CN113552424A - Weak static signal collection system of aeroengine gas circuit granule - Google Patents
Weak static signal collection system of aeroengine gas circuit granule Download PDFInfo
- Publication number
- CN113552424A CN113552424A CN202110728223.XA CN202110728223A CN113552424A CN 113552424 A CN113552424 A CN 113552424A CN 202110728223 A CN202110728223 A CN 202110728223A CN 113552424 A CN113552424 A CN 113552424A
- Authority
- CN
- China
- Prior art keywords
- signal
- electrostatic
- charge
- circuit board
- particles
- 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
- 230000003068 static effect Effects 0.000 title claims abstract description 27
- 239000008187 granular material Substances 0.000 title claims description 4
- 238000012545 processing Methods 0.000 claims abstract description 70
- 239000002245 particle Substances 0.000 claims abstract description 59
- 239000000523 sample Substances 0.000 claims abstract description 57
- 230000006698 induction Effects 0.000 claims abstract description 34
- 238000000034 method Methods 0.000 claims abstract description 20
- 238000006243 chemical reaction Methods 0.000 claims abstract description 18
- 230000003321 amplification Effects 0.000 claims abstract description 16
- 238000003199 nucleic acid amplification method Methods 0.000 claims abstract description 16
- 230000008569 process Effects 0.000 claims abstract description 8
- 239000003990 capacitor Substances 0.000 claims description 36
- 239000002184 metal Substances 0.000 claims description 33
- 229910052751 metal Inorganic materials 0.000 claims description 33
- 239000000919 ceramic Substances 0.000 claims description 19
- 230000005611 electricity Effects 0.000 claims description 13
- 230000001939 inductive effect Effects 0.000 claims description 9
- 238000001914 filtration Methods 0.000 claims description 8
- 230000006870 function Effects 0.000 claims description 8
- 238000004590 computer program Methods 0.000 claims description 7
- 238000012805 post-processing Methods 0.000 claims description 4
- 238000004146 energy storage Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 5
- 239000007789 gas Substances 0.000 description 13
- 238000010586 diagram Methods 0.000 description 12
- 238000005516 engineering process Methods 0.000 description 7
- 238000012544 monitoring process Methods 0.000 description 7
- 239000002923 metal particle Substances 0.000 description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- 230000008859 change Effects 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000001228 spectrum Methods 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 238000013500 data storage Methods 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000036541 health Effects 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012806 monitoring device Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000010412 perfusion Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012552 review Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/12—Measuring electrostatic fields or voltage-potential
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R1/00—Details of instruments or arrangements of the types included in groups G01R5/00 - G01R13/00 and G01R31/00
- G01R1/02—General constructional details
- G01R1/18—Screening arrangements against electric or magnetic fields, e.g. against earth's field
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R1/00—Details of instruments or arrangements of the types included in groups G01R5/00 - G01R13/00 and G01R31/00
- G01R1/30—Structural combination of electric measuring instruments with basic electronic circuits, e.g. with amplifier
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R19/00—Arrangements for measuring currents or voltages or for indicating presence or sign thereof
- G01R19/25—Arrangements for measuring currents or voltages or for indicating presence or sign thereof using digital measurement techniques
- G01R19/2506—Arrangements for conditioning or analysing measured signals, e.g. for indicating peak values ; Details concerning sampling, digitizing or waveform capturing
- G01R19/2509—Details concerning sampling, digitizing or waveform capturing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/24—Arrangements for measuring quantities of charge
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Or Analyzing Materials By The Use Of Electric Means (AREA)
Abstract
The invention belongs to the technical field of sensor design and signal acquisition, and discloses a weak electrostatic signal acquisition system for air passage particles of an aircraft engine, wherein a sensing probe senses charge signals generated by electrostatically charged particles and acquires electrostatic signals carried by the particles in the aircraft engine; the static induction induces charges on the induction probe, the charges are transmitted to the signal processing circuit board through the signal wire, and charge signals are collected and processed by the signal processing circuit board behind the signal processing circuit board. The anti-interference capability of the aircraft engine in the process of acquiring weak electrostatic signals of the air circuit is improved by designing the shielding device of the electrostatic signal sensor; the charge conversion circuit is designed in a targeted manner, and the charge signal is converted into a voltage signal, so that the subsequent signal amplification, acquisition and other processing are facilitated; the bias voltage of the voltage amplification circuit is processed, the bias zero-setting circuit is designed, the influence of the bias voltage is counteracted, and the electrostatic signal acquisition capability of the air passage of the aircraft engine is improved.
Description
Technical Field
The invention belongs to the technical field of sensor design and signal acquisition, and particularly relates to a weak electrostatic signal acquisition system for air path particles of an aircraft engine.
Background
Currently, an aircraft engine is used as the core of an aircraft power system, and the performance and the working health of the aircraft engine are directly related to the flight safety of the aircraft. The engine is easily broken down due to the complex and changeable working environment and the influence of high-intensity vibration, high speed, high temperature and other conditions during the operation, and the engine is easily broken down, so that the engine is easily broken down, and the airplane can be destroyed destructively if the engine is heavy. Therefore, the potential faults of the aero-engine can be found and positioned in time and maintained according to the situation, and the method becomes the primary requirement of the fault monitoring technology. The traditional fault monitoring technology has certain limitation on the evaluation of the real-time state of the aircraft engine. Some faults, which may have already caused some irreparable damage to the engine, can only be detected by these means if they accumulate to a certain extent. The static monitoring technology for the air circuit of the aircraft engine is a technology capable of realizing real-time monitoring of the working condition of the engine and realizing early warning of faults to a certain extent. The invention relates to a weak static signal acquisition device, which is a novel aeroengine gas circuit state monitoring device, monitors the change of static signals of tail gas of an aeroengine by acquiring static signals carried by particles generated by the working of the aeroengine, further realizes the state monitoring and the early warning of faults of the aeroengine, and is a hardware basis of the aeroengine static monitoring technology.
At present, the static monitoring technology is applied to foreign advanced warplanes, and plays a great role in improving the safety of airplanes and early warning of faults. However, the technology is not mature enough at present in China, and the electrostatic sensor designed and manufactured by a domestic research institution has the problems that the shielding function is not good enough, and signals are easily interfered by external vibration, electromagnetism and power frequency; the signal acquisition circuit is simple in design, in the aspect of designing a signal conversion circuit, the existing patent only acquires and amplifies an electrostatic signal by a voltage amplification circuit, and a charge signal conversion circuit is not specifically designed to realize conversion from the electrostatic signal to the voltage signal; in the design of a voltage amplifying circuit, the voltage amplifying circuit is not sufficient, and when the amplifying circuit is built in the existing designed circuit, the offset voltage generated on a feedback resistor by the offset current of an operational amplifier is not considered, so that the accuracy of the acquired electrostatic signal is influenced, and therefore, the offset voltage needs to be zeroed in the design process; considering the zero adjustment of the bias voltage, the signal is easy to be distorted when being collected.
Through the above analysis, the problems and defects of the prior art are as follows: in the prior art, a voltage amplifying circuit is only used for collecting and amplifying an electrostatic signal, and a charge signal conversion circuit is not designed in a targeted manner to realize the conversion from the electrostatic signal to the voltage signal; in the design of the voltage amplifying circuit, zero adjustment of the bias voltage is not fully considered, and the signal is easy to distort when being collected.
The difficulty in solving the above problems and defects is: the selection of an operational amplifier is complicated and time-consuming, and the operational amplifier with small bias current parameter, small offset voltage, large input resistance, good linearity and small temperature drift is selected as the core of the signal conversion circuit; the offset voltage zero setting circuit is designed according to the characteristics of the operational amplifier, a stable direct current voltage source is provided to supply power to the circuit, and a potentiometer with high precision is provided, so that zero setting operation is facilitated.
The significance of solving the problems and the defects is as follows: the charge signal can be converted into a more common and easily processed voltage signal, so that the voltage signal can be conveniently subjected to conventional filtering, amplification and other processing by a subsequent circuit; the voltage bias is adjusted to zero, so that the interference caused by the property of the operational amplifier can be effectively reduced; the overall measure is to help improve the accuracy of the acquired electrostatic signal.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a system for acquiring weak electrostatic signals of air passage particles of an aero-engine.
The invention is realized in this way, a method for collecting weak electrostatic signals of aero-engine gas path particles, which comprises the following steps:
the method comprises the following steps that firstly, a sensing probe senses charge signals generated by electrostatically charged particles to acquire the electrostatic signals carried by the particles in the aircraft engine, moving charged particles can sense changed charge signals on the probe when passing near the sensor probe due to the electrostatic sensing principle, and the changed charge signals can be sensed on the probe due to continuous redistribution of charges in the probe;
and secondly, inducing charges on the induction probe by electrostatic induction, transmitting the charges to the signal processing circuit board through a signal wire, and collecting and processing charge signals by the following signal processing circuit board. The charge signal is led into the charge conversion circuit through the signal line, the charge signal that changes is converted into the voltage signal, then the voltage signal is transmitted to the amplifier circuit again and is carried out the amplification processing, inputs the filter circuit after the amplification and removes high frequency interference, then through the signal acquisition integrated circuit board, analog signal converts the digital signal into, transmits to the computer, is carried out the aftertreatment by the computer program.
It is a further object of the invention to provide a computer device comprising a memory and a processor, the memory storing a computer program which, when executed by the processor, causes the processor to perform the steps of:
firstly, displaying a signal subjected to analog-to-digital conversion by an acquisition board card on a screen, carrying out digital filtering on an original signal, removing power frequency interference, synchronously carrying out Fourier transform on the acquired voltage signal, calculating a power spectrum of the signal, obtaining the frequency domain characteristic of the signal, and displaying the processed signal on the screen;
and secondly, storing the signal data processed by the program into a storage medium so as to facilitate the operations of post processing, review and the like.
It is another object of the present invention to provide a computer-readable storage medium storing a computer program which, when executed by a processor, causes the processor to perform the steps of:
the method comprises the following steps that firstly, a sensing probe senses charge signals generated by particles with static electricity, and static electricity signals carried by the particles in the aircraft engine are collected;
and secondly, inducing charges on the induction probe by electrostatic induction, transmitting the charges to the signal processing circuit board through a signal wire, and collecting and processing charge signals by the following signal processing circuit board.
Another object of the present invention is to provide an aeroengine gas path particle weak electrostatic signal acquisition system operating the aeroengine gas path particle weak electrostatic signal acquisition method, the aeroengine gas path particle weak electrostatic signal acquisition system including:
the electrostatic signal acquisition module is used for sensing a charge signal generated by the probe sensing the particles with static electricity and acquiring the electrostatic signal carried by the particles in the aircraft engine;
and the signal processing module is used for inducing charges on the induction probe by electrostatic induction and transmitting the charges to the signal processing circuit board through a signal wire, and charge signals are collected and processed by the signal processing circuit board behind the signal processing circuit board.
Another object of the present invention is to provide an aeroengine gas path particle weak electrostatic signal acquisition device carrying the aeroengine gas path particle weak electrostatic signal acquisition system, the aeroengine gas path particle weak electrostatic signal acquisition device including:
the electrostatic sensor is used for sensing a charge signal generated by sensing the electrostatic particles by the probe and acquiring the electrostatic signal carried by the particles in the aircraft engine;
and the signal processing circuit board is connected with the electrostatic sensor and used for inducing charges on the induction probe by electrostatic induction and transmitting the charges to the signal processing circuit board through a signal wire, and charge signals are collected and processed by the signal processing circuit board behind the signal processing circuit board.
Further, the electrostatic sensor comprises a probe, a first metal shell, a second metal shell, a ceramic lining, a first signal connecting line, a second signal connecting line and a signal line plug. The inner side of the first metal shell is provided with internal threads, the outer side of the second metal shell is provided with external threads, and the first metal shell and the second metal shell are connected through threads; the size of the ceramic lining is just consistent with the size of the inner space of the metal shell, and the ceramic lining can be fixed in the metal shell; the circuit board is fixed at the step of the upper and lower ceramic lining layers; the sensor probe is fixed on the ceramic lining layer through threads, a second signal connecting wire is led out of the probe and is connected with the input end of the signal processing circuit board, and the first signal connecting wire is connected with the output end of the signal processing circuit board and the signal plug; then the signal is transmitted to the signal acquisition board card from the signal plug and then transmitted to a computer for processing.
Further, the signal processing circuit board includes: the device comprises a charge amplifying circuit, a voltage amplifying circuit, a filter circuit and a power supply filter circuit. The charge amplifying circuit isConverting the charge signal collected by the sensor into a voltage signal, wherein the specific conversion relation is UO-Q/C, determined primarily by the feedback capacitance; the voltage amplifying circuit amplifies the voltage signal converted by the charge amplifying circuit so as to meet the voltage amplitude requirement of analog-to-digital conversion of a rear acquisition board card, and the bias voltage is zeroed in the amplifying process so as to improve the accuracy of the signal; the filter circuit is used for filtering the voltage signal to remove high-frequency interference; the power supply filter circuit filters high-frequency interference possibly mixed from a power supply end, and the influence of the mixed interference on the accuracy of a circuit signal acquisition is reduced.
Further, in the charge amplification circuit, the input end of a charge signal is connected with one end of a feedback resistor R2 and one end of a feedback capacitor C6, the other ends of the feedback resistor R2 and the feedback capacitor C6 are connected with the output end of an operational amplifier U1, one ends of a resistor R1 and a capacitor C5 are connected with a No. 3 pin of the operational amplifier, one section of the resistor R1 is grounded, the input impedance matching of the anode and the cathode of the operational amplifier is realized, the capacitors C7 and C8 are respectively connected with the cathode and the anode of a power supply, and the pins 1, 4 and 8 of the operational amplifier are grounded.
Further, the output end of the charge amplifying circuit is connected with one end of a resistor R3 by the voltage amplifying circuit, the resistor R3 isolates direct-current voltage, the other end of the resistor R3 is connected with a resistor R4 and then connected to a No. 3 pin of the operational amplifier, the resistor R4 protects the operational amplifier, a No. 2 pin is connected with a resistor R5 and then grounded, and R5 plays a role in balancing input resistance; the No. 1 pin of the operational amplifier is connected with a resistor R6 and a slide rheostat Radj2, the No. 8 pin is connected, different voltage amplification factors are obtained by adjusting the slide rheostat, the resistor R9, the resistor R8, the resistor R7 and the slide rheostat Radj1 are connected with the positive electrode and the negative electrode of a power supply, the direct-current voltage bias is adjusted, and high-frequency interference of an input power supply is filtered by capacitors C9 and C10.
Further, the signal output of the voltage amplifying circuit of the low-pass filter circuit passes through the resistor R10 and the resistor R11, the other end of the resistor R11 is connected with the resistor R12 and the capacitor C12, the other end of the resistor R12 and the pin 3 of the operational amplifier are connected with the capacitor C11, and the other end of the capacitor C11 is grounded. The other end of the capacitor C12 is connected with the No. 2 pin and one end of the resistor R13;
the power supply anode of the power supply filter circuit is connected with one end of a diode D1, and the other end of the diode is connected with a capacitor C1 and a capacitor C3, so that the functions of energy storage and high-frequency interference filtering are achieved respectively; and one end of a diode D2 is connected to the negative electrode of the power supply, and the other end of a diode D2 is connected with a capacitor C2 and a capacitor C4, so that high-frequency interference can be stored and filtered respectively.
By combining all the technical schemes, the invention has the advantages and positive effects that: the anti-interference capability of the aircraft engine in the process of acquiring weak electrostatic signals of the air circuit is improved by designing the shielding device of the electrostatic signal sensor; the charge conversion circuit is designed in a targeted manner, and the charge signal is converted into a voltage signal so as to facilitate the processing of signal amplification, acquisition and the like of the later stage; and processing the bias voltage of the voltage amplification circuit, designing a bias zero-setting circuit and offsetting the influence of the bias voltage as much as possible. Through the measures, the signal acquisition device comprehensively improves the acquisition capacity of the signal acquisition device for the static signals of the air circuit of the aircraft engine.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments of the present application will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings can be obtained from the drawings without creative efforts.
Fig. 1 is a flowchart of a method for acquiring weak electrostatic signals of air path particles of an aircraft engine according to an embodiment of the invention.
FIG. 2 is a schematic structural diagram of a system for acquiring a weak electrostatic signal of an aircraft engine gas path particle provided by an embodiment of the invention;
fig. 3 is a schematic structural diagram of a device for acquiring a weak electrostatic signal of air path particles of an aircraft engine according to an embodiment of the present invention;
fig. 4 is a schematic diagram of an electrostatic sensor according to an embodiment of the present invention.
In the figure: 1. a probe; 2. a first metal case; 3. a second metal case; 4. a ceramic liner; 5. a signal line plug; 6. mounting holes; 7. a signal processing circuit board; 8. a first signal connection line; 9. a second signal line plug; 10. a static signal acquisition module; 11. and a signal processing module.
Fig. 5 is a schematic diagram of a charge amplifying circuit according to an embodiment of the present invention.
Fig. 6 is a schematic diagram of a voltage amplifying circuit according to an embodiment of the present invention.
Fig. 7 is a schematic diagram of a filter circuit according to an embodiment of the present invention.
Fig. 8 is a schematic diagram of a power filter circuit according to an embodiment of the present invention.
Fig. 9 is a schematic diagram of an example 1 of signal acquisition provided by an embodiment of the present invention.
FIG. 10 is a time domain plot (top) and a frequency domain plot (bottom) of an injected metal particle signal provided by an embodiment of the present invention.
FIG. 11 is a time domain diagram (top view) and a frequency domain diagram (bottom view) of a signal with injected toner according to an embodiment of the present invention.
Fig. 12 is a schematic diagram of an example of collecting an engine on-line test signal according to an embodiment of the present invention.
Fig. 13 is a schematic diagram of an example of signal acquisition provided by an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Aiming at the problems in the prior art, the invention provides a system for acquiring weak electrostatic signals of air path particles of an aircraft engine, and the invention is described in detail with reference to the accompanying drawings.
As shown in fig. 1, the method for acquiring the weak electrostatic signal of the air passage particles of the aircraft engine provided by the invention comprises the following steps:
s101: the induction probe induces charge signals generated by the particles with static electricity, and static electricity signals carried by the particles in the aircraft engine are collected;
s102: the static induction induces charges on the induction probe, the charges are transmitted to the signal processing circuit board through the signal wire, and charge signals are collected and processed by the signal processing circuit board behind the signal processing circuit board.
The charge signal is led into the charge conversion circuit through the signal line, the charge signal is converted into a voltage signal, then the voltage signal is transmitted to the amplifying circuit for amplification, the amplified voltage signal is input to the filter circuit to remove high-frequency interference, then the analog signal is converted into a digital signal through the signal acquisition board card, the digital signal is transmitted to a computer, and the digital signal is subjected to post-processing by a computer program.
As shown in fig. 2, the system for acquiring the weak electrostatic signal of the air passage particles of the aircraft engine provided by the invention comprises:
and the electrostatic signal acquisition module 10 is used for sensing a charge signal generated by sensing the electrostatic particles by the probe and acquiring the electrostatic signal carried by the particles in the aircraft engine.
And the signal processing module 11 is used for inducing charges on the induction probe by electrostatic induction and transmitting the charges to the signal processing circuit board through a signal wire, and charge signals are collected and processed by the signal processing circuit board behind the signal processing circuit board.
The technical solution of the present invention is further described below with reference to the accompanying drawings.
As shown in fig. 3, the device for acquiring the weak electrostatic signal of the air passage particles of the aircraft engine provided by the invention comprises an electrostatic sensor and a signal processing circuit board. The electrostatic sensor comprises a probe 1, a first metal shell 2, a second metal shell 3, a ceramic lining 4, a first signal connecting wire 8, a second signal connecting wire 9 and a signal wire plug 5; a signal processing circuit board 7.
The inner side of the first metal shell 2 is provided with internal threads, the outer side of the second metal shell 3 is provided with external threads, and the first metal shell and the second metal shell are connected through threads; the size of the ceramic lining 4 is just consistent with the size of the inner space of the metal shell, and the ceramic lining 4 can be fixed in the metal shell; the circuit board is fixed at the step of the upper and lower ceramic lining layers 4; the sensor probe is fixed on the ceramic lining 4 through threads, a second signal connecting wire 9 is led out of the probe, the second signal connecting wire 9 is connected to the input end of the signal processing circuit board 7, and the first signal connecting wire 8 is connected with the output end of the signal processing circuit board 7 and a signal plug; then, the signal is transmitted to the signal acquisition board card from the signal plug 5 and then transmitted to a computer for processing.
As shown in fig. 4, the function of the electrostatic sensor is to realize the collection of electrostatic signals carried by particulate matters in the aircraft engine, and the principle of realizing the signal collection is that the electrostatic induction induces charges on the induction probe when the particulate matters carrying the electrostatic charges pass near the induction probe 1 in the process of moving along with the fuel gas generated by the engine, and the charge signals can be collected and processed by a signal processing circuit board at the back. The working process of the electrostatic sensor is that the induction probe induces charge signals generated by the particles with static electricity and transmits the charge signals to the signal processing circuit board through the signal wire. The components of the electrostatic sensor are an induction probe 1, a ceramic lining 4, a first metal shell 2 and a second metal shell 3. Because the induction probe 1 needs to work in high-temperature fuel gas, the invention adopts high-temperature nickel-based alloy; in order to realize the isolation of the probe and the metal shell, the invention adopts the insulating material ceramic 4, and the ceramic material can also isolate the influence of the external temperature on the internal circuit board; first metal casing 2, the effect of shielding external interference is mainly played in the ground connection of second metal casing 3, wraps up ceramic lining 4 and signal processing circuit board inside simultaneously, makes it form a whole, and then can realize gathering and handling the weak electrostatic signal realization of granule.
As shown in fig. 5, in order to form a charge amplifying circuit, the input end of a charge signal is connected to one end of the feedback resistor R2 and one end of the feedback capacitor C6, and the other ends of the feedback resistor R2 and the feedback capacitor C6 are connected to the output end of the operational amplifier U1, so that the output voltage and the charge have a relationship formula that the range of the output voltage can be changed by changing the size of the feedback capacitor C6. One end of the resistor R1 and one end of the capacitor C5 are connected with the No. 3 pin of the operational amplifier, and one section of the resistor R1 and one end of the capacitor C5 are grounded to realize the impedance matching of the positive input impedance and the negative input impedance of the operational amplifier. The capacitors C7 and C8 are connected to the negative and positive poles of the power supply, respectively, to filter out high frequency noise from the power supply. Pins 1, 4 and 8 of the operational amplifier are grounded to shield the input terminal.
As shown in fig. 6, in the voltage amplifier circuit, the output terminal of the charge amplifier circuit is connected to one end of a resistor R3, and the resistor R3 may be replaced with a capacitor, so that a dc voltage can be isolated. The other end of the resistor R3 is connected with the resistor R4 and then connected into the No. 3 pin of the operational amplifier, the resistor R4 plays a role of protecting the operational amplifier, the No. 2 pin is connected with the resistor R5 and then grounded, and the resistor R5 plays a role of balancing the input resistor. The No. 1 pin of the operational amplifier is connected with a resistor R6 and a slide rheostat Radj2, and is connected with the No. 8 pin, so that different voltage amplification factors can be obtained by adjusting the slide rheostat. The resistors R9, R8 and R7 and the sliding rheostat Radj1 are connected with the positive electrode and the negative electrode of a power supply to realize adjustment of direct-current voltage bias. The capacitors C9 and C10 mainly filter out high frequency interference of the input power.
As shown in fig. 7, for the low pass filter circuit, the signal output of the voltage amplifying circuit passes through the resistor R10, and then passes through the resistors R11, the other ends of R11 are connected to the resistor R12 and the capacitor C12, respectively, the other end of the resistor R12 and the pin No. 3 of the operational amplifier are connected to the capacitor C11, and the other end of the capacitor C11 is grounded. The other end of the capacitor C12 is connected to pin No. 2 and one end of the resistor R13. The whole body forms a second-order low-pass filter with the cut-off frequency of 2 KHz.
As shown in fig. 8, one end of a diode D1 is connected to the positive electrode of the power supply, which has the function of preventing perfusion, and the other end of the diode is connected to capacitors C1 and C3, which respectively function to store energy and filter high-frequency interference; one end of a diode D2 is connected to the cathode of the power supply, and the other end of a diode D2 is connected with capacitors C2 and C4, which respectively play a role in energy storage and high-frequency interference filtering.
The charge amplifying circuit converts charge signals collected by the sensor into voltage signals, and the specific conversion relation is UO-Q/C, determined primarily by the feedback capacitance; the voltage amplifying circuit amplifies the voltage signal converted by the charge amplifying circuit to meet the voltage amplitude requirement of analog-to-digital conversion of a rear acquisition board card, and the voltage amplifying circuit deflects in the amplifying processThe voltage is set for zero setting, so that the accuracy of the signal is improved; the filter circuit is used for filtering the voltage signal to remove high-frequency interference; the power supply filter circuit filters high-frequency interference possibly mixed from a power supply end, and the influence of the mixed interference on the accuracy of a circuit signal acquisition is reduced.
As shown in fig. 9, the processing panel is a program for post-processing after the electrostatic signal is collected by the computer. The panel can be divided into two working areas from left to right. The left half part on the panel can realize the setting of functions such as sampling frequency, collection point number, collection mode, signal data storage position, opening and closing signal collection and the like. The right part of the panel can synchronously realize the functions of displaying signals, calculating power spectrum, phase spectrum, filtering processing and the like.
The technical effects of the present invention will be described in detail with reference to simulations.
The collecting effect shown in fig. 10 is that the rubber stick with negative charge after the fur is rubbed swings near the sensor probe, compared with the situation that no rubber stick moves near the sensor probe, the signal changes dramatically, the faster the rubber stick swings in the sensitive area near the probe, the voltage signal changes sharply, when the rubber stick is close to the probe, the positive charge is induced in the area near the rubber stick on the probe, the negative charge is induced in the area far from the rubber stick, the negative charge is collected and output by the signal processing circuit, the output amplitude of the signal is positively correlated with the moving speed of the rubber stick, when the swinging speed is faster, the amplitude of the signal is larger and the changing time is shorter, and the swinging speed is slower, the amplitude of the signal is smaller and the changing time is slower.
Fig. 11 shows an electrostatic signal collected by the electrostatic sensor when the electrostatic signal sensor is fixed to a metal pipe, a probe is inserted into the pipe, and then metal particles are blown into the pipe by a blower. When metal particles are charged after entering a pipeline through collision friction, charge signals with opposite properties can be induced at the near end of the probe when flowing through the vicinity of the probe of the sensor, charge signals with the same properties can be induced at the far end of the probe, and the same-phase output is obtained after the processing of the signal processing board. As can be seen from the graph, the signal peaks are positively changed, and it can be concluded that the metal particles are positively charged after rubbing, and each signal peak appears in the graph and is injected into the metal particles.
Fig. 12 shows the electrostatic signal collected by the electrostatic sensor when the electrostatic signal sensor is fixed on a metal pipe, the probe is inserted into the pipe, and then carbon powder particles are blown into the pipe by the blower. When carbon powder particles are charged after entering a pipeline through collision friction, charge signals with opposite properties can be induced at the near end of the probe when flowing through the vicinity of the probe of the sensor, charge signals with the same properties can be induced at the far end of the probe, and the same-phase output is obtained after the processing of the signal processing board. As can be seen from the graph, the signal peaks are in negative change, so that it can be inferred that the carbon powder particles are negatively charged after rubbing, and each signal peak in the graph appears and is the process of spraying the carbon powder particles.
Fig. 13 shows an example of signal collection, in which an electrostatic signal sensor is fixed at the outlet of the exhaust pipe of a small turbojet engine to collect an electrostatic signal in the exhaust gas of the engine. And (3) observing the obtained static induction signal in the complete process of the engine online test run, wherein 1-2 represents that the induction signal is increased sharply when the engine starts to ignite and start because the oil supply amount is overlarge, the engine is in an oil-rich state, and the excessive fuel oil is discharged along with tail gas to cause the sharp increase of the induction signal. Then the signal amplitude correspondingly has positive correlation change along with the change of the output power of the engine, the engine is accelerated from 2 to 3 to reach the maximum working state, the deceleration is restarted from 3 to 4 to enter the cruising state from 4 to 5. Finally, when the engine is shut down, indicated at 5-6, the unburned fuel again causes a sudden increase in the sense signal.
In the description of the present invention, "a plurality" means two or more unless otherwise specified; the terms "upper", "lower", "left", "right", "inner", "outer", "front", "rear", "head", "tail", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, should not be construed as limiting the invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The above description is only for the purpose of illustrating the present invention and the appended claims are not to be construed as limiting the scope of the invention, which is intended to cover all modifications, equivalents and improvements that are within the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. The method for acquiring the weak electrostatic signal of the air path particles of the aero-engine is characterized by comprising the following steps of:
the method comprises the following steps that firstly, a sensing probe senses charge signals generated by particles with static electricity, and static electricity signals carried by the particles in the aircraft engine are collected;
secondly, electrostatic induction induces charges on the induction probe, the charges are transmitted to the signal processing circuit board through a signal wire, and charge signals are collected and processed by the following signal processing circuit board; the charge signal is led into the charge conversion circuit through the signal line, the charge signal is converted into a voltage signal, then the voltage signal is transmitted to the amplifying circuit for amplification, the amplified voltage signal is input to the filter circuit to remove high-frequency interference, then the analog signal is converted into a digital signal through the signal acquisition board card, the digital signal is transmitted to a computer, and the digital signal is subjected to post-processing by a computer program.
2. A computer device, characterized in that the computer device comprises a memory and a processor, the memory storing a computer program which, when executed by the processor, causes the processor to carry out the steps of:
the method comprises the following steps that firstly, a sensing probe senses charge signals generated by particles with static electricity, and static electricity signals carried by the particles in the aircraft engine are collected;
and secondly, inducing charges on the induction probe by electrostatic induction, transmitting the charges to the signal processing circuit board through a signal wire, and collecting and processing charge signals by the following signal processing circuit board.
3. A computer-readable storage medium storing a computer program which, when executed by a processor, causes the processor to perform the steps of:
the method comprises the following steps that firstly, a sensing probe senses charge signals generated by particles with static electricity, and static electricity signals carried by the particles in the aircraft engine are collected;
and secondly, inducing charges on the induction probe by electrostatic induction, transmitting the charges to the signal processing circuit board through a signal wire, and collecting and processing charge signals by the following signal processing circuit board.
4. An aeroengine gas path particle weak electrostatic signal acquisition system for operating the aeroengine gas path particle weak electrostatic signal acquisition method of claim 1, wherein the aeroengine gas path particle weak electrostatic signal acquisition system comprises:
the electrostatic signal acquisition module is used for sensing a charge signal generated by the probe sensing the particles with static electricity and acquiring the electrostatic signal carried by the particles in the aircraft engine;
and the signal processing module is used for inducing charges on the induction probe by electrostatic induction and transmitting the charges to the signal processing circuit board through a signal wire, and charge signals are collected and processed by the signal processing circuit board behind the signal processing circuit board.
5. An aeroengine gas path particle weak electrostatic signal acquisition device carrying the aeroengine gas path particle weak electrostatic signal acquisition system of claim 4, wherein the aeroengine gas path particle weak electrostatic signal acquisition device comprises:
the electrostatic sensor is used for sensing a charge signal generated by sensing the electrostatic particles by the probe and acquiring the electrostatic signal carried by the particles in the aircraft engine;
and the signal processing circuit board is connected with the electrostatic sensor and used for inducing charges on the induction probe by electrostatic induction and transmitting the charges to the signal processing circuit board through a signal wire, and charge signals are collected and processed by the signal processing circuit board behind the signal processing circuit board.
6. The device for acquiring the weak electrostatic signals of the air passage particles of the aircraft engine as claimed in claim 5, wherein the electrostatic sensor comprises a probe, a first metal shell, a second metal shell, a ceramic lining, a first signal connecting line, a second signal connecting line and a signal line plug;
the inner side of the first metal shell is provided with internal threads, the outer side of the second metal shell is provided with external threads, and the first metal shell and the second metal shell are connected through threads; the size of the ceramic lining is just consistent with the size of the inner space of the metal shell, and the ceramic lining can be fixed in the metal shell; the circuit board is fixed at the step of the upper and lower ceramic lining layers; the sensor probe is fixed on the ceramic lining layer through threads, a second signal connecting wire is led out of the probe and is connected with the input end of the signal processing circuit board, and the first signal connecting wire is connected with the output end of the signal processing circuit board and the signal plug; then the signal is transmitted to the signal acquisition board card from the signal plug and then transmitted to a computer for processing.
7. The device for acquiring the weak electrostatic signal of the air path particles of the aircraft engine as claimed in claim 5, wherein the signal processing circuit board comprises: the charge amplifying circuit, the voltage amplifying circuit, the filter circuit and the power supply filter circuit;
the charge amplifying circuit converts charge signals collected by the sensor into voltage signals, and the specific conversion relation is UO-Q/C, determined by the feedback capacitance; the voltage amplifying circuit amplifies the voltage signal converted by the charge amplifying circuit so as to meet the voltage amplitude requirement of analog-to-digital conversion of a rear acquisition board card, and the bias voltage is zeroed in the amplifying process; the filter circuit is toFiltering the voltage signal to remove high-frequency interference; the power filter circuit filters out high-frequency interference that may be mixed from the power supply terminal.
8. The device for acquiring the weak electrostatic signals of the air circuit particles of the aircraft engine as claimed in claim 7, wherein the input end of the charge signal of the charge amplification circuit is connected with one end of a feedback resistor R2 and one end of a feedback capacitor C6, the other ends of the feedback resistor R2 and the feedback capacitor C6 are connected with the output end of an operational amplifier U1, one ends of a resistor R1 and a capacitor C5 are connected with a pin 3 of the operational amplifier, one section of the resistor R1 is grounded to realize the input impedance matching of the anode and cathode of the operational amplifier, the capacitors C7 and C8 are respectively connected with the cathode and the anode of a power supply, and pins 1, 4 and 8 of the operational amplifier are grounded;
the output end of the charge amplifying circuit is connected with one end of a resistor R3 by the voltage amplifying circuit, the resistor R3 isolates direct-current voltage, the other end of the resistor R3 is connected with a resistor R4 and then connected to a No. 3 pin of the operational amplifier, the resistor R4 protects the operational amplifier, a No. 2 pin is connected with a resistor R5 and then grounded, and R5 plays a role in balancing input resistance; the No. 1 pin of the operational amplifier is connected with a resistor R6 and a slide rheostat Radj2, the No. 8 pin is connected, different voltage amplification factors are obtained by adjusting the slide rheostat, the resistor R9, the resistor R8, the resistor R7 and the slide rheostat Radj1 are connected with the positive electrode and the negative electrode of a power supply, the direct-current voltage bias is adjusted, and high-frequency interference of an input power supply is filtered by capacitors C9 and C10.
9. The weak static signal collection device of aircraft engine gas circuit granule of claim 7, characterized by, the signal output of the voltage amplification circuit of the said low-pass filter circuit is through the resistance R10, through the resistance R11, the other end of the resistance R11 links with resistance R12 and electric capacity C12 separately, another end of the resistance R12 and No. 3 base pin of the operational amplifier link with electric capacity C11, another end of the electric capacity C11 is grounded, another end of the electric capacity C12 connects with No. 2 base pin and one end of the resistance R13;
the power supply anode of the power supply filter circuit is connected with one end of a diode D1, and the other end of the diode is connected with a capacitor C1 and a capacitor C3, so that the functions of energy storage and high-frequency interference filtering are achieved respectively; and one end of a diode D2 is connected to the negative electrode of the power supply, and the other end of a diode D2 is connected with a capacitor C2 and a capacitor C4, so that high-frequency interference can be stored and filtered respectively.
10. An aircraft engine, characterized in that the aircraft engine is provided with the device for acquiring the weak electrostatic signals of the air path particles of the aircraft engine as claimed in claim 5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110728223.XA CN113552424A (en) | 2021-06-29 | 2021-06-29 | Weak static signal collection system of aeroengine gas circuit granule |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110728223.XA CN113552424A (en) | 2021-06-29 | 2021-06-29 | Weak static signal collection system of aeroengine gas circuit granule |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113552424A true CN113552424A (en) | 2021-10-26 |
Family
ID=78102539
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110728223.XA Pending CN113552424A (en) | 2021-06-29 | 2021-06-29 | Weak static signal collection system of aeroengine gas circuit granule |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113552424A (en) |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU661349A1 (en) * | 1977-12-22 | 1979-05-05 | Предприятие П/Я В-2504 | Electrostatic probe |
| US4578756A (en) * | 1982-12-28 | 1986-03-25 | United Technologies Corporation | Adaptive electrostatic engine diagnostics |
| JPH044268U (en) * | 1990-04-27 | 1992-01-16 | ||
| CN103674788A (en) * | 2013-12-18 | 2014-03-26 | 南京金翅鸟航空科技有限公司 | On-line static monitoring system of aero-engine gas path and special sensors of system |
| CN103888084A (en) * | 2014-03-25 | 2014-06-25 | 中国科学院空间科学与应用研究中心 | Integrated pre-amplifier used for charged particle detector |
| CN106569045A (en) * | 2016-11-04 | 2017-04-19 | 中国航空工业集团公司北京长城航空测控技术研究所 | Scrap electrostatic monitoring sensor used for air passage |
| US9714967B1 (en) * | 2016-01-27 | 2017-07-25 | General Electric Company | Electrostatic dust and debris sensor for an engine |
| CN107145102A (en) * | 2017-05-12 | 2017-09-08 | 天津莱普航空科技有限公司 | A kind of avionic instrument repairs anti-static smart system |
| CN107158564A (en) * | 2017-05-04 | 2017-09-15 | 广州雪利昂生物科技有限公司 | A kind of external diaphragm pacemaker of the medium frequency electric stimulation of low frequency modulations |
| CN108828261A (en) * | 2018-07-04 | 2018-11-16 | 天津大学 | Conditioning circuit and signal restoring method for Dual-Phrase Distribution of Gas olid electrostatic correlation speed measurement |
| CN210005435U (en) * | 2019-02-19 | 2020-01-31 | 安徽巨迪安检科技有限公司 | Fluorescence signal detection circuit of explosive detector |
| CN110731764A (en) * | 2019-10-28 | 2020-01-31 | 重庆大学 | pulse detection system |
| CN213315702U (en) * | 2020-07-29 | 2021-06-01 | 江苏东成工具科技有限公司 | Spraying machine |
-
2021
- 2021-06-29 CN CN202110728223.XA patent/CN113552424A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU661349A1 (en) * | 1977-12-22 | 1979-05-05 | Предприятие П/Я В-2504 | Electrostatic probe |
| US4578756A (en) * | 1982-12-28 | 1986-03-25 | United Technologies Corporation | Adaptive electrostatic engine diagnostics |
| JPH044268U (en) * | 1990-04-27 | 1992-01-16 | ||
| CN103674788A (en) * | 2013-12-18 | 2014-03-26 | 南京金翅鸟航空科技有限公司 | On-line static monitoring system of aero-engine gas path and special sensors of system |
| CN103888084A (en) * | 2014-03-25 | 2014-06-25 | 中国科学院空间科学与应用研究中心 | Integrated pre-amplifier used for charged particle detector |
| US9714967B1 (en) * | 2016-01-27 | 2017-07-25 | General Electric Company | Electrostatic dust and debris sensor for an engine |
| CN106569045A (en) * | 2016-11-04 | 2017-04-19 | 中国航空工业集团公司北京长城航空测控技术研究所 | Scrap electrostatic monitoring sensor used for air passage |
| CN107158564A (en) * | 2017-05-04 | 2017-09-15 | 广州雪利昂生物科技有限公司 | A kind of external diaphragm pacemaker of the medium frequency electric stimulation of low frequency modulations |
| CN107145102A (en) * | 2017-05-12 | 2017-09-08 | 天津莱普航空科技有限公司 | A kind of avionic instrument repairs anti-static smart system |
| CN108828261A (en) * | 2018-07-04 | 2018-11-16 | 天津大学 | Conditioning circuit and signal restoring method for Dual-Phrase Distribution of Gas olid electrostatic correlation speed measurement |
| CN210005435U (en) * | 2019-02-19 | 2020-01-31 | 安徽巨迪安检科技有限公司 | Fluorescence signal detection circuit of explosive detector |
| CN110731764A (en) * | 2019-10-28 | 2020-01-31 | 重庆大学 | pulse detection system |
| CN213315702U (en) * | 2020-07-29 | 2021-06-01 | 江苏东成工具科技有限公司 | Spraying machine |
Non-Patent Citations (1)
| Title |
|---|
| 殷逸冰，左洪福，付宇，刘宸宁: "基于PXI 的航空发动机尾气静电监测系统", 科学技术与工程, vol. 14, no. 9, pages 269 - 287 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101384804A (en) | System for particulate matter sensor signal processing | |
| CN102869860B (en) | DPF failure detection method and DPF failure detection device | |
| CN1908608B (en) | DSP-based engine knock detection including knock sensor and circuit diagnostics | |
| CN106640722B (en) | A kind of device and method of pneumatic stability of gas compressor diagnosis and control | |
| CN102980771A (en) | Portable failure detection system and method for aero-engine gas path component | |
| CN103674788A (en) | On-line static monitoring system of aero-engine gas path and special sensors of system | |
| CN105334483B (en) | Superfrequency partial discharge transducer sensitivity verifying attachment built in a kind of combined electrical apparatus | |
| CN107110757A (en) | Smoke gas sensor | |
| CN205427057U (en) | A sensor for measuring electrified volume of dust | |
| CN101669019B (en) | Improvements in or relating to diagnostics of a capacitive sensor | |
| CN113552424A (en) | Weak static signal collection system of aeroengine gas circuit granule | |
| CN105182203A (en) | Device and method for detecting partial discharge of power capacitor | |
| CN209069414U (en) | A kind of real-time online vibration monitoring equipment of turbofan aircraft engine | |
| CN107389349A (en) | Aerial engine air passage fault monitoring system based on air passage electrostatic detection | |
| Barelli et al. | Cylinders diagnosis system of a 1 MW internal combustion engine through vibrational signal processing using DWT technique | |
| CN103217293B (en) | Based on the casing containment test data acquisition triggering system of vibration values | |
| CN106194547A (en) | Automobile ignition coil device for detecting performance and method thereof | |
| CN205139298U (en) | Power capacitor partial discharge detector device | |
| Wagner et al. | Engine knock detection: Products, tools, and emerging research | |
| CN208277864U (en) | Current sensor control device and electric automobile | |
| JPH048850A (en) | Knocking detecting means for internal combustion engine | |
| CN107247421B (en) | A kind of interface circuit of reliable temperature collection sensor signal | |
| CN216290857U (en) | Filtering and amplifying module for impulse response method winding deformation detection device | |
| CN110276857A (en) | A kind of processing method and circuit of aero-engine pressure sensor signal | |
| CN116818795B (en) | Pipeline photoelectric nondestructive testing system |
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 |