CN112697438B - Device and method for measuring pitch-phase angle-speed of turboprop engine based on sound wheel - Google Patents

Abstract

The invention relates to a turboprop engine pitch-phase angle-speed measuring device and method based on a sound wheel, and belongs to the field of aviation turboprop engine control. The measuring device disclosed by the invention comprises: a sound wheel (6), a magnetic induction probe (7) and a signal processing module (9), the sound wheel (6) is coupled to the propeller, and the magnetic induction probe (7) can A signal is generated in response to the passage of a plurality of conventional teeth (1), first marking teeth (2) and second marking teeth (3) on the tone wheel (6), the signal processing module (9) being capable of generating signals based on the The specific delay, specific time and expected delay of the pulses are used to determine the pitch, phase angle and rotational speed of the propeller, respectively. By adopting the chevron-shaped marking tooth whose quality is equal to that of the conventional tooth (1), the pitch can be measured and the reference position of the phase angle can be used, and the two symmetrical teeth have the functions of complementary correction of magnetoelectric detection signals and reduction of unbalance , overcome the impact of random phase angle reference position and vibration noise on the measurement, and improve the measurement accuracy, sensitivity and working stability.

Description

Device and method for measuring pitch-phase angle-speed of turboprop engine based on sound wheel

technical field

The invention relates to a turboprop engine pitch-phase angle-speed measuring device and method based on a sound wheel, and belongs to the field of aviation turboprop engine control.

Background technique

Aeroengine control systems are developing from single variable control to multivariable control. How to increase the number of sensors to measure parameters without increasing the number of sensors to increase the safety of the aircraft control system and reduce the weight of the aircraft. High requirements are placed on the multi-parameter measurement of the sensor. The control of modern turboprop aircraft mostly uses a multivariable control system, which needs to measure the pitch, phase angle and rotational speed of the propeller in real time to allow the aircraft to fly smoothly.

At present, the domestic propeller pitch, phase angle and rotational speed measurement of the turboprop engine are mostly separate and independent sensors. For example, the patent publication number CN105486220A discloses a propeller pitch measuring device, which adopts an eddy current sensor for detecting its The displacement change corresponding to the change of the blade pitch angle of the measured object is converted into an electrical signal and output to the engine control box, and finally the signal processing can only calculate the pitch; in the prior art, there is a method of measuring the rotational speed through the speed measuring motor. That is to collect the AC voltage signal of the speed sensor speed measuring motor, and its frequency is proportional to the engine speed. The rotor speed can be obtained by measuring the frequency or period of the AC signal, but the other two parameters cannot be measured; Among the speed sensors, the magnetoelectric speed sensor with a sound wheel has the characteristics of simple structure and high precision, and is the most widely used, but what can be realized at present is only the measurement of the speed. In the measurement of the propeller phase angle of the turboprop engine It is still in the experimental stage. In China, a method of marking the reference position of the phase angle by embedding high-magnetic materials on the sound wheel has been proposed, which can realize the measurement of two parameters, but there is a problem of rotor imbalance, and a balance counterweight is required.

To sum up, these multi-parameter and multi-sensor measurement methods will increase the mutual interference of sensor hardware equipment and connection lines, which is very taboo in the aviation field where the weight and safety requirements of aircraft are very strict, and there is an urgent need for a high-performance A measurement device that measures the three parameters of pitch, phase angle and rotational speed simultaneously without multi-sensor mutual interference.

Contents of the invention

The purpose of the present invention is to provide a turboprop engine pitch-phase angle-rotational speed measuring device and method based on a sound wheel, aiming to realize the pitch, phase angle and rotational speed by using only a magnetic sensor with a sound wheel. High precision and sensitivity measurement, and the sound wheel structure has good static and dynamic balance characteristics.

To achieve the above object, the present invention provides the following technical solutions:

A turboprop engine pitch-phase angle-speed measuring device based on a sound wheel, comprising: a sound wheel, a magnetic induction probe and a signal processing module, the sound wheel includes circumferentially evenly spaced holes arranged on the outer circumferential surface of the sound wheel a plurality of conventional teeth and a first marking tooth and a second marking tooth arranged on the outer surface, the first marking tooth and the second marking tooth are respectively closer to certain two adjacent conventional teeth in the circumferential direction, And the initial phase angle reference position of the propeller is represented by the apex angle boundary position of the first mark tooth and the second mark tooth, and the apex angle position of the first mark tooth and the second mark tooth is represented as the pitch reference position of the propeller , the tone wheel is configured to rotate and move axially with the propeller during operation of the turboprop engine;

the magnetic induction probe, affixed to a stationary part of the engine, adjacent to the tone wheel and configured to generate a signal comprising a plurality of signal pulses in response to passage of the regular tooth and the marker tooth , the occurrence timing of the plurality of signal pulses corresponds to the passing timing of the plurality of regular teeth, the first marking teeth and the second marking teeth during the rotation of the tone wheel;

The signal processing module, which is coupled to the magnetic induction probe for obtaining the signal, is configured for:

determining an expected delay based on the plurality of signal pulses, the expected delay representing the time interval of the plurality of regular teeth;

identifying a first specific pulse associated with the first marking tooth from within the plurality of signal pulses, the specific pulse having a delay shorter than the expected delay;

determining, based on the first specific pulse, a specific delay of a second specific pulse associated with said second marking tooth which occurs consecutively thereto, said specific delay representing the time interval between said first and second specific pulses;

Determining the first and second marking teeth for a certain axial position of the propeller based on a specific delay of said first and second specific pulses associated with said first and second marking teeth The circumferential distance generally takes the apex angle position of the first marking tooth and the second marking tooth as 0 pitch, so the circumferential distance can be converted into the pitch of the propeller according to the angular relationship between the first marking tooth and the second marking tooth ;

Based on the time average of the first and second specific times generated by the first specific pulse and the second specific pulse, determine the current data acquisition moment, the position of the apex angle boundary line of the magnetic sensor probe relative to the first marking tooth and the second marking tooth The phase angle of the propeller, that is, the phase angle of the propeller, eliminates the error of the random reference position and vibration noise caused by only one marked helical tooth on the phase angle measurement accuracy;

And based on said expected delay, a calculation of propeller speed is performed.

The structure of the sound wheel includes teeth, a cylinder and a through hole, and the thickness of the sound wheel is greater than or equal to the variation range of the pitch, so a cylindrical sound wheel structure with a certain thickness is adopted to reduce the weight of the sound wheel , the plurality of conventional teeth are arranged in parallel in the circumferential direction, and are all parallel to the axis of the tone wheel. The through hole is used to be sleeved on the rotating shaft of the propeller, and rotates and moves axially with the propeller. The first The volume and quality of the marking tooth and the second marking tooth are set to be half of that of any other conventional tooth, and the first marking tooth and the second marking tooth form the same angle a° with the parallel line of the conventional teeth arranged in the circumferential direction , the two symmetrical teeth form a complementary differential double-gain sensitivity, which has the functions of complementary correction of the magnetoelectric detection signal and reduction of unbalance, thereby improving the measurement accuracy, sensitivity and static and dynamic balance characteristics of the rotor. There is no special structure of the marking teeth And the static and dynamic balance of the rotor of the tone wheel is carried out with special high magnetic materials.

The described sound wheel-based turboprop engine pitch-phase angle-speed measuring device is characterized in that the signal processing module includes: a signal conditioning circuit, an F/D conversion circuit and an embedded on-chip programmable system, so The above-mentioned signal conditioning circuit connects the magnetic sensor probe, and has a first connection end and a second connection end. The first connection end is directly connected to the embedded on-chip programmable system, and sends data out through the bus interface; the second connection end is first connected to The F/D conversion circuit is connected to the embedded on-chip programmable system, and finally the data is sent out through the bus interface.

The measuring method of the turboprop propeller pitch-phase angle-speed measuring device based on the sound wheel is characterized in that it comprises the following process:

The tone wheel and the propeller are coupled together to work with the motor, and the magnetic induction probe responds to the passage of a plurality of uniformly spaced conventional teeth, first index teeth and second index teeth on the outer peripheral surface of the tone wheel Generate associated pulse signals and transmit them to the signal processing module, the signal processing module will perform denoising, amplification and shaping, clipping and filtering negative voltage on the multiple pulse signals collected from the magnetic sensor probe processing, thereby obtaining a positive square wave signal, the square wave signal is directly transmitted to the embedded on-chip programmable system through the first connection end of the signal conditioning circuit, and the embedded on-chip programmable system can be programmed by software The specific function code reads the rising edge time or falling edge time from the square wave signal for data processing and storage, reads the expected delay, specific delay, and the average value of the first and second specific times, and then Calculate the pitch, phase angle and rotating speed of the current data acquisition moment; the square wave signal can also be transmitted to the F/D conversion circuit through the second connection end of the signal conditioning circuit, and in the F/D conversion circuit The frequency of the square wave signal is converted into the digital quantity of the rotational speed, and finally transmitted to the embedded on-chip programmable system, and the said rotational speed, pitch and phase angle are sent out through the bus interface.

The code for the specific function mentioned above can make the algorithm have good robustness by setting the threshold e related to the size of the marking tooth, and considering that the data collection time is not necessarily the time when a specific pulse is generated, it is necessary to store the latest time in real time The expected delay, the specific delay, and the average of the first and second specific times, the pitch, phase angle and rotational speed of the propeller have the following calculation steps:

Step 1: Initially set the threshold e that can identify the first specific pulse, the number of conventional teeth Z, and the radius R of the addendum circle;

Step 2: Obtain rising edge times T ₁ , T ₂ , and T ₃ of three continuous square wave signals;

Step 3: Perform logical operation |(T ₂ -T ₁ )-(T ₃ -T ₂ )|<e, if true, store expected delay T _A =T ₃ -T ₂ , if false, return to step 2;

Step 4: Obtain rising edge times T ₁ , T ₂ , and T ₃ of three continuous square wave signals;

Step 5: Perform logical operation |T _A -(T ₂ -T ₁ )|>e, if true, store the specific delay T _C =T ₃ -T ₂ , the time mean value T _S of the first specific time and the second specific time =(T ₂ +T ₃ )/2, if false, return to step 4;

Step 6: Whether to execute the data acquisition instruction, if true, obtain the time T _N of the current execution instruction time, and perform the following calculation, pitch = π·R· _TC /{(Z+1)· _TA ·tan(a° )}, phase angle=360·(T _N -T _S )/{(Z+1)·T _A )}, speed n=60/{(Z+1)·T _A }, end at last, return if false step2.

Compared with the prior art, the advantage of the present invention is that only using a magnetic sensor with a sound wheel can identify a plurality of conventional teeth evenly spaced in the circumferential direction from a plurality of pulse signals responded by the magnetic sensor probe. The pulse signal associated with the first marking tooth and the second marking tooth arranged on the outer surface, so as to determine the expected delay, specific delay, and the average value of the first and second specific time through the signal processing module, and finally realize the rotation speed, phase angle And the measurement of the three parameters of the pitch, the cylindrical sound wheel structure with herringbone marking teeth with approximately uniform mass has good static and dynamic balance characteristics of the rotor with light weight, and there is no special structure of the marking teeth and special The static and dynamic balance of the rotor of the sound wheel is made of high-magnetic materials, thereby simplifying the manufacturing process and reducing the cost; and its symmetrical first and second marking teeth form complementary differential double-gain sensitivity, with complementary magnetoelectric detection signals The function of correction overcomes the influence of the random phase angle reference position and vibration noise of the single-mark helical gear on the measurement accuracy, and improves the measurement accuracy, sensitivity and work stability. At the same time, it not only ensures the measurement accuracy, but also reduces the difficulty of processing and manufacturing.

Description of drawings

Fig. 1 is a structural perspective view and a left view of the present invention.

Fig. 2 is a structural diagram of the signal processing module of the present invention.

Fig. 3 is a corresponding diagram of the pulse signal of the present invention and the circumferential tooth profile development at a certain axial position of the propeller.

Fig. 4 is a schematic diagram of conditioning a pulse signal into a square wave signal according to the present invention.

Fig. 5 is a logic flow diagram of specific function codes of the present invention.

In the figure: 1-regular tooth, 2-first marking tooth, 3-second marking tooth, 4-cylinder, 5-through hole, 6-tone wheel, 7-magnetic sensor probe, 8-wire, 9-signal Processing module, 10-bus interface.

Detailed ways

The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

Please refer to Fig. 1, in the embodiment of the present invention, the turboprop engine pitch-phase angle-speed measurement device based on sound wheel, comprises: sound wheel 6, magnetic induction probe 7 and signal processing module 9, and described sound wheel comprises setting On the outer circumferential surface of the tone wheel, a plurality of conventional teeth 1 evenly spaced in the circumferential direction and the first marking teeth 2 and the second marking teeth 3 arranged on the outer surface, the first marking teeth 2 and the second marking teeth Marking teeth 3 are closer to two adjacent conventional teeth 1 in the circumferential direction, and the initial phase angle reference position of the propeller is represented by the apex angle boundary position of the first marking tooth 2 and the second marking tooth 3, so The apex angle positions of the first index tooth 2 and the second index tooth 3 described above are indicated as the pitch reference position of the propeller, and the tone wheel 6 is configured to rotate together with the propeller along the "E" direction during the operation of the turboprop engine. and "F" move axially;

The structure of the tone wheel comprises teeth, cylinder 4 and through hole 5, and the structure of the tone wheel teeth is characterized in that the thickness of the tone wheel is greater than or equal to the variation range of the pitch, so it is adopted to have a certain thickness. Cylindrical sound wheel structure, in order to reduce the weight of the sound wheel, the plurality of conventional teeth 1 are arranged in parallel in the circumferential direction, and all parallel to the axis of the sound wheel 6, also parallel to the "D" line, the said The through hole is used to be sleeved on the rotating shaft of the propeller, and together with the propeller to rotate in the "E" direction and move axially in the "F" direction, the volume and quality of the first marking tooth 2 and the second marking tooth 3 are set to It is half of any other regular tooth 1, and the first marking tooth 2 and the second marking tooth 3 are at the same a° angle with the "D" line, these two symmetrical teeth form complementary differential double gain sensitivity, with magnetoelectric The function of detection signal complementary correction and reduction of unbalance degree does not exist due to the special structure of the marking tooth and the special high magnetic material to carry out the static and dynamic balance of the rotor of the sound wheel, thereby improving the measurement accuracy, sensitivity and static and dynamic balance of the rotor characteristic.

Referring to FIG. 3 , the magnetic sensor probe 7 is fixed to the stationary part of the engine, adjacent to the tone wheel 6 and configured to generate a signal in response to the passage of the conventional tooth 1 and the marking tooth, Said signal comprises a plurality of signal pulses whose timing of occurrence corresponds to the passage of said plurality of regular teeth 1 , first marking teeth 2 and second marking teeth 3 during rotation of said tone wheel 6 Timing, when the propeller drives the sound wheel to rotate, the tooth peaks and tooth valleys of the sound wheel will cause the change of the gap δ between the sound wheel and the permanent magnet, so that the magnetic flux in the magnetic circuit composed of permanent magnets will change. When the first side of the tooth peak approaches When the magnetic induction probe is used, the reluctance decreases, and the derivative of the magnetic flux is positive, thereby generating a signal pulse; the gap between the top surface of the tooth peak is the same, so no induced voltage is generated, and the voltage is 0; when the second side of the tooth peak is close to the magnetic induction When the probe is used, the reluctance increases, and the derivative of the magnetic flux is negative, thereby generating a signal pulse in the opposite direction;

Please refer to Fig. 2, described turboprop engine pitch-phase angle-speed measuring device based on sound wheel, it is characterized in that, described signal processing module 9, removes F/D conversion circuit during specific implementation, comprises: signal The conditioning circuit and the embedded on-chip programmable system, the signal conditioning circuit connects the magnetic sensor probe 7, the output is directly connected to the embedded on-chip programmable system, and sends data out through the bus interface.

The signal processing module 9 is coupled to the magnetic induction probe 7 for obtaining the signal, and is configured for:

Please refer to FIG. 4, the signal conditioning circuit in the signal processing module 9 will perform denoising, amplification and shaping, limiting and negative voltage filtering through the diode to the pulse signal collected in the upper part of FIG. 4, thereby obtaining FIG. 4 The lower square wave positive voltage signal;

determining an expected delay based on said plurality of signal pulses, said expected delay representing the time interval of said plurality of regular teeth 1;

identifying, from within said plurality of signal pulses, a first specific pulse associated with said first marking tooth 2, said specific pulse having a delay shorter than said expected delay, i.e. T _A > T _B ;

Based on the first specific pulse, a specific delay T _C of the second specific pulse associated with said second marking tooth 3 occurring consecutively to it is determined, said specific delay representing the time interval of said first and second specific pulse ;

Based on the specific delay _TC of said first and second specific pulses associated with said first marking tooth 2 and second marking tooth 3, said first marking tooth 2 and said second marking tooth 3 at a certain axial position of the propeller are determined The circumferential distance of the second marking tooth 3 generally takes the apex angle position of the first marking tooth 2 and the second marking tooth 3 as 0 pitch, so the circumferential distance can be calculated according to the first marking tooth 2 and the second marking tooth The angle relationship of 3 is converted into the pitch of the propeller;

Based on the time average value of the first and second specific times generated by the first specific pulse and the second specific pulse, the current data acquisition moment is determined, and the apex angle of the magnetic induction probe relative to the first marking tooth 2 and the second marking tooth 3 is divided The phase angle at the boundary position, that is, the phase angle of the propeller, eliminates the error of the random reference position and vibration noise on the phase angle measurement accuracy caused by using only one marked helical tooth;

And based on said expected delay, a calculation of propeller speed is performed.

Please refer to Fig. 2, the measuring method of the turboprop propeller pitch-phase angle-rotating speed measurement device based on the described sound wheel, it is characterized in that, during concrete implementation, remove F/D conversion circuit, and comprise following process:

The tone wheel 6 and the propeller are coupled together to work together with the motor, and the magnetic induction probe 7 responds to a plurality of conventional teeth 1, the first marking teeth 2 and the second teeth 2 which are evenly spaced in the circumferential direction on the outer peripheral surface of the tone wheel. The passage of the marking tooth 3 generates an associated pulse signal, and transmits it to the signal processing module 9, and the signal processing module 9 performs denoising, amplification and shaping on the multiple pulse signals collected from the magnetic induction probe 7 , clipping and filtering negative voltage processing, thereby obtaining a square wave signal, the square wave signal is directly transmitted to the embedded on-chip programmable system through the signal conditioning circuit, and the embedded on-chip programmable system can use software The code of the specific function written, read the rising edge time or falling edge time from the square wave signal for data processing and storage, read the expected delay, specific delay, and the average value of the first and second specific time, and then Calculate the rotation speed, pitch and phase angle at the current data collection time, and send the data through the bus interface.

Please refer to Figure 5, the code of the specific function described above can make the algorithm have good robustness by setting the threshold e related to the size of the marking tooth, and considering that the data acquisition time is not necessarily the time when a specific pulse is generated, so It is necessary to store the expected delay at the latest moment, the specific delay, and the average value of the first and second specific time in real time. The pitch, phase angle and rotational speed of the propeller have the following calculation steps:

Step 1: Initially set the threshold e that can identify the first specific pulse, the number of conventional teeth Z, and the radius R of the addendum circle;

Step 2: Obtain rising edge times T ₁ , T ₂ , and T ₃ of three continuous square wave signals;

Step 3: Perform logical operation |(T ₂ -T ₁ )-(T ₃ -T ₂ )|<e, if true, store expected delay T _A =T ₃ -T ₂ , if false, return to step 2;

Step 4: Obtain rising edge times T ₁ , T ₂ , and T ₃ of three continuous square wave signals;

Step 5: Perform logical operation |T _A -(T ₂ -T ₁ )|>e, if true, store the specific delay T _C =T ₃ -T ₂ , the time mean value T _S of the first specific time and the second specific time =(T ₂ +T ₃ )/2, if false, return to step 4;

Step 6: Whether to execute the data acquisition instruction, if true, obtain the time T _N of the current execution instruction time, and perform the following calculation, pitch = π·R· _TC /{(Z+1)· _TA ·tan(a° )}, phase angle=360·(T _N -T _S )/{(Z+1)·T _A )}, speed n=60/{(Z+1)·T _A }, end at last, return if false step2.

The working principle of the present invention is: magnetic induction probe 7 is made up of induction coil and permanent magnet material, can cause the change of sound wheel to permanent magnet gap δ in the process of sound wheel rotation, reluctance and gap size are directly related, manifested in the time of magnetic flux In terms of the rate of change, the changing magnetic field will produce a changing current, so the magnetic induction probe 7 can respond to the associated pulses generated by the passage of a plurality of conventional teeth 1, first marking teeth 2 and second marking teeth 3 on the sound wheel The signal is passed through the signal processing module 9 to calculate the expected delay T _A , the specific delay T _C , the time mean value T _S of the first and second specific times, and then calculate the rotational speed and phase angle. For the pitch, in the structure of the tone wheel, the spacing between the first marking tooth 2 and the second marking tooth 3 at different axial positions of the propeller is different, and the apex angle position of the first marking tooth 2 and the second marking tooth 3 is generally taken is 0 pitch, so the pitch can be calculated by trigonometric function conversion,

Function: It can measure the pitch, phase angle and rotational speed of the propeller with high precision only by using the magnetoelectric sensor with the sound wheel, and provide the measurement parameters of the sensor for the control of the turboprop aircraft.

The present invention is not limited to the above-mentioned embodiments. On the basis of the technical solutions disclosed in the present invention, those skilled in the art can make some simple modifications to some of the technical features according to the disclosed technical content without creative work. , equivalent changes and modifications all belong to the scope of the technical solution of the present invention.

Claims (3)

1. Turboprop engine pitch-phase angle-rotational speed measuring device based on phonic wheel includes: a tone wheel (6), a magnetic induction probe (7) and a signal processing module (9), wherein the tone wheel comprises a plurality of regular teeth (1) which are uniformly spaced in the circumferential direction and are arranged on the outer circumferential surface of the tone wheel (6), and a first marker tooth (2) and a second marker tooth (3) which are arranged on the outer circumferential surface, the first marker tooth (2) and the second marker tooth (3) are respectively closer to two adjacent regular teeth (1) in the circumferential direction, the vertex angle position of the propeller is represented by the boundary line position of the first marker tooth (2) and the second marker tooth (3), the vertex angle position of the first marker tooth (2) and the second marker tooth (3) is represented by the pitch reference position of the propeller, and the tone wheel is configured to rotate and move axially along with the propeller during the operation of the propeller turboprop; the structure of the sound wheel (6) comprises teeth, a cylinder (4) and a through hole (5), the thickness of the sound wheel is larger than or equal to the variation range of the propeller pitch, the conventional teeth (1) are arranged in parallel in the circumferential direction and are all parallel to the axis of the sound wheel (6), the through hole (5) is used for being sleeved on the rotating shaft of the propeller, the volume and the mass of the first marking tooth (2) and the second marking tooth (3) are all set to be half of that of any one of the other conventional teeth (1), the first marking tooth (2) and the second marking tooth (3) form the same angle of a degrees with the parallel line of the conventional teeth (1) arranged in the circumferential direction, the two symmetrical teeth form complementary differential double-gain sensitivity, and have the effects of complementary correction of magnetoelectric detection signals and reduction of unbalance;

the magnetic induction probe (7), fixed to a stationary part of the engine, is adjacent to the tone wheel and is configured for generating a signal in response to the passage of the conventional teeth (1) and the marking teeth, the signal comprising a plurality of signal pulses, the timing of the occurrence of the plurality of signal pulses corresponding to the timing of the passage of the plurality of conventional teeth (1), the first marking teeth (2) and the second marking teeth (3) during the rotation of the tone wheel (6);

the signal processing module (9) coupled to the magneto inductive probe (7) for obtaining the signal and configured for:

determining an expected delay based on the plurality of signal pulses, the expected delay representing a time interval of the plurality of regular teeth (1);

identifying a first particular pulse associated with the first marker tooth (2) from within the plurality of signal pulses, the first particular pulse having a shorter delay than the expected delay;

determining, based on the first specific pulse, a specific delay of a second specific pulse associated with said second marker tooth (3) with which it occurs consecutively, said specific delay representing the time interval of the first and second specific pulses;

-determining the circumferential distance of said first (2) and second (3) marker teeth for a certain axial position of the propeller based on the specific delays of said first and second specific pulses associated with said first (2) and second (3) marker teeth, taking the apex angle position of the first (2) and second (3) marker teeth as 0 pitch, so that said circumferential distance can be converted to the pitch of the propeller according to the angular relationship of the first (2) and second (3) marker teeth;

determining the current data acquisition time based on the time average value of first and second specific time generated by the first specific pulse and the second specific pulse, wherein the phase angle of the magnetic induction probe relative to the vertex angle boundary line position of the first marking tooth (2) and the second marking tooth (3), namely the phase angle of the propeller;

and calculating the propeller rotation speed based on the expected delay;

the pitch, phase angle and rotation speed of the propeller have the following calculation steps:

step 1: setting a threshold e capable of identifying a first specific pulse, a conventional tooth number Z and a tooth top radius R at first;

step 2: obtaining rising edge time T of three continuous square wave signals ₁ 、T ₂ 、T ₃ ；

And step 3: perform logical operation | (T) ₂ -T ₁ )-(T ₃ -T ₂ ) If true, | < e, store the expected delay T _A ＝T ₃ -T ₂ If false, returning to the step 2;

and 4, step 4: obtaining rising edge time T of three continuous square wave signals ₁ 、T ₂ 、T ₃ ；

And 5: perform a logical operation | T _A -(T ₂ -T ₁ ) If true, store a particular delay T _C ＝T ₃ -T ₂ Time average T of the first specific time and the second specific time _S ＝(T ₂ +T ₃ ) And/2, if false, returning to the step 4;

step 6: whether to execute the data acquisition instruction, if true, obtaining the time T of the current instruction execution time _N And calculated as follows, pitch = π · R · T _C /{(Z+1)·T _A Tan (a °), phase angle =360 · (T) _N -T _S )/{(Z+1)·T _A ) N =60/{ (Z + 1) · T at a rotational speed _A And finally, ending, and if false, returning to the step 2.

2. A pitch-phase angle-speed measuring device of a turboprop-based turboprop according to claim 1, wherein the signal processing module (9) comprises: the magnetic induction probe (7) is accessed into the signal conditioning circuit, and the signal conditioning circuit is provided with a first connecting end and a second connecting end, wherein the first connecting end is directly connected with the embedded on-chip programmable system and sends data out through a bus interface; the second connecting end is connected with the F/D conversion circuit, then connected with the embedded on-chip programmable system and finally sends out data through the bus interface.

3. A method of measuring a pitch-phase angle-rotation speed measuring apparatus of a turboprop based turboprop according to claim 1, comprising the steps of:

the sound wheel (6) and the propeller are coupled together and work together with the engine, the magnetic induction probe (7) responds to the passing of a plurality of regular teeth (1), first marking teeth (2) and second marking teeth (3) which are evenly spaced along the circumferential direction on the outer circumferential surface of the sound wheel to generate associated pulse signals and transmits the pulse signals to the signal processing module (9), the signal processing module (9) carries out the processes of denoising, amplifying, shaping, amplitude limiting and negative voltage filtering on the pulse signals collected from the magnetic induction probe (7) so as to obtain positive square wave signals, the square wave signals are directly transmitted to the embedded on-chip programmable system through the first connecting end of the signal conditioning circuit, the embedded on-chip programmable system can read rising edge time or falling edge time from the square wave signals by using codes with specific functions written by software for data processing and storage, and read out the expected delay, the specific delay and the average value of the first specific time and the second specific time, so as to calculate the rotating speed, the propeller pitch and the phase angle of the current data collection time; the square wave signal can also be transmitted to the F/D conversion circuit through the second connecting end of the signal conditioning circuit, the F/D conversion circuit converts the frequency quantity of the square wave signal into a digital quantity of the rotating speed, and finally the digital quantity is transmitted to the embedded on-chip programmable system, and the rotating speed, the propeller pitch and the phase angle are transmitted out through the bus interface.

Images