CN112697438B - Turboprop engine pitch-phase angle-rotating speed measuring device and method based on tone wheel - Google Patents
Turboprop engine pitch-phase angle-rotating speed measuring device and method based on tone wheel Download PDFInfo
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Abstract
The invention relates to a device and a method for measuring a propeller pitch-phase angle-rotating speed of a turboprop based on a sound wheel, belonging to the field of control of aviation turboprops. The measuring device disclosed by the invention comprises: a tone wheel (6), a magnetic induction probe (7) and a signal processing module (9), the tone wheel (6) being coupled to the propeller, the magnetic induction probe (7) being capable of generating a signal in response to the passage of a plurality of regular teeth (1), first marker teeth (2) and second marker teeth (3) on the tone wheel (6), the signal processing module (9) being capable of determining the pitch, phase angle and rotational speed of the propeller, respectively, based on a specific delay, a specific time and an expected delay of a signal pulse. The herringbone marking teeth with the same mass as the conventional teeth (1) are adopted, so that the propeller pitch can be measured and can also be used as the reference position of a phase angle, the two symmetrical teeth have the effects of complementary correction of magnetoelectric detection signals and reduction of unbalance, the influence of random phase angle reference positions and vibration noise on measurement is overcome, and the measurement precision, the sensitivity and the working stability are improved.
Description
Technical Field
The invention relates to a device and a method for measuring a propeller pitch-phase angle-rotating speed of a turboprop based on a sound wheel, belonging to the field of control of aviation turboprops.
Background
The development of the aircraft engine control system is towards the direction from single-variable control to multi-variable control, and how to increase the number of the parameters measured by the sensors without increasing the number of the sensors so as to increase the safety of the aircraft control system and reduce the weight of the aircraft, which puts high requirements on the multi-parameter measurement of the single sensor. In modern turboprop aircraft, a multivariable control system is mostly adopted, and the propeller pitch, the phase angle and the rotating speed of a propeller need to be measured in real time to enable the aircraft to fly stably.
At present, in China, the pitch, phase angle and rotating speed of turboprop engines are mostly separated and independent sensors, for example, a patent with publication number CN105486220A discloses a pitch measuring device, which adopts an eddy current sensor for detecting displacement change of a measured body corresponding to the pitch angle change of a blade, converting the displacement change into an electric signal and outputting the electric signal to an engine control box, and finally processing the signal to only calculate the pitch; in the prior art, a method for measuring the rotating speed by a speed measuring motor is available, namely, an alternating-current voltage signal of the speed measuring motor of a speed measuring sensor is collected, the frequency of the alternating-current voltage signal is in direct proportion to the rotating speed of an engine, the rotating speed of a rotor can be obtained by measuring the frequency or the period of the alternating-current voltage signal, but the measurement of the other two parameters cannot be carried out; for another example, among the rotation speed sensors generally used in an aircraft engine, the magnetoelectric rotation speed sensor with a sound wheel has the characteristics of simple structure and high precision, and is most widely applied, but currently, only the measurement of the rotation speed can be realized, the measurement of the propeller phase angle of a turboprop engine is still in the test stage, and a method for marking the phase angle reference position by embedding a high-magnetism material on the sound wheel is provided domestically, so that the measurement of double parameters can be realized, but the problem of rotor unbalance exists, and balance weight needs to be carried out.
In summary, the methods using multi-parameter and multi-sensor measurement increase mutual interference between sensor hardware devices and connecting lines, which is very undesirable in the field of aviation where requirements on aircraft weight and safety are very strict, and there is a need for a measuring apparatus without mutual interference between multi-sensors, which can measure three parameters of pitch, phase angle and rotation speed with high precision.
Disclosure of Invention
The invention aims to provide a device and a method for measuring a propeller pitch-phase angle-rotating speed of a turboprop engine based on a tone wheel, aiming at realizing high-precision and sensitivity measurement of the propeller pitch, the phase angle and the rotating speed only by using a magnetoelectric sensor with the tone wheel, and the tone wheel structure has good static and dynamic balance characteristics.
In order to achieve the purpose, the invention provides the following technical scheme:
turboprop engine pitch-phase angle-rotational speed measuring device based on phonic wheel includes: the pitch wheel comprises a plurality of regular teeth which are uniformly spaced in the circumferential direction and arranged on the outer circumferential surface of the pitch wheel, and a first mark tooth and a second mark tooth which are arranged on the outer surface, wherein the first mark tooth and the second mark tooth are respectively closer to two adjacent regular teeth in the circumferential direction, the initial phase angle reference position of the propeller is represented by the vertex angle boundary line position of the first mark tooth and the second mark tooth, the vertex angle position of the first mark tooth and the second mark tooth is represented as the pitch reference position of the propeller, and the pitch wheel is configured to rotate and move axially along with the propeller during the operation of the turboprop;
the magnetic induction probe is fixed on a stationary part of the engine, is adjacent to the tone wheel and is configured to respond to the passing of the conventional teeth and the marking teeth to generate a signal, and the signal comprises a plurality of signal pulses, wherein the occurrence timing of the plurality of signal pulses corresponds to the passing timing of the plurality of conventional teeth, the first marking teeth and the second marking teeth during the rotation of the tone wheel;
the signal processing module coupled to the magnetic sensing probe 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;
identifying a first particular pulse associated with the first marker tooth from within the plurality of signal pulses, the particular pulse having a shorter delay than the expected delay;
determining, based on a first particular pulse, a particular delay of a second particular pulse associated with the second marking tooth that occurs consecutively therewith, the particular delay representing a time interval of the first and second particular pulses;
determining a circumferential distance of said first and second marked teeth for an axial position of the propeller based on the specific delays of said first and second specific pulses associated with said first and second marked teeth, typically taking the apex position of the first and second marked teeth to be 0 pitch, so that said circumferential distance can be converted to the pitch of the propeller according to the angular relationship of the first and second marked teeth;
the method comprises the steps that the current data acquisition time is determined based on the time average value of first specific time and second specific time generated by a first specific pulse and a second specific pulse, and the phase angle of a magnetic induction probe relative to the vertex angle boundary line position of a first marking tooth and a second marking tooth, namely the phase angle of a propeller, eliminates the error of random reference position and vibration noise caused by only using one marking helical tooth on the phase angle measurement precision;
and calculating the propeller rotation speed based on the expected delay.
The structure of the sound wheel comprises teeth, a cylinder and a through hole, the thickness of the sound wheel is larger than or equal to the variation range of the blade pitch, so that 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 parallel to the axis of the sound wheel, the through hole is used for being sleeved on a rotating shaft of a propeller and rotates and axially moves together with the propeller, the volume and the mass of each of the first marking teeth and the second marking teeth are half of the volume and the mass of any other conventional teeth, the first marking teeth and the second marking teeth form the same angle of alpha degrees with the parallel line of the conventional teeth arranged in the circumferential direction, the two symmetrical teeth form complementary differential dual-gain sensitivity, and have the effects of complementary correction of a magnetoelectric detection signal and reduction of unbalance, so that the measurement precision, the sensitivity and the static and dynamic balance characteristics of a rotor are improved, and the static and dynamic balance characteristics of the rotor of the sound wheel are not caused by the special structure of the marking teeth and special high magnetic material, and the problem of the static and dynamic balance weight of the rotor of the sound wheel is solved.
The turboprop engine pitch-phase angle-rotating speed measuring device based on the sound wheel is characterized in that the signal processing module comprises: the signal conditioning circuit is used for accessing the magnetic induction probe and is provided with a first connecting end and a second connecting end, and 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.
The measuring method of the turboprop engine pitch-phase angle-rotating speed measuring device based on the tone wheel is characterized by comprising the following steps of:
the tone wheel and the propeller are coupled together and work together with the engine, the magnetic induction probe responds to the passing of a plurality of conventional teeth, first marking teeth and second marking teeth which are evenly spaced along the circumferential direction on the outer circumferential surface of the tone wheel to generate associated pulse signals and transmits the pulse signals to the signal processing module, the signal processing module carries out the processes of denoising, amplifying and shaping, amplitude limiting and negative voltage filtering on the pulse signals collected from the magnetic induction probe 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, and 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, reads out the expected delay, the specific delay and the mean value of the first specific time and the second specific time, and further calculates the pitch, phase angle and rotating speed 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 frequency quantity of the square wave signal is converted into the digital quantity of the rotating speed in the F/D conversion circuit, 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.
The code of the specific function enables the algorithm to have good robustness by setting a threshold value e related to the size of the marked teeth, and needs to store the expected delay of the latest moment, the specific delay and the mean value of the first specific time and the second specific time in real time in consideration that the data acquisition moment is not necessarily the moment of generating the specific pulse, and the pitch, the phase angle and the rotating 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 | e, the storage specific delay T C ＝T 3 -T 2 Time mean value T of first specific time and 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, if false, returning to the step 2.
Compared with the prior art, the invention has the advantages that: the cylindrical voice wheel structure with herringbone mark teeth and approximately uniform mass has good light-mass rotor static and dynamic balance characteristics, the problem of rotor static and dynamic balance counterweight of the voice wheel due to the special structure and special high-magnetic material of the mark teeth does not exist, and the manufacturing process is simplified, so that the cost is reduced; the first and second symmetrical marking teeth form complementary differential double-gain sensitivity, and have the function of complementary correction of magnetoelectric detection signals, overcome the influence of random phase angle reference positions and vibration noise of single-marking helical teeth on the measurement precision, and improve the measurement precision, the sensitivity and the working stability, so the device not only ensures the measurement precision while measuring three parameters of a pitch angle, a phase angle and a rotating speed, but also reduces the difficulty of processing and manufacturing.
Drawings
Fig. 1 is a perspective view and a left side view of the structure of the present invention.
Fig. 2 is a block diagram of a signal processing module according to the present invention.
Fig. 3 is a corresponding diagram of the pulse signal and the circumferential tooth profile development of the propeller at a certain axial position.
FIG. 4 is a schematic diagram of the present invention for conditioning a pulse signal into a square wave signal.
FIG. 5 is a logic flow diagram of specific function code of the present invention.
In the figure: 1-conventional teeth, 2-first marking teeth, 3-second marking teeth, 4-cylinder, 5-through hole, 6-tone wheel, 7-magnetic induction probe, 8-lead, 9-signal processing module and 10-bus interface.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, in an embodiment of the present invention, a pitch-phase angle-rotation speed measuring apparatus for a turboprop engine based on a sound wheel includes: a tone wheel 6, a magnetic induction probe 7 and a signal processing module 9, the tone wheel including a plurality of regular teeth 1 uniformly spaced in a circumferential direction provided on an outer circumferential surface of the tone wheel and first and second flag teeth 2 and 3 provided on the outer surface, the first and second flag teeth 2 and 3 being respectively closer to some of the regular teeth 1 adjacent thereto in a circumferential position and representing a prime phase angle reference position of the propeller by a vertex angle boundary position of the first and second flag teeth 2 and 3, the vertex angle position of the first and second flag teeth 2 and 3 being represented as a pitch reference position of the propeller, the tone wheel 6 being configured to rotate in an "E" direction and move axially in an "F" direction together with the propeller during operation of the turboprop;
the structure of the sound wheel comprises teeth, a cylinder 4 and a through hole 5, and the structure of the sound wheel teeth is characterized in that the thickness of the sound wheel is more than or equal to the variation range of a propeller pitch, so a cylindrical sound wheel structure with a certain thickness is adopted to reduce the weight of the sound wheel, a plurality of conventional teeth 1 are arranged in parallel in the circumferential direction and are parallel to the axis of the sound wheel 6 and are also parallel to a line D, the through hole is sleeved on a rotating shaft of a propeller and rotates along the direction E and moves axially along the direction F together with the propeller, the volumes and the masses of the first marking teeth 2 and the second marking teeth 3 are half of any other conventional teeth 1, the first marking teeth 2 and the second marking teeth 3 form the same angle a degrees with the line D, the two symmetrical teeth form complementary differential double-gain, the effects of complementary correction of magnetoelectric detection signals and reduction of unbalance degrees are achieved, and the problems of high rotor dynamic balance sensitivity, high static balance and high rotor static dynamic balance accuracy are solved due to the special structure of the marking teeth and special material of the marking teeth.
Referring to fig. 3, said magneto resistive probe 7, fixed to the stationary part of the engine, is adjacent to said tone wheel 6 and is configured for generating a signal in response to the passage of said regular teeth 1 and said marking teeth, said signal comprising a plurality of signal pulses, the timing of the occurrence of said plurality of signal pulses corresponding to the timing of the passage of said plurality of regular teeth 1, first marking teeth 2 and second marking teeth 3 during the rotation of said tone wheel 6, the peaks and valleys of the tone wheel causing a variation of the tone wheel to permanent magnet gap δ when the tone wheel is rotated by the propeller, thereby causing a variation of the magnetic flux in the magnetic circuit formed by the permanent magnets, the magneto resistance decreasing when the first side of the tooth peak is close to the magneto resistive probe, the derivative of the magnetic flux being positive, thereby generating a signal pulse; the gaps on the top surfaces of the tooth peaks are the same, so that no induced voltage is generated, and the voltage is 0; when the second side of the tooth peak is close to the magnetic induction probe, the magnetic resistance is increased, and the derivative of the magnetic flux is negative, so that a signal pulse in the opposite direction is generated;
referring to fig. 2, the pitch-phase angle-rotation speed measuring device for a turboprop based on a sound wheel is characterized in that the signal processing module 9, which is implemented without an F/D conversion circuit, includes: the magnetic induction probe 7 is connected with the signal conditioning circuit, the output of the signal conditioning circuit is directly connected with the embedded on-chip programmable system, and data are sent out through a bus interface.
The signal processing module 9, which is coupled to the magnetic induction probe 7 for obtaining the signal, and is configured for:
referring to fig. 4, the signal conditioning circuit in the signal processing module 9 performs denoising, amplification and shaping, amplitude limiting, and negative voltage filtering processing through a diode on the collected pulse signal at the upper part of fig. 4, so as to obtain a square wave positive voltage signal at the lower part of fig. 4;
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 particular pulse having a shorter delay, T, than the expected delay A ＞T B ；
Determining, based on the first specific pulse, the specific delay T of the second specific pulse associated with said second marking tooth 3 that occurs consecutively thereto C The specific delay represents a time interval of the first and second specific pulses;
based on the specific delay T of the first and second specific pulses associated with the first and second marking teeth 2, 3 C Determining the circumferential distance of the first and second mark teeth 2 and 3 at a certain axial position of the propeller, and generally taking the vertex angle position of the first and second mark teeth 2 and 3 as 0 pitch, so that the circumferential distance can be converted into the pitch of the propeller according to the angular relation of the first and second mark teeth 2 and 3;
the method comprises the steps that the current data acquisition time is determined based on the time average value of first specific time and second specific time generated by first specific pulse and second specific pulse, and the phase angle of a magnetic induction probe relative to the vertex angle boundary position of a first marking tooth 2 and a second marking tooth 3, namely the phase angle of a propeller, eliminates the error of random reference position and vibration noise caused by only using one marking helical tooth on the phase angle measurement precision;
and calculating the propeller rotation speed based on the expected delay.
Referring to fig. 2, the method for measuring the pitch-phase angle-rotation speed of the turboprop based on the sound wheel is characterized by being implemented without an F/D conversion circuit and comprising the following steps:
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 mark teeth 2 and second mark 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 square wave signals, the square wave signals are directly transmitted to the embedded on-chip programmable system through 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, reads out the expected delay, the specific delay and the average value of the first specific time and the second specific time, and further calculates the rotating speed, the propeller pitch and the phase angle of the current data collection time, and sends out the rotating speed, the propeller pitch and the phase angle through a bus interface.
Referring to fig. 5, the code of the specific function can make the algorithm robust by setting a threshold e related to the size of the marked teeth, and considering that the data acquisition time is not necessarily the time of the specific pulse generation, the expected delay, the specific delay, and the mean value of the first and second specific time of the latest time need to be stored in real time, and the pitch, the phase angle, and the 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 the rising edge time T of three continuous square 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 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 | e, the storage specific delay T C ＝T 3 -T 2 Time mean value T of first specific time and second specific time S ＝(T 2 +T 3 ) 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 of rotation speed A And finally ending, if false, returning to the step 2.
The working principle of the invention is as follows: the magnetic induction probe 7 consists of an induction coil and a permanent magnet material, the change of the gap delta between the tone wheel and the permanent magnet is caused in the rotation process of the tone wheel, the magnetic resistance and the gap size are directly related, the time change rate of the magnetic flux is represented, and the changing magnetic field can generate changing current, so the magnetic induction probe 7 can respond to the associated pulse signals generated by the passing of a plurality of conventional teeth 1, a first mark tooth 2 and a second mark tooth 3 on the tone wheel, and the expected delay T is calculated through a signal processing module 9 A A specific delay T C Time mean T of the first and second specific times S And further calculating the rotating speed and the phase angle. For the pitch, the pitch of the first marking teeth 2 and the second marking teeth 3 is different in the axial positions of different propellers in the structure of the tone wheel, the pitch angle position of the first marking teeth 2 and the second marking teeth 3 is generally taken as 0 pitch, so the pitch can be calculated through trigonometric function conversion,
the functions are as follows: high-precision measurement of the pitch, phase angle and rotational speed of the propeller can be carried out by using only magneto-electric sensors with tone wheels, and the measured parameters of the sensors are provided for the control of the turboprop.
The present invention is not limited to the above embodiments, and based on the technical solutions disclosed in the present invention, those skilled in the art can make some simple modifications, equivalent changes and modifications to some technical features without creative efforts based on the disclosed technical contents, and all fall into 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011542906.8A CN112697438B (en) | 2020-12-23 | 2020-12-23 | Turboprop engine pitch-phase angle-rotating speed measuring device and method based on tone wheel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011542906.8A CN112697438B (en) | 2020-12-23 | 2020-12-23 | Turboprop engine pitch-phase angle-rotating speed measuring device and method based on tone wheel |
Publications (2)
| Publication Number | Publication Date |
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| CN113959722B (en) * | 2021-10-28 | 2023-06-09 | 南京航空航天大学 | Torque-pitch-phase angle-rotating speed integrated measurement device and method based on tone wheel |
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