CN114136556B - Spacecraft composite structure leakage positioning method based on wave velocity correction - Google Patents
Spacecraft composite structure leakage positioning method based on wave velocity correction Download PDFInfo
- Publication number
- CN114136556B CN114136556B CN202111448440.XA CN202111448440A CN114136556B CN 114136556 B CN114136556 B CN 114136556B CN 202111448440 A CN202111448440 A CN 202111448440A CN 114136556 B CN114136556 B CN 114136556B
- Authority
- CN
- China
- Prior art keywords
- leakage
- wave velocity
- wave
- sensor
- array
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 39
- 239000002131 composite material Substances 0.000 title claims abstract description 24
- 238000012937 correction Methods 0.000 title claims abstract description 15
- 238000002474 experimental method Methods 0.000 claims abstract description 15
- 238000001514 detection method Methods 0.000 claims abstract description 11
- 239000000463 material Substances 0.000 claims abstract description 10
- 238000003491 array Methods 0.000 claims description 12
- 238000005259 measurement Methods 0.000 claims description 10
- 238000005315 distribution function Methods 0.000 claims description 6
- 238000010146 3D printing Methods 0.000 claims description 3
- 239000012141 concentrate Substances 0.000 claims description 3
- 239000007822 coupling agent Substances 0.000 claims description 3
- FGUUSXIOTUKUDN-IBGZPJMESA-N C1(=CC=CC=C1)N1C2=C(NC([C@H](C1)NC=1OC(=NN=1)C1=CC=CC=C1)=O)C=CC=C2 Chemical compound C1(=CC=CC=C1)N1C2=C(NC([C@H](C1)NC=1OC(=NN=1)C1=CC=CC=C1)=O)C=CC=C2 FGUUSXIOTUKUDN-IBGZPJMESA-N 0.000 claims description 2
- 238000004364 calculation method Methods 0.000 claims description 2
- 230000036541 health Effects 0.000 abstract description 4
- 238000012544 monitoring process Methods 0.000 abstract description 3
- 238000013461 design Methods 0.000 abstract 1
- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000003331 infrared imaging Methods 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 239000013307 optical fiber Substances 0.000 description 2
- 102100032040 Amphoterin-induced protein 2 Human genes 0.000 description 1
- 101000776165 Homo sapiens Amphoterin-induced protein 2 Proteins 0.000 description 1
- KWYCPUNAAYFHAK-UHFFFAOYSA-N N-(2,6-Dimethylphenyl)-4-[[(diethylamino)acetyl]amino]benzamide Chemical compound C1=CC(NC(=O)CN(CC)CC)=CC=C1C(=O)NC1=C(C)C=CC=C1C KWYCPUNAAYFHAK-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000005802 health problem Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/04—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point
- G01M3/24—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using infrasonic, sonic, or ultrasonic vibrations
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Velocity Or Position Using Acoustic Or Ultrasonic Waves (AREA)
- Examining Or Testing Airtightness (AREA)
Abstract
The invention discloses a spacecraft composite structure leakage positioning method based on wave velocity correction, which comprises the following steps: a. carrying out a lead breaking experiment on the center position of the detected board by using an automatic pencil, measuring the wave speed distribution conditions of all directions, and establishing a wave speed-direction curve; b. determining sensor array parameters for leak location from the wave velocity-direction curve; c. performing sound source orientation experiments in the appointed direction, and correcting a wave velocity-direction curve; d. building a leakage positioning detection system, and collecting leakage signals by using a sensor array; e. through a single sensor array. In the application, the functional relation between the wave velocity and the direction is established by measuring the wave velocity in each direction of 0-360 degrees, and the functional relation is applied to the sensor array parameter design, so that the leak detection of the composite material laminated plate structure with all symmetrical structures can be aimed at, the material application trend in various projects in the future is met, and the functional relation has important significance for the future structural health monitoring.
Description
Technical Field
The invention relates to the technical field of gas leakage detection, in particular to a spacecraft composite structure leakage positioning method based on wave velocity correction.
Background
The composite material is a new material formed by optimally combining material components with different properties by utilizing an advanced material preparation technology, and has the advantages of high specific strength, light weight, high specific modulus, good fatigue resistance and the like compared with traditional materials such as metal materials, although the development time is short, the composite material has very rapid development trend and has been applied to the fields of aviation, aerospace and the like. In these fields, structural health directly determines success or failure of engineering tasks, and leakage is a very urgent one of many structural health problems. For example, structures such as fuel tanks may be prone to explosion events once they leak, and spacecraft tanks may be subject to pressure loss. Once the leakage problem occurs, potential safety hazards are formed, the life safety of operators is endangered, and serious losses are caused.
Common methods for detecting leaks on aerospace engineering structures are infrared imaging, fiber optic measurements, and the like. The infrared imaging method is used for carrying out leakage positioning on temperature reduction caused by gas leakage, and the optical fiber measuring method is used for acquiring physical parameters of a structure to be detected through a distributed optical fiber sensor so as to judge the integrity. However, the equipment of the two methods is complex in distribution and low in reliability. The applicability is general. The acoustic positioning method is widely applied due to the characteristics of simple system arrangement, good stability, high sensitivity, high detection speed and the like. However, most of the conventional leak location methods are applied to isotropic metal material structures, and the above methods will be difficult to be applied to composite material structures due to the anisotropic properties of the composite materials.
The invention provides a spacecraft composite structure leakage positioning method based on wave velocity correction, which aims at positioning leakage events of a composite structure. The method accords with the material application trend in various projects in the future, and has important significance for the future structural health monitoring.
Disclosure of Invention
The invention aims at: in order to solve the problems, the method for positioning the leakage of the spacecraft composite structure based on wave velocity correction is provided.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
a spacecraft composite structure leakage positioning method based on wave velocity correction comprises the following steps:
a. carrying out a lead breaking experiment on the center position of the detected board by using an automatic pencil, measuring the wave speed distribution conditions of all directions, and establishing a wave speed-direction curve;
b. determining sensor array parameters for leak location from the wave velocity-direction curve;
c. performing sound source orientation experiments in the appointed direction, carrying out orientation through an array, and correcting a wave speed-direction curve according to the orientation error;
d. building a leakage positioning detection system, and collecting leakage signals by using a sensor array;
e. directing, by a single sensor array, the leakage source using a beam forming directing method based on an anisotropic material wave velocity-direction curve;
f. the leakage source is finally positioned by triangulation with two sensor arrays.
Preferably, the wave speed measurement in the step a is as follows:
when a lead breaking signal is generated at a specific position, defining the transverse direction of the measured plate as a 0-degree direction, and setting the transverse direction as the positive direction of an x-axis; the longitudinal direction is 90 degrees, the y-axis forward direction is set, two sensors are placed in the same direction, the distance between the sensors is 30cm, the wave velocity measurement is carried out every 10 degrees, and after the measurement is finished, a wave velocity array V (theta) can be obtained:
in order to further improve the precision, the function of the wave velocity and the angle can be obtained by fitting V (theta) by an interpolation method: v=f (θ).
Preferably, the sensor array parameter calculation flow in the step b is as follows:
according to the function v=f (theta) of wave speed and angle, taking the O point as a reference point, every 10 DEGA sensor is placed at a distance l from the reference point i (θ i ) And wave velocity v (θ) i ) The relation of (2) is:
pair l i (θ i ) Fitting to obtain a distribution function of the distance and angle between the array element and the datum point: l=h (θ), 10 sensors are laid for each array, covering the 0 ° -90 ° direction.
Preferably, the wave speed correction flow in the step c is as follows:
generating leakage acoustic signals in a specified method, carrying out leakage experiments when the sensor array and the sensor array are respectively angled by 0-90 degrees, carrying out experiments at intervals of 10 degrees, and carrying out directional treatment to obtain a corresponding energy function B (theta):
B(θ)＝∫g 4 (t,θ)dt
the corresponding g (t, theta) function can be deduced according to the energy function, the corresponding delay deltat can be deduced, and the corresponding deduced wave velocity function V' (theta) can be deduced according to the delay formula. And correcting and compensating the wave speed-direction curve according to the derived wave speed function to obtain a corrected wave speed-direction curve v=f' (theta).
Preferably, the experimental detection system of the step D comprises a tested composite material structure, a sensor clamp, an array sensor, a signal amplifier, a signal acquisition card and a PC, wherein the sensor clamp is designed and manufactured through 3D printing according to the sensor array parameters determined in the step b. The leakage signal acquisition flow is as follows:
sticking 2 groups of sensor arrays to the surface of a detected structure through a coupling agent, collecting leakage signals by using the sensor arrays at a reference point distance L of the 2 groups of sensors, amplifying the signals by using a voltage amplifier, collecting the signals by using a collecting device, and storing the data to a PC;
preferably, the improved beam forming method in the step e includes the following steps:
assuming that the sound source direction is θ, the time delay of the nth sensor array element signal is expressed as:
wherein V (θ) is a wave velocity distribution function, d n The relative distance is:
the signal will concentrate energy by time-delay superposition, after which the signal:
the signal energy may be obtained by time-domain squaring and integrating the superimposed signal. By scanning all angles, one can get an energy function B (θ) for the angle:
B(θ)＝∫g 4 (t,θ)dt
and the angle theta corresponding to the peak value of the B (theta) energy function is the leakage orientation result obtained by the array sensor.
Preferably, the improved beam forming method in the step f includes the following steps:
when two array sensors are used for positioning a leakage source, the relationship between the leakage source and the orientation angle is as follows:
wherein, (x) 1 ,y 1 )、(x 2 ,y 2 ) The coordinates of reference sensors of the sensor arrays 1 and 2 are respectively, L is the reference point distance of the two array sensors, and theta 1 、θ 2 Respectively, sensorsThe orientation angles (x, y) of the arrays 1 and 2 are coordinates for positioning the leakage source, and the leakage source position (x, y) can be obtained by solving the formula, so that the leakage positioning is completed.
In summary, due to the adoption of the technical scheme, the beneficial effects of the invention are as follows:
in the application, the functional relation between the wave velocity and the direction is established by measuring the wave velocity in each direction of 0-360 degrees, and the functional relation is designed according to the parameters of the sensor array; by carrying out sound source orientation experiments in the designated direction, the wave velocity-direction curve is corrected according to the orientation error. The method can be used for detecting the leakage of the anisotropic composite laminated board structure, accords with the material application trend in various projects in the future, and has important significance for the health monitoring of the structure in the future.
Drawings
Fig. 1 shows a flowchart of a positioning method according to an embodiment of the present invention:
FIG. 2 shows a schematic wave velocity-direction curve test provided according to an embodiment of the present invention;
FIG. 3 shows a schematic diagram of an array sensor structure provided according to an embodiment of the present invention;
FIG. 4 shows a schematic diagram of a detection system according to an embodiment of the present invention;
fig. 5 shows a leakage orientation schematic provided according to an embodiment of the invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1-5, the present invention provides a technical solution:
a spacecraft composite structure leakage positioning method based on wave velocity correction comprises the following steps of:
a. carrying out a lead breaking experiment on the center position of the detected board by using an automatic pencil, measuring the wave speed distribution conditions of all directions, and establishing a wave speed-direction curve;
b. determining sensor array parameters for leak location from the wave velocity-direction curve;
c. performing sound source orientation experiments in the appointed direction, carrying out orientation through an array, and correcting a wave speed-direction curve according to the orientation error;
d. building a leakage positioning detection system, and collecting leakage signals by using a sensor array;
e. directing, by a single sensor array, the leakage source using a beam forming directing method based on an anisotropic material wave velocity-direction curve;
f. the leakage source is finally positioned by triangulation with two sensor arrays.
Specifically, as shown in fig. 2, the wave velocity measurement in the step a includes:
when a lead breaking signal is generated at a determined position, the signal is transmitted in a plate in the form of plane waves, the transverse direction of a measured plate is defined to be 0 DEG, and the direction is set to be the positive direction of an x axis; the longitudinal direction is 90 degrees, the y-axis direction is set as the positive direction, two sensors are placed in the same direction, the distance between the sensors is 30cm, the wave speed measurement is carried out every 10 degrees, and the frequency dispersion phenomenon is generated when plane waves propagate in a flat plate, and the frequency band of the signals to be researched is below 300kHz, so that the A is mainly measured during the wave speed measurement 0 The wave velocity of the modal signal can be measured to obtain a wave velocity array V (theta):
in order to further improve the precision, the function of the wave velocity and the angle can be obtained by fitting V (theta) by an interpolation method: v=f (θ).
Specifically, as shown in fig. 3, the construction flow of the sensor array structure in the step b is as follows:
according to the function v=f' (θ) of wave velocity and angle, one is placed every 10 ° with the O point as the reference pointSensor, distance l between sensor and reference point i (θ i ) And wave velocity v (θ) i ) The relation of (2) is:
clearly, the distance between the sensor and the reference point in the array is proportional to the wave speed in the direction, for l i (θ i ) Fitting to obtain a distribution function of the distance and angle between the array element and the datum point: l=h (θ), 10 sensors are laid for each array, covering the 0 ° -90 ° direction.
Specifically, in order to improve the applicability of the wave velocity-direction curve to the leakage signal, gas leakage is generated at the leak hole. The sensor array and the sensor array are respectively made to form angles of 0-90 degrees to perform leakage experiments, the experiments are performed every 10 degrees, and directional treatment is performed to obtain a corresponding energy function B (theta):
B(θ)＝∫g 4 (t,θ)dt
the corresponding g (t, theta) function can be deduced according to the energy function, the corresponding delay deltat can be deduced, and the corresponding deduced wave velocity function V' (theta) can be deduced according to the delay formula. And correcting and compensating the wave speed-direction curve according to the derived wave speed function to obtain a corrected wave speed-direction curve v=f' (theta).
Specifically, as shown in fig. 4, the experimental detection system in the step D comprises a tested composite material structure, a sensor clamp, an array sensor, a signal amplifier, a signal acquisition card and a PC, wherein the sensor clamp is designed and manufactured through 3D printing according to the sensor array parameters determined in the step b. The leakage signal acquisition flow is as follows: pasting a sensor array on the surface of a detected structure through a coupling agent, collecting leakage signals by using the sensor array, amplifying the signals by using a voltage amplifier, collecting the signals by using a collecting device, and storing the data into a PC;
specifically, as shown in fig. 5, the improved beam forming method in the steps e and f includes:
when a leakage signal is generated, sound waves are transmitted in a plane wave mode, the sound waves are acquired by sensors and are defined as signals acquired by the sensors at the moment t, a measured sound source is a far-field model, the distance between the leakage source and an array is far greater than the length of the array, the directions of the signals acquired by all the sensors can be approximately considered to be the same, the beam forming angle is set to be an angle theta formed by the connection line of the leakage source and an O point and the positive direction of an x axis, the sensor at the O point is a number 0 sensor, the numbers of 10 sensors placed from the 0-90 DEG direction are 1-10, the included angle between the positions of two array elements and the connection line of the O point is phi, and the time delay between the sensors of the array is determined by the relative distance between the signal source and the sensors of the array and a direction wave velocity function.
When a leakage signal is generated, the wave velocity V of plane waves generated on the composite structure i Let f' (θ) set the beamforming angle to be the O-point-leakage source connection and O-point-1 # sensor connection, the time delay between sensors is determined by the relative distance of the signal source to each sensor (compared to the 1# sensor in the direction of arrival) and the wave velocity.
Assuming that the sound source direction is θ, the delay of the nth signal is expressed as:
wherein V (θ) is a wave velocity distribution function, d n The relative distance is:
the signal will concentrate energy by time-delay superposition, after which the signal:
the signal energy can be obtained by summing the time domain squares of the superimposed signals, and by scanning all angles, an energy function B (θ) with respect to the angle can be obtained:
B(θ)＝∫g 4 (t,θ)dt
the peak angle θ of the energy function is the leakage orientation result of the sensor array.
When two L arrays are used for positioning the leakage source, the relationship between the leakage source and the orientation angle is as follows:
wherein, (x) 1 ,y 1 )、(x 2 ,y 2 ) The coordinates of reference sensors of the sensor arrays 1 and 2 are respectively, L is the center distance of the two array sensors, and theta 1 、θ 2 The orientation angles of the sensor arrays 1 and 2 are respectively, (x, y) are coordinates for positioning the leakage source, and the leakage source position (x, y) can be obtained by solving the formula, so that positioning is completed.
The previous description of the embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (5)
1. The spacecraft composite structure leakage positioning method based on wave velocity correction is characterized by comprising the following steps of:
a. carrying out a lead breaking experiment on the center position of the detected board by using an automatic pencil, measuring the wave speed distribution conditions of all directions, and establishing a wave speed-direction curve;
the wave speed measurement process in the step a is as follows:
when a lead breaking signal is generated at a determined position, defining the transverse direction of the measured plate as a 0-degree direction and setting the transverse direction as the positive direction of an x-axis; the longitudinal direction is 90 degrees, the y-axis forward direction is set, two sensors are placed in the same direction, the distance between the sensors is 30cm, the wave velocity measurement is carried out every 10 degrees, and after the measurement is finished, a wave velocity array V (theta) can be obtained:
in order to further improve the precision, the function of the wave velocity and the angle can be obtained by fitting V (theta) by an interpolation method: v=f (θ);
b. determining sensor array parameters for leak location from the wave velocity-direction curve;
the sensor array parameter calculation method in the step b is as follows:
according to the function v=f (theta) of wave speed and angle, taking 0 point as reference point, placing a sensor every 10 deg. and spacing l of sensor and reference point i (θ i ) And wave velocity v (θ) i ) The relation of (2) is:
pair l i (θ i ) Fitting to obtain a distribution function of the distance and angle between the array element and the datum point: l=h (θ), 10 sensors are laid for each array, covering the 0 ° -90 ° direction;
c. performing sound source orientation experiments in the appointed direction, carrying out orientation through an array, and correcting a wave speed-direction curve according to the orientation error;
the wave speed correction flow in the step c is as follows:
generating leakage acoustic signals in a specified method, carrying out leakage experiments when the sensor array and the sensor array are respectively angled by 0-90 degrees, carrying out experiments at intervals of 10 degrees, and carrying out directional treatment to obtain a corresponding energy function B (theta):
B(θ)＝∫g 4 (t，θ)dt
the corresponding g (t, theta) function can be deduced according to the energy function, the corresponding delay deltat can be deduced, the corresponding deduced wave speed function V '(theta) can be deduced according to the delay formula, the wave speed-direction curve is corrected and compensated according to the deduced wave speed function, and the corrected wave speed-direction curve v=f' (theta) is obtained;
d. building a leakage positioning detection system, and collecting leakage signals by using a sensor array;
e. directing, by a single sensor array, the leakage source using a beam forming directing method based on an anisotropic material wave velocity-direction curve;
f. the leakage source is finally positioned by triangulation with two sensor arrays.
2. The method for positioning leakage of a spacecraft composite structure based on wave velocity correction according to claim 1, wherein the leakage positioning detection system of the step D comprises a tested composite structure, a sensor clamp, an array sensor, a signal amplifier, a signal acquisition card and a PC, and the sensor clamp is designed and manufactured through 3D printing according to the sensor array parameters determined in the step b.
3. The spacecraft composite structure leakage positioning method based on wave velocity correction according to claim 1, wherein the leakage signal acquisition flow in the step d is as follows:
the sensor array is stuck to the surface of a detected structure through the coupling agent, the sensor array is used for collecting leakage signals, the signals are amplified through the voltage amplifier and collected through the collecting equipment, and data are stored in the PC.
4. The method for positioning leakage of a spacecraft composite structure based on wave velocity correction according to claim 1, wherein the improved wave beam forming method in the step e is characterized in that the flow of the wave beam forming method is as follows:
assuming that the sound source direction is θ, the time delay of the nth sensor array element signal is expressed as:
wherein V (θ) is a wave velocity distribution function, d n The relative distance is:
the signal will concentrate energy by time-delay superposition, after which the signal:
the signal energy can be obtained by summing the time domain squares of the superimposed signals, and by scanning all angles, an energy function B (θ) with respect to the angle can be obtained:
B(θ)＝∫g 4 (t，θ)dt
and the angle theta corresponding to the peak value of the B (theta) energy function is the leakage orientation result obtained by the array sensor.
5. The method for positioning leakage of a spacecraft composite structure based on wave velocity correction according to claim 1, wherein the improved wave beam forming method in the step f is characterized in that the flow of the wave beam forming method is as follows:
when two array sensors are used for positioning a leakage source, the relationship between the leakage source and the orientation angle is as follows:
wherein, (x) 1 ,y 1 )、(x 2 ,y 2 ) Respectively, are sensorsThe sensor arrays 1 and 2 refer to the coordinates of the sensors, L is the distance between the reference points of the two array sensors, and theta 1 、θ 2 The orientation angles of the sensor arrays 1 and 2 are respectively, (x, y) are coordinates for positioning the leakage source, and the leakage source position (x, y) can be obtained by solving the formula, so that the leakage positioning is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111448440.XA CN114136556B (en) | 2021-11-30 | 2021-11-30 | Spacecraft composite structure leakage positioning method based on wave velocity correction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111448440.XA CN114136556B (en) | 2021-11-30 | 2021-11-30 | Spacecraft composite structure leakage positioning method based on wave velocity correction |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114136556A CN114136556A (en) | 2022-03-04 |
| CN114136556B true CN114136556B (en) | 2024-03-08 |
Family
ID=80386406
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111448440.XA Active CN114136556B (en) | 2021-11-30 | 2021-11-30 | Spacecraft composite structure leakage positioning method based on wave velocity correction |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114136556B (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103576195A (en) * | 2013-10-28 | 2014-02-12 | 西北大学 | Method for forecasting fissured medium transverse wave velocity varying with pressure |
| CN103698748A (en) * | 2013-12-16 | 2014-04-02 | 南京航空航天大学 | 2D-MUSIC (Two Dimensional-Multiple Signal Classification) impact locating method based on signal wave speed and attenuation compensation in composite material |
| CN104374532A (en) * | 2014-10-29 | 2015-02-25 | 北京卫星环境工程研究所 | Spacecraft ontrack leakage orientation method |
| CN104515807A (en) * | 2014-10-27 | 2015-04-15 | 浙江省特种设备检验研究院 | Pressure pipeline ultrasonic internal detection automation device |
| CN104597126A (en) * | 2015-01-07 | 2015-05-06 | 北京卫星环境工程研究所 | Method for detecting structure health of spacecraft based on acoustic sensor |
| CN106706760A (en) * | 2016-12-20 | 2017-05-24 | 北京工业大学 | Acoustic emission source positioning method of composite material plate of omnidirectional dual circular array |
| WO2017219469A1 (en) * | 2016-06-22 | 2017-12-28 | 杨越 | Ultrasonic detector for crack propagation of unmanned vessel body |
| CN110088588A (en) * | 2016-10-17 | 2019-08-02 | 麻省理工学院 | Pipeline internal leakage detection system, device and method |
| CN112254891A (en) * | 2020-10-22 | 2021-01-22 | 北京卫星环境工程研究所 | Spacecraft reinforcing rib structure leakage positioning method |
| CN112345643A (en) * | 2020-11-09 | 2021-02-09 | 吉林大学 | Acoustic emission source positioning method suitable for surface of spherical container |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9217807B2 (en) * | 2013-07-23 | 2015-12-22 | Schlumberger Technology Corporation | Systems and methods for identifying sanding in production wells using time-lapse sonic data |
-
2021
- 2021-11-30 CN CN202111448440.XA patent/CN114136556B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103576195A (en) * | 2013-10-28 | 2014-02-12 | 西北大学 | Method for forecasting fissured medium transverse wave velocity varying with pressure |
| CN103698748A (en) * | 2013-12-16 | 2014-04-02 | 南京航空航天大学 | 2D-MUSIC (Two Dimensional-Multiple Signal Classification) impact locating method based on signal wave speed and attenuation compensation in composite material |
| CN104515807A (en) * | 2014-10-27 | 2015-04-15 | 浙江省特种设备检验研究院 | Pressure pipeline ultrasonic internal detection automation device |
| CN104374532A (en) * | 2014-10-29 | 2015-02-25 | 北京卫星环境工程研究所 | Spacecraft ontrack leakage orientation method |
| CN104597126A (en) * | 2015-01-07 | 2015-05-06 | 北京卫星环境工程研究所 | Method for detecting structure health of spacecraft based on acoustic sensor |
| WO2017219469A1 (en) * | 2016-06-22 | 2017-12-28 | 杨越 | Ultrasonic detector for crack propagation of unmanned vessel body |
| CN110088588A (en) * | 2016-10-17 | 2019-08-02 | 麻省理工学院 | Pipeline internal leakage detection system, device and method |
| CN106706760A (en) * | 2016-12-20 | 2017-05-24 | 北京工业大学 | Acoustic emission source positioning method of composite material plate of omnidirectional dual circular array |
| CN112254891A (en) * | 2020-10-22 | 2021-01-22 | 北京卫星环境工程研究所 | Spacecraft reinforcing rib structure leakage positioning method |
| CN112345643A (en) * | 2020-11-09 | 2021-02-09 | 吉林大学 | Acoustic emission source positioning method suitable for surface of spherical container |
Non-Patent Citations (2)
| Title |
|---|
| qi lei.Research on Leakage Location of Spacecraft in Orbit Based on Frequency Weighting Matrix Beamforming Algorithm by LambWaves.《Applied Sciences》.2020,第3-13页. * |
| 一种航天器舱壁加筋结构泄漏定位方法;綦磊;岳桂轩;孙立臣;邵容平;芮小博;张宇;;航天器工程(02);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114136556A (en) | 2022-03-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102288123B (en) | Method for accurately positioning three-dimensional non-contact measurement of welding deformation | |
| CN104374532B (en) | The in-orbit leakage orientation method of spacecraft | |
| CN107085038A (en) | The total focus imaging method of the amendment of anisotropy weld defect array detection | |
| CN105258662B (en) | A kind of shafting engineering component end face space displacement and angle change measuring method based on stay-supported type displacement sensor | |
| CN101387546A (en) | Space sailboard bend and torsion low frequency mode detecting method and apparatus based on vision | |
| CN103105140A (en) | Large building deformation monitoring device and monitoring method through large building deformation monitoring device | |
| CN106771709A (en) | A kind of S parameter De- embedding method of multiport network | |
| CN113432977B (en) | Method for obtaining dynamic rigidity of rock joint | |
| CN105910742A (en) | Ultrasonic residual stress test surface positioning coupling device | |
| CN103529428A (en) | Method for passively positioning point sound source based on spatial ten-element array | |
| CN105136361A (en) | Method by utilizing X-ray diffraction to measure stress of cubic single-crystal material | |
| CN114136556B (en) | Spacecraft composite structure leakage positioning method based on wave velocity correction | |
| CN103616436B (en) | A kind of high-precision ultrasound detection method of contact stiffness | |
| CN110940257B (en) | Device and method for measuring inclination angle change of pipeline | |
| CN203310549U (en) | A welded joint residual stress measurement apparatus | |
| CN105509665B (en) | A kind of measuring point space displacement measurement apparatus and method based on ultrasonic wave principle | |
| CN100405009C (en) | Symmetrical closed laser arch dam deformation monitoring method | |
| CN114608567B (en) | USBL positioning method under small pitch angle condition | |
| CN112946085B (en) | Ultrasonic positioning method for plate-like structure damaged sound source | |
| CN113340727B (en) | Device and method for nondestructive testing of mechanical parameters of building concrete | |
| CN205786103U (en) | A kind of biasing effect detection device and strain detecting system | |
| CN115792921A (en) | Composite material structure collision source positioning method based on acoustic emission time difference approximation | |
| CN115127771A (en) | High-speed wind tunnel transverse asymmetric weak disturbance wave detection and disturbance source positioning method | |
| CN113533531A (en) | Material damage positioning device, positioning method and verification method | |
| CN108427014B (en) | Method for identifying impact position of composite material laminated plate |
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 |