CN102183350B - Real-time impact monitoring instrument and method of large-scale aviation structure - Google Patents
Real-time impact monitoring instrument and method of large-scale aviation structure Download PDFInfo
- Publication number
- CN102183350B CN102183350B CN 201110057547 CN201110057547A CN102183350B CN 102183350 B CN102183350 B CN 102183350B CN 201110057547 CN201110057547 CN 201110057547 CN 201110057547 A CN201110057547 A CN 201110057547A CN 102183350 B CN102183350 B CN 102183350B
- Authority
- CN
- China
- Prior art keywords
- module
- data
- signal
- input
- programmable logic
- 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.)
- Expired - Fee Related
Links
- 238000012544 monitoring process Methods 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title claims abstract description 16
- 230000003993 interaction Effects 0.000 claims abstract description 4
- 238000004891 communication Methods 0.000 claims description 14
- 238000005070 sampling Methods 0.000 claims description 12
- 230000002452 interceptive effect Effects 0.000 claims description 9
- 230000001960 triggered effect Effects 0.000 claims description 6
- 230000003750 conditioning effect Effects 0.000 claims description 2
- 230000001131 transforming effect Effects 0.000 claims description 2
- 230000003321 amplification Effects 0.000 abstract description 5
- 238000003199 nucleic acid amplification method Methods 0.000 abstract description 5
- 238000013500 data storage Methods 0.000 abstract description 3
- 239000002131 composite material Substances 0.000 description 6
- 230000006378 damage Effects 0.000 description 6
- 230000008901 benefit Effects 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 5
- 230000006870 function Effects 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 238000002474 experimental method Methods 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 230000002463 transducing effect Effects 0.000 description 4
- 230000036541 health Effects 0.000 description 3
- 230000005055 memory storage Effects 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000001914 filtration Methods 0.000 description 2
- 230000003116 impacting effect Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 240000004859 Gamochaeta purpurea Species 0.000 description 1
- 206010061245 Internal injury Diseases 0.000 description 1
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 239000011157 advanced composite material Substances 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000002929 anti-fatigue Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000010205 computational analysis Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000013481 data capture Methods 0.000 description 1
- 238000013480 data collection Methods 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000003745 diagnosis Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000010363 phase shift Effects 0.000 description 1
- 239000011160 polymer matrix composite Substances 0.000 description 1
- 229920013657 polymer matrix composite Polymers 0.000 description 1
- 238000007781 pre-processing Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
Images
Abstract
The invention discloses a real-time impact monitoring instrument and method of a large-scale aviation structure. The monitoring instrument disclosed by the invention comprises a system power supply module, a signal interface module, a charge amplifier module, an A/D (Analog to Digital) converter module, a programmable logic device module, a control and computing center, a high-capacity onboard high-speed memory module, an external interaction interface and n paths of piezoelectric sensors. The method disclosed by the invention comprises the following steps: the configuration is initialized; strain signals are collected; a charge amplification circuit converts the input charge quantity into the voltage quantity, and the voltage signals are input into a programmable logic device after being converted by the A/D converter; the input voltage quantity is firstly compared with the reference voltage digital quantity; when the high level occurs, the channel for triggering the data and the ambient three channels with the maximum signal energy are taken as the effective channel for data storage, and the data of the other channels are abandoned; the region in which the current impact accident occurs and the accurate position in which the impact occurs are judged; and the stored data are transmitted out through the external interface.
Description
Technical field
The present invention relates to a kind of large aerospace structure real-time impact monitoring instrument and method, relate in particular to for the real-time impact zone of large aerospace structure and the impact signal that the impact exact position is determined, shock load is big or small and the shock load course is calculated and gather occasion, can automatically extract the effective piezoelectric sensor data of multichannel when impacting, can work under master control and the controlled mode, Monitoring Data and result of calculation are submitted to the external control center by external bus.
Background technology
Compound substance is high with its specific strength, specific stiffness is large, anti-fatigue performance reaches well the series of advantages such as material property can design, obtain increasingly extensive application at engineering fields such as Aeronautics and Astronautics, automobiles, especially on military, civil aircraft, begun to use more and more advanced composite structure.Present state-of-the-art the 4th generation opportunity of combat F22 in the world, consumption of polymer matrix composites has reached 24% of aircaft configuration weight above it.On the A380 passenger plane, the weight of composite structure has reached 25% of complete machine weight, and on Boeing 787 passenger planes up to 50%.In general, use composite structure to reach and alleviate housing construction weight, improve the purpose of housing construction quality.
Yet the impact that Test of Laminate Composites inevitably will bear various energy objects in the process under arms, being subject to gunslinging and instrument such as collision, the aircraft of, the bump of hail, aircraft aerofoil and aerial flying bird drops at aircraft surface in the maintenance process of being everlasting etc.These impact interior laminate layer, MATRIX CRACKING and the fibre breakage equivalent damage that very easily causes composite structure.These internal injuries will make the mechanical property serious degradation of laminate structures, and intensity can weaken 35%～40%, cause load-bearing capacity greatly to reduce, and the integral body of structure be destroyed and lost efficacy forming potential threat.And these damages mostly occur and are difficult for finding from the surface at material internal, stay serious hidden danger, have sudden and potential ability catastrophic failure so that have the composite structure of damage, and its performance at aspects such as damage, inefficacies but is complicated mechanism, phenomenon is various, differentiates difficulty.Therefore the necessary monitoring of composite structure being carried out the life-cycle is with stability and the security of guaranteeing structure.People are generally by preventing the upgrading of degree of injury to making regular check on of aircraft, but aircraft is regularly detected and General Maintenance, need expensive time and expense, and take the EF-111A of the U.S. as example, annual detection approximately needs more than 8000 hours man-hour.Present existing many traditional Dynamic Non-Destruction Measurements that have been widely used, such as knock, the methods such as ultrasonic, X ray, current vortex ray, potential measurement and stress field.But these detection method general device are complicated, take time and effort, need to preliminary understanding be arranged to the position of damage, use inconvenience, limitation is large, be difficult for accomplishing the real time on-line monitoring under the Service Environment, be not suitable for following large aerospace, aerospacecraft health monitoring of structure and diagnosis.Can adopt the passive structure health monitoring to obtain the information such as position of impact for this reason.For experiencing all kinds of parameters of configuration state and environment, there is the multiple sensors part can be in order to detect, piezoelectric element and measuring system thereof have the advantages such as cost is low, highly sensitive, frequency response is wide, dynamic range is large, are widely used in health monitoring research.
But the Impact monitoring engineering experiment for the large aerospace structure, to adopt 24 road piezoelectric elements monitoring impact signal as example, carry out the monitor signal collection according to traditional high-speed data acquisition test mode, system hardware adopts 4 commercial passage high speed analog data acquisition cards and 4 channel charges to amplify conditioner, the experiment of finishing so this project needs 6 data capture cards and 6 electric charge conditioners at least, adds processor and cabinet that the required band of integrated this quantity is unified control core.Extensive application functional independence, the module that integrated level is not high directly cause the raising of test environment complexity and test macro debugging difficulty, and the cost expense on hardware and software is also given carrying out with very large difficulty of experiment simultaneously.
The compound substance impact monitoring system that is applied to the Large Scale Space Vehicle structure is must monitoring range wide, integrated level is high, volume is little, quality is light, be easy to carry, install and use, and can obtain Monitoring Data by Real-time Collection.
Summary of the invention
Technical matters:
The problem to be solved in the present invention is a kind of large aerospace structure real-time impact monitoring instrument of exploitation and method, and this equipment acquisition channel is many, and monitoring range is wide, and the hardware resource expense is few, and level of integrated system is high.This equipment satisfies the continuous data collection of n road piezoelectric sensing passage, can judge the arrival of impact signal, and according to the most effective principle in location the data that a plurality of passages collect is screened, and the data that keep effective passage are preserved and transmitted.Equipment can adopt signal to process computing method and obtain impacting generation area and impact the exact position.System can work in master mode and controlled mode.Under the master mode, according to the work of default parameters guidance system, Monitoring Data is stored in the storage card of internal system by system's microcontroller.Under the controlled mode, system is controlled by external unit or bus line command.System takes full advantage of the machine-processed advantage of programmable logic device parallel work, and impact signal judgement, data preservation and data transmission and monitor signal pre-service 3 thread parallel work guarantee the quick real-time of monitoring to greatest extent.
Technical scheme
In order to solve above-mentioned technical matters, a kind of large aerospace structure real-time impact monitoring instrument is characterized in that, comprises the system power supply module, Signal interface module, the charge amplifier module, analog to digital converter module, programmable logic device (PLD) module, control and computing center, large capacity plate carries high speed memory modules, outside interactive interface, and n road piezoelectric sensor; The external monitoring signal is by Signal interface module input charge amplifier module module, the output terminal serial connection analog to digital converter module of charge amplifier module is connected with the input end of programmable logic device (PLD) module, the output termination control of programmable logic device (PLD) module and the input end of computing center, the programmable logic device (PLD) module is carried the high speed memory modules two-way communication with large capacity plate, control and computing center carry out data interaction by outside interactive interface and outside, described n road piezoelectric sensor is arranged on the monitoring target, the system power supply module provides power supply for above-mentioned module, and wherein n is the natural number greater than 1.
Preferably, described charge amplifier module comprises n the charge amplifier that structure is identical, and each charge amplifier comprises charge amplifying circuit and voltage amplifier circuit, and wherein n is the natural number greater than 1.
Preferably, described analog to digital converter module comprises n analog to digital converter, and each analog to digital converter is connected in series successively by signal conditioning circuit that difference turns single-end circuit and high-speed AD converter spare consists of.
Preferably, described programmable logic device (PLD) module comprises Logic control module and the canonical parameter module that is made up by its internal resource, the canonical parameter module comprises that n is triggered front data buffer, data buffer module after triggering, a logic manage center and n voltage comparator, wherein the output terminal of the front data buffer of the corresponding triggering that arranges and voltage comparator connects respectively the input end at logic manage center, the input end of data buffer module after the output terminal contact at logic manage center is sent out, the negative input termination reference voltage of voltage comparator, the output terminal of the positive input termination analog to digital converter module of voltage comparator.
Preferably, described with outside interactive interface comprises Can bus interface, 1553b bus interface and serial data bus interface.
A kind of monitoring method of large aerospace structure real-time impact monitoring instrument is as follows, after described monitor works on power, and the initial configuration of control and computing center's completion system circuit; Outside piezoelectric sensor is experienced structural strain, is converted into charge signal; Charge amplifying circuit is converted into voltage with the quantity of electric charge of input, and voltage signal inputs in the programmable logic device (PLD) after transforming by AD converter; N passage piezoelectric signal all deposits in the interior ram storer of sheet of programming device; Open up n voltage comparator at programming device inner utilization gate-array circuit, the voltage of input at first compares with the reference voltage digital quantity: when high level appears in the result of comparer a certain passage in n road after relatively, the logic manage center will trigger the place passage and on every side the passage of three signal energy maximums classify data as and store effective passage, and abandon the data of other passage; Among data buffer #1～#4, after band count down to sampling number, the more front image data of the triggering of four-way and the rear image data of triggering are deposited in the outside high-capacity and high-speed storer after institute's signal unloading of counting of gathering entered to trigger after the logic manage center will be triggered; Calculating and control center can judge the zone that current impact event occurs and impact the exact position that occurs; Outside high-capacity and high-speed memory wait, sends out stored data the download command that control center sends from bus by external interface.
The present invention is for shorten the time interval of twice Impact monitoring as far as possible, namely avoid single-threaded work in series, fill the parallel running advantage of utilizing programming device of sending out, Impact monitoring, data are preserved and data transmission will form three independently concurrent working tasks, utilize the mode such as semaphore between task, to keep communication, guarantee to greatest extent the real-time impact monitoring.
Beneficial effect
(1) system possesses the functional circuit of the passive monitoring of large aerospace structure, connects corresponding host computer finder and can realize determining of the impact information such as impact position.
(2) system possesses the pre-collection of triggering and continuous acquisition function, guarantees to trigger whole records of front and back useful signal.
(3) system selects to form rectangle monitoring array from four nearest sensors of impulse source automatically, guaranteeing to reduce to greatest extent data storage and transmission under the bearing accuracy prerequisite, reduces unnecessary memory hardware resource and bus communication resource.
(4) the parallel working mechanism of system multiplex reduces the time interval of twice monitoring task greatly, improves the real-time of Impact monitoring.
(5) system provides the conventional data transmission interface of the airborne application of Aviation, makes things convenient for the download of batch data.
(6) system works can be born the monitoring task with independent instrument under master control and controlled mode, also can be as participate in more big comprehensive experiments from equipment.
Description of drawings
Fig. 1 is a kind of structural representation of large aerospace structure real-time impact monitoring instrument;
Fig. 2 is power distribution schematic diagram of the present invention;
Fig. 3 is multichannel electric charge amplifier signal structured flowchart, (a) signal amplification module structural drawing, (b) single amplification channel structural drawing;
Fig. 4 is high-speed data acquisition structured flowchart and circuit diagram,
Fig. 5 is the connection diagram of programmable logic device (PLD) and outside Mass memory card;
Fig. 6 is that external interface of the present invention connects and the interface chip schematic diagram;
Fig. 7 is the stack manner schematic diagram of internal hardware integrated circuit board of the present invention;
Fig. 8 is the communication connected mode of the present invention and external bus, among the figure: 1 Signal interface module, 2 system power supply modules, 3 high-speed AD converter modules, charge amplifier module, 4 programmable logic device (PLD) modules, control and computing center, large capacity buffered memory modules, external interface module, 5 equipment cabinets.
Embodiment
As shown in Figure 1, a kind of large aerospace structure real-time impact monitoring instrument of the present embodiment, comprise the system power supply module, Signal interface module, charge amplifier module, the analog to digital converter module, the programmable logic device (PLD) module, control and computing center, large capacity plate carries high speed memory modules, and the interactive interface of system and outside, comprise the serial data bus interface such as Can bus interface, 1553b bus interface and RS232.
Be illustrated in figure 2 as whole system the outside direct current 28V power supply that provides is provided, the system power supply module converts the power supply that the outside provides to each module of internal system required power supply by DC/DC, comprise+1.2V, + 3.3V ,+5V, ± 12V, this part power supply offers respectively the different function power input of internal system.Except Signal interface module adopts passive connected mode, the power supply of all the other modules is supplied with and is respectively: charge amplifier module ± 12V, analog to digital converter module+5V, programmable logic device (PLD) I/O power supply+3.3V, kernel power supply+1.2V, the interactive interface use+5V power supply of high speed memory modules and system and outside.Taking into account system integrated, outside ± 12V power supply was obtained by the DC/DC module converts, all the other low-tension supplies all realized by the low-dropout regulator of small size paster.
The function of signal amplifier module is the transducing signal of amplifying piezo-electric element.Bandwidth of operation be 0.2Hz to 500KHz, enlargement factor can be adjusted by program according to the demand of actual monitoring, accepts the enlargement factor control figure signal from control center.The ability that it possesses n road low noise, amplifies simultaneously is shown in Fig. 3 (a).By the n road quantity of electric charge signal on the signal interface circuit plate is accessed to this circuit, output signal is linked in the analog-to-digital circuit.Fig. 3 (b) is the structural drawing of single amplification channel, and adopt three grades of circuit structures: the electric charge amplifier stage converts the quantity of electric charge transducing signal of piezoelectric sensor to voltage signal, and the sensitivity of this grade can be controlled; The low pass filtered wave scale plays the effect of filtering high frequency clutter, it-three dB bandwidth is at 500KHz; Last phase compensation enlargement factor adjustment level is used for compensating the signal phase shift that front two-stage causes, and what is program control at this for enlargement factor.
As shown in Figure 4 the analog to digital converter module comprise signal condition unit, single-ended transfer difference circuit and A the D AD conversion unit.Its function is that the voltage signal after the transducing signal conversion is carried out high-speed data acquisition, receives the amplifying signal of signal amplification module.It has the independent ability that gathers simultaneously of n passage, and sampling rate can arrive 10MHz, and sampling precision can reach 12, range ± 10V.Its high-speed, high precision performance guarantee the precision of transducing signal, thereby improved accuracy and the real-time of im-pact location.
Be illustrated in figure 5 as the structured flowchart that the programmable logic device (PLD) module realizes.It mainly includes: voltage comparator, communication interface, sampling clock generation module, data buffer area before triggering, inner large capacity data memory and outside large capacity data memory control module, and logic control center.Wherein voltage comparator and the inner large capacity data memory library of parameterized module that adopts FPGA to carry makes up and finishes.The task that whole module is mainly finished can be divided into three aspects: at first, the communication interface of utilization and control center carries out alternately.Control and computing center utilize the SPI universal serial bus to assign control command to FPGA, and the inner reception of FPGA is from these orders, and corresponding parameter register is set, such as trigger voltage register and the sampling parameters such as sampling length, sampling rate.After starting collection, system carries out work according to the register value of setting.Secondly, the arrival of trigger pip is judged by system.Buffer area was preserved before the digital quantity of n paths entered into triggering according to sampling rate, meanwhile, these digital quantities participate in the comparison with threshold voltage, in case when saltus step appears in the comparative result of a certain passage, logic centre will detect the arrival of trigger pip.The digital channel that produces trigger pip is identified as trigger port, and is intracardiac in logic control, and according to triggering each passage numeral discharge amplitude size that arrives constantly, other three paths around the ruling impulse source are effective passage.The data of this four paths will all be retained in this trigger event, and be stored in the external memory storage as Monitoring Data.At last, together with after effectively channel selecting is finished, the data on these four paths are all recorded in the time in sampling length/sampling rate at trigger port, and this data division is contained the prerecord value that is stored in the front data buffer of triggering.The data of four passages at first are stored in the storer of FPGA inside, after sampling is finished again, by the external memory storage control module data in the buffer area are preserved in the outside high-capacity and high-speed buffer area again.
Outside high-capacity and high-speed data-carrier store adopts the CF card to realize.CF card power consumption is lower, and capacity relative is larger, and speed is fast, low price.As shown in Figure 6, cooperatively interact by address path module, control command generation module and data path module in the external memory storage control module, for the CF card provides correct address, data and control command, thereby the data that collect are preserved in this device endlessly.
The control of system and computing center adopt DSP to realize, can process in real time and produce corresponding control signal to signal.Under master mode, system is responsible for co-ordination by local control center.Control center at first finishes setting to each register of internal system according to the parameter value of acquiescence of design, and system carries out the monitoring task according to certain condition of work, and Monitoring Data is preserved in the jumbo data storage card according to foregoing workflow.After task to be monitored was finished, the user can take out this memory card, and essential information and the signal data that is kept in the memory card extracted.Under the controlled mode of system, the order that comes from bus or external unit transmission mainly be responsible for to be passed on by control center, and the data of local system are transported on the external bus.When bus line command requires control and computing center to start the baseband signal preprocessing function, in the memory card data at first by computing center carry out signal filtering, go will to process rear data after processings such as direct current and the extraction essential characteristic value or eigenwert transfers out.Under the prerequisite of not losing useful information, reduce data transfer on the bus, can greatly reduce the time that system takies bus, further guarantee real-time.The signal data that control and computing center pass over after can also utilizing the senior location algorithm of integrated wavelet analysis that current impact is occured carries out computational analysis, and the im-pact location zone, the im-pact location exact position that obtain can directly pass to the next stage control core by bus interface.
Be depicted as the communication connected mode of designed system and external bus such as Fig. 7,8.Include the communication mode of CAN bus communication mode, 1553B and the communication mode of RS232 serial.When CAN bus communication pattern is used in the outside design, the CAN controller that internal system adopts and CAN bus transceiver will be finished order and data interaction between the two.When 1553B bus communication pattern was used in the outside design, internal system adopted the mutual of 1553B bus protocol chip completion system and outside.In non-airborne occasion, use external piloting control equipment by universal serial bus and system interconnection, the protocol chip of use can be adopted as the usb bus interface chip or generate the soft nuclear of serial communication interface in programmable logic device (PLD) inside.
In the present embodiment as shown in Figure 8.Whole hardware integration is in embeddeding computer integral aluminum alloy heat-dissipating casing, and modules supports mutually with stack manner.Each integrated circuit board from top to bottom stacking order is followed successively by No. 1 plate that the system power supply module forms, No. 2 plates that high-speed AD converter module and charge amplifier module form and No. 3 plates that are comprised of programmable logic device (PLD) module, control and computing center, large capacity buffered memory modules and external interface module.The piezoelectric sensor signal is introduced from the equipment cabinets outside via the Signal interface module circuit board.
Claims (1)
1. the monitoring method of a large aerospace structure real-time impact monitoring instrument, the employed monitor of this monitoring method, comprise the system power supply module, Signal interface module, charge amplifier module, the analog to digital converter module, the programmable logic device (PLD) module, control and computing center, large capacity plate carries high speed memory modules, outside interactive interface, and n road piezoelectric sensor; The external monitoring signal is by Signal interface module input charge amplifier module, the output terminal serial connection analog to digital converter module of charge amplifier module is connected with the input end of programmable logic device (PLD) module, the output termination control of programmable logic device (PLD) module and the input end of computing center, the programmable logic device (PLD) module is carried the high speed memory modules two-way communication with large capacity plate, control and computing center carry out data interaction by outside interactive interface and outside, described n road piezoelectric sensor is arranged on the monitoring target, the system power supply module provides power supply for above-mentioned module, described charge amplifier module comprises n the charge amplifier that structure is identical, and each charge amplifier comprises charge amplifying circuit and voltage amplifier circuit; Described analog to digital converter module comprises n analog to digital converter, each analog to digital converter is made of signal conditioning circuit successively series connection single end slip parallel circuit and high-speed AD converter spare, and the output of the charge amplifier of the n in the charge amplifier module connects one to one with the input of n analog to digital converter respectively; Described programmable logic device (PLD) module comprises that n is triggered front data buffer, n voltage comparator, data buffer module after 1 logic manage center and the triggering that formed by data buffer after 4 triggerings, the output of a described n analog to digital converter is corresponding continuous one by one with the positive input of the input of data buffer before n is triggered and n voltage comparator respectively, the output of the output of data buffer and each voltage comparator connect respectively the input at logic manage center before each triggered, the input end of data buffer module after the output contact at logic manage center is sent out, the negative input termination reference voltage of each voltage comparator; Described outside interactive interface comprises Can bus interface, 1553b bus interface and serial data bus interface, described n is the natural number greater than 1, it is characterized in that, the monitoring method of described real-time impact monitoring instrument is, after monitor worked on power, control and computing center finished the initial configuration of monitor; N road piezoelectric sensor is experienced structural strain, is converted into charge signal; Charge amplifier is converted into voltage signal with the charge signal of input, and voltage signal inputs in the programmable logic device (PLD) module after transforming by analog to digital converter; N channel voltage signal all deposits in the interior ram storer of sheet of programmable logic device (PLD) module; Utilize gate-array circuit to open up a described n voltage comparator in the programmable logic device (PLD) inside modules, the voltage signal of input at first compares with the digital quantity of reference voltage: when high level appears in a certain passage of the n road voltage comparator result after relatively, the logic manage center will trigger the place passage and on every side the passage of three voltage signal energy maximums classify data as and store effective passage, and abandon the data of other passage; The voltage signal unloading of counting that gathers entered after 4 described triggerings in the data buffer after the logic manage center will be triggered, after counting down to sampling number, deposit image data after the front image data of the triggering of four-way and the triggering in large capacity plate again and carry in the high speed memory modules; Control and computing center can judge the zone that current impact event occurs and impact the exact position that occurs; Large capacity plate carries high speed memory modules to be waited for from bus the download command that control and computing center send is sent out stored data by described outside interactive interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110057547 CN102183350B (en) | 2011-03-10 | 2011-03-10 | Real-time impact monitoring instrument and method of large-scale aviation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110057547 CN102183350B (en) | 2011-03-10 | 2011-03-10 | Real-time impact monitoring instrument and method of large-scale aviation structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102183350A CN102183350A (en) | 2011-09-14 |
| CN102183350B true CN102183350B (en) | 2013-01-09 |
Family
ID=44569578
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110057547 Expired - Fee Related CN102183350B (en) | 2011-03-10 | 2011-03-10 | Real-time impact monitoring instrument and method of large-scale aviation structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102183350B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105366066A (en) * | 2015-10-20 | 2016-03-02 | 南京航空航天大学 | Micro-miniature ultra-low-power-consumption impact monitoring system based on diode array digitization |
| US10227142B1 (en) * | 2017-09-13 | 2019-03-12 | The Boeing Company | Systems and methods for detecting impacts to vehicle surfaces |
| CN109406315A (en) * | 2018-11-29 | 2019-03-01 | 清华大学 | Firer's shock response many reference amounts cooperative device |
| CN109738102A (en) * | 2019-01-21 | 2019-05-10 | 深圳市大可奇科技有限公司 | A kind of 3D sensing module and application method |
| CN111721450B (en) * | 2020-06-22 | 2021-06-29 | 山东大学 | Impact positioning recognition device and method |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201134025Y (en) * | 2007-12-25 | 2008-10-15 | 杭州亿恒科技有限公司 | Impact measurement control instrument adopting DSP |
| CN101701880B (en) * | 2009-08-05 | 2011-06-29 | 南京航空航天大学 | Embedded health monitoring system for active and passive structure of aeroplane |
| CN101807953B (en) * | 2010-02-10 | 2013-07-24 | 南京航空航天大学 | Multichannel data integration center node of wireless sensor network |
-
2011
- 2011-03-10 CN CN 201110057547 patent/CN102183350B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN102183350A (en) | 2011-09-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102288346B (en) | Miniaturized digital large-scale sensor array impact monitoring system | |
| CN102183350B (en) | Real-time impact monitoring instrument and method of large-scale aviation structure | |
| CN101701880B (en) | Embedded health monitoring system for active and passive structure of aeroplane | |
| CN100524366C (en) | Missile-borne solid state recorder | |
| CN101275928B (en) | Spaceflight electronic device excess article automatic detection system and detection method | |
| CN106081136B (en) | Unmanned aerial vehicle sliding lateral deviation detection method and device | |
| CN102706420A (en) | Device and method for dynamically detecting vehicle loading capacity and vehicle speed in real time | |
| CN101581295A (en) | Airborne hydraulic pump source fault diagnosis system based on DSP | |
| CN104102127B (en) | A kind of machine load Aerodynamic Parameter Identification system | |
| CN108051126B (en) | A kind of Varying-thickness Composite Laminated Plate under Low-Velocity Impact Thin interbed system and its working method | |
| CN102323779A (en) | Measurement and control sensor network for heavy numerical control equipment | |
| US10145746B2 (en) | Diode array-based digitized miniature ultra-low-power-consumption impact monitoring system | |
| CN105676755A (en) | Dual-core flight control computer | |
| CN102889896A (en) | Two-stage noise reduction method for impact monitoring digital sequence of composite structure | |
| CN111174845A (en) | MEMS accelerometer-based aircraft oil quantity measuring system and measuring method | |
| Henke | “A 320 HLF Fin” flight tests completed | |
| CN113311858A (en) | Flight control system and method based on unmanned aerial vehicle | |
| CN101793590B (en) | Structural impact damage diagnostic method based on blackboard cooperation | |
| CN111189490A (en) | Aircraft environment monitoring system | |
| Lee-Rausch et al. | FUN3D airloads predictions for the full-scale UH-60A airloads rotor in a wind tunnel | |
| CN110631467A (en) | Multichannel self-adaptive high-precision LVDT data acquisition and measurement system and method | |
| CN103471870A (en) | Method for researching sensibility and clustering performance for recognizing states of coal mine equipment based on two-dimensional projection characteristic indexes | |
| CN110471340A (en) | Elastic wave acquisition device and its control method between a kind of hole based on ARM | |
| CN105571799A (en) | Measuring apparatus and system of mechanical environment of spacecraft | |
| CN110631468A (en) | Numerical measurement system and method based on LVDT sensor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130109 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |