CN115824545B - Method and system for determining fatigue damage acceleration endurance test conditions of airborne equipment - Google Patents
Method and system for determining fatigue damage acceleration endurance test conditions of airborne equipment Download PDFInfo
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Abstract
The invention relates to equipment fatigue test in intelligent manufacturing, and discloses a method and a system for determining an accelerated endurance test condition of fatigue damage of airborne equipment so as to quickly and reliably determine the accelerated endurance test condition. The method comprises the following steps: judging whether load data of any task section is larger than or equal to a grading threshold according to the load amplitude change of the preprocessed actual measurement signals, if so, sequencing, reorganizing and grading the corresponding task sections according to the load amplitude change trend, intercepting waveforms of representative time sections for the load data of each task section, calculating corresponding fatigue damage values, and obtaining the fatigue damage values of the machine-carried equipment in a full-task state according to intercepting proportions of the task sections at all levels; and finally, according to the acceleration time of the preset endurance test condition, the input load condition of the same fatigue damage spectrum can be generated by back-pushing through iterative calculation by taking the equivalent of the fatigue damage spectrum as a principle.
Description
Technical Field
The invention relates to equipment fatigue test in intelligent manufacturing, in particular to a method and a system for determining fatigue damage acceleration endurance test conditions of airborne equipment.
Background
The vibration endurance test is a test that simulates the longest vibration time that an equipment may experience over the life cycle to assess the fatigue resistance of the equipment over the life cycle.
In the past, most of conditions and methods of vibration endurance test projects in the environment test of the airborne equipment in China are formulated by referring to GJB 150.16A-2009 or related industry standards, and the method is to directly give an acceleration factor of 1.6 times to calculate the vibration endurance test value and duration through a fatigue endurance equivalent formula. Although the standard recommended method is simple and quick to calculate, the standard recommended vibration endurance test conditions are different from the actual measurement environment, the test of the long-life multitasking equipment is too conservative, and the situation that the standard recommended conditions cannot cover the actual vibration load exists in the very individual equipment.
Along with the improvement of the degree of visibility of the universal quality characteristics of equipment by various equipment development units, the actual measurement of the vibration environment conditions becomes the work content commonly developed in the equipment development process, and along with the accumulation of vibration actual measurement data of various equipment, the difficult problem of no actual measurement data or poor coverage of the actual measurement data is gradually solved. If the real load born by the airborne equipment can be completely repeated on the vibrating table, the method can accurately check the fatigue resistance of the equipment in the service life period, but the endurance test period directly based on the un-accelerated time domain measured data is too long, and the method for formulating accurate and efficient vibration endurance test conditions for the vibration measured data is still immature, so that the method for determining the fatigue damage acceleration endurance test conditions of the airborne equipment based on the measured signals is to be established.
Disclosure of Invention
The invention mainly aims to disclose a method and a system for determining fatigue damage acceleration endurance test conditions of airborne equipment so as to quickly and reliably determine the acceleration endurance test conditions.
To achieve the above object, the method of the present invention comprises:
step one: and preprocessing the collected actual measurement signals of the full task segment.
Step two: judging the load of any task section according to the load amplitude change of the preprocessed actual measurement signalWhether the data is larger than or equal to the grading threshold value, if so, sorting, reorganizing and grading the corresponding task segments according to the change trend of the load amplitude, and then loading the data T to each grade of task segments i Intercepting a representative period of time T i section Wherein the waveform of (c), wherein,
，/>
a task segment that is a hierarchical number of full task segments and is less than the hierarchical threshold is considered to be the same level.
Step three: fatigue damage value D generated by corresponding to waveform intercepted at each stage of computer-carried equipment Ti section The method comprises the steps of carrying out a first treatment on the surface of the The method specifically comprises the following steps: calculating stress-time functions for each waveform, and counting stress circulation times under each amplitude by adopting a rain flow counting method; and then, according to the Miner criterion, calculating fatigue damage values generated by the waveforms intercepted by corresponding stages by combining the characteristic parameters of the standard S-N curve of the airborne equipment.
Step four: fatigue damage value D generated according to waveform intercepted at each stage Ti section Obtaining a fatigue damage value D of the on-board equipment in a full-task state:
step five: the method comprises the steps of presetting endurance test condition acceleration time, taking load stress less than or equal to material yield strength of airborne equipment and not changing failure mechanism of the equipment as constraint, taking fatigue damage spectrum equivalence as principle, generating input load conditions of the same fatigue damage spectrum through iterative calculation and carrying out backward pushing, and obtaining endurance vibration test conditions under the condition that the damage mechanism of a system structure is not changed.
Preferably, the preprocessing in the first step includes: removing abnormal data, supplementing lost data, and carrying out induction processing on the measured data through tolerance upper limit coefficient estimation and tolerance upper limit estimation.
Alternatively, the classification threshold is such that the absolute value ratio of the maximum amplitude to the minimum amplitude is equal to 2.
Optionally, in the recombination process of the second step, the same load amplitude of the original discrete time point is continuously arranged, and the load amplitude is adjacently arranged in the order from big to small or from small to big according to the sequence of the change trend of the load amplitude.
Preferably, in the third step, the method specifically includes: calculating stress-time functions for each waveform, and counting stress circulation times under each amplitude by adopting a rain flow counting method; and then, according to the Miner criterion, calculating fatigue damage values generated by the waveforms intercepted by corresponding stages by combining the characteristic parameters of the standard S-N curve of the airborne equipment. Further, calculating the stress-time function may specifically include:
waveform intercepted by each stage of task section is applied to a series of linear single-degree-of-freedom mass-spring systems, and a time function of relative displacement between each single-degree-of-freedom system and an excitation platform applying load is calculated
。
Proportional constant by stress-relative displacement
Calculating the stress to which the equipment system is subjected +.>
Time function of (2)
。
Preferably, in the iterative calculation process of the fifth step, the method specifically includes:
calculating the fatigue damage value of the original load before recombination after pretreatment by the same method for calculating the fatigue damage value of the airborne equipment in the all-task state under random interception acceleration time, and expanding the intercepted corresponding load amplitude by acceleration time by 2 if the fatigue damage value after acceleration is smaller than the fatigue damage value before acceleration u Doubling the fatigue damage value until the fatigue damage value after acceleration is larger than the fatigue damage value before acceleration;and then continuously reducing the load amplitude through the load attenuation coefficient, when the fatigue damage value after acceleration is smaller than the fatigue damage value before acceleration, continuously increasing the load amplitude through the load amplification coefficient, and performing iterative calculation according to the load amplitude, so that the fatigue damage value before acceleration is finally equal to the fatigue damage value after acceleration, and reversely pushing out the time domain load after acceleration, wherein u is a positive integer.
Optionally, the representative time periods intercepted by each hierarchy are equal in duration.
In order to achieve the above purpose, the invention also discloses a system for determining the fatigue damage acceleration endurance test condition of the airborne equipment, which comprises a memory, a processor and a computer program stored on the memory and capable of running on the processor, wherein the processor realizes the method when executing the computer program.
The invention has the following beneficial effects:
1. the accelerated endurance test conditions are determined based on the actual measurement signals, so that the actual use environment of the equipment can be better simulated, the phenomena of over test and under test are avoided, and the accuracy of the load of the airborne equipment is ensured.
2. Under the condition of not changing the fatigue damage mechanism of the equipment, the endurance test is reasonably accelerated based on the fatigue damage equivalent principle, and a more scientific test assessment method is provided for the life evaluation of the equipment in the endurance vibration environment; the device is not only suitable for single-task equipment, but also suitable for equipment subjected to different vibration loads in long-service-life multi-task states.
3. In addition, in the calculation process of fatigue damage, the fatigue damage value of the airborne equipment under the whole task section can be rapidly and reliably determined through grading and proportional amplification after the section is cut off.
The invention will be described in further detail with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
fig. 1 is a schematic diagram of actual measurement data of a model item according to an embodiment of the present invention.
FIG. 2 is a schematic diagram of segment reorganization of the data of FIG. 1.
Fig. 3 is a schematic diagram of the distribution of the single degree of freedom systems of the excitation platform according to the present embodiment.
FIG. 4 is a schematic diagram of time domain load data before acceleration taken according to an embodiment of the present invention.
FIG. 5 is a comparative schematic of fatigue damage spectra before and after acceleration in accordance with an embodiment of the present invention.
FIG. 6 is a schematic diagram of time domain load data after acceleration according to an embodiment of the present invention.
FIG. 7 is a time-consuming schematic of an embodiment of the invention for calculating fatigue loss without segments.
FIG. 8 is a time-consuming schematic of the calculation of fatigue loss after the data segment of FIG. 7 in accordance with an embodiment of the present invention.
Detailed Description
Embodiments of the invention are described in detail below with reference to the attached drawings, but the invention can be implemented in a number of different ways, which are defined and covered by the claims.
Example 1
The embodiment discloses a method for determining fatigue damage acceleration endurance test conditions of airborne equipment based on actual measurement signals. Firstly, carrying out data preprocessing on the actual measurement signals, including data inspection and data induction, and confirming the validity of the data; carrying out grading treatment on load data of different task segments according to the change of the load amplitude; according to Miner criterion (fatigue damage linear accumulation hypothesis), combining characteristic parameters of equipment standard S-N curve, calculating fatigue damage value for different section load signals, and obtaining fatigue damage spectrum. Finally, setting the time of an accelerated endurance vibration test by taking the material yield strength of which the load stress is not higher than the equipment and the failure mechanism of which is not changed as constraint and the equivalent of a fatigue damage spectrum as a principle, and obtaining the endurance vibration test condition under the condition that the damage mechanism of a system structure is not changed by performing iterative calculation and reversely pushing to generate the input load condition of the same fatigue damage spectrum.
The technical scheme of the invention mainly comprises the following steps: step one: the validity of the collected full-task segment actual measurement signal is confirmed, and whether the data has abnormality or not is checked, wherein the abnormality comprises, but is not limited to, signal clipping, false trend, electromagnetic interference, intermittent noise, singular point, data loss and the like. Editing time domain data according to the screening, correction or eliminating rules of the data, and carrying out induction processing on the multi-time measurement data of the same measuring point through tolerance upper limit coefficient estimation and tolerance upper limit estimation.
In this step, the collected full-task segment actual measurement signal is preprocessed. For the source of the measured data, a vibration data acquisition system suitable for the multi-equipment multi-task state can be adopted, and the measured data is developed for the environmental vibration data of the equipment. The actual measurement process covers the full-mission flight process in the service process of the airborne equipment, and an actual measurement vibration signal is collected, wherein the vibration signal is generally a time-vibration acceleration two-dimensional array, and actual measurement data of a certain type of project is shown in fig. 1; the vibration measured data of the same type of airborne equipment can be collected.
Step two: judging whether the load data of any task segment is greater than or equal to a classification threshold according to the load amplitude change of the preprocessed actual measurement signal, if so, sequencing, reorganizing and classifying the corresponding task segments according to the load amplitude change trend, and then carrying out load data T on each stage of task segments i Intercepting a representative period of time T i section Is a waveform of (a); wherein,
，/>
a task segment that is a hierarchical number of full task segments and is less than the hierarchical threshold is considered to be the same level.
In this step, when fatigue damage spectrum calculation is performed by using the time domain signal, since the endurance test random load is generally long in duration, if time domain data simplification processing is not performed, a large amount of calculation is caused by directly calculating the full time domain data, and the solving efficiency is affected. In order to accelerate the fatigue damage spectrum calculation time, the whole time domain is subjected to grading simplification processing according to different task states and load amplitude changes. Preferably, the classification threshold is such that the absolute value ratio of the maximum amplitude to the minimum amplitude is equal to 2. If the classification adopts two stages of a low-amplitude time domain segment and a high-amplitude time domain segment, a classification schematic diagram of each task segment based on the data shown in fig. 1 is shown in fig. 2; the specific process comprises the following steps:
firstly, segmenting full-time domain data according to different task states, wherein the different task states are determined according to flight profiles (climbing, cruising, sliding down and the like) of a carrier; and judging the time domain amplitude change condition of each task state, when the absolute value ratio of the maximum amplitude value and the minimum amplitude value of the time domain is smaller than 2, considering the time domain data of the task state as stable random data, not segmenting the task state data, when the absolute value ratio of the maximum amplitude value and the minimum amplitude value of the time domain is larger than 2, indicating that the time domain data of the task state has large amplitude change and cannot be considered as stable random data, carrying out secondary segmentation and data recombination on the task state data, and dividing and recombining the task segment into a high-amplitude time domain segment and a low-amplitude time domain segment according to all time histories comprising the maximum load peak value of the task segment with the absolute value of load exceeding 50 percent. Finally, the full-time domain measured data is classified into stable random data containing different task states. Thereby, the data of the all time domain segment is divided into stable random data which are passed through each state through processing; further, in order to improve the overall calculation efficiency, the load data T is loaded for each segment i Intercepting a representative period of time T i section The fatigue damage spectrum is calculated according to the waveform of the model (C). For example, the truncated representative time period may take 5s; and usually, a time period with the peak absolute value in the middle and more different amplitude values after recombination is selected as a intercepting section; therefore, the fatigue damage of each stage of task section can be guaranteed to have enough safety margin according to the follow-up evaluation of the intercepting proportion. Wherein, referring to fig. 2, the process of reorganization is essentially: and carrying out continuous arrangement processing on the same load amplitude values of the original discrete time points, and carrying out adjacency in the order from large to small or from small to large according to the sequence of the change trend of the load amplitude values.
Step three: t for interception i section Waveform, calculating stress-time function, and calculating each amplitude by rain flow counting methodThe number of stress cycles; according to Miner criterion, calculating fatigue damage value D of each task section of the equipment by combining characteristic parameters of equipment standard S-N curve Ti section 。
In this step, it can be further subdivided into:
0048. step S31, T of intercepting each segment i section The waveform is applied to a series of linear single degree of freedom mass-spring systems shown in FIG. 3, the natural frequencies of the individual single degrees of freedom of the system
Different, the damping ratio is the same and is +.>
Calculating the time function of the relative displacement between the excitation platforms corresponding to the single degree of freedom systems>
. In the calculation process, the following conditions are satisfied:
in the formula ：
to excite the absolute displacement of the platform.
Step S32, proportional constant by stress-relative displacement
Calculating the stress to which the equipment system is subjected +.>
Is>
。
Step S33, counting the peak-valley value of the stress-time function by using a rain flow counting method to obtain each stress amplitude value
Corresponding number of cycles->
。
Step S34, calculating the fatigue damage value of each segmented airborne equipment according to Miner criterion and combining the characteristic parameters of the equipment standard S-N curve
：
in the formula ：
is the intercept of the standard S-N curve, < >>
Is the slope reciprocal of the standard S-N curve; />
The number of stress amplitude values.
Step four: calculated fatigue damage value D from each segment Ti section Obtaining a fatigue damage value D of the on-board equipment in a full-task state:
step five: the method comprises the steps of presetting endurance test condition acceleration time, taking load stress not higher than material yield strength of airborne equipment and not changing failure mechanism of the equipment as constraint, taking fatigue damage spectrum equivalence as principle, generating input load conditions of the same fatigue damage spectrum through iterative calculation and performing backward pushing, and obtaining endurance vibration test conditions under the condition that the damage mechanism of a system structure is not changed.
Preferably, in this step, the fatigue damage value of the on-board equipment in the all-task state is calculated in the same manner as described aboveThe fatigue damage value of the original load under random intercepting acceleration time is enlarged by 2 according to the intercepting corresponding load amplitude of the acceleration time if the fatigue damage value after acceleration is smaller than the fatigue damage value before acceleration u Doubling the fatigue damage value until the fatigue damage value after acceleration is larger than the fatigue damage value before acceleration; and then continuously reducing the load amplitude through the load attenuation coefficient, when the fatigue damage value after acceleration is smaller than the fatigue damage value before acceleration, continuously increasing the load amplitude through the load amplification coefficient, sequentially performing iterative computation, finally enabling the fatigue damage value before acceleration to be equal to the fatigue damage value after acceleration, and reversely pushing out the time domain load after acceleration, wherein u is a positive integer.
Wherein, in the iterative calculation process, the material yield strength or sigma S or the material S-N curve life 10 is higher than the structural danger 3 ~10 4 The corresponding stress segments are reserved in load, and damage equivalent acceleration is carried out on the segments with low stress caused by the structure. Finally, under the condition of not changing the damage mechanism of the structure, an acceleration time domain signal is obtained. And performing Fast Fourier Transform (FFT) on the accelerated time domain signals to convert the time domain signals into Power Spectral Density (PSD), and performing sectional envelope processing on the PSD to finally obtain the fatigue damage acceleration endurance test conditions of the airborne equipment based on the actual measurement signals.
The above-described accelerated iteration process is described below using a section of random time domain load signal as an example. The original task segment load duration is 180s, and the 5s time domain representative data is intercepted as shown in fig. 4. Presetting equipment characteristic parameters: the quality factor is set to 10, the slope reciprocal of the standard S-N curve is set to 8, the intercept of the standard S-N curve is 1, the proportionality constant of stress/displacement is 1, the upper limit frequency of the fatigue damage spectrum is set to 2000Hz, the spectral line interval is 1Hz, and the pre-acceleration fatigue damage spectrum curve of the fatigue damage spectrum as shown in figure 5 is calculated. When 36s is taken as an input parameter of the duration of the endurance test, fatigue damage spectrum equivalence is taken as a principle, the fatigue spectra before and after acceleration are close as shown in fig. 5, the load input condition when the fatigue damage spectrum approaches is inversely deduced through 20 iterative computations, the load acceleration coefficient factor iterative computation value is 1.7, and the time domain load after acceleration is obtained as shown in fig. 6. The time domain load signal before acceleration with the duration of 180s can be replaced by the time domain load signal after acceleration with the duration of 36s for a durable vibration test, so that the aim of improving the test efficiency is fulfilled.
Noteworthy are: in this embodiment, the length of the intercepted time period does not affect the solving accuracy within a certain range. For example: time domain data of 5s and 9s are intercepted from a certain task segment respectively, a fatigue damage spectrum integral value calculated by the 5s time domain data is 9.9e-26, a fatigue damage spectrum integral value calculated by the 9s time domain data is 1.58e-25, a fatigue damage spectrum ratio is 1.6, a duration ratio is 1.8, and therefore the solving precision of the fatigue damage spectrum in the cut-off time is smaller, and the cut-off time can be determined according to practical conditions. In contrast, the present invention is applicable to a variety of applications; if the measured signal is not subjected to the segment simplification process, the fatigue damage spectrum calculation is directly performed, as shown in fig. 7, the time domain data calculation time length of one 60s is 473s, after the time domain segment is segmented, the 5s time domain data is taken to calculate the fatigue damage spectrum, as shown in fig. 8, the calculation time length is 97s, so that the time is shortened by 387%, and the solving efficiency is greatly improved.
In conclusion, the embodiment directly adopts the actual measurement vibration data of the airborne equipment, accords with the actual environment, and ensures the accuracy of the load of the airborne equipment; the fatigue acceleration is carried out on the vibration fatigue of the on-board equipment by utilizing the fatigue damage spectrum equivalent theory, so that the method is not only suitable for single-task equipment, but also suitable for equipment subjected to different vibration loads in long-life multi-task state; by adopting the method based on the actual measurement spectrum and fatigue damage equivalence, the phenomena of over test and under test are avoided, and a more scientific test assessment method is provided for the service life evaluation of the durable vibration environment of the airborne equipment.
Example 2
The embodiment discloses a system for determining fatigue damage acceleration endurance test conditions of airborne equipment, which comprises a memory, a processor and a computer program stored on the memory and capable of running on the processor, wherein the processor executes the computer program to realize the method corresponding to the embodiment.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The method for determining the fatigue damage acceleration endurance test condition of the airborne equipment is characterized by comprising the following steps of:
step one: preprocessing the collected actual measurement signals of the full task section;
step two: judging whether the load data of any task segment is greater than or equal to a classification threshold according to the load amplitude change of the preprocessed actual measurement signal, if so, sequencing, reorganizing and classifying the corresponding task segments according to the load amplitude change trend, and then carrying out load data T on each stage of task segments i Intercepting a representative period of time T i section Is a waveform of (a); wherein,
，/>
the task segments are classified into the same level, wherein the classification number of the task segments is the total number of the task segments, and the task segments smaller than the classification threshold value are regarded as the same level;
step three: fatigue damage value D generated by corresponding to waveform intercepted at each stage of computer-carried equipment Ti section The method comprises the steps of carrying out a first treatment on the surface of the The method specifically comprises the following steps: calculating stress-time functions for each waveform, and counting stress circulation times under each amplitude by adopting a rain flow counting method; then, according to Miner criterion, calculating fatigue damage values generated by corresponding to the intercepted waveforms of each level by combining the characteristic parameters of the standard S-N curve of the airborne equipment;
step four: fatigue damage value D generated according to waveform intercepted at each stage Ti section Obtaining a fatigue damage value D of the on-board equipment in a full-task state:
step five: the method comprises the steps of presetting endurance test condition acceleration time, taking load stress less than or equal to material yield strength of airborne equipment and not changing failure mechanism of the equipment as constraint, taking fatigue damage spectrum equivalence as principle, generating input load conditions of the same fatigue damage spectrum through iterative calculation and carrying out backward pushing, and obtaining endurance vibration test conditions under the condition that the damage mechanism of a system structure is not changed.
2. The method according to claim 1, wherein the preprocessing in the first step includes: removing abnormal data, supplementing lost data, and carrying out induction processing on the measured data through tolerance upper limit coefficient estimation and tolerance upper limit estimation.
3. The method of claim 1, wherein the classification threshold is such that the absolute value ratio of the maximum amplitude to the minimum amplitude is equal to 2.
4. A method according to claim 3, wherein in the reorganization of the second step, the same load amplitudes at the original discrete time points are continuously arranged, and the load amplitudes are adjacently arranged in the order from the large to the small or from the small to the large according to the order of the change trend of the load amplitudes.
5. The method according to claim 1, wherein calculating the stress-time function comprises:
waveform intercepted by each stage of task section is applied to a series of linear single-degree-of-freedom mass-spring systems, and a time function of relative displacement between each single-degree-of-freedom system and an excitation platform applying load is calculated
；
Proportional constant by stress-relative displacement
Calculating the stress to which the equipment system is subjected +.>
Time function of (2)
。
6. The method according to any one of claims 1 to 5, wherein during the iterative calculation in step five, the method specifically comprises:
calculating the fatigue damage value of the original load before recombination after pretreatment by the same method for calculating the fatigue damage value of the airborne equipment in the all-task state under random interception acceleration time, and expanding the intercepted corresponding load amplitude by acceleration time by 2 if the fatigue damage value after acceleration is smaller than the fatigue damage value before acceleration u Doubling the fatigue damage value until the fatigue damage value after acceleration is larger than the fatigue damage value before acceleration; and then continuously reducing the load amplitude through the load attenuation coefficient, when the fatigue damage value after acceleration is smaller than the fatigue damage value before acceleration, continuously increasing the load amplitude through the load amplification coefficient, sequentially performing iterative computation, finally enabling the fatigue damage value before acceleration to be equal to the fatigue damage value after acceleration, and reversely pushing out the time domain load after acceleration, wherein u is a positive integer.
7. The method of any one of claims 1 to 5, wherein the representative time periods intercepted by each hierarchy are of equal duration.
8. An on-board equipment fatigue damage acceleration endurance test condition determining system comprising a memory, a processor and a computer program stored on the memory and executable on the processor, characterized in that the processor implements the method of any of the preceding claims 1 to 7 when executing the computer program.
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| PCT/CN2024/076760 WO2024174914A1 (en) | 2023-02-21 | 2024-02-07 | Method and system for determining conditions of fatigue damage accelerated durability test for airborne device |
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| CN116029180B (en) * | 2023-03-30 | 2023-07-14 | 湖南云箭科技有限公司 | Airborne store fatigue simulation method and system |
| CN116050229B (en) * | 2023-03-31 | 2023-07-14 | 湖南云箭科技有限公司 | Optimization method and system of finite element model in airborne store fatigue simulation |
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| JP3908873B2 (en) * | 1998-06-16 | 2007-04-25 | カヤバ工業株式会社 | Vibration / excitation testing machine |
| CN100570307C (en) * | 2008-02-02 | 2009-12-16 | 长沙理工大学 | A kind of turbine carries the vibration damping experimental system of damping structure vane |
| CN101539493A (en) * | 2009-04-28 | 2009-09-23 | 中国地震局工程力学研究所 | Symmetric signal method for structural damage diagnosis |
| CN102798508A (en) * | 2011-05-27 | 2012-11-28 | 上海天纳克排气系统有限公司 | Accelerated endurance test method for catalytic converter assembly of commercial vehicle |
| WO2017186306A1 (en) * | 2016-04-29 | 2017-11-02 | Siemens Industry Software Nv | Method and system for accelerated fatigue damage testing of an object |
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| CN108548646B (en) * | 2018-03-28 | 2020-06-19 | 中国航发北京航空材料研究院 | Quantitative test method for whole damage evolution process in vibration fatigue test |
| CN110750851B (en) * | 2018-08-05 | 2024-07-19 | 北京航空航天大学 | Method for compiling accelerated fatigue load spectrum |
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| CN111581715B (en) * | 2020-03-23 | 2023-08-08 | 中国农业大学 | Rapid compression method for accelerating load spectrum of tractor part |
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