CN110789731A - System and method for monitoring health of helicopter tail boom structure based on Lamb wave - Google Patents
System and method for monitoring health of helicopter tail boom structure based on Lamb wave Download PDFInfo
- Publication number
- CN110789731A CN110789731A CN201910965667.8A CN201910965667A CN110789731A CN 110789731 A CN110789731 A CN 110789731A CN 201910965667 A CN201910965667 A CN 201910965667A CN 110789731 A CN110789731 A CN 110789731A
- Authority
- CN
- China
- Prior art keywords
- signal
- module
- tail boom
- helicopter tail
- channel control
- 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.)
- Pending
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
The invention belongs to the technical field of helicopter health state and use monitoring, and discloses a system and a method for monitoring the health of a helicopter tail boom structure based on Lamb waves, wherein the system comprises the following steps: the device comprises a main controller module, a waveform generation module, a channel control module, a waveform acquisition module and a data acquisition module; the signal output end of the main controller module is connected with the signal input end of the waveform generation module, the signal output end of the waveform generation module is connected with the selection switch input end of the channel control module, the signal output end of the channel control module is connected with the signal input end of the data acquisition module, the signal output end of the data acquisition module is connected with the signal input end of the channel control module, the selection switch output end of the channel control module is connected with the signal input end of the waveform acquisition module, the signal output end of the waveform acquisition module is connected with the signal input end of the main controller module, the signal to noise ratio of damage scattering signals can be improved, and efficient structural damage monitoring is achieved.
Description
Technical Field
The invention belongs to the technical field of helicopter health state and use monitoring, and particularly relates to a system and a method for monitoring the health of a helicopter tail boom structure based on Lamb waves.
Background
The tail boom of the helicopter with the conventional structure is positioned between the fuselage and the oblique beam and is an important bearing structure between the fuselage and the oblique beam. Under the combined action of the main rotor downwash circulation vibration load and the tail transmission link rotation vibration load, the main damage mode of the helicopter tail boom structure is embodied as fatigue crack damage, the fatigue damage is mostly generated in the material and is not easy to be found from the surface, serious hidden dangers are easy to remain, sudden expansion can be generated when the small damage of a key part is subjected to a larger load or an extremely severe flight state, so that the bearing characteristic of the structure is failed instantly, early damage of the key structure part can be found as soon as possible or in time, the health condition of the structure is always in a monitored state, and important basis can be provided for safety, economic use and timely maintenance of an airplane.
At present, the common structural health monitoring method mainly comprises a damage diagnosis method based on structural vibration response analysis, but the method relies on a structural model, is insensitive to small damage and damage expansion, requires more vibration measuring points and is particularly sensitive to changes of boundaries and environments; the damage diagnosis method based on the structural mechanical impedance can only monitor through the structural impedance change in a small range around the sensor arrangement, and cannot monitor the damage far away from the sensor. The sensitivity and the precision of monitoring the small damage are low; the damage diagnosis method based on the structural load parameters is insensitive to small damage of the structure, and the damage can be monitored only when the structural damage is large enough to change the parameter distribution of the structure; the damage diagnosis method based on the change of the sensing characteristics, but the sensor can only sense the change of the structure at the arrangement point, the damage at the arrangement point cannot be monitored, and only the damage on the surface of the structure can be monitored.
Disclosure of Invention
In view of the above problems, the present invention aims to provide a Lamb wave based helicopter tail boom structure health monitoring system and method, which can improve the signal-to-noise ratio of the damage scattering signal and realize efficient structural damage monitoring.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme.
The first technical scheme is as follows:
a Lamb wave based helicopter tail boom structure health monitoring system, the system comprising: the device comprises a main controller module, a waveform generation module, a channel control module, a waveform acquisition module and a data acquisition module;
the signal output end of the main controller module is connected with the signal input end of the waveform generation module, the signal output end of the waveform generation module is connected with the selection switch input end of the channel control module, the signal output end of the channel control module is connected with the signal input end of the data acquisition module, the signal output end of the data acquisition module is connected with the signal input end of the channel control module, the selection switch output end of the channel control module is connected with the signal input end of the waveform acquisition module, and the signal output end of the waveform acquisition module is connected with the signal input end of the main controller module.
The first technical scheme of the invention has the characteristics and further improvements that:
(1) the data acquisition module comprises a plurality of piezoelectric sensors which are respectively arranged on the helicopter tail boom.
(2) The channel control module is a piezoelectric sensor selection circuit and comprises an input selection switch and an output selection switch which are arranged on each piezoelectric sensor.
(3) The system further comprises: the temperature measurement module, the temperature signal output part of temperature measurement module with the temperature signal input part of main control unit module is connected, just the temperature measurement module is used for acquireing the temperature of helicopter tail boom.
(4) The channel control module is connected with a plurality of piezoelectric sensors in the data acquisition module through cables.
(5) The main controller module, the waveform generation module, the channel control module and the waveform acquisition module are integrated by adopting a PC104 bus overlapping and inserting structure.
The second technical scheme is as follows:
a Lamb wave based health monitoring method for a helicopter tail boom structure is applied to a system according to the first technical scheme, the helicopter tail boom structure is divided into a plurality of unit points, the output waveform of a waveform generator is recorded as an excitation signal, the moment of a wave crest when a first piezoelectric sensor sends out the excitation signal is the excitation moment, and the moment of the wave crest when a second piezoelectric sensor receives a feedback signal is the receiving moment;
recording a certain point on the unit points as a virtual damage point;
acquiring a time interval between an excitation time and a receiving time;
acquiring a first distance from a first piezoelectric sensor to a virtual damage point and a second distance from a second piezoelectric sensor to the virtual damage point, wherein the sum of the first distance and the second distance is the propagation distance of a scattering signal;
obtaining the moment of a scattering signal emitted from a virtual damage point according to the time interval, the propagation distance and the propagation speed of the Lamb wave, wherein the scattering signal is the difference between an actual signal and a healthy signal of an excitation signal at the virtual damage point; the health signal is a signal detected at the virtual damage point when the helicopter tail boom structure is not damaged;
sequentially and respectively using the piezoelectric sensors as first piezoelectric sensors to obtain a plurality of scattering signals at the virtual damage point;
superposing the signal amplitudes of the multiple scattering signals at the virtual damage point to obtain the superposed signal amplitudes at the virtual damage point;
sequentially and respectively taking the plurality of unit points as virtual damage points, so as to obtain the superposed signal amplitudes of all the virtual damage points;
and determining the virtual damage point where the maximum value is located in the signal amplitudes after the superposition of all the virtual damage points as a real damage point.
The second technical scheme of the invention has the characteristics and further improvements that:
the signal amplitudes obtained after the superposition of all the virtual damage points are specifically as follows:
wherein A isnIs a weight coefficient, fnIs the nth scattered signal, t0The time interval between the excitation instant and the reception instant,
respectively the distance from the virtual damage point to the first piezoelectric sensor and the second piezoelectric sensor, v is the Lamb wave propagation wave velocity, fv is the image resolution,
is the abscissa and ordinate of the first piezoelectric sensor,
the abscissa and ordinate of the second piezoelectric sensor.
According to the helicopter tail boom structure health monitoring method, the mode aliasing problem in the Lamb wave monitoring process in the complex multi-reflection structure is solved, the signal-to-noise ratio of damage scattering signals is improved, and efficient structure damage monitoring is realized.
Drawings
Fig. 1 is a schematic structural diagram of a Lamb wave-based health monitoring system for a tail boom structure of a helicopter provided in an embodiment of the present invention;
fig. 2 is a schematic circuit structure diagram of a health monitoring system of a tail boom structure of a helicopter based on Lamb waves according to an embodiment of the present invention;
fig. 3 is a schematic diagram of an integrated structure of a main controller module, a waveform generation module, a channel control module, and a waveform acquisition module according to an embodiment of the present invention, which adopts a PC104 bus overlay plug-in structure;
fig. 4 is a schematic flow chart of a method for monitoring health of a tail boom structure of a helicopter based on Lamb waves according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The helicopter tail boom structure health monitoring method based on time reversal focusing imaging comprises the following steps:
(1) for any Lamb wave excitation-sensing monitoring channel, the time interval from the excitation starting moment to any moment point in the signal in the monitoring signal corresponds to the time required by the propagation of the excitation signal to reach the sensor;
(2) dividing the structure to be detected into a plurality of unit points according to the set infinitesimal size, assuming that a signal reaches the sensor after being scattered by one unit point in the structure, the sum of the distances from the point to the exciter and the sensor is the propagation distance of the scattered signal of the point, and combining the propagation speed of the Lamb wave signal to obtain the time when the scattered signal reaches the sensor;
(3) because the damage is a secondary wave source of the scattering signal, and all signals contain the scattering signal caused by the damage, the channels are respectively analyzed and assigned, and the signal amplitudes at the damage can be superposed and displayed, such as time reversal focusing, thereby realizing the monitoring and imaging of the damage;
(4) the waveform acquisition module in the system is used for acquiring the waveform received by the sensor after the waveform is transmitted in the structure and storing the waveform;
for any point in the image matrix, as shown in fig. 1, the pixel value assignment expressions thereof are as shown in equations (1) and (2). Wherein An is weight coefficient, normalization coefficient of each damage scattering signal is taken, fn is nth damage scattering signal, and time reversal method is time reversalThe converted scattering fluctuation amplitude of the damage, t0 is the time when the excitation signal is input and the monitoring signal is collected,
the distances from the pixel point to the exciting element and the sensing element, v is the Lamb wave propagation wave velocity, fv is the image resolution,
is the abscissa and ordinate of the actuator,
is the abscissa and ordinate of the sensor. All kinds of parameters related to imaging need to be set preferentially according to experimental research results and actual monitoring conditions.
The invention has the advantages that: the method has the advantages that damage and impact positioning accuracy are guaranteed, the implementation process is simple and easy, mechanical modeling is not needed for the structure, signal time reversal focusing is directly carried out on response signals obtained by the piezoelectric sensor array on software, and structural damage of images is generated, so that efficient structural damage monitoring is realized, and the method is more easily applied to actual engineering.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. A Lamb wave based helicopter tail boom structure health monitoring system, comprising: the device comprises a main controller module, a waveform generation module, a channel control module, a waveform acquisition module and a data acquisition module;
the signal output end of the main controller module is connected with the signal input end of the waveform generation module, the signal output end of the waveform generation module is connected with the selection switch input end of the channel control module, the signal output end of the channel control module is connected with the signal input end of the data acquisition module, the signal output end of the data acquisition module is connected with the signal input end of the channel control module, the selection switch output end of the channel control module is connected with the signal input end of the waveform acquisition module, and the signal output end of the waveform acquisition module is connected with the signal input end of the main controller module.
2. The Lamb wave based helicopter tail boom structure health monitoring system of claim 1, wherein the data acquisition module comprises a plurality of piezoelectric sensors respectively disposed on the helicopter tail boom.
3. The Lamb wave based helicopter tail boom structure health monitoring system of claim 1, wherein the channel control module is a piezoelectric sensor selection circuit comprising an input selection switch and an output selection switch disposed on each piezoelectric sensor.
4. The Lamb wave based helicopter tail boom structure health monitoring system of claim 1, further comprising: the temperature measurement module, the temperature signal output part of temperature measurement module with the temperature signal input part of main control unit module is connected, just the temperature measurement module is used for acquireing the temperature of helicopter tail boom.
5. The Lamb wave based helicopter tail boom structure health monitoring system of claim 2,
the channel control module is connected with a plurality of piezoelectric sensors in the data acquisition module through cables.
6. The Lamb wave based helicopter tail boom structure health monitoring system of claim 1, wherein the master controller module, the waveform generation module, the channel control module and the waveform acquisition module are integrated by a PC104 bus stacking structure.
7. A Lamb wave based helicopter tail boom structure health monitoring method is applied to the system as claimed in any one of claims 1-6, and is characterized in that the helicopter tail boom structure is divided into a plurality of unit points, the output waveform of a waveform generator is recorded as an excitation signal, the moment of a peak when a first piezoelectric sensor sends out the excitation signal is the excitation moment, and the moment of the peak when a second piezoelectric sensor receives a feedback signal is the receiving moment;
recording a certain point on the unit points as a virtual damage point;
acquiring a time interval between an excitation time and a receiving time;
acquiring a first distance from a first piezoelectric sensor to a virtual damage point and a second distance from a second piezoelectric sensor to the virtual damage point, wherein the sum of the first distance and the second distance is the propagation distance of a scattering signal;
obtaining the moment of a scattering signal emitted from a virtual damage point according to the time interval, the propagation distance and the propagation speed of the Lamb wave, wherein the scattering signal is the difference between an actual signal and a healthy signal of an excitation signal at the virtual damage point; the health signal is a signal detected at the virtual damage point when the helicopter tail boom structure is not damaged;
sequentially and respectively using the piezoelectric sensors as first piezoelectric sensors to obtain a plurality of scattering signals at the virtual damage point;
superposing the signal amplitudes of the multiple scattering signals at the virtual damage point to obtain the superposed signal amplitudes at the virtual damage point;
sequentially and respectively taking the plurality of unit points as virtual damage points, so as to obtain the superposed signal amplitudes of all the virtual damage points;
and determining the virtual damage point where the maximum value is located in the signal amplitudes after the superposition of all the virtual damage points as a real damage point.
8. The Lamb wave-based helicopter tail boom structure health monitoring method according to claim 7, wherein the signal amplitudes obtained after superposition at all virtual damage points are specifically:
wherein A isnIs a weight coefficient, fnIs the nth scattered signal, t0The time interval between the excitation instant and the reception instant,
respectively the distance from the virtual damage point to the first piezoelectric sensor and the second piezoelectric sensor, v is the Lamb wave propagation wave velocity, fv is the image resolution,is the abscissa and ordinate of the first piezoelectric sensor,
the abscissa and ordinate of the second piezoelectric sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910965667.8A CN110789731A (en) | 2019-10-11 | 2019-10-11 | System and method for monitoring health of helicopter tail boom structure based on Lamb wave |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910965667.8A CN110789731A (en) | 2019-10-11 | 2019-10-11 | System and method for monitoring health of helicopter tail boom structure based on Lamb wave |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110789731A true CN110789731A (en) | 2020-02-14 |
Family
ID=69440269
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910965667.8A Pending CN110789731A (en) | 2019-10-11 | 2019-10-11 | System and method for monitoring health of helicopter tail boom structure based on Lamb wave |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110789731A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111610202A (en) * | 2020-06-03 | 2020-09-01 | 西安电子科技大学 | Medium material damage detection system and method based on time reversal |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101701880A (en) * | 2009-08-05 | 2010-05-05 | 南京航空航天大学 | Embedded health monitoring system for active and passive structure of aeroplane |
| CN102323337A (en) * | 2011-06-13 | 2012-01-18 | 南京邮电大学 | Method for actively monitoring damage of engineering structure excited by adopting synthesis wave front |
| CN104374830A (en) * | 2014-11-26 | 2015-02-25 | 南京信息工程大学 | Near field phased array structure health monitoring method based on piezoelectric array |
| CN105784853A (en) * | 2016-04-14 | 2016-07-20 | 苏州泛能电力科技有限公司 | Active monitoring and evaluating method for directional damage of engineering structure |
| CN105928695A (en) * | 2016-05-11 | 2016-09-07 | 中国矿业大学 | Fault diagnosis system and method for mechanical parts of small-size unmanned helicopter |
| US20170168021A1 (en) * | 2015-12-15 | 2017-06-15 | University Of South Carolina | Structural health monitoring method and system |
| CN107543581A (en) * | 2017-08-09 | 2018-01-05 | 国网山东省电力公司经济技术研究院 | Multi-functional substation framework health monitoring and damnification recognition method |
-
2019
- 2019-10-11 CN CN201910965667.8A patent/CN110789731A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101701880A (en) * | 2009-08-05 | 2010-05-05 | 南京航空航天大学 | Embedded health monitoring system for active and passive structure of aeroplane |
| CN102323337A (en) * | 2011-06-13 | 2012-01-18 | 南京邮电大学 | Method for actively monitoring damage of engineering structure excited by adopting synthesis wave front |
| CN104374830A (en) * | 2014-11-26 | 2015-02-25 | 南京信息工程大学 | Near field phased array structure health monitoring method based on piezoelectric array |
| US20170168021A1 (en) * | 2015-12-15 | 2017-06-15 | University Of South Carolina | Structural health monitoring method and system |
| CN105784853A (en) * | 2016-04-14 | 2016-07-20 | 苏州泛能电力科技有限公司 | Active monitoring and evaluating method for directional damage of engineering structure |
| CN105928695A (en) * | 2016-05-11 | 2016-09-07 | 中国矿业大学 | Fault diagnosis system and method for mechanical parts of small-size unmanned helicopter |
| CN107543581A (en) * | 2017-08-09 | 2018-01-05 | 国网山东省电力公司经济技术研究院 | Multi-functional substation framework health monitoring and damnification recognition method |
Non-Patent Citations (2)
| Title |
|---|
| 李新民: "基于直11型机的故障诊断与预测管理系统技术研究", 《直升机技术》 * |
| 王星等: "便携式主动Lamb波结构健康监测集成系统设计", 《压电与声光》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111610202A (en) * | 2020-06-03 | 2020-09-01 | 西安电子科技大学 | Medium material damage detection system and method based on time reversal |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3112857B1 (en) | System comprising an aircraft structural object attached to an ultrasonic test system, and ultrasonic test method | |
| US7647206B2 (en) | System and method for monitoring structures for damage using nondestructive inspection techniques | |
| US8042397B2 (en) | Damage volume and depth estimation | |
| US8060319B2 (en) | Acoustic structural integrity monitoring system and method | |
| EP2485026B1 (en) | Structural health monitoring system | |
| Mickens et al. | Structural health monitoring of an aircraft joint | |
| US20130268154A1 (en) | Detection system for detection of damages on rotating components of components of aircraft and method of operating such a detection system | |
| US7891247B2 (en) | Method and system for detecting an anomaly and determining its size | |
| US20060106550A1 (en) | Structural health management system and method for enhancing availability and integrity in the structural health management system | |
| JP2008501951A (en) | Distributed mode system for real-time monitoring of acoustic emission | |
| US20050209791A1 (en) | Manufacturing process or in service defects acoustic imaging using sensor array | |
| CN102007402A (en) | Imaging an anomaly using backscattered waves | |
| Qiu et al. | Design of an all-digital impact monitoring system for large-scale composite structures | |
| KR101586039B1 (en) | Advanced structual heath monitoring system for aircraft and method thereof | |
| CN110789731A (en) | System and method for monitoring health of helicopter tail boom structure based on Lamb wave | |
| Prosser | Development of structural health management technology for aerospace vehicles | |
| JPH0511895B2 (en) | ||
| Pan et al. | Automatic localization of the rotor-stator rubbing fault based on acoustic emission method and higher-order statistics | |
| EP3709012A1 (en) | Acoustic inspection device and method of operation | |
| US10386264B2 (en) | Self-powered multi-functional structural health monitoring sensor | |
| CN105865612A (en) | Power transmission line galloping traction monitoring system and method based on ultrasonic transducer | |
| Prosser et al. | Sensor technology for integrated vehicle health management of aerospace vehicles | |
| Oliver | Scanning laser vibrometer for dynamic deflection shape characterization of aerospace structures | |
| Ksica et al. | Application of piezoelectric sensors for structural health monitoring in aerospace | |
| Sendeckyj et al. | Some smart structures concepts |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200214 |
|
| RJ01 | Rejection of invention patent application after publication |