CN112394707A - Circuit for simulating dynamic model of position sensor LVDT of aero-engine fuel regulator - Google Patents
Circuit for simulating dynamic model of position sensor LVDT of aero-engine fuel regulator Download PDFInfo
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- CN112394707A CN112394707A CN202011192268.1A CN202011192268A CN112394707A CN 112394707 A CN112394707 A CN 112394707A CN 202011192268 A CN202011192268 A CN 202011192268A CN 112394707 A CN112394707 A CN 112394707A
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- 239000000446 fuel Substances 0.000 title claims abstract description 23
- 230000005284 excitation Effects 0.000 claims abstract description 15
- 230000003321 amplification Effects 0.000 claims abstract description 11
- 238000003199 nucleic acid amplification method Methods 0.000 claims abstract description 11
- 238000013461 design Methods 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 19
- 238000005516 engineering process Methods 0.000 abstract description 6
- 238000004088 simulation Methods 0.000 abstract description 6
- 230000003750 conditioning effect Effects 0.000 abstract description 5
- 238000001514 detection method Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000005094 computer simulation Methods 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0208—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the configuration of the monitoring system
- G05B23/0213—Modular or universal configuration of the monitoring system, e.g. monitoring system having modules that may be combined to build monitoring program; monitoring system that can be applied to legacy systems; adaptable monitoring system; using different communication protocols
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24065—Real time diagnostics
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- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Testing Of Engines (AREA)
Abstract
The invention may relate to the fields of aero-engine control systems, loop tests, circuits and the like, and particularly relates to a circuit for simulating an aero-engine fuel regulator position sensor LVDT dynamic model. The circuit comprises a sum value fixing circuit, an amplification adjusting circuit and a multiplier; the LVDT position signals are processed by a sum value fixing circuit to output a signal V1 and a signal V2, the signal V1 and the signal V2 are respectively corrected by an amplification adjusting circuit to output normalized VA and VB electric signal effective values in an analog mode, and the normalized VA and VB electric signals are multiplied by an excitation signal sent by a controller through a multiplier to obtain the VA and VB electric signals in phase with the excitation signal. The circuit for simulating the LVDT dynamic model of the position sensor of the aero-engine fuel regulator is provided, and the technical problem that a simulation test of a signal conditioning, acquiring and operating circuit of the position sensor LVDT in an aero-engine control system cannot be carried out in the prior art is solved. And further the comprehensiveness of the aircraft engine control system in the detection and test of the loop simulation test electronic controller technology is improved.
Description
Technical Field
The invention may relate to the fields of aero-engine control systems, loop tests, circuits and the like, and particularly relates to a circuit for simulating an aero-engine fuel regulator position sensor LVDT dynamic model.
Background
In the process of a loop test and a closed-loop control simulation test of the position of the fuel regulator in the existing engine control system, the position of the fuel regulator is calculated by a model machine, data are sent to an electronic controller in a communication mode, and the electronic controller directly transfers the position data to serve as position acquisition data. Compared with the actual working state of the engine control system, the system bypasses a conditioning acquisition operation circuit of the LVDT signals of the position sensor in the electronic controller. Therefore, the control system has the problem of incomplete detection and test coverage of the electronic controller technology in the loop simulation test.
Disclosure of Invention
The purpose of the invention is as follows: the circuit for simulating the LVDT dynamic model of the position sensor of the aero-engine fuel regulator is provided, and the technical problem that a simulation test of a signal conditioning, acquiring and operating circuit of the position sensor LVDT in an aero-engine control system cannot be carried out in the prior art is solved. And further the comprehensiveness of the aircraft engine control system in the detection and test of the loop simulation test electronic controller technology is improved.
The technical content of the invention is as follows: the circuit simulates a dynamic model of the position sensor LVDT of the fuel regulator of the aero-engine, and comprises a sum value fixing circuit, an amplification regulating circuit and a multiplier;
the LVDT position signals are processed by a sum value fixing circuit to output a signal V1 and a signal V2, the signal V1 and the signal V2 are respectively corrected by an amplification adjusting circuit to output normalized VA and VB electric signal effective values in an analog mode, and the normalized VA and VB electric signals are multiplied by an excitation signal sent by a controller through a multiplier to obtain the VA and VB electric signals in phase with the excitation signal.
Preferably, the amplification and adjustment circuit is of a symmetrical design.
Preferably, the amplification adjustment circuit further includes a bias adjustment circuit.
Preferably, the LVDT position signal is output through a fuel regulator valve model machine.
The invention has the technical effects that: the position sensor LVDT of the aircraft engine fuel regulator can be dynamically simulated, and VA and VB coil electric signals can be dynamically simulated and output. The method is applied to the loop test process of the engine control system. The problem that an existing conditioning acquisition operation circuit bypassing signals of a position sensor LVDT in an electronic controller is solved. Therefore, the detection and test coverage of the electronic controller technology in the loop test process is more comprehensive.
The invention utilizes the characteristic of secondary coil sum value fixation of the linear position sensor, adopts the sum value fixing circuit, ensures that Va and Vb are simultaneously output through the sum value fixing circuit after inputting the position voltage signal, and is a continuous analog signal source instead of a mode of D/A respective conversion.
The Va and Vb adjusting and converting circuit adopts a symmetrical design, and the synchronism and consistency of the change of the output signal source are better ensured.
Two aspects of innovation are added in the proportion amplifying circuit for adjusting the transformation link of the V1V 2. Firstly, the offset circuit has been increased, has solved the V1V2 signal source through the offset circuit and in the link process through proportional amplification circuit, synchronous amplifier circuit, leads to VA VB output zero offset problem because of the precision difference of components and parts itself, has guaranteed the zero offset problem that VA VB converting circuit leads to because of welding dress technology, components and parts precision difference. And the second is that the excitation signal output by the controller is multiplied by the homodromous multiplier, so that the excitation signal sent by the controller is correlated. The same phase of the VA VB signal and the excitation signal is better ensured, and high-precision analog output is realized.
Drawings
FIG. 1 is a control schematic of a position sensor in an aircraft engine control system;
FIG. 2 is a schematic block diagram of the circuit of the present invention;
FIG. 3 is a circuit layout diagram of the present invention.
Detailed Description
As shown in fig. 1, in an aircraft engine control system, a fuel regulator position sensor LVDT receives an excitation signal, such as 3V, 3KHz, from an electronic controller of the engine control system, and after the electronic controller controls a fuel valve of the fuel regulator to move, the fuel valve drives the position sensor LVDT to move, and the position sensor dynamically outputs VA and VB electric signals, such as 0-2V, 3KHz, which follow the position change.
The circuit of the dynamic model of the position sensor LVDT of the present invention is shown in fig. 2. In operation, an excitation signal, e.g., 3V, 3KHz, is received from an electronic controller of the engine control system, and an electrical position signal is received from an oil regulator model machine, e.g.: 0 ~ 5V, VA, VB electric signal that the position change is followed in the dynamic output of analog position sensor, example: 0 to 2V 3 KHz.
The circuit working process of the invention for simulating the LVDT dynamic model of the position sensor of the aero-engine fuel regulator is as follows:
the chip special for the original electronic controller provides an excitation signal for the sensor excitation coil, for example: 3V 3KHz, simulating and outputting position voltage signals by a valve model of the fuel regulator, outputting V1 and V2 signals for regulation by using the characteristic of fixed sum value of a secondary coil of the LVDT sensor through sum value fixing operation, correcting according to VA and VB electric signal curves of an actual sensor, simulating and outputting normalized VA and VB electric signal effective values, and multiplying an excitation signal by a multiplier to obtain VA and VB electric signals in phase with the excitation signal. Therefore, the generation of electrical signals of the secondary coils VA and VB of the position sensor LVDT is realized. After the valve model machine of the fuel regulator simulates and changes the output position electric signals, the VA and VB electric signals output in a simulating way are changed, and the VA and VB electric signals output dynamically along with the position change are realized.
The invention is applied to products, is applied to loop tests of certain type of aeroengine control systems, and solves the problem that the conventional conditioning acquisition operation circuit bypassing the LVDT signals in an electronic controller. Therefore, the detection and test coverage of the electronic controller technology in the loop test process is more comprehensive.
When a certain type of aero-engine control system is subjected to a loop test, the comparison condition of the dynamic simulation output and the real sensor standard value is shown in the following table 1. Through comparison of standard value data, the electrical signal linearity of the VA coil and the VB coil is basically consistent, and the steady-state error value is less than 0.03V.
TABLE 1 comparison of the dynamic analog output of the present invention with the true sensor standard
| Position signal | Va standard value | Vb standard value | Va measured value | Measured value of |
| 7 | 2.006 | 1.269 | 2 | 1.278 |
| 6 | 1.957 | 1.32 | 1.934 | 1.338 |
| 4 | 1.853 | 1.426 | 1.852 | 1.431 |
| 2 | 1.746 | 1.534 | 1.768 | 1.534 |
| 0 | 1.64 | 1.64 | 1.637 | 1.637 |
| -2 | 1.532 | 1.745 | 1.545 | 1.730 |
| -4 | 1.422 | 1.85 | 1.414 | 1.835 |
| -6 | 1.315 | 1.951 | 1.321 | 1.938 |
| -7 | 1.264 | 1.997 | 1.270 | 1.977 |
Claims (4)
1. The circuit for simulating the dynamic model of the position sensor LVDT of the fuel regulator of the aircraft engine is characterized by comprising a sum fixed circuit, an amplification adjusting circuit and a multiplier;
the LVDT position signals are processed by a sum value fixing circuit to output a signal V1 and a signal V2, the signal V1 and the signal V2 are respectively corrected by an amplification adjusting circuit to output normalized VA and VB electric signal effective values in an analog mode, and the normalized VA and VB electric signals are multiplied by an excitation signal sent by a controller through a multiplier to obtain the VA and VB electric signals in phase with the excitation signal.
2. The circuit for modeling an LVDT for an aircraft engine fuel regulator position sensor according to claim 1, wherein the amplification adjustment circuit is of symmetrical design.
3. The circuit for modeling an LVDT for an aircraft engine fuel regulator according to claim 1, wherein the amplification adjustment circuit further includes a bias adjustment circuit.
4. The circuit for simulating an LVDT of an aircraft engine fuel regulator position sensor according to claim 1, wherein the LVDT position signal is output by a fuel regulator valve model machine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011192268.1A CN112394707A (en) | 2020-10-30 | 2020-10-30 | Circuit for simulating dynamic model of position sensor LVDT of aero-engine fuel regulator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011192268.1A CN112394707A (en) | 2020-10-30 | 2020-10-30 | Circuit for simulating dynamic model of position sensor LVDT of aero-engine fuel regulator |
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| CN112394707A true CN112394707A (en) | 2021-02-23 |
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| CN202011192268.1A Pending CN112394707A (en) | 2020-10-30 | 2020-10-30 | Circuit for simulating dynamic model of position sensor LVDT of aero-engine fuel regulator |
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101769709A (en) * | 2009-12-30 | 2010-07-07 | 国电南京自动化股份有限公司 | Analog circuit and method for detecting wire breaking of displacement sensor LVDT |
| CN101788627A (en) * | 2009-12-30 | 2010-07-28 | 国电南京自动化股份有限公司 | Digital circuit for detecting disconnection of displacement sensor LVDT and detection method thereof |
| CN102590692A (en) * | 2012-02-13 | 2012-07-18 | 浙江中控技术股份有限公司 | Wire breakage detecting device of displacement sensor |
| CN203705942U (en) * | 2013-12-11 | 2014-07-09 | 中国航空工业第六一八研究所 | Simulation circuit with electrical characteristics of LVDT/RVDT sensors |
| CN105527906A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Displacement sensor receiving channel monitoring circuit |
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| CN106813564A (en) * | 2015-11-30 | 2017-06-09 | 杭州奥莫自动化科技有限公司 | A kind of LVDT displacement transducers digitalized processing method and device |
| JP2017133989A (en) * | 2016-01-29 | 2017-08-03 | 株式会社東京精密 | LVDT sensor |
| CN108111168A (en) * | 2017-11-23 | 2018-06-01 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of modified engine fuel flow sensor signal Acquisition Circuit |
| CN108170128A (en) * | 2017-12-28 | 2018-06-15 | 西安庆安航空试验设备有限责任公司 | Simulator, analogy method and the simulated assembly of LVDT input-output characteristics |
| CN111273191A (en) * | 2020-03-03 | 2020-06-12 | 中国船舶重工集团公司第七0七研究所九江分部 | RVDT/LVDT signal processing circuit and detection method |
-
2020
- 2020-10-30 CN CN202011192268.1A patent/CN112394707A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101769709A (en) * | 2009-12-30 | 2010-07-07 | 国电南京自动化股份有限公司 | Analog circuit and method for detecting wire breaking of displacement sensor LVDT |
| CN101788627A (en) * | 2009-12-30 | 2010-07-28 | 国电南京自动化股份有限公司 | Digital circuit for detecting disconnection of displacement sensor LVDT and detection method thereof |
| CN102590692A (en) * | 2012-02-13 | 2012-07-18 | 浙江中控技术股份有限公司 | Wire breakage detecting device of displacement sensor |
| CN203705942U (en) * | 2013-12-11 | 2014-07-09 | 中国航空工业第六一八研究所 | Simulation circuit with electrical characteristics of LVDT/RVDT sensors |
| CN105527906A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Displacement sensor receiving channel monitoring circuit |
| CN106813564A (en) * | 2015-11-30 | 2017-06-09 | 杭州奥莫自动化科技有限公司 | A kind of LVDT displacement transducers digitalized processing method and device |
| JP2017133989A (en) * | 2016-01-29 | 2017-08-03 | 株式会社東京精密 | LVDT sensor |
| CN205748924U (en) * | 2016-06-30 | 2016-11-30 | 中航商用航空发动机有限责任公司 | Aero-engine LVDT signal hardware is at loop test device |
| CN108111168A (en) * | 2017-11-23 | 2018-06-01 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of modified engine fuel flow sensor signal Acquisition Circuit |
| CN108170128A (en) * | 2017-12-28 | 2018-06-15 | 西安庆安航空试验设备有限责任公司 | Simulator, analogy method and the simulated assembly of LVDT input-output characteristics |
| CN111273191A (en) * | 2020-03-03 | 2020-06-12 | 中国船舶重工集团公司第七0七研究所九江分部 | RVDT/LVDT signal processing circuit and detection method |
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