overall variation amplitude is taken as the stress deviation degree of the supporting structure area of ​​the landing gear under each load.

4. A comprehensive performance testing method for landing gear maintenance according to claim 2, characterized in that: Determining the degree of influence of each support structure area on the health of the landing gear according to the change amplitude, stress magnitude and total stress magnitude of each support structure area of ​​the landing gear under different loads of the static test stress of the landing gear includes: Calculate the average value of stress deviation degrees of different supporting structure areas of the landing gear under the same load as the stress deviation average value; Calculate the difference between the stress deviation degree of each supporting structure area of ​​the landing gear under the current load and the stress deviation average value corresponding to the same load as the overall deviation of each supporting structure area under the current load; Calculate the ratio of the stress magnitude of each supporting structure area of ​​the landing gear under the current load to the total stress magnitude of all supporting structures of the landing gear under the current load, as the stress proportion of each supporting structure area under the current load; The product of the overall deviation and the stress proportion of each supporting structure area under the current load is used as the individual influence of each supporting structure area on the landing gear under the current load; The sum of the individual influence of each supporting structure area on the landing gear under all loads is calculated as the health influence degree of each supporting structure area on the landing gear.

5. A comprehensive performance testing method for landing gear maintenance according to claim 1, characterized in that: The method of performing multiple ground taxiing simulations on the landing gear and determining the absorption ratio of the low-frequency vibration signal of each shock-absorbing structure area according to the displacement during the ground taxiing simulation includes: For any number of ground sliding simulations, the displacement size collected by each displacement monitoring device during the ground sliding simulation is obtained, the displacement size is converted into a frequency domain signal by Fourier transform, the sum of the energy of the frequency domain signal at different frequencies is calculated as the bandwidth energy, and the sum of the bandwidth energies of all displacement monitoring devices corresponding to the current shock absorbing structure area during the ground sliding simulation is used as the energy absorption of the shock absorbing structure area; The energy absorption of the shock absorbing structure area is used as the numerator, the low-frequency vibration signal in the vibration signal is used as the denominator, and the ratio formed by the numerator and the denominator is used as the fractional simulation absorption ratio of the low-frequency vibration signal in the current shock absorbing structure area; The absorption ratio of each shock-absorbing structure area obtained by multiple ground sliding simulations is averaged to obtain the absorption ratio of each shock-absorbing structure area.

6. A comprehensive performance testing method for landing gear maintenance according to claim 1, characterized in that: The step of obtaining the load size corresponding to the shock absorbing structure area according to the vibration signal and the absorption ratio, and determining the load deviation degree corresponding to the shock absorbing structure area of ​​the landing gear includes: Obtain the vibration signal after removing the low-frequency vibration signal, calculate the product value of the magnitude of the vibration signal after removing the low-frequency vibration signal and the absorption ratio of the low-frequency vibration signal, as the first product; take the difference between the stress magnitude at the current acquisition moment and the first product as the load magnitude of the corresponding shock-absorbing structure area, recorded as the structural area load; Obtain the average value of the load magnitudes corresponding to all the seismic buffer structure regions at the current acquisition time as the regional load average; For any shock absorbing structure area of ​​the landing gear, the difference between the structural area load at the current collection moment and the average load of the area is used as the numerator, and the average load of the area is used as the denominator to obtain the load deviation degree of the load size corresponding to the shock absorbing structure area of ​​the landing gear at the current collection moment.

7. A comprehensive performance testing method for landing gear maintenance according to claim 1, characterized in that: The load deviation degree is corrected in combination with the vibration signal and the stress change to obtain the structural damage degree of each shock absorbing structure area, including: According to the vibration signal and the stress change, a correction coefficient of the load deviation degree is determined; in combination with the correction coefficient, the load deviation degree is corrected to obtain the structural damage degree in each shock-absorbing structure area.

8. A comprehensive performance testing method for landing gear maintenance according to claim 7, characterized in that: Determining the correction coefficient of the load deviation degree according to the vibration signal and the stress change includes: Obtain the slope value and standard deviation of the vibration signal corresponding to each shock absorbing structure area; The product of the slope value of the vibration signal, the standard deviation of the vibration signal and the mean value of the stress is normalized, and the normalized result value is used as the correction coefficient of the load deviation degree.

9. A comprehensive performance testing method for landing gear maintenance according to claim 7, characterized in that: The load deviation degree is corrected in combination with the correction coefficient to obtain the structural damage degree of each shock absorbing structure area, including: Performing negative correlation mapping on the correction coefficient to obtain a target correction coefficient; For any collection time, the product of load deviation degree and target correction coefficient is calculated as the degree of foundation structure loss; The normalized value of the mean value of the basic structure loss degree at all acquisition moments is taken as the structural damage degree.

10. A comprehensive performance testing method for landing gear maintenance according to claim 1, characterized in that: The comprehensive performance of the landing gear is obtained by combining the structural damage degree of each shock absorbing structure area and the health impact degree of the supporting structure area on the landing gear, including: For any landing gear, the mean value of the structural damage degree of all shock-absorbing structure areas is multiplied by the mean value of the health impact degree of all supporting structure areas on the landing gear, and the resulting value is used as the comprehensive damage value; the comprehensive damage value is negatively correlated and mapped to obtain the comprehensive performance of the landing gear.

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