CN110243941A - A kind of lossless detection method of solid propellant rocket interfacial detachment defect - Google Patents
A kind of lossless detection method of solid propellant rocket interfacial detachment defect Download PDFInfo
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Abstract
A kind of lossless detection method of solid propellant rocket interfacial detachment defect is used for Solid Rocket Motor combustion chamber Interface detection by dynamo-electric impedance method in conjunction with frequency response function method.The present invention is with composition detection systems such as common apparatus NI multi-channel high-speed data collector, PCB power hammer and sensors, the power that body structure surface to be measured gives pulse type is tapped using power hammer, the time domain waveform of response signal is measured by signal acquisition program, and then engine heat insulation layer/lining/propellant interface frequency response function curve is obtained, to determine whether the interfacial structure is intact.The present invention for the complex fiber material of diameter about 2000mm solid propellant rocket propellant/lining // heat insulation layer interfacial detachment defect is motor-driven, quick non-destructive testing, for the integral product of general assembly, without decomposing just detection can be realized at storage scene, have the characteristics that convenient and efficient, is suitble to the quick investigation of the integral product interfacial detachment defect of general assembly.
Description
Technical field
The present invention relates to field of non destructive testing, specially a kind of solid propellant rocket propellant/lining/insulation bed boundary
The lossless detection method that debonding defect is quickly checked.
Background technique
Currently, domestic be directed to the lossless inspection of solid propellant rocket propellant/lining interface/heat insulation layer interfacial detachment defect
Survey method only has radiography detection and two kinds of ultrasound detection according to the difference of case material.
It (1) is the solid propellant rocket of nonmetal-fiber-material, propellant/lining/heat insulation layer for case material
The debonding defect at interface is only capable of uniquely radiography techniques being relied on to be detected at present, such as the forth academy, Aerospace Science and Technology Corporation Xi'an boat
Its chemomotive force Co., Ltd is early in decades ago with regard to having used radiography techniques to carry out all kinds of engine propellant/linings
Layer/insulation bed boundary it is actually detected.Ray detection generally uses electron linear accelerator, and for energy in 1~15MeV, utilization is micro-
Wave electric field, along rectilinear orbit accelerate electronics arrive higher-energy, generate X-ray penetration power by force, high sensitivity, in solid-rocket
It is used widely in the quality testing of engine chamber.X-ray usually energy in 1MeV or more is referred to as high energy X
Ray can penetrate the tested position of combustion chamber, generate scattering in the process and absorb, and intensity gradually weakens, and decay journey
Degree has close relationship with examined workpiece material and structure.Ray through overdamping projects on film for industrial radiography, and formation can
Visible image judges the quality of examined workpiece for testing staff.If object regional area existing defects, it will change object to penetrating
The decaying of line causes the variation of transmitted ray intensity, detects transmitted ray intensity using film, so that it may inside judgment object
Defect and substance distribution.
(2) for the solid propellant rocket of metal housing materials, propellant/lining/insulation bed boundary unsticking is lacked
Falling into early stage is also to be detected using radiography techniques always.2014, eight institute, Shanghai Aerospace Science and Technology Corporation used low first
Frequency ultrasonic technical method realizes steel sheel engine of the diameter of the housing greater than 200mm, heat insulation layer thickness less than 8mm and promotes
The detection of agent/lining/heat insulation layer interfacial detachment defect.Its mechanism is fixed for the boundary condition side of heat insulation layer, the other side is free,
By adjusting the odd-multiple of 1/4 wavelength of ultrasonic wave incident acoustic wave, heat insulation layer thickness is made it equal to, thus the generation office in heat insulation layer
Portion's resonance shows as the increase and the extension of die-away time of echo waveform saturation length, finally judges propellant/lining/insulation
Bed boundary whether debonding defect.
In above two method, the limitation of ultrasound detection is to be only capable of having on the solid propellant rocket of steel sheel material
Realization propellant/lining/heat insulation layer interfacial detachment defect detection of condition, for being nonmetal-fiber-material in case material
Solid propellant rocket detection, ultrasound detection be not possible to realize application.And although metal may be implemented in high-energy ray photographic process
Effective detection of material housing and nonmetal-fiber-material shell, but there is many limitations.
(1) detection efficiency is low, and site requirements is fixed, operate and transport it is many and diverse, especially after solid engines general assembly finished product
The quality testing of propellant/lining interface is carried out again, it is necessary to entire product is subjected to decomposition disassembly, then be transported to the dedicated field of ray
Ground is detected, and during which process needs to expend the several months, complicated for operation and there are more safe mass risks.
(2) to human body there are potential radiation injury, the requirement to security protection is very high for radiography detection.
(3) higher cost and detection position are difficult to all standing.
(4) motion in the field, easily detection especially cannot achieve for large-sized solid rocket engine.
Summary of the invention
For overcome detection efficiency existing in the prior art it is low, it is complicated for operation and there are more safe mass risk, with
And detection position is difficult to the deficiency of all standing, the invention proposes a kind of lossless inspections of solid propellant rocket interfacial detachment defect
Survey method.
Detailed process of the invention is:
Step 1: the measurement of sensor is pasted.
The capacitor of selected sensor should be 2.5nF ± 30%.
The sensor paste position is determining according to the length of motor body, and along the circumference of the motor body
It is uniformly distributed, uniformly distributed eight sensors on each circumference, and make the distance between the sensor paste positions of two adjacent circumference be
300mm。
Step 2: connection sensor
Boxcar is connect with high speed data acquisition system.One sensor is connect with the boxcar.
Step 3: equipment debugging and setting
The equipment debugging is to open the multi-channel high-speed data collector with setting, and opening force hammer pumping signal is adopted
Collection program enters the main interface of capture program, and setting sample frequency is 10000Hz, sampling time 2s.
Step 4: the detection of sensor
Each sensor is detected respectively by pretest.
When peak frequencies after being tapped obtained in the detection three times are consistent with amplitude, sensor detection is qualified；It is on the contrary
Then determine that sensor detection is unqualified, should check the sticking state of sensor or re-measure the capacitance parameter of sensor, when
When pasting loosening or capacitance parameter exception, it should re-replace, paste sensor.
When all sensors detection finishes and determines all sensors qualification, then 5 are entered step, respectively to whole sensings
Device carries out official testing.
The detailed process of each sensor detection is: operation program is simultaneously emitted by percussion instruction, make in power hammer 2s with
Surface of shell in the sensor perimeter 100mm of boxcar connection carries out first time percussion；It taps strength and is not more than 5N.After percussion
Signal after being tapped by sensor acquisition.If acquiring successfully, 1 can be generated in the signal time domain channel of the main interface of capture program
A pulse signal can generate 1 time domain waveform in the signal frequency domain channel of the main interface of capture program；Obtain what first time tapped
Waveform.If acquisition failure, can generate sky in the signal time domain channel of the main interface of capture program and adopt straight line, in signal frequency domain channel
Zigzag noise signal can be generated.
The percussion and collection process are repeated, progress the is continued at sensor perimeter 100mm connect to this with boxcar
Secondary percussion obtains the waveform of second of percussion.
Second of percussion and collection process are repeated, is continued at the sensor perimeter 100mm being connect to this with boxcar
Third time percussion is carried out, the wavy line that third time taps is obtained.
So far, the pretest detection process to first sensor is completed.
The conducting wire that first sensor is connect with boxcar is removed, boxcar is connect with second sensor and repeats institute
The detection process for stating first sensor detects second sensor, and completes the judgement to second sensor.
It is iteratively repeated the detection process to second sensor, remaining each sensor is detected respectively.Until completing
Detection to all sensors, and complete the judgement to all sensors.
Step 5: the test of engine defect
Respectively obtain the waveform after tapping each sensor each time.
When the test of the engine defect, first sensor is connect with boxcar, make in 2s power hammer this
First time percussion is carried out in one sensor perimeter 100mm；It taps strength and is not more than 5N.It is acquired and is tapped by sensor after percussion
Signal afterwards.1 pulse signal can be generated in the signal time domain channel of the main interface of capture program, in the main interface of capture program
Signal frequency domain channel can generate 1 time domain waveform；Obtain the waveform tapped for the first time.The waveform that the first time taps is with electricity
The form of pressure response signal and voltage excitation signals is saved.The voltage responsive signal is acquired and is saved by sensor, voltage
Pumping signal is applied on sensor by multi-channel high-speed data collector.
The process for tapping waveform for the first time is obtained described in repeating, and the 2nd~5 percussion is carried out to first sensor, point
It does not obtain and saves the waveform obtained after the 2nd~5 percussion.
So far, the test result of first sensor is obtained.
The conducting wire that removal sensor is connect with boxcar connect with next sensor and repeats first sensor
Test process, second sensor is tested；Obtain the test result of second sensor.
The test process of second sensor is repeated, until completing the test of all sensors.Step 6: test
As a result processing and analysis
The detailed process of the test result processing and analysis is:
Five test datas of obtain first sensor are imported in Matlab program, it will by the Matlab program
The voltage responsive signal of five test datas and the voltage excitation signals of application are collected on first sensor, are passed through
Cross-spectral density function in Matlab program respectively obtains five tests divided by the Power spectral density of pumping signal
The frequency response function curve of data.
Peak frequencies analysis is carried out to five test datas of first sensor, if it does not exist the defect, then
The wavy curve of five times obtained tests is smooth parabola shaped main wave crest；The defect if it exists, then five obtained
Wave crest quantity of the wavy curve of secondary test in the frequency in 1000Hz can reach more than two, it is apparent jagged to present
Wave crest, and the jagged wave crest can extend in the frequency of 1000~3000Hz.
The processing and analytic process to first sensor test results are repeated, one by one to each sensor test results
It is handled and is analyzed, until completing the processing and analysis of all each sensor test results.So far.It completes to the solid-rocket
The non-destructive testing of engine defect.
The present invention is named as electromechanical impedance frequency response function method, and the dynamo-electric impedance method is a kind of well-known technique, frequency response letter
Number method is a kind of data processing method, and the two R. concomitans are recorded currently without discovery is related, do not started in solid-rocket more
The record of machine combustion chamber Interface detection application.It is complex fiber material present invention is generally directed to diameter about 2000mm, case material
Solid propellant rocket propellant/lining // heat insulation layer interfacial detachment defect is motor-driven, quick non-destructive testing, particularly with
For integral product through general assembly, just detection can be realized at storage scene without decomposing, there is the advantage of very convenient and efficient,
It is very suitable to the quick investigation of the integral product interfacial detachment defect of general assembly.The present invention is high with common apparatus NI multichannel
The composition detection systems such as fast data collector, PCB power hammer and sensor, tap body structure surface to be measured using power hammer and give pulse type
Power, measure the time domain waveform of response signal by signal acquisition program, and then obtain engine heat insulation layer/lining/propellant
The frequency response function curve at interface, to determine whether the interfacial structure is intact.
Its test philosophy is according to formula for natural frequency:
In formula: ωnFor n-th order intrinsic frequency, K is stiffness matrix, and M is mass matrix.
When interfacial structure is there are when debonding defect, stiffness matrix and mass matrix change, the impedance of structure and intrinsic
Frequency can also generate corresponding variation, i.e., when interfacial structure unsticking and non-unsticking, stiffness matrix K and mass matrix M can occur
Change.Pass through the intrinsic frequency of statistical framework and analyze its variation, it can be determined that the debonding of interfacial structure.
When engine heat insulation layer/lining/propellant interfacial structure is intact, only one is more smooth for frequency response function curve
And frequency be less than 1000Hz main wave crest, when there is unsticking in engine heat insulation layer/lining/propellant interface, frequency response function
The wave crest of curve becomes abundant at branch, occurs several zigzag wave crests at frequency 1000Hz, or even may extend to frequency
At 3000Hz.
This method on the engine actually detected the results are shown in Table 1.
1. frequency response function method testing result of table
As it can be seen from table 1 this method can realize heat insulation layer/lining/propellant by wave crest quantity and peak frequencies
Glue well qualitative with unsticking in interface.When engine heat insulation layer/lining/propellant interfacial structure is intact, frequency response function curve exists
(about in 1000Hz) only has a wave crest in rather low-frequency area.When engine cylinder section heat insulation layer/lining/propellant interface occurs
When debonding defect, frequency response function curve will appear more than two wave crests, at maximum up to 9, and wave crest can extend to it is relatively high
Frequency area (about 1000~3000Hz).
The solid propellant rocket propellant that the present invention is suitable for diameter about 2000mm, case material is complex fiber material
The non-destructive testing of/lining/heat insulation layer interfacial detachment defect can judge that heat insulation layer/lining/is pushed away by wave crest quantity and frequency
Into the whether intact stickup in agent interface, when engine heat insulation layer/lining/propellant interfacial structure is intact, frequency response function curve exists
Rather low-frequency area (about in 1000Hz) only has a smooth parabola shaped main wave crest.When engine cylinder section heat insulation layer/lining
When debonding defect occurs in layer/propellant interface, the wave crest information of frequency response function curve can become abundant, (big in rather low-frequency area
In about 1000Hz) wave crest quantity can reach more than two, apparent zigzag is presented, and wave crest can extend to relative high frequency area
(about 1000~3000Hz).Quick, convenient and fast field can be carried out to the integral product for having delivered assembling using this method
Detection investigation, judges product heat insulation layer/whether intact stickup in lining/propellant interface by wave crest quantity and frequency, to discovery
The product of interfacial detachment defect is implemented to decompose transhipment again, further confirms that defect interface position, area by radiography detection
Etc. information, the accurate decomposition of engine may be implemented, avoid intact product it is unnecessary decomposition and transhipment.
Detailed description of the invention
Fig. 1 is specific implementation block diagram；
Fig. 2 is the intact waveform of engine interfacial structure；
Fig. 3 is engine interfacial detachment waveform；
Fig. 4 is flow chart of the invention.
Specific embodiment
The present embodiment is that certain solid propellant rocket propellant/lining/heat insulation layer interfacial detachment defect is motor-driven, quick nothing
Detection method is damaged, engine diameters detected are 2000mm, and case material is complex fiber material, and housing interior structure is successively
It is insulated layer material, lining material and composite solidpropellant for rubber, interface quality is required between various materials
It is bonded intact.
Specific implementation process is:
Step 1: the measurement of sensor is pasted
Confirmation measurement is carried out using capacitor of the multimeter to the sensor of whole lead zirconate titanates, the standard of confirmation is each sensing
The capacitor of device should be 2.5nF ± 30%.Measurement result is incongruent not to be used.
According to design requirement, sensor paste position is marked in the detection zone of motor body.The label passes
Sensor paste position is determined according to the length of motor body, and, each circumference uniformly distributed along the circumference of the motor body
It is upper to be evenly distributed with eight sensors, and the distance between adjacent sensor paste position of two circumference is made to be 300mm.
When stickup, the surface of shell of each sensor paste position is wiped to clean dustless.The AB glue of equivalent is taken to fill
It is uniformly applied to surface of shell position to be pasted and sensor bottom surface after dividing stirring, by the sensor alignment paste position finger
It gently compresses, until adhesive solidifies.
All sensors are numbered and record after pasting.
Step 2: connection sensor
Boxcar is connect with NI PXIe-1071 high speed data acquisition system.First sensor and the boxcar are connected again
It connects.
Step 3: equipment debugging and setting
The multi-channel high-speed data collector is opened, opening force hammer pumping signal capture program enters the master of capture program
Interface, setting sample frequency are 10000Hz, sampling time 2s.
Step 4: the detection of sensor
By pretest, sensor is detected respectively.The detailed process of each sensor detection is: operation program, together
When issue and tap instruction, so that surface of shell in the sensor perimeter 100mm connecting with boxcar in power hammer 2s is carried out first
Secondary percussion；It taps strength and is not more than 5N.Signal after being tapped after percussion by sensor acquisition.If acquiring successfully, in acquisition journey
The signal time domain channel of the main interface of sequence can generate 1 pulse signal, in the signal frequency domain channel meeting of the main interface of capture program
Generate 1 time domain waveform；Obtain the waveform tapped for the first time.If acquisition failure, in the signal time domain of the main interface of capture program
Channel can generate sky and adopt straight line, can generate zigzag noise signal in signal frequency domain channel.
The percussion and collection process are repeated, progress the is continued at sensor perimeter 100mm connect to this with boxcar
Secondary percussion obtains the waveform of second of percussion.
Second of percussion and collection process are repeated, is continued at the sensor perimeter 100mm being connect to this with boxcar
Third time percussion is carried out, the wavy line that third time taps is obtained.
When acquisition peak frequencies are consistent with amplitude after obtained percussion three times, sensor detection is qualified；It is on the contrary then sentence
Fixed sensor detection is unqualified, should check the sticking state of sensor or re-measure the capacitance parameter of sensor, work as stickup
When loosening or capacitance parameter exception, it should re-replace, paste sensor.
So far, the pretest detection process to first sensor is completed.
The conducting wire that first sensor is connect with boxcar is removed, boxcar is connect with second sensor and repeats institute
The detection process for stating first sensor detects second sensor, and completes the judgement to second sensor.
It is iteratively repeated the detection process to second sensor, remaining each sensor is detected respectively.Until completing
Detection to all sensors, and complete the judgement to all sensors.
When all sensors detection finishes and determines all sensors qualification, then 5 are entered step, respectively to whole sensings
Device carries out official testing.
Step 5: the test of engine defect
The engine defect refers to that the boundary defect, heat insulation layer and engine shell body interface of propellant and heat insulation layer lack
It falls into.
When test, first sensor is connect with boxcar.
When test, power hammer is made to carry out first time percussion in first sensor perimeter 100mm in 2s；Tap strength
No more than 5N.Signal after being tapped after percussion by sensor acquisition.In the signal time domain channel meeting of the main interface of capture program
1 pulse signal is generated, 1 time domain waveform can be generated in the signal frequency domain channel of the main interface of capture program；It obtains for the first time
The waveform of percussion.The waveform that the first time taps is saved in the form of voltage responsive signal and voltage excitation signals.It is described
Voltage responsive signal is acquired and is saved by sensor, and voltage excitation signals are to be applied to sensing by multi-channel high-speed data collector
On device.
The process for tapping waveform for the first time is obtained described in repeating, and the 2nd~5 percussion is carried out to first sensor, point
It does not obtain and saves the waveform obtained after the 2nd~5 percussion.
So far, the test result of first sensor is obtained.
The conducting wire that removal sensor is connect with boxcar connect with next sensor and repeats first sensor
Test process, second sensor is tested；Obtain the test result of second sensor.
The test process of second sensor is repeated, until completing the test of all sensors.
Step 6: the processing and analysis of test result
Five test datas of obtain first sensor are imported in Matlab program, it will by the Matlab program
The voltage responsive signal of five test datas and the voltage excitation signals of application are collected on first sensor, are passed through
Cross-spectral density function in Matlab program respectively obtains five tests divided by the Power spectral density of pumping signal
The frequency response function curve of data.The Matlab program is Wuhan University's establishment.
Peak frequencies analysis is carried out to five test datas of first sensor, if it does not exist the defect, then
The wavy curve of five times obtained tests is smooth parabola shaped main wave crest；The defect if it exists, then five obtained
Wave crest quantity of the wavy curve of secondary test in the frequency in 1000Hz can reach more than two, it is apparent jagged to present
Wave crest, and the jagged wave crest can extend in the frequency of 1000~3000Hz.
The processing and analytic process to first sensor test results are repeated, one by one to each sensor test results
It is handled and is analyzed, until completing the processing and analysis of all each sensor test results.So far.It completes to the solid-rocket
The non-destructive testing of engine defect.
Claims (6)
1. a kind of lossless detection method of solid propellant rocket interfacial detachment defect, which is characterized in that detailed process is:
Step 1, the measurement, stickup of sensor；
Step 2, it connects sensor: boxcar is connect with high speed data acquisition system；One sensor is connect with the boxcar；
Step 3, equipment debugging and setting；
Step 4, the detection of sensor: each sensor is detected respectively by pretest；
When peak frequencies after being tapped obtained in the detection three times are consistent with amplitude, sensor detection is qualified；It is on the contrary then sentence
Fixed sensor detection is unqualified, should check the sticking state of sensor or re-measure the capacitance parameter of sensor, work as stickup
When loosening or capacitance parameter exception, it should re-replace, paste sensor；
When all sensors detection finish and determine all sensors qualification when, then enter step 5, respectively to all sensors into
Row official testing；
Step 5, the test of engine defect；Respectively obtain the waveform after tapping each sensor each time；
Step 6, the processing and analysis of test result:
The detailed process of the test result processing and analysis is:
Five test datas of obtain first sensor are imported in Matlab program, by the Matlab program by first
The voltage responsive signal of five test datas and the voltage excitation signals of application are collected on a sensor, pass through Matlab program
In cross-spectral density function divided by the Power spectral density of pumping signal, respectively obtain the frequency response of five test datas
Function curve；
Peak frequencies analysis is carried out to five test datas of first sensor, the defect, then obtain if it does not exist
Five times test wavy curves be smooth parabola shaped main wave crest；The defect if it exists, then five surveys obtained
Wave crest quantity of the wavy curve of examination in the frequency in 1000Hz can reach more than two, apparent jagged wave is presented
Peak, and the jagged wave crest can extend in the frequency of 1000~3000Hz；
The processing and analytic process to first sensor test results are repeated, each sensor test results are carried out one by one
Processing and analysis, until completing the processing and analysis of all each sensor test results；So far；The solid-rocket is started in completion
The non-destructive testing of machine defect.
2. the lossless detection method of solid propellant rocket interfacial detachment defect as described in claim 1, which is characterized in that selected
The capacitor of sensor should be 2.5nF ± 30%.
3. the lossless detection method of solid propellant rocket interfacial detachment defect as described in claim 1, which is characterized in that described
Sensor paste position is determined according to the length of motor body, and, Mei Geyuan uniformly distributed along the circumference of the motor body
Uniformly distributed eight sensors on week, and the distance between adjacent sensor paste position of two circumference is made to be 300mm.
4. the lossless detection method of solid propellant rocket interfacial detachment defect as described in claim 1, which is characterized in that described
Equipment debugging makes with setting, opens the multi-channel high-speed data collector, and opening force hammer pumping signal capture program, which enters, to be adopted
Collect the main interface of program, setting sample frequency is 10000Hz, sampling time 2s.
5. the lossless detection method of solid propellant rocket interfacial detachment defect as described in claim 1, which is characterized in that described
The detailed process of each sensor detection is: operation program is simultaneously emitted by percussion instruction, makes connecting in power hammer 2s with boxcar
Surface of shell in sensor perimeter 100mm carries out first time percussion；It taps strength and is not more than 5N；It is adopted after percussion by sensor
Signal after collection percussion；If acquiring successfully, 1 pulse signal can be generated in the signal time domain channel of the main interface of capture program,
1 time domain waveform can be generated in the signal frequency domain channel of the main interface of capture program；Obtain the waveform tapped for the first time；If acquisition
Failure, can generate sky in the signal time domain channel of the main interface of capture program and adopt straight line, can generate sawtooth in signal frequency domain channel
Shape noise signal；
The percussion and collection process are repeated, continues to carry out at the sensor perimeter 100mm for connecting this with boxcar second
It taps, obtains the waveform of second of percussion；
Second of percussion and collection process are repeated, continues to carry out at the sensor perimeter 100mm for connecting this with boxcar
Third time taps, and obtains the wavy line that third time taps；
When acquisition peak frequencies are consistent with amplitude after obtained percussion three times, sensor detection is qualified；On the contrary then judgement is somebody's turn to do
Sensor detection is unqualified, should check the sticking state of sensor or re-measure the capacitance parameter of sensor, loosens when pasting
Or when capacitance parameter exception, it should re-replace, paste sensor；
So far, the pretest detection process to first sensor is completed；
The conducting wire that first sensor is connect with boxcar is removed, boxcar is connect with second sensor and repeats described
The detection process of one sensor detects second sensor, and completes the judgement to second sensor；
It is iteratively repeated the detection process to second sensor, remaining each sensor is detected respectively；Until completing to complete
The detection of portion's sensor, and complete the judgement to all sensors.
6. the lossless detection method of solid propellant rocket interfacial detachment defect as described in claim 1, which is characterized in that described
When the test of engine defect, first sensor is connect with boxcar, makes power hammer in first sensor week in 2s
First time percussion is carried out in the 100mm of side；It taps strength and is not more than 5N；Signal after being tapped after percussion by sensor acquisition；?
The signal time domain channel of the main interface of capture program can generate 1 pulse signal, in the signal frequency domain of the main interface of capture program
Channel can generate 1 time domain waveform；Obtain the waveform tapped for the first time；The waveform that the first time taps is with voltage responsive signal
It is saved with the form of voltage excitation signals；The voltage responsive signal is acquired and is saved by sensor, and voltage excitation signals are
It is applied on sensor by multi-channel high-speed data collector；
The process for tapping waveform for the first time is obtained described in repeating, and the 2nd~5 percussion is carried out to first sensor, respectively
To and save the 2nd~5 time tap after obtained waveform；
So far, the test result of first sensor is obtained；
The conducting wire that removal sensor is connect with boxcar connect with next sensor and repeats the survey of first sensor
Examination process tests second sensor；Obtain the test result of second sensor；
The test process of second sensor is repeated, until completing the test of all the sensors.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN114151237B (en) * | 2021-11-26 | 2022-11-18 | 武汉大学 | Intelligent detection system for debonding of solid rocket engine III interface and application method |
| CN115290597A (en) * | 2022-10-08 | 2022-11-04 | 首都师范大学 | Terahertz technology-based method and system for detecting coating adhesion-free defect |
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