CN104075841B - aircraft engine pressure sensor detection circuit - Google Patents
aircraft engine pressure sensor detection circuit Download PDFInfo
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- CN104075841B CN104075841B CN201410265263.5A CN201410265263A CN104075841B CN 104075841 B CN104075841 B CN 104075841B CN 201410265263 A CN201410265263 A CN 201410265263A CN 104075841 B CN104075841 B CN 104075841B
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Abstract
A kind of aircraft engine pressure sensor detection circuit that the present invention proposes, pressure transmitter connects AD conversion unit by sensor loop detecting unit and input instrument amplifier electric respectively; The voltage input instrument amplifier U2 of pressure transmitter Wheatstone bridge four detection resistance, the magnitude of voltage collected is transferred to AD conversion unit by instrument amplifier U2, check point pressure drop on loop detection unit inspection Wheatstone bridge four detection resistance, operational amplifier amplifier on loop detection circuit delivers to AD conversion unit after processing, engine electronic control system device CPU, according to the output voltage values of a wherein road loop detection circuit, judges pressure transmitter electric bridge check point fault according to voltage after AD conversion unit AD conversion. It is reliable and stable that the present invention has voltage, and output voltage ripple is very little, and test precision height, can not affect the millivolt level voltage difference of P3 Output pressure. It is no more than 0.05bar through actual test worst error.
Description
Technical field
This technology is applicable to adopt the pressure sensor detection circuit of Huygens's balanced bridge of strain resistor composition, the especially detection circuit of aircraft engine pressure transmitter.
Background technology
Along with the development of unicircuit and semiconductor technology, the semi-conductor force-sensing sensor made by principle of the pressure inhibition effect of semiconductor material occurs, and silicon piezoresistance type pressure sensor wherein is because having, and the advantage such as volume is little, performance height, cheapness is widely applied. But utilize electric bridge resistance that diffusion technique is formed easily with temperature change, and the piezoresistance coefficient of pressure drag component has bigger negative temperature coefficient, these easily cause the discrete of resistance value and temperature coefficient of resistance, cause thermal sensitivity drift and the zero wander of pressure transmitter. Source of error due to semiconductor material temperature is very responsive, four of piezoresistive pressure sensor detection resistance connect as Wheatstone bridge form more, and it has constant current and constant voltage two kinds of mode of operation.
Pressure transmitter is a kind of conventional detection device, has certain application in multiple industry. When using pressure transmitter, user determines how detecting pressure sensor seems very important. What aircraft engine P3 pressure transmitter mainly adopted is Huygens's balanced bridge of strain resistor composition, electric bridge supply voltage 9.5V��10.5V, excitation limit impedance is 0.9��10K ��, the impedance of signal limit is 0.8��4K ��, pressure range 0��1300KPa absolute pressure, the absolute pressure that corresponding output voltage is 0��26mV, output voltage and applying is linear. Thus require to provide to engine electronic control system device P3 pressure sensor detection circuit and reliablely and stablely encourage power supply, have energized circuit detection circuit, P3 input signal is carried out high-precision low-drift amplification.
The detection method that pressure transmitter is conventional has 3 kinds:
1, pressurization detection, with the pressure source of standard, to cell pressure, according to the size of pressure and the variable quantity of output signal, calibrates sensor. And when condition is permitted, carry out the temperature detection of correlation parameter.
2, the detection of zero point, with the voltage gear of volt ohm-milliammeter, detection is not being executed under stressed condition, the offset output of sensor.This exports the voltage being generally mV level, if beyond the technical indicator of sensor, the zero deviation over range of sensor is just described.
3, the detection on bridge road, whether the circuit of main detecting sensor is correct, is generally Hui Sitong full-bridge circuit, utilizes the ohms range of volt ohm-milliammeter, measuring the impedance between input terminus and the impedance between output terminal, these two impedances are exactly the input, output-resistor of pressure transmitter. If impedance is infinitely great, bridge road disconnects, and illustrates that sensor has the definition of problem or pin not judge correctly. Although above-mentioned inspection method is simple and convenient, but the inspection for aircraft engine pressure transmitter is not suitable for, and it is not high to test precision. What be input to engine controller due to P3 sensor is the voltage difference of millivolt level, and this voltage difference needs the instrument amplifier pole high-amplification-factor through high-precision low-drift could obtain P3 force value.
The external P3 pressure transmitter of aeroengine electronic controller is Huygens's balanced bridge of strain resistor composition. Pressure transmitter normal operation electric current generally at 5��10mA, if there is pressure sensor inside short circuit or easily the pressure transmitter feed circuit of engine electronic control system device being damaged during the fault such as sensor line is damaged. In order to not affect balanced bridge normal operation, the loop detection general resistance of resistance is less. In order to avoid aircraft engine pressure transmitter Huygens's balanced bridge excitation input power to introduce undesired signal; usually requiring that pressure transmitter excitation power supply output must have current limliting protection function and outward current controls at about 10mA, power requirement voltage precision height, ripple are little.
Summary of the invention
It is reliable that the task of the present invention is to provide a kind of working stability, test precision height, having excitation output short-circuit can not cause engine electronic control system device to damage, engine pressure value can be obtained, especially can judge the detection circuit of the aircraft engine P3 pressure transmitter whether pressure transmitter is working properly.
The above-mentioned purpose of the present invention can be reached by following measure, a kind of aircraft engine pressure sensor detection circuit, comprise excitation power supply, loop detection unit and input instrument amplifier, it is characterized in that: excitation power supply is by the integral capacity C3 that is connected electrically between the reverse input terminus of comparison amplifier U1A and output terminal and output terminal current limliting resistance R11 triode Q4, triode Q3 in parallel, by Q3 base stage voltage pull-down after Q4 conducting, cut-off Q3, composition votage reference excitation exports cut-off current-limiting protection circuit; The excitation power supply electrical connection external pressure transmitter of engine electronic control system device, pressure transmitter connects AD conversion unit by sensor loop detecting unit and input instrument amplifier electric respectively; The voltage input instrument amplifier U2 of pressure transmitter Wheatstone bridge four detection resistance, the magnitude of voltage collected is transferred to AD conversion unit, check point pressure drop on loop detection unit inspection Wheatstone bridge four detection resistance, operational amplifier amplifier on loop detection circuit delivers to AD conversion unit after processing, engine electronic control system device CPU, according to the output voltage values of a wherein road loop detection circuit, judges pressure transmitter electric bridge check point fault according to voltage after AD conversion unit AD conversion.
The present invention has following useful effect compared to prior art.
Excitation power supply is stable, reliable, ripple is little. The present invention adopts excitation power supply by the integral capacity C3 that is connected electrically between the reverse input terminus of comparison amplifier U1A and output terminal and output terminal current limliting resistance R11 triode Q4, triode Q3 in parallel; by Q3 base stage voltage pull-down after Q4 conducting; cut-off Q3; composition votage reference excitation exports cut-off current-limiting protection circuit; output voltage is reliable and stable; ripple is very little, can not affect the millivolt level voltage difference of P3 Output pressure, and protection pressure transmitter excitation power source circuit can not damage by overcurrent.Export for aircraft engine P3 pressure transmitter detection technique provides reliable and stable excitation power supply. The strength of current that P3 encourages power supply to export is moderate, even if P3 encourages output short-circuit that engine electronic control system device also can not be caused to damage.
The present invention is input to the characteristic of 0��26mV voltage difference of engine controller according to aircraft engine P3 pressure transmitter, adopt high-precision low-drift, the input signal magnifier that can amplify about 100 times obtains P3 force value, solving P3 sensor electrical pressure reduction faint, force value obtains the problem of difficulty.
The present invention's protection and detection function are perfect, prove that this circuit working is reliable and stable through test of long duration, test precision height, test worst error through reality and are no more than 0.05bar, and common errors is at about 0.01bar.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the present invention is further described.
Fig. 1 is aircraft engine pressure sensor detection circuit block diagram of the present invention.
Fig. 2 is the circuit principle schematic of Fig. 1 pressure transmitter excitation power supply.
The circuit principle schematic of Fig. 3 Fig. 1.
Embodiment
Consult Fig. 1, Fig. 2. Huygens's balanced bridge that aircraft engine pressure transmitter is made up of strain resistor, its detection circuit mainly comprises pressure transmitter excitation power supply, pressure transmitter loop detection unit and pressure transmitter input instrument amplifier. Excitation power supply is by the integral capacity C3 that is connected electrically between the reverse input terminus of comparison amplifier U1A and output terminal and output terminal current limliting resistance R11 triode Q4, triode Q3 in parallel, by Q3 base stage voltage pull-down after Q4 conducting, cut-off Q3, composition votage reference excitation exports cut-off current-limiting protection circuit; Excitation power supply electrical connection pressure transmitter, pressure transmitter connects AD conversion unit by sensor loop detecting unit and input instrument amplifier electric respectively; The voltage input instrument amplifier U2 of pressure transmitter Wheatstone bridge four detection resistance, the magnitude of voltage collected is transferred to AD conversion unit by instrument amplifier U2, check point pressure drop on loop detection unit inspection Wheatstone bridge four detection resistance, operational amplifier amplifier on loop detection circuit delivers to AD conversion unit after processing, engine electronic control system device CPU, according to the output voltage values of a wherein road loop detection circuit, judges pressure transmitter electric bridge check point fault according to voltage after AD conversion unit AD conversion.
Pressure transmitter excitation power supply comprises: the loop in parallel that point compressive resistance R5 and R7 current limliting resistance R6, filter capacitor C1 in parallel and stake resistance R7 shunt capacitance C2 form, the integral capacity C3 being parallel between the reverse input terminus of comparison amplifier U1A and output terminal and output terminal current limliting resistance R11, through the resistance resistance R12 of triode Q4 integral capacity C3 in parallel, and through triode Q4, the triode Q3 of resistance R11 parallel connection and peripheral resistance R8, resistance R9, resistance R10 and diode D1, resistance R3, resistance R14 and diode D2. The 10V votage reference that engine electronic control system device provides is through current limliting resistance R6 current limliting and filter capacitor C1 filtering input U1A comparison amplifier positive input, output voltage is gathered to U1A comparer negative terminal by resistance R12, comparer exports and controls Q3 conducting after R11 current limliting, after Q3 conducting, the electric current of+15V is through current limliting resistance R10 and Q3, from Q3 emtting electrode outward current to current sampling resistor R13, exporting 10V voltage to external pressure sensor from R13, this output is exactly pressure transmitter excitation power positive end. It is the reverse feedback device suppressing ripple that U1A compares the integral capacity C3 amplified in circuit, it is possible to make output voltage ripple less.
Secondly, the 10V votage reference that engine electronic control system device provides is equally through resistance R5 and R7 dividing potential drop, this partial pressure value arrives triode Q4 after electric capacity C2 filtering, owing to partial pressure value size makes Q4 be in off condition, this partial pressure value increases again a bit just can allow Q4 be in conducting, on the resistance R13 that samples voltage after resistance R8 and R9 just can with this partial pressure value superposition and make Q4 conducting. Pressure transmitter normal operation electric current is generally at 5��10mA. When external pressure sensor outward current is excessive, on resistance R13, voltage increases, and this voltage superposes with R5 and R7 partial pressure value just can by Q4 conducting; by Q3 base stage voltage pull-down after Q4 conducting; Q3 ends, and pressure transmitter exports and turns off, and protection pressure transmitter excitation power source circuit can not damage by overcurrent. Owing to Q3, Q4 are operated in linear state, pressure transmitter excitation electric power output voltage temperature is reliable, ripple is little, and pressure transmitter short circuit can not cause circuit to damage.
Consult Fig. 3. In aircraft engine pressure sensor detection circuit, energizing voltage is just just being held from the input of electric bridge power supply and is being entered, and outputs to through electric bridge power supply negative terminal and returns to energizing voltage negative terminal after energized circuit detection resistance. Pressure transmitter 10V energizing voltage is after R1, R3 or R2, R4 two branch roads of Huygens's balanced bridge, R1, R3 Kelvin double bridge contact pressure input that sensor loop detecting unit detects resistance input terminus electric bridge from Wheatstone bridge four is just being held extraction circuit, electrical connection is connected across penetrates between operational amplifier U3A positive input and output terminal resistance R20, by shunting resistance R18 series capacity C7, through the loop in parallel that resistance R19 forms, by resistance R20 series resistance R21, shunting resistance R22 forms a loop detection circuit 1. Diagonal angle electric bridge R3, R4 both arms contact that sensor loop detecting unit detects resistance input terminus electric bridge from Wheatstone bridge four is drawn circuit, connect an energized circuit being made up of resistance R30 shunting resistance R31 and electric capacity C10, by resistance R30, with electric capacity C10's and interface is electrically connected operational amplifier U4B positive input to described energized circuit, forms a loop detection circuit 2 of voltage detecting point; And draw circuit from R2, R4 Kelvin double bridge contact, electrical connection is connected across penetrates with between amplifier U3B positive input and output terminal resistance R25, by shunting resistance R24 series capacity C8, through the loop in parallel that resistance R23 forms, another loop detection circuit 3 formed by resistance R25 series resistance R27. Instrument amplifier U2 phase running fire, with amplifier U3B positive input, is electrically connected operational amplifier U4A positive input by resistance R29 shunt capacitance C9 and forms pressure transmitter collection voltage output circuit; Above-mentioned loop detection circuit output voltage is after a/d converter converts, and engine electronic control system device CPU is according to the output voltage values of a wherein road loop detection circuit judging pressure transmitter electric bridge check point fault.
Pressure transmitter output voltage is within the scope of 0��26mV, and linear corresponding pressure is 0��1300kpa, and the instrument amplifier that this voltage has to pass through high input impedance, high-amplification-factor, high precision, low temperature waft amplifies about 100 times. Instrument amplifier U2 circuit can adopt the difference voltage amplification 100 times that electric bridge both arms input by AD621 instrument amplifier, resistance R28 is the device regulating magnification, instrument amplifier U2 output voltage carries out penetrating with amplification to U4A after resistance R29 and electric capacity C9 current limliting filtering, like this through U4A process after pressure signal more reliable and more stable, U4A output voltage delivers to AD conversion cell processing.CPU just can go out engine force value according to linear sensor property calculation according to voltage after AD conversion.
Resistance R3, R4 bridge electric contact and resistance R30, R31 contact place voltage are the check point of energized circuit voltage, resistance R1, R3 and resistance R2, R4 bridge electrical nodes place voltage are the check point of electric bridge both arms voltage, also it is just end and the negative terminal of external pressure sensor input signal simultaneously, just has 3 voltage detecting points so in the loop.
The amplification circuit being made up of operational amplifier U3A and U3B is respectively the voltage detecting point circuit of electric bridge two-arm, and the amplifier detection energized circuit that U4B is formed also is voltage detecting point circuit. Pressure sensor signal is just being held after resistance R18 and ground capacitance C7 current limliting impedance matching, it is input to operational amplifier U3A just holding and just hold with instrument amplifier U2, electric capacity C7 is filtered into and just holds input filter, U3A is for penetrating with amplifier, resistance R17 is feedback resistance, it is intended that allows U3A export and stablizes as early as possible. Resistance R20, R21 of the series connection of U3A output terminal are output current limiting resistance, and stake resistance R22 is output load resistance. Same pressure sensor signal negative terminal is after the resistance R24 current limliting impedance matching that resistance R2, R4 bridge electrical nodes is connected, it is input to operational amplifier U3B just holding and U2 instrument amplifier negative terminal, electric capacity C8 is filtered into negative terminal input filter, U3B is for penetrating with amplifier, resistance R23 is feedback resistance, object allows U3B export stablize as early as possible, and resistance R25, R27 that U3B output terminal is connected are output current limiting resistance, and stake resistance R26 is output load resistance. Energized circuit detection voltage is to the just end of U4B after resistance R30 and electric capacity C10 current limliting filtering, and U4B is for penetrating with amplifier, and its output voltage values is generally at about 0.5V.
General output ring alignment detection circuit 1, loop detection circuit 2 output voltage are at about 4.5V, loop detection circuit 3 output voltage is about 0.5V voltage, these 3 voltages are after a/d converter converts, engine electronic control system device CPU just can judge electric bridge whether short circuit, disconnected arm, the resistance not fault such as coupling according to magnitude of voltage, wherein loop detection 1, loop detection 2 export and are not necessary to possess, because can judge whether both arms disconnect or short circuit equally according to loop detection circuit 3 output voltage values, so loop detection circuit 3 must possess.
Claims (10)
1. the detection circuit of an aircraft engine pressure transmitter, comprise excitation power supply, loop detection unit and input instrument amplifier, it is characterized in that: excitation power supply is by the integral capacity C3 that is connected electrically between the reverse input terminus of comparison amplifier U1A and output terminal and output terminal current limliting resistance R11 triode Q4, triode Q3 in parallel, by Q3 base stage voltage pull-down after Q4 conducting, cut-off Q3, composition votage reference excitation exports cut-off current-limiting protection circuit; The excitation power supply electrical connection external pressure transmitter of engine electronic control system device, pressure transmitter connects AD conversion unit by sensor loop detecting unit and input instrument amplifier electric respectively; The voltage input instrument amplifier U2 of pressure transmitter Wheatstone bridge four detection resistance, the magnitude of voltage collected is transferred to AD conversion unit, check point pressure drop on loop detection unit inspection Wheatstone bridge four detection resistance, operational amplifier amplifier on loop detection circuit delivers to AD conversion unit after processing, engine electronic control system device CPU, according to the output voltage values of a wherein road loop detection circuit, judges pressure transmitter electric bridge check point fault according to voltage after AD conversion unit AD conversion.
2. the detection circuit of aircraft engine pressure transmitter as claimed in claim 1, it is characterised in that: pressure transmitter excitation power supply comprises: the loop in parallel that point compressive resistance R5 and R7 current limliting resistance R6, filter capacitor C1 in parallel and stake resistance R7 shunt capacitance C2 form.
3. the detection circuit of aircraft engine pressure transmitter as claimed in claim 1, it is characterized in that: the 10V votage reference that engine electronic control system device provides is through current limliting resistance R6 current limliting and filter capacitor C1 filtering input U1A comparison amplifier positive input, output voltage is gathered to U1A comparer negative terminal by resistance R12, comparer exports and controls Q3 conducting after R11 current limliting, after Q3 conducting, the electric current of+15V is through current limliting resistance R10 and Q3, from Q3 emtting electrode outward current to current sampling resistor R13, 10V voltage is exported to external pressure sensor from R13, this output is exactly pressure transmitter excitation power positive end.
4. the detection circuit of aircraft engine pressure transmitter as claimed in claim 1, it is characterised in that: it is the reverse feedback device suppressing ripple that U1A compares the integral capacity C3 amplified in circuit.
5. the detection circuit of aircraft engine pressure transmitter as claimed in claim 1, it is characterized in that: the 10V votage reference that engine electronic control system device provides is equally through resistance R5 and R7 dividing potential drop, this partial pressure value arrives triode Q4 after electric capacity C2 filtering, partial pressure value size makes Q4 be in off condition, the upper voltage of sampling resistance R13 after resistance R8 and R9 with this partial pressure value superposition conducting Q4.
6. the detection circuit of aircraft engine pressure transmitter as claimed in claim 5, it is characterised in that: by Q3 base stage voltage pull-down after Q4 conducting, Q3 ends, and pressure transmitter exports and turns off, and protection pressure transmitter excitation power source circuit can not damage by overcurrent.
7. the detection circuit of aircraft engine pressure transmitter as claimed in claim 1, it is characterized in that: pressure transmitter 10V energizing voltage is through the R1 of Wheatstone bridge, R3 or R2, after R4 two branch roads, sensor loop detecting unit detects the R1 of resistance input terminus electric bridge from Wheatstone bridge four, the input of R3 Kelvin double bridge contact pressure is just being held and is being drawn on circuit, electrical connection is connected across between operational amplifier U3A positive input and output terminal resistance R20, by shunting resistance R18 series capacity C7, through the loop in parallel that resistance R19 forms, by resistance R20 series resistance R21, shunting resistance R22 forms a loop detection circuit 1.
8. the detection circuit of aircraft engine pressure transmitter as claimed in claim 1, it is characterized in that: diagonal angle electric bridge R3, R4 both arms contact that sensor loop detecting unit detects resistance input terminus electric bridge from Wheatstone bridge four is drawn circuit, connects an energized circuit being made up of resistance R30 shunting resistance R31 and electric capacity C10.
9. the detection circuit of aircraft engine pressure transmitter as claimed in claim 8, it is characterized in that: by resistance R30, with electric capacity C10's and interface is electrically connected operational amplifier U4B positive input to described energized circuit, forms a loop detection circuit 2 of voltage detecting point; And draw circuit from R2, R4 Kelvin double bridge contact, electrical connection is just being connected across operational amplifier U3B
To between input terminus and output terminal resistance R25, by shunting resistance R24 series capacity C8, through the loop in parallel that resistance R23 forms, form another loop detection circuit 3 by resistance R25 series resistance R27.
10. the detection circuit of aircraft engine pressure transmitter as claimed in claim 1, it is characterized in that: instrument amplifier U2 connects operational amplifier U3B positive input, it is electrically connected operational amplifier U4A positive input by resistance R29 shunt capacitance C9 and forms pressure transmitter collection voltage output circuit; Above-mentioned loop detection circuit output voltage is after a/d converter converts, and engine electronic control system device CPU is according to the output voltage values of a wherein road loop detection circuit judging pressure transmitter electric bridge check point fault.
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| CN201410265263.5A CN104075841B (en) | 2014-06-13 | 2014-06-13 | aircraft engine pressure sensor detection circuit |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105634496B (en) * | 2015-12-25 | 2018-11-20 | 北京航天微电科技有限公司 | The production method of pumping signal in a kind of senile experiment |
| CN106405214B (en) * | 2016-08-18 | 2019-04-05 | 中国航空工业集团公司上海航空测控技术研究所 | A kind of piezoelectric transducer detection device |
| CN108956005B (en) * | 2018-08-08 | 2024-03-22 | 陈德连 | Pressure sensor |
| CN109412542B (en) * | 2018-12-10 | 2022-11-04 | 中国航发南方工业有限公司 | Pressure signal conditioning circuit and electronic controller |
| US11877864B2 (en) | 2019-05-29 | 2024-01-23 | Measurement Specialties, Inc. | Voltage nulling pressure sensor preamp |
| CN112254875B (en) * | 2020-10-26 | 2022-03-08 | 南通大学 | Circuit and method for judging connection state of bridge sensor |
| CN112798180A (en) * | 2021-01-04 | 2021-05-14 | 珠海格力电器股份有限公司 | Fault detection method of force sensor and computer-readable storage medium |
| CN113865757B (en) * | 2021-09-16 | 2024-07-09 | 歌尔微电子股份有限公司 | Detection circuit, detection method and electronic equipment of piezoresistive pressure sensor |
| CN114812915B (en) * | 2022-06-24 | 2022-10-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Pressure scanning valve circuit |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4003248A (en) * | 1974-02-20 | 1977-01-18 | Regie Nationale Des Usines Renault | Faulty combustion device for controlled ignition internal combustion engine |
| CN201522356U (en) * | 2009-09-30 | 2010-07-07 | 贵州黎阳航空发动机公司 | Aircraft engine alternating current supply pressure sensor calibrating device |
| CN201754115U (en) * | 2010-07-28 | 2011-03-02 | 四川蜀谷仪表科技有限公司 | Digital pressure meter |
| CN102901549A (en) * | 2012-09-18 | 2013-01-30 | 北京航空航天大学 | Driving, signal conditioning and acquisition device for strain resistance type pressure sensor |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6518880B2 (en) * | 2000-06-28 | 2003-02-11 | Denso Corporation | Physical-quantity detection sensor |
-
2014
- 2014-06-13 CN CN201410265263.5A patent/CN104075841B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4003248A (en) * | 1974-02-20 | 1977-01-18 | Regie Nationale Des Usines Renault | Faulty combustion device for controlled ignition internal combustion engine |
| CN201522356U (en) * | 2009-09-30 | 2010-07-07 | 贵州黎阳航空发动机公司 | Aircraft engine alternating current supply pressure sensor calibrating device |
| CN201754115U (en) * | 2010-07-28 | 2011-03-02 | 四川蜀谷仪表科技有限公司 | Digital pressure meter |
| CN102901549A (en) * | 2012-09-18 | 2013-01-30 | 北京航空航天大学 | Driving, signal conditioning and acquisition device for strain resistance type pressure sensor |
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