A method and apparatus for simulating an aircraft engine speed sensor

Abstract

This invention discloses a method and apparatus for simulating an aero-engine speed sensor, relating to the field of testing equipment technology. The invention includes a magnetoelectric speed sensor composed of a permanent magnet, a ferromagnetic core, an induction coil, and a tuning wheel. The permanent magnet generates a magnetic field of a certain intensity. When the rotor rotates, the gap between the magnetic head and the rotor's external teeth changes proportional to the rotational speed, causing a corresponding change in the magnetic reluctance in the magnetic circuit formed by the magnetic head and rotor. The aero-engine speed sensor simulation apparatus can accurately generate AC sinusoidal signals of specified frequency and amplitude, and provides electrical interface characteristics consistent with real sensors. This apparatus provides an accurate signal source for the debugging and testing of engine electronic controllers and can be applied in semi-physical simulation and all-electric simulation experiments of engine control systems, providing the engine control system with a speed signal consistent with that of a real sensor.

Description

Technical Field

[0001] This invention relates to the field of testing equipment technology, and specifically to a method and apparatus for simulating an aero-engine speed sensor. Background Technology

[0002] The aircraft engine control system is responsible for receiving and processing signals from various sensors. The parameters that the sensors are sensitive to play an important role in the automatic control of the aircraft and the engine. When testing equipment, the frequency and amplitude of the test cannot accurately generate AC sinusoidal signals, which are inconsistent with the electrical interface characteristics of the real sensors. During the debugging of the engine electronic controller, it cannot provide an accurate signal source. In semi-physical simulation and all-electric simulation tests, the speed signal provided to the engine control system is inconsistent with the real sensor. Summary of the Invention

[0003] The purpose of this invention is to solve the problem that the signal provided by the aircraft engine speed sensor during the testing process is inconsistent with that of the actual sensor. This invention provides an aircraft engine speed sensor simulation method and device.

[0004] To achieve the above objectives, the present invention specifically adopts the following technical solution:

[0005] A method for simulating an aircraft engine speed sensor includes the following steps:

[0006] S1. The sound wheel is mounted on the shaft being measured and rotates with it. The sensor coil outputs a periodic, symmetrical sinusoidal pulse voltage signal at both ends.

[0007] S2. The size and rate of change of the magnetic gap between the sensor and the sound wheel directly affect the permeability of the ferromagnetic material, and thus affect the output electromotive force of the coil.

[0008] S3. When the air gap increases or its change slows down, the permeability of the ferromagnetic material decreases, the magnetic reluctance of the magnetic circuit increases, the magnetic flux decreases, and the induced electromotive force decreases. When the air gap decreases or its change accelerates, the permeability of the ferromagnetic material increases, the magnetic reluctance of the magnetic circuit decreases, the magnetic flux increases, and the induced electromotive force increases. Sensitivity is high when the air gap is small or changes rapidly; sensitivity is low when the air gap is large or changes slowly.

[0009] S4. The engine electronic controller processes the speed sensor signal, including circuit breakage BIT check and speed signal acquisition. The electronic controller performs BIT check by measuring the voltage borne by the sensor in the circuit. Based on the voltage borne by the sensor coil, the corresponding threshold is set in the controller software.

[0010] S5. If the sensor has an open circuit or open circuit fault, the voltage shared by the sensor will exceed the set threshold. The controller will then determine that the sensor has an open circuit or open circuit fault and take corresponding measures.

[0011] S6. The electronic controller receives sensor signals and aircraft commands, and after calculation, controls the actuators to operate according to a predetermined control law. The controller's acquisition period for the speed signal is approximately 10ms, and the acquisition accuracy of the speed signal is required to be no less than ±0.05% FS.

[0012] S7. The signal simulation device must provide the engine electronic controller with a signal consistent with the real speed sensor, and the electrical interface characteristics must also be consistent with the real sensor. Furthermore, the signal response time and conversion accuracy must meet the requirements of the electronic controller.

[0013] S8, the speed signal simulation device is designed based on a digital programmable waveform generator (DDS) and a digital amplitude modulation circuit (DAC). The former generates a sine wave signal with a fixed amplitude and continuously adjustable frequency, while the latter adjusts the amplitude of the signal generated by the former. The combination of the two produces a sine wave with continuously adjustable frequency and amplitude.

[0014] S9, DDS, and DAC all have a serial peripheral (SPI) interface. The analog device obtains the target instruction containing the frequency and amplitude information of the signal to be generated from the host computer. DDS parses the frequency modulation instruction and outputs a sine signal of the specified frequency as required. The sine signal is then output to the signal amplifier AMP after passing through a high-pass filter (HPF).

[0015] S10 and DAC analyze the amplitude modulation command and perform analog multiplier digital amplitude modulation on the signal after HPF as required. The amplitude-modulated signal is filtered by a low-pass filter (LPF) and then output to the transformer. The transformer isolates the signal and outputs it as a speed sensor signal provided to the engine electronic controller.

[0016] The internal circuitry of S11 and AD9833 consists of both digital and analog components. The sine lookup table contains digital amplitude information for one cycle of a sine wave, with each address corresponding to a phase point within the 0°–360° range of the sine wave. The lookup table maps the input address phase information into a digital signal S(n) representing the sine wave amplitude. This signal is then converted into a stepped wave S(t) by a D / A converter, and smoothed by a low-pass filter to obtain the synthesized signal waveform. Its shape depends on the amplitude code stored in the waveform ROM; therefore, DDS can generate arbitrary waveforms. The output sine wave frequency is: fOUT = M(fMCK / 228), where M is the frequency control word, given by external programming, and its range is 0 ≤ M ≤ 228-1.

[0017] S12 and SPI bus transmit the code value corresponding to the frequency to be generated to DDS, and control DDS to output a sine wave signal of a specified frequency. The signal amplitude is 620mV at high level and 40mV at low level, which is a sine wave signal that does not cross zero.

[0018] The output signals of S13 and DDS are conditioned into zero-crossing sine signals by an active high-pass filter. The non-zero-crossing sine signal output from pin 10 of AD9833 is filtered by a high-pass filter to block DC and pass AC, becoming a zero-crossing sine signal that enters the positive input terminal of the non-inverting amplifier OP07. After the first stage of amplification, it is connected to the analog multiplier.

[0019] S14. To ensure the safety of the electronic controller, the simulator uses a TamuraMET-37 audio transformer to achieve the final signal output, ensuring electrical isolation between the signal simulation device and the controller.

[0020] Furthermore, according to S5, for the controller, sensor impedance is an important parameter for determining whether the sensor is functioning properly.

[0021] Furthermore, based on S7 and referencing the signal parameters of various sensors, and considering the need to cover the signal characteristics of commonly used magnetoelectric speed sensors as much as possible, the design requirements for the signal simulator are determined as follows:

[0022] (1) Generates AC sinusoidal signals with continuously adjustable frequency and amplitude, with a response time of ≤5ms;

[0023] (2) Generation frequency range: (0~5000)Hz, accuracy: better than ±0.01%;

[0024] (3) Output signal amplitude: (0.55~50)VP-P range continuously adjustable;

[0025] (4) Output port DC resistance: (10~460)Ω.

[0026] Furthermore, according to S11, the internal circuit of AD9833 includes two parts: digital devices and analog devices. It mainly consists of a phase accumulator (composed of an adder and a phase register), a ROM waveform lookup table, a digital-to-analog converter (DAC), and a low-pass filter (LPF). Here, M is the frequency control word, and FMCLK is the clock frequency. The phase accumulator accumulates in steps M under the control of the clock FMCLK. The output of the phase register is added to the phase control word and then input into the address of the sine lookup table.

[0027] Furthermore, according to S12, the AD9833 has a standard SPI interface that uses an external clock to write data or control information to the device.

[0028] Furthermore, according to S14, the input / output signal ratio of the audio transformer is 600:600, and the gain flatness is ±0.5dB in the (0~5000)Hz frequency band, ensuring good stability across the entire frequency range.

[0029] An aircraft engine speed sensor simulation device, comprising:

[0030] A magnetoelectric speed sensor consists of a permanent magnet, a ferromagnetic core, an induction coil, and a sound wheel;

[0031] A permanent magnet can generate a magnetic field of a certain strength. When the rotor rotates, the gap between the magnetic head and the external teeth of the rotor changes, which is proportional to the rotational speed, thereby causing a corresponding change in the magnetic reluctance in the magnetic circuit formed by the magnetic head and the rotor.

[0032] A ferromagnetic core converts magnetic signals into electrical signals, enabling the measurement of position and motion.

[0033] An induction coil is used to increase the strength of a magnetic field; an iron core concentrates the magnetic lines of force around the coil.

[0034] The tone wheel is mounted on the shaft being measured and rotates with it.

[0035] The beneficial effects of this invention are as follows:

[0036] 1. This invention can accurately generate AC sinusoidal signals of specified frequency and amplitude, and provides electrical interface characteristics consistent with those of real sensors.

[0037] 2. The present invention provides an accurate signal source for the debugging and testing of engine electronic controllers, and is applied to the semi-physical simulation and all-electric simulation tests of engine control systems, providing the engine control system with a speed signal consistent with the real sensor. Attached Figure Description

[0038] Figure 1 This is a waveform diagram of the sensor signal of the present invention;

[0039] Figure 2 This is a schematic diagram showing the relationship between the peak value, magnetic gap, and rotational speed of the present invention;

[0040] Figure 3 This is a schematic diagram of the speed signal simulation device of the present invention;

[0041] Figure 4 This is a basic structural schematic diagram of the AD9833 of this invention;

[0042] Figure 5 This is a signal waveform diagram of the AD9833 of this invention;

[0043] Figure 6 This is a schematic diagram of the digital amplitude modulation circuit of the present invention;

[0044] Figure 7 This is a schematic diagram of the digital amplitude modulation circuit of the present invention;

[0045] Figure 8 This is a schematic diagram of the signal output of the present invention;

[0046] Figure 9 This is a schematic diagram of the principle of the magnetoelectric speed sensor of the present invention.

[0047] Reference numerals in the attached diagram: 1. Sound wheel; 2. Ferromagnetic core; 3. Magnet; 4. Induction coil. Detailed Implementation

[0048] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings.

[0049] like Figure 1 As shown, a simulation method for an aero-engine speed sensor is provided, wherein the output signal waveform of the magnetoelectric speed sensor is related to the tooth profile of the sound wheel, the magnetic gap δ, and the magnetic permeability μ of the ferromagnetic material, and the sensor coil outputs a periodic, symmetrical sinusoidal pulse voltage signal.

[0050] like Figure 2 As shown, the size and rate of change of the magnetic gap between the sensor and the sound wheel directly affect the permeability of the ferromagnetic material, and thus affect the output electromotive force of the coil.

[0051] When the air gap increases or its change slows down, the permeability of the ferromagnetic material decreases, the magnetic reluctance of the magnetic circuit increases, the magnetic flux decreases, and the induced electromotive force decreases. When the air gap decreases or its change accelerates, the permeability of the ferromagnetic material increases, the magnetic reluctance of the magnetic circuit decreases, the magnetic flux increases, and the induced electromotive force increases.

[0052] The sensitivity is high when the air gap is small or changes rapidly; the sensitivity is low when the air gap is large or changes slowly.

[0053] Among them, the sensor coil impedance: The engine electronic controller's processing of the speed sensor signal includes circuit open-circuit (BIT) checks and speed signal acquisition. The electronic controller performs BIT checks by measuring the voltage borne by the sensor in the circuit. Based on the voltage borne by the sensor coil, a corresponding threshold is set in the controller software. If the sensor has an open circuit or open-circuit fault, the voltage borne by the sensor will exceed the set threshold, and the controller will determine that the sensor has an open circuit or open-circuit fault, and thus take corresponding measures.

[0054] The engine typically employs a digital electronic control system. The electronic controller receives sensor signals and aircraft commands, and after calculation, controls the actuators according to predetermined control laws. The controller acquires the speed signal approximately every 10ms, and the acquisition accuracy of the speed signal is required to be no less than ±0.05%FS.

[0055] In the simulation test, the signal simulation device needs to provide the engine electronic controller with a signal consistent with that of the actual speed sensor. The electrical interface characteristics must also be consistent with the actual sensor, and the signal response time and conversion accuracy must meet the requirements of the electronic controller. Based on the preceding analysis and referring to the signal parameters of various sensor types, and considering the need to cover the signal characteristics of commonly used magnetoelectric speed sensors as much as possible, the design requirements for the signal simulator are determined as follows:

[0056] (1) Generates AC sinusoidal signals with continuously adjustable frequency and amplitude, with a response time of ≤5ms;

[0057] (2) Generation frequency range: (0~5000)Hz, accuracy: better than ±0.01%;

[0058] (3) Output signal amplitude: (0.55~50)VP-P range continuously adjustable;

[0059] (4) Output port DC resistance: (10~460)Ω.

[0060] like Figure 3 As shown, the speed signal simulation device is designed based on a digitally programmable waveform generator (DDS) and a digital amplitude modulation circuit (DAC). The former generates a sine wave signal with a fixed amplitude and continuously adjustable frequency, while the latter adjusts the amplitude of the signal generated by the former. The combination of the two produces a sine wave with continuously adjustable frequency and amplitude.

[0061] Both the DDS and DAC have a Serial Peripheral Interface (SPI). The analog device obtains the target instruction containing the frequency and amplitude information of the signal to be generated from the host computer. The DDS parses the frequency modulation instruction and outputs a sine wave signal of the specified frequency as required. The sine wave signal is then passed through a high-pass filter (HPF) and output to the signal amplifier (AMP). The DAC parses the amplitude modulation instruction and performs analog multiplication on the signal after HPF for digital amplitude modulation as required. The amplitude-modulated signal is then filtered by a low-pass filter (LPF) and output to a transformer. The transformer isolates the signal before outputting it as the speed sensor signal provided to the engine electronic controller.

[0062] like Figure 4 As shown, the internal circuitry of the AD9833 consists of both digital and analog components.

[0063] It mainly consists of a phase accumulator (composed of an adder and a phase register), a ROM waveform lookup table, a digital-to-analog converter (DAC), and a low-pass filter (LPF);

[0064] Where M is the frequency control word, FMCLK is the clock frequency, the phase accumulator accumulates in steps M under the control of the clock FMCLK, and the output of the phase register is added to the phase control word and then input into the address of the sine lookup table.

[0065] The sine lookup table contains digital amplitude information for a single-cycle sine wave, with each address corresponding to a phase point within the 0° to 360° range of the sine wave.

[0066] The lookup table maps the input address phase information into a digital signal S(n) with sinusoidal amplitude, which is then converted into a stepped wave S(t) by a D / A converter and smoothed by a low-pass filter to obtain the synthesized signal waveform.

[0067] Its shape depends on the amplitude code stored in the waveform ROM, therefore, DDS can generate arbitrary waveforms. The output sine wave frequency is: fOUT = M(fMCK / 228);

[0068] Where M is the frequency control word, which is given by external programming and its range is 0≤M≤228-1.

[0069] like Figure 5 As shown, the AD9833 has a standard SPI interface, which uses an external clock to write data or control information to the device;

[0070] The SPI bus transmits the code value corresponding to the frequency to be generated to the DDS, which controls the DDS to output a sine wave signal of a specified frequency. The signal amplitude is 620mV at the high level and 40mV at the low level, which is a sine wave signal that does not cross zero.

[0071] like Figure 6 and Figure 7 As shown, the DDS output signal is conditioned into a zero-crossing sine wave signal by an active high-pass filter, such as... Figure 7 As shown, the zero-crossing sine signal output from pin 10 of AD9833 passes through a high-pass filter, which blocks DC and allows AC to pass through, transforming it into a zero-crossing sine signal that enters the positive input of the non-inverting amplifier OP07. After the first stage of amplification, it is connected to the analog multiplier.

[0072] like Figure 8As shown, to ensure the safety of the electronic controller, the simulator uses a TamuraMET-37 audio transformer to achieve the final signal output, ensuring electrical isolation between the signal simulation device and the controller. The audio transformer has an input / output signal ratio of 600:600 and a gain flatness of ±0.5dB in the (0~5000)Hz frequency band, ensuring good stability across the entire frequency range.

[0073] like Figure 9 As shown, an aircraft engine speed sensor simulation device includes:

[0074] A magnetoelectric speed sensor consists of a permanent magnet, a ferromagnetic core, an induction coil, and a sound wheel;

[0075] A permanent magnet can generate a magnetic field of a certain strength. When the rotor rotates, the gap between the magnetic head and the external teeth of the rotor changes, which is proportional to the rotational speed, thereby causing a corresponding change in the magnetic reluctance in the magnetic circuit formed by the magnetic head and the rotor.

[0076] A ferromagnetic core converts magnetic signals into electrical signals, enabling the measurement of position and motion.

[0077] An induction coil is used to increase the strength of a magnetic field; an iron core concentrates the magnetic lines of force around the coil.

[0078] The tone wheel is mounted on the shaft being measured and rotates with it.

[0079] The magnetoelectric speed sensor consists of a permanent magnet, a ferromagnetic core, an induction coil, and a sound wheel, with the sound wheel mounted on the shaft being measured and rotating with it.

[0080] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A method for simulating the rotational speed of an aero-engine, characterized in that: Includes the following steps: S1. The sound wheel is mounted on the shaft being measured and rotates with it. The sensor coil outputs a periodic, symmetrical sinusoidal pulse voltage signal at both ends. S2. The size and rate of change of the magnetic gap between the sensor and the sound wheel directly affect the permeability of the ferromagnetic material, and thus affect the output electromotive force of the coil. S3. When the magnetic gap increases or changes slowly, the permeability of the ferromagnetic material decreases, the magnetic reluctance of the magnetic circuit increases, the magnetic flux decreases, and the induced electromotive force decreases. When the air gap decreases or changes rapidly, the permeability of the ferromagnetic material increases, the magnetic reluctance of the magnetic circuit decreases, the magnetic flux increases, and the induced electromotive force increases. The sensitivity is high when the air gap is small or changes rapidly, and low when the air gap is large or changes slowly. S4. The engine electronic controller processes the speed sensor signal, including circuit breakage BIT check and speed signal acquisition. The electronic controller performs BIT check by measuring the voltage borne by the sensor in the circuit. Based on the voltage borne by the sensor coil, the corresponding threshold is set in the controller software. S5. If the sensor has an open circuit or open circuit fault, the voltage shared by the sensor will exceed the set threshold. The controller will then determine that the sensor has an open circuit or open circuit fault and take corresponding measures. S6. The electronic controller receives sensor signals and aircraft commands, and controls the actuators to move according to a predetermined control law after calculation. The controller's acquisition period for the speed signal is 10ms, and the acquisition accuracy of the speed signal is required to be no less than ±0.05%FS. S7. The signal simulation device must provide the engine electronic controller with a signal consistent with the real speed sensor, and the electrical interface characteristics must also be consistent with the real sensor. Furthermore, the signal response time and conversion accuracy must meet the requirements of the electronic controller. S8, the speed signal simulation device is designed based on a digital programmable waveform generator (DDS) and a digital amplitude modulation circuit (DAC). The former generates a sine wave signal with a fixed amplitude and continuously adjustable frequency, while the latter adjusts the amplitude of the signal generated by the former. The combination of the two produces a sine wave with continuously adjustable frequency and amplitude. S9, DDS, and DAC all have a serial peripheral SPI interface. The analog device obtains the target instruction containing the frequency and amplitude information of the signal to be generated from the host computer. DDS parses the frequency modulation instruction and outputs a sine signal of the specified frequency as required. The sine signal is output to the signal amplifier AMP after passing through the high-pass filter HPF. S10 and DAC analyze the amplitude modulation command and perform analog multiplier digital amplitude modulation on the signal after HPF as required. The amplitude-modulated signal is filtered by low-pass filter LPF and then output to transformer. The transformer isolates the signal and outputs it as a speed sensor signal provided to the engine electronic controller. The internal circuitry of S11 and AD9833 consists of both digital and analog components. The sine lookup table contains digital amplitude information for one cycle of a sine wave, with each address corresponding to a phase point within the 0° to 360° range of the sine wave. The lookup table maps the input address phase information into a digital signal S(n) of the sine wave amplitude. This signal is then converted into a stepped wave S(t) by a D / A converter and smoothed by a low-pass filter to obtain the synthesized signal waveform. The shape of this waveform depends on the amplitude code stored in the waveform ROM, thus allowing the DDS to generate arbitrary waveforms. The output sine wave frequency is fOUT = M(fMCK / 228), where M is the frequency control word, given by external programming, and its range is 0 ≤ M ≤ 227. S12 and SPI bus transmit the code value corresponding to the frequency to be generated to DDS, and control DDS to output a sine wave signal of a specified frequency. The signal amplitude is 620mV at high level and 40mV at low level, which is a sine wave signal that does not cross zero. The output signals of S13 and DDS are conditioned into zero-crossing sine signals by an active high-pass filter. The non-zero-crossing sine signal output from pin 10 of AD9833 is filtered by a high-pass filter to block DC and pass AC, becoming a zero-crossing sine signal that enters the positive input terminal of the non-inverting amplifier OP07. After the first stage of amplification, it is connected to the analog multiplier. S14. To ensure the safety of the electronic controller, the simulator uses a TamuraMET-37 audio transformer to achieve the final signal output, ensuring electrical isolation between the signal simulation device and the controller.

2. The method for simulating an aero-engine speed sensor according to claim 1, characterized in that, In S5, for the controller, sensor impedance is an important parameter for determining whether the sensor is functioning properly.

3. The method for simulating an aero-engine speed sensor according to claim 1, characterized in that, In step S7, referencing the signal parameters of various sensors and considering the need to cover the signal characteristics of commonly used magnetoelectric speed sensors as much as possible, the design requirements for the signal simulator are determined as follows: (1) Generates AC sinusoidal signals with continuously adjustable frequency and amplitude, with a response time of ≤5ms; (2) Generation frequency range: 0~5000Hz, accuracy: better than ±0.01%; (3) Output signal amplitude: continuously adjustable within the range of 0.55~50VP-P; (4) Output port DC resistance: 10~460Ω.

4. The method for simulating an aero-engine speed sensor according to claim 1, characterized in that, In S11, the internal circuit of AD9833 includes two parts: digital devices and analog devices. It consists of a phase accumulator, a ROM waveform lookup table, a digital-to-analog converter (DAC), and a low-pass filter (LPF). M is the frequency control word, and FMCLK is the clock frequency. The phase accumulator accumulates in steps M under the control of the clock FMCLK. The output of the phase register is added to the phase control word and then input into the address of the sine lookup table.

5. The method for simulating an aero-engine speed sensor according to claim 4, characterized in that, In S12, the AD9833 has a standard SPI interface and uses an external clock to write data or control information to the device.

6. The method for simulating an aero-engine speed sensor according to claim 1, characterized in that, In step S14, the input / output signal ratio of the audio transformer is 600:600, and the gain flatness is ±0.5dB in the 0~5000Hz frequency band, ensuring good stability across the entire frequency range.

7. An aircraft engine speed sensor simulation device, applied to the aircraft engine speed sensor simulation method according to any one of claims 1-6, characterized in that: include: A magnetoelectric speed sensor consists of a permanent magnet, a ferromagnetic core, an induction coil, and a sound wheel; A permanent magnet can generate a magnetic field of a certain strength. When the rotor rotates, the gap between the magnetic head and the external teeth of the rotor changes, which is proportional to the rotational speed, thereby causing a corresponding change in the magnetic reluctance in the magnetic circuit formed by the magnetic head and the rotor. A ferromagnetic core converts magnetic signals into electrical signals, enabling the measurement of position and motion. An induction coil is used to increase the strength of a magnetic field; an iron core concentrates the magnetic lines of force around the coil. The tone wheel is mounted on the shaft being measured and rotates with it.

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