CN113390643B - Method and device for measuring rotating speed of aircraft engine - Google Patents
Method and device for measuring rotating speed of aircraft engine Download PDFInfo
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- CN113390643B CN113390643B CN202110761513.4A CN202110761513A CN113390643B CN 113390643 B CN113390643 B CN 113390643B CN 202110761513 A CN202110761513 A CN 202110761513A CN 113390643 B CN113390643 B CN 113390643B
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- rotating speed
- aircraft engine
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P21/00—Testing or calibrating of apparatus or devices covered by the preceding groups
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
- G01P3/42—Devices characterised by the use of electric or magnetic means
- G01P3/44—Devices characterised by the use of electric or magnetic means for measuring angular speed
Abstract
The invention discloses a method for measuring the rotating speed of an aircraft engine, wherein a magnetic component is arranged on a rotating shaft of the aircraft engine and used for generating a magnetic field, the direction of the magnetic field is vertical to the axial direction of the rotating shaft of the aircraft engine, and the distribution of the magnetic field is periodically changed along with the rotation of the rotating shaft of the aircraft engine; the peripheral side of the aircraft engine is provided with at least one pair of Hall sensors which are arranged in a manner that measuring planes are perpendicular to the direction of a magnetic field and are in reverse symmetry with each other, the Hall sensors are used for collecting a pair of differential rotating speed signals with the same amplitude but opposite phases, and the rotating speed of the aircraft engine is obtained by processing the differential rotating speed signals. The invention also discloses a device for measuring the rotating speed of the aircraft engine. Compared with the prior art, the invention can avoid various signal interference problems to the maximum extent and is easy to realize the self-diagnosis function of the rotating speed sensor.
Description
Technical Field
The invention relates to a method for measuring the rotating speed of an aircraft engine.
Background
In the control of an aircraft engine, the engine speed is a very important controlled quantity, the control of the engine state is embodied in the control of the speed, and the speed is also an important parameter for evaluating the performance of the engine. Therefore, the accuracy and stability of the rotation speed measurement directly affect the control state of the engine.
The rotation speed sensors generally used in aircraft engines are: hall sensor, magnetoelectric tachometric transducer, photoelectric tachometric transducer and tachometric motor sensor. At present, most of aircraft engines adopt Hall sensors for measuring the rotating speed, but because the rotating speed signals generated by the Hall sensors are interfered by external noise, differential Hall sensors are often adopted. The traditional differential Hall sensor can avoid the signal interference problem in signal transmission to a certain extent, but still does not solve the noise interference problem in a complex environment from the perspective of a signal source; in addition, the conventional differential hall sensor is difficult to realize in terms of sensor self-diagnosis due to the limitation of the signal generation manner thereof.
Disclosure of Invention
The invention aims to solve the technical problem of overcoming the defects in the prior art, and provides a method for measuring the rotating speed of an aircraft engine, which can avoid the interference problem of various signals to the greatest extent and is easy to realize the self-diagnosis function of a rotating speed sensor.
The invention specifically adopts the following technical scheme to solve the technical problems:
a magnetic component is arranged on a rotating shaft of an aero-engine and used for generating a magnetic field which has a magnetic field direction perpendicular to the axial direction of the rotating shaft of the aero-engine and magnetic field distribution which is periodically changed along with the rotation of the rotating shaft of the aero-engine; the peripheral side of the aircraft engine is provided with at least one pair of Hall sensors which are arranged in a manner that measuring planes are perpendicular to the direction of a magnetic field and are in reverse symmetry with each other, the Hall sensors are used for collecting a pair of differential rotating speed signals with the same amplitude but opposite phases, and the rotating speed of the aircraft engine is obtained by processing the differential rotating speed signals.
Further, the measurement method further includes: and comparing the signal characteristics of the pair of differential rotating speed signals to judge whether the Hall sensors break down or not and whether the installation positions between the two Hall sensors deviate or not.
Preferably, the signal characteristic comprises amplitude and/or phase.
Based on the same inventive concept, the following technical scheme can be obtained:
a magnetic component is arranged on a rotating shaft of an aero-engine and used for generating a magnetic field, wherein the direction of the magnetic field is perpendicular to the axial direction of the rotating shaft of the aero-engine, and the distribution of the magnetic field is periodically changed along with the rotation of the rotating shaft of the aero-engine; the aircraft engine rotational speed measuring device includes:
the rotating speed sensor comprises at least one pair of Hall sensors which are arranged on the peripheral side of the aircraft engine, wherein the Hall sensors are perpendicular to the direction of the magnetic field and are symmetrically arranged in opposite directions, and are used for acquiring a pair of differential rotating speed signals with the same amplitude but opposite phases;
and the signal processing circuit is used for processing the differential rotating speed signal to obtain the rotating speed of the aircraft engine.
Further, the apparatus further comprises:
and the fault self-diagnosis circuit is used for comparing the signal characteristics of the pair of differential rotating speed signals to judge whether the Hall sensors have faults or not and whether the installation positions between the two Hall sensors have deviations or not.
Preferably, the signal characteristic comprises amplitude and/or phase.
Preferably, the signal processing circuit includes a differential filter, a differential amplifying circuit, and a hysteresis comparing circuit connected in sequence.
Preferably, the signal processing circuit is arranged on a circuit board, and the pair of hall sensors are reversely and symmetrically arranged on the front surface and the back surface of the circuit board at the same position.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
according to the invention, the differential rotating speed signal is directly acquired by the pair of Hall sensors which are symmetrically arranged in the reverse direction, so that the problem that the rotating speed signal of the aircraft engine is easily interfered by environmental noise especially under the condition of low rotating speed is solved from a signal source, and compared with the traditional differential Hall sensor, the sensing precision is better, and a required signal processing circuit is simpler;
because the two paths of differential rotating speed signals with the same amplitude and opposite phases are collected, the fault self-diagnosis function of the sensor can be easily realized by comparing the signal characteristics of the two paths of signals, so that the anti-interference performance, the stability and the fault self-diagnosis performance of the rotating speed signals are improved on the basis of not increasing the design complexity and the sensor complexity, and the robustness and the stability of the control of the aircraft engine are further improved.
Drawings
FIG. 1 is a schematic view of a rotational speed sensor mounting structure of an aircraft engine rotational speed measuring device according to the present invention;
FIG. 2 is a schematic diagram of a preferred layout structure of the aircraft engine speed measuring device of the invention;
FIG. 3 is a schematic block diagram of the electrical circuit of the aircraft engine speed measuring device of the present invention;
FIG. 4 is a schematic diagram of a preferred circuit structure of the aircraft engine speed measuring device of the present invention;
FIG. 5 is a schematic diagram of a comparison between an aircraft engine speed measurement device of the present invention and a conventional aircraft engine speed measurement device.
Detailed Description
The problems of severe working environment of the aircraft engine, such as high temperature, vibration, complex electromagnetic environment and the like, all bring influence on the measurement of the rotating speed of the aircraft engine, and for signals with weak amplitude, such as rotating speed signals, the external noise interference is directly superposed on the original signals, so that the original signals are submerged in noise signals; the external noise signals often exist in the form of differential mode signals, and it is necessary to generate a differential rotation speed signal to suppress the differential mode noise; when a single Hall sensor or a differential Hall sensor is used for acquiring the rotating speed in the prior art, the amplitude of the generated rotating speed signal is small and is easily interfered by environmental noise, after the rotating speed signal is amplified layer by layer and compared with hysteresis, the influence of the interference signal on the normal rotating speed signal is more serious, the immeasurable influence is generated on the control of an aeroengine, and the fault self-diagnosis of the sensor of the traditional differential Hall sensor is difficult to realize due to the limitation of a signal acquisition mode.
In order to solve the technical problems, the idea of the invention is that a differential rotating speed signal is directly collected by a pair of Hall sensors which are symmetrically arranged in a reverse direction from the source of signal generation, when external noise interference and power supply interference inside a circuit board occur, because the differential rotating speed signal is characterized by being a differential signal, two paths of signals can simultaneously receive or superpose the same interference signal, and the inevitable noise interference problem of the traditional differential Hall sensor can be effectively inhibited through differential signal processing; in addition, because two paths of differential rotating speed signals with the same amplitude and opposite phases are collected, the fault self-diagnosis function of the sensor can be easily realized by comparing the signal characteristics of the two paths of signals.
The invention specifically adopts the following technical scheme to solve the technical problems:
a magnetic component is arranged on a rotating shaft of an aero-engine and used for generating a magnetic field which has a magnetic field direction perpendicular to the axial direction of the rotating shaft of the aero-engine and magnetic field distribution which is periodically changed along with the rotation of the rotating shaft of the aero-engine; the peripheral side of the aircraft engine is provided with at least one pair of Hall sensors which are arranged in a manner that measuring planes are perpendicular to the direction of a magnetic field and are in reverse symmetry with each other, the Hall sensors are used for collecting a pair of differential rotating speed signals with the same amplitude but opposite phases, and the rotating speed of the aircraft engine is obtained by processing the differential rotating speed signals.
Further, the measurement method further includes: and comparing the signal characteristics of the pair of differential rotating speed signals to judge whether the Hall sensors break down or not and whether the installation positions between the two Hall sensors deviate or not.
Preferably, the signal characteristic comprises amplitude and/or phase.
Based on the same inventive concept, the following technical scheme can be obtained:
a magnetic component is arranged on a rotating shaft of an aero-engine and used for generating a magnetic field, wherein the direction of the magnetic field is perpendicular to the axial direction of the rotating shaft of the aero-engine, and the distribution of the magnetic field is periodically changed along with the rotation of the rotating shaft of the aero-engine; the aircraft engine rotational speed measuring device includes:
the rotating speed sensor comprises at least one pair of Hall sensors which are arranged on the peripheral side of the aircraft engine, wherein the Hall sensors are perpendicular to the direction of the magnetic field and are symmetrically arranged in opposite directions, and are used for acquiring a pair of differential rotating speed signals with the same amplitude but opposite phases;
and the signal processing circuit is used for processing the differential rotating speed signal to obtain the rotating speed of the aircraft engine.
Further, the apparatus further comprises:
and the fault self-diagnosis circuit is used for comparing the signal characteristics of the pair of differential rotating speed signals to judge whether the Hall sensors have faults or not and whether the installation positions between the two Hall sensors have deviations or not.
Preferably, the signal characteristic comprises amplitude and/or phase.
Preferably, the signal processing circuit includes a differential filter, a differential amplifying circuit, and a hysteresis comparing circuit connected in sequence.
Preferably, the signal processing circuit is arranged on a circuit board, and the pair of hall sensors are reversely and symmetrically arranged on the front surface and the back surface of the circuit board at the same position.
For the public understanding, the technical scheme of the invention is explained in detail by the specific embodiment and the attached drawings:
as shown in fig. 1, a magnetic ring is embedded in a rotor shaft of an aircraft engine, and the direction of a magnetic induction line of a generated magnetic field is shown in the figure; when the aircraft engine runs, the rotor shaft drives the magnetic ring to rotate, so that a periodic magnetic field changing along with the rotating speed is generated; at least one pair of Hall sensors are arranged on the periphery of the aircraft engine, as shown in fig. 1 and 2, the measuring planes of the two Hall sensors are perpendicular to the magnetic field direction and are arranged in a reverse symmetry mode, and when the magnetic field characteristic of the aircraft engine is not changed, by adopting the special Hall sensor oppositely-mounting mode, when a magnetic induction line passes through the oppositely-mounted Hall sensors, the magnetic induction line can equivalently pass through the front side and the back side of the Hall sensors at the same time, so that a pair of differential signals with the same amplitude and opposite phases are generated.
As shown in fig. 3, the differential rotation speed signals collected by the pair of hall sensors are processed by the differential filter circuit, the differential amplifier circuit and the hysteresis comparison circuit in sequence to generate square wave signals with the same frequency as the rotation speed signals, so that the rotation speed of the engine can be further processed. The differential filter circuit is used for filtering the differential rotating speed signal; the differential mode noise suppression circuit comprises a differential mode signal filter circuit and a common mode signal filter circuit, and achieves differential mode noise suppression and common mode noise suppression on differential signals. The differential amplification circuit is used for carrying out differential amplification on the filtered differential rotating speed signal; the differential amplification circuit can change the amplification factor by configuring the resistance value of the resistor, and is fully suitable for the difference of differential rotating speed signals generated by different types of Hall elements. The hysteresis comparison circuit is used for generating square wave signals with the same frequency as the rotating speed signals, so that the rotating speed signals can be conveniently collected and analyzed by collection modules such as a single chip microcomputer, and the hysteresis comparison circuit can change the comparison threshold voltage by setting the resistance value of a resistor of the hysteresis comparison circuit, and is fully suitable for the universality under different environments and use conditions.
The actual engine speed can be calculated by the following formula:
wherein n is the actual rotating speed of the engine, the unit is rpm, f is the frequency of the square wave signal output by the hysteresis comparison circuit, the unit is Hz, and p is the number of magnetic ring pairs on the rotor of the engine.
As shown in fig. 3, the aircraft engine measuring device of this embodiment further includes a fault self-diagnosis circuit, which is configured to determine whether the hall sensor itself has a fault and whether the installation position between the two hall sensors has a deviation by comparing signal characteristics such as the amplitude and the phase of the pair of differential rotational speed signals. For example, one path of signals in the differential rotation speed signals can be collected, the signals are processed through a reverse rail-to-rail operational amplifier, the processed signals are compared with the other path of differential rotation speed signals, amplitude calculation is carried out through a subtracter, when the position of the sensor is accurate and the working state is normal, the compared signals cannot trigger the threshold voltage of a comparator, fault signal pulses cannot be generated, and due to the existence of the threshold voltage, the problems of installation position errors and fault sensitivity can be solved, and the faults of the sensor can be judged in real time. Or, the phase difference value between the output signal of the reverse rail-to-rail operational amplifier and the other path of differential rotation speed signal is compared through a phase comparator, and a sensor fault pulse signal with unmatched phase is generated.
Fig. 4 shows a preferred circuit configuration of the aircraft engine speed measuring device of the present invention. As shown in fig. 4, a pair of differential speed signals with the same amplitude and opposite phases are generated by oppositely mounting hall sensors; the frequency of the signal is related to the rotating speed of the engine, and the amplitude of the generated differential rotating speed signal is related to the characteristics of the Hall sensor and the distance from the sensor to the rotor shaft; the resistor R1 and the capacitor C1 at the differential input end realize low-pass filtering, high-frequency noise is filtered, a normal differential rotating speed signal is reserved, the cutoff frequency is changed by configuring the values of R1 and C1, and the filter characteristic under different conditions is adapted; resistor R2 and capacitor C2 are as described above; the capacitor C3 and the capacitor C4 realize filtering processing of common-mode signals in the differential filter and are used for inhibiting common-mode interference in the circuit; the capacitor C5 is a differential mode capacitor and is used for filtering differential mode noise in the differential speed signal; the resistor R5, the resistor R6, the resistor R7, the resistor R8 and the operational amplifier U1 jointly form a differential amplification circuit, and the amplification factor of the differential mode amplifier is changed by changing the values of the resistor R5, the resistor R6, the resistor R7 and the resistor R8, and is shown as the following formula:
because the amplitude of the differential rotating speed signal generated by the Hall sensor is influenced by the characteristics of the Hall sensor and the distance between the Hall sensor and the sensor, the gain of the signal is required to be adjusted by adjusting the differential amplification factor, and the rotating speed signal with proper amplitude is generated for hysteresis comparison; the resistor R9, the resistor R10 and the operational amplifier U2 form a hysteresis comparison circuit, and the threshold voltage of the hysteresis comparison is set by configuring the resistance values of the resistor R9 and the resistor R10, so as to output a square wave signal with a high level of 5V and a low level of 0V.
The fault self-diagnosis circuit comprises an amplitude comparison circuit and a phase comparison circuit, a resistor R12 and a resistor R11 operational amplifier U3 form a reverse following circuit in the amplitude comparison circuit, a resistor R13, a resistor R14, a resistor R22, a resistor R15 and an operational amplifier U4 form a comparator of the amplitude comparison circuit, and a fault threshold is set by setting a resistor R16, a resistor R17 and an operational amplifier U5 through a threshold; the phase comparison circuit consists of two comparators R19 and R18 and an operational amplifier U6, and then outputs a fault signal after being compared by a phase comparator (consisting of R23, R24, R26, R25 and an operational amplifier U8).
Fig. 5 shows a comparison result between the rotating speed measuring device of the present invention and the rotating speed measuring device of the conventional differential hall sensor, and it is obvious that the rotating speed measuring device of the present invention can effectively suppress various noise influences including electromagnetic interference under a severe environment, power supply noise, and environmental noise during signal transmission, which cannot be achieved by the rotating speed measuring scheme of the conventional differential hall sensor.
Claims (6)
1. A magnetic component is arranged on a rotating shaft of an aero-engine and used for generating a magnetic field which has a magnetic field direction perpendicular to the axial direction of the rotating shaft of the aero-engine and magnetic field distribution which is periodically changed along with the rotation of the rotating shaft of the aero-engine; the method is characterized in that at least one pair of Hall sensors with measuring planes perpendicular to the direction of a magnetic field and arranged in a reverse symmetry mode are arranged on the peripheral side of the aircraft engine, a pair of differential rotating speed signals with the same amplitude and opposite phases are acquired by the Hall sensors, and the rotating speed of the aircraft engine is obtained by processing the differential rotating speed signals; the aircraft engine rotating speed measuring method further comprises the following steps: and comparing the signal characteristics of the pair of differential rotating speed signals to judge whether the Hall sensors break down or not and whether the installation positions between the two Hall sensors deviate or not.
2. A method of measuring aircraft engine speed as claimed in claim 1, wherein said signal characteristics include amplitude and/or phase.
3. A magnetic component is arranged on a rotating shaft of an aero-engine and used for generating a magnetic field, wherein the direction of the magnetic field is perpendicular to the axial direction of the rotating shaft of the aero-engine, and the distribution of the magnetic field is periodically changed along with the rotation of the rotating shaft of the aero-engine; characterized in that, aeroengine rotational speed measuring device includes:
the rotating speed sensor comprises at least one pair of Hall sensors which are arranged on the peripheral side of the aircraft engine, wherein the Hall sensors are perpendicular to the direction of the magnetic field and are symmetrically arranged in opposite directions, and are used for acquiring a pair of differential rotating speed signals with the same amplitude but opposite phases;
the signal processing circuit is used for processing the differential rotating speed signal to obtain the rotating speed of the aircraft engine;
and the fault self-diagnosis circuit is used for comparing the signal characteristics of the pair of differential rotating speed signals to judge whether the Hall sensors have faults or not and whether the installation positions between the two Hall sensors have deviations or not.
4. An aircraft engine speed measurement device according to claim 3, wherein the signal characteristics comprise amplitude and/or phase.
5. An aircraft engine speed measuring device according to claim 3, wherein the signal processing circuit comprises a differential filter, a differential amplifying circuit and a hysteresis comparing circuit which are connected in sequence.
6. The aircraft engine speed measuring device according to claim 3, wherein the signal processing circuit is disposed on a circuit board, and the pair of Hall sensors are oppositely and symmetrically mounted on the front and back surfaces of the circuit board at the same position.
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| CN202110761513.4A CN113390643B (en) | 2021-07-06 | 2021-07-06 | Method and device for measuring rotating speed of aircraft engine |
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| CN113775457B (en) * | 2021-11-09 | 2022-02-11 | 金城集团有限公司 | Ignition control method and fault diagnosis method for aviation piston engine |
| CN114318479B (en) * | 2021-12-17 | 2023-05-09 | 宁波韵升股份有限公司 | Cleaning process of electroplated nickel ultrathin magnetic steel |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6446005B1 (en) * | 1999-08-13 | 2002-09-03 | Prolink, Inc. | Magnetic wheel sensor for vehicle navigation system |
| CN201408199Y (en) * | 2009-03-26 | 2010-02-17 | 南京奥联汽车电子电器有限公司 | Rotating speed sensor for Hall gear |
| CN204944565U (en) * | 2015-08-26 | 2016-01-06 | 北京云网天成科技有限公司 | A kind of flow sensor |
| CN105424966A (en) * | 2015-12-11 | 2016-03-23 | 中国航空工业集团公司西安航空计算技术研究所 | Engine rotating speed measurement circuit and method |
| CN106500584A (en) * | 2016-09-29 | 2017-03-15 | 南京邮电大学 | A kind of angle measurement system and measuring method based on linear hall sensor |
| US20170167950A1 (en) * | 2015-12-10 | 2017-06-15 | Fujitsu Limited | Estimation apparatus, estimation method and engine system |
| CN208432631U (en) * | 2018-06-07 | 2019-01-25 | 嘉默传感技术(上海)有限公司 | A kind of sensor detecting Anti-pinch motor revolving speed, steering |
| CN209356656U (en) * | 2018-12-28 | 2019-09-06 | 哈尔滨博乐恩机器人技术有限公司 | High sensitivity seeks Magnetic Sensor |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102017121467A1 (en) * | 2017-09-15 | 2019-03-21 | Infineon Technologies Ag | MAGNETIC SENSOR COMPONENT AND METHOD FOR DETERMINING A ROTATIONAL SPEED, A ROTATIONAL DIRECTION, AND / OR A ROTATION ANGLE OF A MAGNETIC COMPONENT FOR A ROTATIONAL AXIS |
-
2021
- 2021-07-06 CN CN202110761513.4A patent/CN113390643B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6446005B1 (en) * | 1999-08-13 | 2002-09-03 | Prolink, Inc. | Magnetic wheel sensor for vehicle navigation system |
| CN201408199Y (en) * | 2009-03-26 | 2010-02-17 | 南京奥联汽车电子电器有限公司 | Rotating speed sensor for Hall gear |
| CN204944565U (en) * | 2015-08-26 | 2016-01-06 | 北京云网天成科技有限公司 | A kind of flow sensor |
| US20170167950A1 (en) * | 2015-12-10 | 2017-06-15 | Fujitsu Limited | Estimation apparatus, estimation method and engine system |
| CN105424966A (en) * | 2015-12-11 | 2016-03-23 | 中国航空工业集团公司西安航空计算技术研究所 | Engine rotating speed measurement circuit and method |
| CN106500584A (en) * | 2016-09-29 | 2017-03-15 | 南京邮电大学 | A kind of angle measurement system and measuring method based on linear hall sensor |
| CN208432631U (en) * | 2018-06-07 | 2019-01-25 | 嘉默传感技术(上海)有限公司 | A kind of sensor detecting Anti-pinch motor revolving speed, steering |
| CN209356656U (en) * | 2018-12-28 | 2019-09-06 | 哈尔滨博乐恩机器人技术有限公司 | High sensitivity seeks Magnetic Sensor |
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