CN108548646A - The quantitative measuring method of damage development overall process in a kind of vibration fatigue test - Google Patents
The quantitative measuring method of damage development overall process in a kind of vibration fatigue test Download PDFInfo
- Publication number
- CN108548646A CN108548646A CN201810268754.3A CN201810268754A CN108548646A CN 108548646 A CN108548646 A CN 108548646A CN 201810268754 A CN201810268754 A CN 201810268754A CN 108548646 A CN108548646 A CN 108548646A
- Authority
- CN
- China
- Prior art keywords
- sample
- vibration
- exciting
- test
- damage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0001—Type of application of the stress
- G01N2203/0005—Repeated or cyclic
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention is a kind of quantitative measuring method of damage development overall process in vibration fatigue test, this method uses the displacement sinusoidal signal of laser displacement sensor synchronous recording sample, using the exciting acceleration signal of acceleration transducer synchronous recording vibration rig stage body；Sentence method for distinguishing by phase difference and capture intrinsic frequency of sample during vibrating fatigue, and energy real-time tracking and the change procedure for recording intrinsic frequency come accurate, to realize the quantitative test to sample damage development overall process in vibration fatigue test.Test method proposed by the present invention can measure damage starting and loss evolution overall process of the sample in vibration fatigue test life cycle management online, and require test equipment low, the accuracy height of data, and the reference significance of data result is big.Fatigue damage feature and fatigue life rule for research material and structure have important application value.
Description
Technical field
The present invention is a kind of quantitative measuring method of damage development overall process in vibration fatigue test, belongs to mechanical property survey
Try technical field.
Background technology
Fatigue failure is failure mode common in engineering material.Carry out fatigue property test for engineering material, for
The design and life prediction of engineering structure part have very important significance.Vibration is forms of motion common in engineering structure,
And the major reason for causing engineering structure and fatigue of materials to fail, therefore vibrationfatigue test is that acquisition material and structural member exist
The important means of testing of fatigue behaviour under vibration condition.
During fatigue loading, in-situ observation is carried out to the tired danger area of sample, with obtain fatigue damage starting and
Damage development overall process has a very important significance the fatigue behaviour of research material and structure.Sample is in vibrating fatigue
In test process, vibration frequency is usually relatively high (hundreds of arrive thousands of Hz), under so high vibrating fatigue frequency condition, uses
The method real-time acquisition difficult to realize to sample fatigue damage starting and damage development image of online in-situ image observation, this
Outside, since the fatigue and cyclic cycle required by vibrationfatigue test is higher, 10 have been generally reached7To 109Recurring number, single sample
Test period possibly even be up to dozens of days, even if the tired danger area image in damage development overall process can be collected,
Its image scale also will be quite huge, and very high challenge is proposed for image storage and processing.Therefore, suitable there is an urgent need for finding
Alternative damages sample during vibration fatigue test to realize the quantitative test of starting and evolution overall process.
Invention content
The present invention is exactly designed and is provided in a kind of vibration fatigue test in view of the above-mentioned deficiencies in the prior art
The quantitative measuring method of damage development overall process, the purpose is to easy, quickly and accurately acquisition material vibrating fatigue damage develops
Overall process.
Technical solution of the invention is as follows：
The quantitative measuring method of damage development overall process in this kind of vibration fatigue test, it is characterised in that：The step of this method
It is rapid as follows：
Step 1: according to air standard《Engine blade and material vibrating fatigue test method》(HB5277-1984) accurate
Standby sample；
Step 2: sample is mounted on vibration rig, sample is loaded, Loaded contact analysis is sine wave, is adjusted
The excited frequency of vibration rig stage body is saved to the intrinsic frequency f of sample0, so that sample is resonated, then, adjust vibration examination
The exciting acceleration for testing equipment stage body after so that sample amplitude is reached specified value, keeps experiment stress state and starts the cycle over counting；
The specified value is the amplitude corresponding to the stress level of test requirements document；
Using the displacement sinusoidal signal of laser displacement sensor synchronous recording sample, using acceleration transducer synchronous recording
The exciting acceleration signal of vibration rig stage body；
The displacement sinusoidal signal is described with following formula：
In formula：
The shift value of the sample of x-laser displacement sensor synchronous recording, unit mm；
x0The specified value of-sample amplitude, unit mm；
T-time, unit s；
f1The frequency of displacement sinusoidal signal of the sample of-laser displacement sensor record under resonance state, unit Hz；
The phase difference of-displacement sinusoidal signal and exciting acceleration signal；
The exciting acceleration signal is described with following formula：
A=a0sin(2πf2t)…………………………………………………[2]
In formula：
The acceleration value of the vibration rig stage body of a-acceleration transducer synchronous recording, unit m/s2；
a0The exciting acceleration amplitude of-vibration rig stage body when sample amplitude being made to reach specified value, unit m/s2；
f2The frequency of exciting acceleration signal of the sample of-acceleration transducer record under resonance state, unit Hz；
Step 3: after fatigue damage occurs for sample, declines with the intrinsic frequency of sample, adjust exciting acceleration signal
Frequency f2So that sample is kept resonance, and keep the specified value of sample amplitude, until sample fails；
Step 4: according to the exciting acceleration signal of the vibration rig stage body of acceleration transducer synchronous recording, obtain
To the frequency f of the exciting acceleration signal under resonance state2The real-time f of N is counted with loaded cycle2- N relation curves, by the song
Line exports the real-time relationship curve of the damaging parameter D and loaded cycle counting N of sample, and damaging parameter D is described with following formula：
In formula：
The variation range of the damage variable of D-sample, dimensionless, D is：0≤D≤1, wherein as D=1, sample is complete
Damage and failure；
K-fail-ure criterion coefficient, according to air standard《Engine blade and material vibrating fatigue test method》
(HB5277-1984) regulation is chosen.
After damage starting occurs for sample, declines with the intrinsic frequency of sample, f need to be increased2- N and D-N data record frequencies
It is secondary；And before sample damages, within longer test period, f2Without significant change, f can be reduced2- N and D-N data records
The frequency stores pressure to mitigate data.When D=1 is calculated in formula [3], fatigue rupture occurs for judgement sample, or reaches
Provide largest loop number NfWhen, experiment terminates.
The vibration rig includes stage body, laser displacement sensor, acceleration transducer, vibration controller and master control
Computer, vibration controller are used for the control and acquisition of signal, and main control computer being capable of real-time storage and display vibration controller
The various signals transmitted.
In step 2, the phase difference of real-time displacement sinusoidal signal and exciting acceleration signalWork as phase differenceIt is 90 °, examination
Sample is resonance state.
In actual moving process,It is difficult to capture at the time of being equal to 90 °, it is believed thatWhen being substantial access to 90 ° just
It resonates, works as phase differenceWhen meeting following formula [4], sample is in resonance state：
In formula：
ζ-phase difference offset threshold, unit be °, value be more than 0 °, be less than 2 °.
After Vibration on Start-up pilot system, before fatigue damage occurs for sample, phase differenceThe requirement of coincidence formula [4], exciting
The frequency f2 of acceleration signal is equal with the initial intrinsic frequency f0 of sample.
The present invention has the special feature that and has the beneficial effect that：
Using the displacement sinusoidal signal of laser displacement sensor synchronous recording sample, using acceleration transducer synchronous recording
The exciting acceleration signal of vibration rig stage body；Method for distinguishing is sentenced by phase difference accurately to capture sample in vibrating fatigue
Intrinsic frequency in the process, and energy real-time tracking and the change procedure for recording intrinsic frequency, it is tired in vibration to sample to realize
The quantitative test of damage development overall process in labor experiment.It is tired in vibration that test method proposed by the present invention can measure sample online
Labor tests damage starting and loss evolution overall process in life cycle management, and requires low, the accuracy of data to test equipment
The reference significance of height, data result is big.Fatigue damage feature and fatigue life rule for research material and structure have weight
The application value wanted.
Description of the drawings
Fig. 1 is the test method flow chart of the present invention.
Fig. 2 is the sheet coupon figure used in the embodiment of the present invention.
Fig. 3 is the evolution curve of frequency in embodiment-cycle cycle and damage variable-cycle cycle.
Specific implementation mode
It elaborates to the present invention below with reference to drawings and examples.
Shown in attached drawing 1, in this kind of vibration fatigue test the step of the quantitative measuring method of damage development overall process such as
Under：
Step 1: according to air standard《Engine blade and material vibrating fatigue test method》(HB5277-1984) it makes
Standby sample；
Sample uses TA11 titanium alloy plates, thickness 2mm, sample long 120mm, width 20mm, and dangerouse cross-section is minimum
Width is 10mm, and specimen shape and size are shown in Fig. 2.By actual measurement, sample initial intrinsic frequency f is determined0For 246Hz, maximum is followed
Number of rings NfIt is 107Cycle, it is specified that maximum proof stress value be 440MPa, demarcated through overstress, determine the specified value of sample amplitude
For 2.505mm；
Step 2: sample is mounted on vibration rig, vibration rig is the vibration that closed-loop control can be achieved
Fatigue test system, the vibration rig include stage body, laser displacement sensor, acceleration transducer, vibration controller
And main control computer, vibration controller are used for the control and acquisition of signal, main control computer being capable of real-time storage and display vibration
The various signals that controller transmits connect each measurement and control unit, form closed loop, can realize during the experiment certainly
Dynamic closed loop accurately controls, and mitigates manual operation intensity；
Sample is loaded, Loaded contact analysis is sine wave, adjusts the excited frequency of vibration rig stage body to sample
Intrinsic frequency f0, after the two is coincide, sample resonates, and then, adjusts the exciting acceleration of vibration rig stage body, makes
After sample amplitude reaches specified value, keeps experiment stress state and start the cycle over counting；
The specified value is the amplitude corresponding to the stress level of test requirements document；
Using the displacement sinusoidal signal of laser displacement sensor synchronous recording sample, using acceleration transducer synchronous recording
The exciting acceleration signal of vibration rig stage body；
The displacement sinusoidal signal is described with following formula：
In formula：
The shift value of the sample of x-laser displacement sensor synchronous recording, unit mm；
x0The specified value of-sample amplitude, unit mm；
T-time, unit s；
f1The frequency of displacement sinusoidal signal of the sample of-laser displacement sensor record under resonance state, unit Hz；
The phase difference of-displacement sinusoidal signal and exciting acceleration signal；
The exciting acceleration signal is described with following formula：
A=a0sin(2f2t)……………………………………………………[2]
In formula：
The exciting acceleration value of the vibration rig stage body of a-acceleration transducer synchronous recording, unit m/s2；
a0The exciting acceleration amplitude of-vibration rig stage body when sample amplitude being made to reach specified value, unit m/s2；
f2The frequency of exciting acceleration signal of the sample of-acceleration transducer record under resonance state, unit Hz；
In step 2, the phase difference of real-time displacement sinusoidal signal and exciting acceleration signalWork as phase differenceIt is 90 °, examination
Sample is resonance state.But in actual moving process,It is difficult to capture at the time of being equal to 90 °, it is believed thatIt is substantial access to
It just resonates at 90 °, works as phase differenceWhen meeting following formula [4], sample is in resonance state：
In formula：
ζ-phase difference offset threshold, unit be °, value be 2 °；
Whether vibration rig in real time judge in resonance state sample according to the result of calculation of formula [4],
If the judgment is No, continue to adjusting the excited frequency of vibration rig stage body to the intrinsic frequency f of sample0, adjust simultaneously
The exciting acceleration of vibration rig stage body, makes sample amplitude reach specified value；
Step 3: after fatigue damage occurs for sample, declines with the intrinsic frequency of sample, adjust exciting acceleration signal
Frequency f2So that sample is kept resonance, and keep the specified value of sample amplitude, until sample fails；
Step 4: according to the exciting acceleration signal of the vibration rig stage body of acceleration transducer synchronous recording, obtain
To the frequency f of the exciting acceleration signal under resonance state2The real-time f of N is counted with loaded cycle2- N relation curves, by the song
Damaging parameter D and the loaded cycle that line exports sample count the real-time relationship curve of N, as shown in figure 3, damaging parameter D is with following
Formula describes：
In formula：
The variation range of the damage variable of D-sample, dimensionless, D is：0≤D≤1, wherein as D=1, sample is complete
Damage and failure；
K-fail-ure criterion coefficient, value 0.01, according to air standard《Engine blade and material vibrating fatigue test
Method》(HB5277-1984) regulation is chosen.
In Fig. 3, the relation curve of damaging parameter D and loaded cycle number N is provided in real time, and wherein damaging parameter D presses formula [3]
It is calculated.When recurring number reaches 5.269 × 106When, D=1, sample destroys, off-test, exports f2- N curves and D-N
Data simultaneously draw curve.
Claims (3)
1. the quantitative measuring method of damage development overall process in a kind of vibration fatigue test, it is characterised in that：The step of this method
It is as follows：
Step 1: according to air standard《Engine blade and material vibrating fatigue test method》(HB5277-1984) prepare examination
Sample；
Step 2: sample is mounted on vibration rig, sample is loaded, Loaded contact analysis is sine wave, and adjusting is shaken
The excited frequency of dynamic test equipment stage body makes sample resonate to the intrinsic frequency f0 of sample, then, adjusts vibration test and sets
The exciting acceleration of standby stage body after so that sample amplitude is reached specified value, keeps experiment stress state and starts the cycle over counting；
The specified value is the amplitude corresponding to the stress level of test requirements document；
Using the displacement sinusoidal signal of laser displacement sensor synchronous recording sample, vibrated using acceleration transducer synchronous recording
The exciting acceleration signal of testing equipment stage body；
The displacement sinusoidal signal is described with following formula：
In formula：
The shift value of the sample of x-laser displacement sensor synchronous recording, unit mm；
x0The specified value of-sample amplitude, unit mm；
T-time, unit s；
f1The frequency of displacement sinusoidal signal of the sample of-laser displacement sensor record under resonance state, unit Hz；
The phase difference of-displacement sinusoidal signal and exciting acceleration signal；
The exciting acceleration signal is described with following formula：
A=a0sin(2πf2t)………………………………………………………[2]
In formula：
The exciting acceleration value of the vibration rig stage body of a-acceleration transducer synchronous recording, unit m/s2；
a0The exciting acceleration amplitude of-vibration rig stage body when sample amplitude being made to reach specified value, unit m/s2；
f2The frequency of exciting acceleration signal of the sample of-acceleration transducer record under resonance state, unit Hz；
Step 3: after fatigue damage occurs for sample, declines with the intrinsic frequency of sample, adjust the frequency of exciting acceleration signal
Rate f2So that sample is kept resonance, and keep the specified value of sample amplitude, until sample fails；
Step 4: according to the exciting acceleration signal of the vibration rig stage body of acceleration transducer synchronous recording, obtain
The frequency f of exciting acceleration signal under resonance state2The real-time f of N is counted with loaded cycle2- N relation curves are led by the curve
The damaging parameter D for going out sample counts the real-time relationship curve of N with loaded cycle, and damaging parameter D is described with following formula：
In formula：
The variation range of the damage variable of D-sample, dimensionless, D is：0≤D≤1, wherein as D=1, sample damages completely
It destroys；
K-fail-ure criterion coefficient, according to air standard《Engine blade and material vibrating fatigue test method》(HB5277-
1984) regulation is chosen.
2. the quantitative measuring method of damage development overall process, feature exist in vibration fatigue test according to claim 1
In：In step 2, the phase difference of real-time displacement sinusoidal signal and exciting acceleration signalWork as phase differenceIt it is 90 °, sample is
Resonance state.
3. the quantitative measuring method of damage development overall process, feature exist in vibration fatigue test according to claim 2
In：Work as phase differenceWhen meeting following formula [4], sample is in resonance state：
In formula：
ζ-phase difference offset threshold, unit be °, value be more than 0 °, be less than 2 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810268754.3A CN108548646B (en) | 2018-03-28 | 2018-03-28 | Quantitative test method for whole damage evolution process in vibration fatigue test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810268754.3A CN108548646B (en) | 2018-03-28 | 2018-03-28 | Quantitative test method for whole damage evolution process in vibration fatigue test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108548646A true CN108548646A (en) | 2018-09-18 |
| CN108548646B CN108548646B (en) | 2020-06-19 |
Family
ID=63517285
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810268754.3A Active CN108548646B (en) | 2018-03-28 | 2018-03-28 | Quantitative test method for whole damage evolution process in vibration fatigue test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108548646B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109632229A (en) * | 2019-01-25 | 2019-04-16 | 北京航空航天大学 | Resonance fatigue test method, device and engineering testing fatigue platform |
| CN109946057A (en) * | 2019-03-28 | 2019-06-28 | 湖南科技大学 | A kind of pneumatic equipment bladess damage diagnosis method based on intrinsic frequency |
| CN110542525A (en) * | 2019-06-25 | 2019-12-06 | 上海航空材料结构检测股份有限公司 | Method for testing vibration fatigue performance of metal in axial resonance state |
| CN113624434A (en) * | 2021-07-23 | 2021-11-09 | 东风汽车集团股份有限公司 | Test method and device for hybrid electric drive assembly |
| CN114813003A (en) * | 2022-06-27 | 2022-07-29 | 中国飞机强度研究所 | Multi-parameter measurement method for vibration fatigue damage of metal component of airplane |
| CN114813005A (en) * | 2022-06-29 | 2022-07-29 | 中国飞机强度研究所 | System and method for testing vibration fatigue characteristics of airplane components |
| CN115824545A (en) * | 2023-02-21 | 2023-03-21 | 湖南云箭科技有限公司 | Method and system for determining fatigue damage accelerated endurance test conditions of airborne equipment |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005308732A (en) * | 2004-03-26 | 2005-11-04 | Sekisui Jushi Co Ltd | Vibration durability evaluation method for mark pillar |
| JP2007147634A (en) * | 2006-12-22 | 2007-06-14 | Rikogaku Shinkokai | Method and device for vibration analysis and computer-readable recording medium |
| CN201876344U (en) * | 2010-05-17 | 2011-06-22 | 王士敏 | Resonant vibration table with adjustable supporting rigidity |
| CN105651496A (en) * | 2014-11-19 | 2016-06-08 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining fatigue life index of hydraulic conduit |
-
2018
- 2018-03-28 CN CN201810268754.3A patent/CN108548646B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005308732A (en) * | 2004-03-26 | 2005-11-04 | Sekisui Jushi Co Ltd | Vibration durability evaluation method for mark pillar |
| JP2007147634A (en) * | 2006-12-22 | 2007-06-14 | Rikogaku Shinkokai | Method and device for vibration analysis and computer-readable recording medium |
| CN201876344U (en) * | 2010-05-17 | 2011-06-22 | 王士敏 | Resonant vibration table with adjustable supporting rigidity |
| CN105651496A (en) * | 2014-11-19 | 2016-06-08 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining fatigue life index of hydraulic conduit |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109632229A (en) * | 2019-01-25 | 2019-04-16 | 北京航空航天大学 | Resonance fatigue test method, device and engineering testing fatigue platform |
| CN109946057A (en) * | 2019-03-28 | 2019-06-28 | 湖南科技大学 | A kind of pneumatic equipment bladess damage diagnosis method based on intrinsic frequency |
| CN109946057B (en) * | 2019-03-28 | 2020-09-01 | 湖南科技大学 | Wind turbine blade damage diagnosis method based on natural frequency |
| CN110542525A (en) * | 2019-06-25 | 2019-12-06 | 上海航空材料结构检测股份有限公司 | Method for testing vibration fatigue performance of metal in axial resonance state |
| CN113624434A (en) * | 2021-07-23 | 2021-11-09 | 东风汽车集团股份有限公司 | Test method and device for hybrid electric drive assembly |
| CN113624434B (en) * | 2021-07-23 | 2023-12-19 | 东风汽车集团股份有限公司 | Test method and device for hybrid electric drive assembly |
| CN114813003A (en) * | 2022-06-27 | 2022-07-29 | 中国飞机强度研究所 | Multi-parameter measurement method for vibration fatigue damage of metal component of airplane |
| CN114813005A (en) * | 2022-06-29 | 2022-07-29 | 中国飞机强度研究所 | System and method for testing vibration fatigue characteristics of airplane components |
| CN114813005B (en) * | 2022-06-29 | 2022-09-20 | 中国飞机强度研究所 | System and method for testing vibration fatigue characteristics of airplane components |
| CN115824545A (en) * | 2023-02-21 | 2023-03-21 | 湖南云箭科技有限公司 | Method and system for determining fatigue damage accelerated endurance test conditions of airborne equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108548646B (en) | 2020-06-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108548646A (en) | The quantitative measuring method of damage development overall process in a kind of vibration fatigue test | |
| WO2020057270A1 (en) | Ultrasonic nondestructive detection method for expanded size of micro crack of material | |
| CN106950280B (en) | Fibre reinforced composites parameter identification method based on the lossless scanning of laser | |
| Chaudhry et al. | Local-area health monitoring of aircraft via piezoelectric actuator/sensor patches | |
| CN102759487B (en) | Partial stiffness method based composite material non-destructive detection system and detection method | |
| Chaudhry et al. | Monitoring the integrity of composite patch structural repair via piezoelectric actuators/sensors | |
| CN102466597B (en) | Nondestructive test and evaluation method of metal member / material residual life | |
| CN109406036A (en) | Monitor the system and method for wind-driven generator bolt fastening stress on-line | |
| EP3435044A1 (en) | Apparatus and method for performing an impact excitation technique | |
| WO2020019531A1 (en) | Assessment system and early warning method for steam turbine blade cracks | |
| CN105067703A (en) | Plate-like metal member/material remaining life non-destructive detection and evaluation method | |
| CN103760024A (en) | Method for objectively determining crack initiation strength of rock on basis of accumulated sound emission impact times | |
| CN203178052U (en) | Blade vibration fatigue automatic test system | |
| CN108318238A (en) | A kind of fatigue test system of engine blade | |
| CN105784238A (en) | Method for measuring material surface residual stress and system thereof | |
| Winston et al. | Structural health monitoring with piezoelectric active sensors | |
| CN110108430A (en) | A kind of high-precision damage positioning method of fibre reinforced composites beam | |
| CN104977218A (en) | Device and method for detecting rigidity of micro elastic parts | |
| WO2020191704A1 (en) | Composite material dynamic fatigue testing device and method based on reverse resonance | |
| CN105092708A (en) | System and method for detecting damages on helicopter composite material blades | |
| CN111678990A (en) | Ultrasonic fatigue crack propagation rate measuring method based on natural frequency | |
| Keilers Jr et al. | Damage detection and diagnosis of composites using built-in piezoceramics | |
| CN107525848A (en) | The detection method and equipment of the material parameter of cement-based material | |
| Whitlow et al. | Failure prediction in ceramic composites using acoustic emission and digital image correlation | |
| CN110082432B (en) | Ultrasonic resonance quantitative nondestructive detection method for plate structure defects based on uniform design |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |