An airborne fuel level measurement method, system, device, and medium

Abstract

The present application relates to fuel measurement technical field, specifically, it is a kind of airborne fuel liquid level measurement method, system, equipment and medium;First, according to the temperature value obtained, the number of excitation waves is set, and ultrasonic pulse signal is collected;Then, according to the ultrasonic pulse signal collected, time point sequence is calculated;Finally, according to time point sequence and the liquid level partition set, the current liquid level area is judged, if the current liquid level area is low liquid level area, then according to the ultrasonic wave flight time, the height of float ball immersed in fuel, the speed of sound, the mechanical blind area of transducer, the liquid level height is calculated;If the current liquid level area is high liquid level area, then according to the ultrasonic wave flight time, the length of sub-wave guide pipe, the mechanical blind area of sub-wave guide pipe, the height of float ball immersed in fuel, the mechanical blind area of main wave guide pipe, the liquid level height value is calculated, improve the measurement precision of aircraft in high and low temperature environment.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of fuel measurement, in particular to an airborne fuel liquid level measurement method, system, device and medium. BACKGROUND

[0002] At present, the airborne fuel liquid level measurement sensor mainly adopts a capacitive liquid level sensor. The capacitive liquid level measurement technology has been nearly a hundred years from invention to now, and is a very mature technology. Its advantages are simple structure, small measurement blind area, and adaptability to aircraft attitude tilt. However, due to the very small capacitance, the capacitive liquid level sensor is greatly affected by parasitic capacitance, bypass capacitance and electromagnetic interference, has low signal-to-noise ratio, and thus has weak anti-interference ability and low precision in theory. Compared with the capacitive liquid level sensor, the ultrasonic liquid level sensor has strong anti-interference ability, high signal-to-noise ratio, high measurement precision, light weight and other advantages, and is an aviation fuel liquid level measurement technology with great development prospects.

[0003] Although the ultrasonic liquid level sensor has been widely used in industry, it is used in static and quasi-static situations on the ground. In the field of aviation, the main problems and difficulties of the ultrasonic airborne fuel liquid level measurement system are as follows: due to the measurement normal line deviation of ultrasonic waves, the sensor cannot adapt to large attitude tilt and swing changes of the aircraft; the fuel liquid surface fluctuation caused by aircraft vibration will lead to unclear wave front directivity of ultrasonic waves, and seriously affect the measurement precision and reliability of the sensor. SUMMARY

[0004] The present application proposes an airborne fuel liquid level measurement method, system, device and medium to solve the problems that the above-mentioned sensor cannot adapt to large attitude tilt and swing changes of the aircraft, and seriously affects the measurement precision and reliability of the sensor. First, the number of excitation waves is set according to the obtained temperature value, and an ultrasonic pulse signal is collected. Then, the time point sequence is calculated according to the collected ultrasonic pulse signal. Finally, the current liquid level zone is determined according to the time point sequence and the set liquid level partition. If the current liquid level zone is a low liquid level zone, the liquid level height is calculated according to the ultrasonic flight time, the fuel immersion height of the float ball, the sound speed, and the mechanical blind zone of the transducer. If the current liquid level zone is a high liquid level zone, the liquid level height value is calculated according to the ultrasonic flight time, the length of the secondary wave guide tube, the mechanical blind zone of the secondary wave guide tube, the fuel immersion height of the float ball, and the mechanical blind zone of the primary wave guide tube, thereby improving the measurement precision of the aircraft in high and low temperature environments.

[0005] The present application specifically realizes the following contents:

[0006] An airborne fuel liquid level measurement method specifically includes the following steps:

[0007] Step S1: The number of excitation waves is set according to the obtained temperature value, and an ultrasonic pulse signal is collected.

[0008] Step S2: calculating a time point sequence according to the collected ultrasonic pulse signals;

[0009] Step S3: judging a current liquid level zone according to the time point sequence and a set liquid level partition, if the current liquid level zone is a low liquid level zone, calculating a liquid level height according to an ultrasonic wave flight time, a float ball immersion fuel height, a sound speed and a mechanical blind zone of a transducer, if the current liquid level zone is a high liquid level zone, calculating a liquid level height value according to the ultrasonic wave flight time, a secondary wave guide tube length, a secondary wave guide tube mechanical blind zone, the float ball immersion fuel height and a primary wave guide tube mechanical blind zone.

[0010] In order to better realize the present application, further, the step S1 specifically comprises the following steps:

[0011] Step S11: measuring a fuel temperature value and setting a number of excitation waves according to the fuel temperature value;

[0012] Step S12: obtaining an original ultrasonic pulse signal according to the set number of excitation waves;

[0013] Step S13: calling a Kalman filtering method to filter the original ultrasonic pulse signal to obtain a filtered ultrasonic pulse signal.

[0014] In order to better realize the present application, further, the step S2 specifically comprises the following steps:

[0015] Step S21: performing a power operation on the filtered ultrasonic pulse signal to obtain a power-operated ultrasonic pulse signal according to a set power parameter;

[0016] Step S22: calculating an echo phase difference according to an ultrasonic wave length, calling an envelope superposition method to superimpose ultrasonic pulse signals at different time points according to the phase difference to obtain an envelope-superimposed ultrasonic pulse signal;

[0017] Step S23: calling a comparison method to identify envelope wave peak time points of the envelope-superimposed ultrasonic pulse signal to obtain a time point sequence.

[0018] In order to better realize the present application, further, the step S3 specifically comprises the following steps:

[0019] Step S31: judging a current liquid level zone according to the time point sequence and a set liquid level partition, if the current liquid level zone is a low liquid level zone, calculating a liquid level height according to an ultrasonic wave flight time, a float ball immersion fuel height, a sound speed and a mechanical blind zone of a transducer, if the current liquid level zone is a high liquid level zone, calculating a liquid level height value according to the ultrasonic wave flight time, a secondary wave guide tube length, a secondary wave guide tube mechanical blind zone, the float ball immersion fuel height and a primary wave guide tube mechanical blind zone;

[0020] Step S32: correcting the liquid level height value according to the set temperature parameter to obtain a corrected liquid level height.

[0021] In order to better realize the present application, further, before collecting the ultrasonic pulse signal in step S1, the system parameters are initialized, the system parameters including default sound speed, baud rate, and set IO port.

[0022] In order to better realize the present application, further, the airborne fuel liquid level measurement method further comprises:

[0023] Step S4: performing median calculation on the liquid level heights obtained by multiple measurements to obtain a liquid level height value.

[0024] Based on the above proposed airborne fuel liquid level measurement method, in order to better realize the present application, further, an airborne fuel liquid level measurement system is proposed for executing the above airborne fuel liquid level measurement method; comprising a collection unit, a timing unit, and a calculation unit.

[0025] The collection unit is configured to set the number of excitation waves according to the obtained temperature value, and collect the ultrasonic pulse signal.

[0026] The timing unit is configured to calculate the time point sequence according to the collected ultrasonic pulse signal.

[0027] The calculation unit is configured to determine the current liquid level zone according to the time point sequence and the set liquid level partition, if the current liquid level zone is a low liquid level zone, calculate the liquid level height according to the ultrasonic wave flight time, the float ball immersion fuel height, the sound speed, and the mechanical blind area of the transducer; if the current liquid level zone is a high liquid level zone, calculate the liquid level height according to the ultrasonic wave flight time, the length of the secondary wave guide tube, the mechanical blind area of the secondary wave guide tube, the float ball immersion fuel height, and the mechanical blind area of the primary wave guide tube.

[0028] Based on the above proposed airborne fuel liquid level measurement method, in order to better realize the present application, further, an electronic device is proposed, comprising a memory and a processor; the memory stores a computer program; when the computer program is executed on the processor, the above airborne fuel liquid level measurement method is realized.

[0029] Based on the above proposed airborne fuel liquid level measurement method, in order to better realize the present application, further, a computer readable storage medium is proposed, the computer readable storage medium stores computer instructions; when the computer instructions are executed on the processor, the above airborne fuel liquid level measurement method is realized.

[0030] The present application has the following beneficial effects:

[0031] (1) The present application measures the fuel level in a non-contact manner, and calculates the liquid level height by setting the liquid level partitions, thereby overcoming the influence of liquid surface fluctuation caused by aircraft vibration.

[0032] (2) The present application uses the envelope superposition method to overcome the influence of aircraft vibration, greatly reduces the interference of random noise, improves the signal-to-noise ratio of the direct ultrasonic wave by using the power method, and further improves the reliability of the measurement results by median calculation. BRIEF DESCRIPTION OF DRAWINGS

[0033] Figure 1 The flowchart of the airborne fuel level measurement method provided by the present application is shown. DETAILED DESCRIPTION

[0034] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. It should be understood that the described embodiments are only a part of the embodiments of the present application, not all the embodiments, and therefore should not be regarded as limiting the scope of protection. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without making creative efforts fall within the scope of protection of the present application.

[0035] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "provided", "connected", "connected" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be connected inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0036] Embodiment 1

[0037] The present embodiment proposes an airborne fuel level measurement method, which specifically includes the following steps:

[0038] Step S1: According to the obtained temperature value, set the number of excitation waves, and collect the ultrasonic pulse signal.

[0039] Before collecting the ultrasonic pulse signal in step S1, it includes initializing system parameters; the system parameters include default sound speed, baud rate, and setting IO port.

[0040] Further, the step S1 specifically includes the following steps:

[0041] Step S11: Measure the fuel temperature value, and set the number of excitation waves according to the fuel temperature value;

[0042] Step S12: obtaining the original ultrasonic pulse signal according to the set number of excitation waves;

[0043] Step S13: calling the Kalman filtering method to filter the original ultrasonic pulse signal to obtain a filtered ultrasonic pulse signal.

[0044] Step S2: calculating a time point sequence according to the collected ultrasonic pulse signal.

[0045] Further, the step S2 specifically comprises the following steps:

[0046] Step S21: performing power operation on the filtered ultrasonic pulse signal according to the set power parameter to obtain a power-operated ultrasonic pulse signal;

[0047] Step S22: calculating the echo phase difference according to the ultrasonic wavelength, and calling the envelope superposition method to superimpose the ultrasonic pulse signals at different times according to the phase difference to obtain an envelope-superimposed ultrasonic pulse signal;

[0048] Step S23: calling the comparison method to identify the envelope wave peak time point of the envelope-superimposed ultrasonic pulse signal to obtain the time point sequence.

[0049] Step S3: judging the current liquid level zone according to the time point sequence and the set liquid level partition, if the current liquid level zone is a low liquid level zone, calculating the liquid level height according to the ultrasonic flight time, the float ball immersion fuel height, the sound speed, and the mechanical blind zone of the transducer; if the current liquid level zone is a high liquid level zone, calculating the liquid level height value according to the ultrasonic flight time, the secondary wave guide tube length, the secondary wave guide tube mechanical blind zone, the float ball immersion fuel height, and the primary wave guide tube mechanical blind zone.

[0050] Further, the step S3 specifically comprises the following steps:

[0051] Step S31: judging the current liquid level zone according to the time point sequence and the set liquid level partition, if the current liquid level zone is a low liquid level zone, calculating the liquid level height according to the ultrasonic flight time, the float ball immersion fuel height, the sound speed, and the mechanical blind zone of the transducer; if the current liquid level zone is a high liquid level zone, calculating the liquid level height according to the ultrasonic flight time, the secondary wave guide tube length, the secondary wave guide tube mechanical blind zone, the float ball immersion fuel height, and the primary wave guide tube mechanical blind zone.

[0052] Step S32: correcting the liquid level height value according to the set temperature parameter to obtain a corrected liquid level height.

[0053] Step S4: performing median calculation on the liquid level heights obtained by multiple measurements to obtain a liquid level height value.

[0054] Working principle: the embodiment first sets the number of excitation waves according to the acquired temperature value, and collects an ultrasonic pulse signal; then calculates a time point sequence according to the collected ultrasonic pulse signal; and finally judges a current liquid level zone according to the time point sequence and the set liquid level zone, and if the current liquid level zone is a low liquid level zone, calculates a liquid level height according to the ultrasonic wave flight time, the fuel immersion height of the float ball, the sound speed, and the mechanical blind zone of the transducer; if the current liquid level zone is a high liquid level zone, calculates the liquid level height value according to the ultrasonic wave flight time, the length of the secondary wave guide tube, the mechanical blind zone of the secondary wave guide tube, the fuel immersion height of the float ball, and the mechanical blind zone of the primary wave guide tube, thereby improving the measurement precision of the aircraft in a high-low temperature environment.

[0055] The embodiment measures the fuel liquid level in a non-contact manner, and calculates the liquid level height through setting the liquid level zones, thereby overcoming the influence of liquid surface fluctuation caused by aircraft vibration; through the envelope superposition method, the influence of aircraft vibration is overcome while the random noise interference is greatly reduced; through the multiplication method, the signal-to-noise ratio of the ultrasonic direct wave is improved, and the reliability of the measurement result is further improved through median calculation.

[0056] Embodiment 2

[0057] The embodiment is based on the above-described embodiment 1, and is described in detail with a specific embodiment as shown in Figure 1

[0058] Step S1: setting the number of excitation waves according to the acquired temperature value, and collecting an ultrasonic pulse signal;

[0059] First, the parameters are initialized, including the default sound speed, the baud rate, and the set IO port and other parameters. After the initialization is completed, self-detection is performed, and if there is a fault in the self-detection, a fault signal is output; if the self-detection is passed, the appropriate gain is set, and then the primary wave guide tube is sampled and calculated, the high-low liquid level zone is judged according to the calculation result, and if the liquid level is in the low liquid level zone, the low liquid level zone parameter setting is performed, and if it is in the high liquid level zone, the high liquid level zone parameter setting is performed; after the setting is completed, the ultrasonic pulse signal is collected again.

[0060] Before collecting the ultrasonic pulse signal, the temperature value is measured, the number of excitation waves is set through the measured temperature value, and the frequency of the excitation wave is taken as the main frequency of the transducer. According to the set number of excitation waves, an ultrasonic wave is generated, and an ultrasonic pulse signal is collected. Finally, the Kalman filtering method is called to filter the original ultrasonic pulse signal, and a filtered ultrasonic pulse signal is obtained. The denoising and smoothing ultrasonic pulse signal is obtained through Kalman filtering.

[0061] Step S2: calculating a time point sequence according to the collected ultrasonic pulse signal.

[0062] ​First, according to the set power parameter, the filtered ultrasonic pulse signal is subjected to power operation to obtain the power operated ultrasonic pulse signal; then, according to the ultrasonic wavelength, the echo phase difference is calculated, and according to the phase difference, the envelope superposition method is called to superimpose the ultrasonic pulse signals at different times to obtain the envelope superimposed ultrasonic pulse signal; finally, the comparison method is called to identify the envelope wave peak time point of the envelope superimposed ultrasonic pulse signal to obtain the time point sequence.

[0063] Step S3: According to the time point sequence and the set liquid level partition, the current liquid level area is judged, and if the current liquid level area is a low liquid level area, the liquid level height is calculated according to the ultrasonic flight time, the floating ball immersion fuel height, the sound speed, and the mechanical blind area of the transducer, and the specific operation is as follows:

[0064] H1 = Δt1 * C / 2 + H a + H b

[0065] Wherein, H1 represents the liquid level height of the low liquid level area, Δt1 represents the ultrasonic flight time, C represents the ultrasonic sound speed, H a represents the floating ball immersion fuel height, H b represents the mechanical blind area of the transducer.

[0066] If the current liquid level area is a high liquid level area, the liquid level height value is calculated according to the ultrasonic flight time, the secondary wave guide tube length, the secondary wave guide tube mechanical blind area, the floating ball immersion fuel height, and the primary wave guide tube mechanical blind area, and the specific operation is as follows:

[0067] H2 = t1 * (L - H c ) / t0 + H d + H e

[0068] Wherein, t1 represents the flight time of the ultrasonic wave in the primary wave guide tube, t0 represents the flight time of the ultrasonic wave in the secondary wave guide tube, L represents the length of the secondary wave guide tube, H c represents the secondary wave guide tube mechanical blind area, H d represents the floating ball immersion fuel height, H e represents the primary wave guide tube mechanical blind area.

[0069] Step S4: The liquid level heights obtained by multiple measurements are subjected to median calculation to obtain the liquid level height value.

[0070] The other parts of this embodiment are the same as those of the above-mentioned embodiment 1, and will not be described again.

[0071] Embodiment 3:

[0072] The embodiment is based on any one of the above-mentioned embodiments 1-2, and proposes an airborne fuel liquid level measurement system for performing the above-mentioned airborne fuel liquid level measurement method; comprising an acquisition unit, a timing unit, and a calculation unit.

[0073] The acquisition unit is configured to set the number of excitation waves according to the acquired temperature value, and acquire an ultrasonic pulse signal.

[0074] The timing unit is configured to calculate a time point sequence according to the acquired ultrasonic pulse signal.

[0075] The calculation unit is configured to determine a current liquid level zone according to the time point sequence and the set liquid level zone, calculate a liquid level height according to the ultrasonic wave flight time, the float ball immersion fuel height, the sound speed, and the mechanical blind area of the transducer if the current liquid level zone is a low liquid level zone, and calculate the liquid level height according to the ultrasonic wave flight time, the secondary wave guide tube length, the secondary wave guide tube mechanical blind area, the float ball immersion fuel height, and the primary wave guide tube mechanical blind area if the current liquid level zone is a high liquid level zone.

[0076] The embodiment also proposes an electronic device comprising a memory and a processor; the memory stores a computer program; when the computer program is executed on the processor, the above-mentioned airborne fuel liquid level measurement method is implemented.

[0077] The embodiment also proposes a computer readable storage medium, which stores computer instructions; when the computer instructions are executed on the processor, the above-mentioned airborne fuel liquid level measurement method is implemented.

[0078] The other parts of the embodiment are the same as any one of the above-mentioned embodiments 1-2, and will not be described again.

[0079] The above is only a preferred embodiment of the present application, and does not limit the present application in any form. Any simple modification or equivalent change based on the technical essence of the present application to the above embodiment falls within the protection scope of the present application.

Claims

1. An airborne fuel level measurement method, characterized by, Specifically comprising the following steps: Step S1: according to the temperature value, set the number of excitation waves, and collect the ultrasonic pulse signal; Step S2: according to the collected ultrasonic pulse signal, calculate the time point sequence; Step S3: according to the time point sequence and the set liquid level partition, judge the current liquid level area, if the current liquid level area is a low liquid level area, calculate the liquid level height according to the ultrasonic wave flight time, the float ball immersion fuel height, the sound speed, and the mechanical blind area of the transducer; if the current liquid level area is a high liquid level area, calculate the liquid level height value according to the ultrasonic wave flight time, the secondary wave guide tube length, the secondary wave guide tube mechanical blind area, the float ball immersion fuel height, and the main wave guide tube mechanical blind area.

2. An airborne fuel level measurement method according to claim 1, characterised in that, The step S1 specifically comprises the following steps: Step S11: measure the fuel temperature value, and set the number of excitation waves according to the fuel temperature value; Step S12: according to the set number of excitation waves, obtain the original ultrasonic pulse signal; Step S13: call the Kalman filtering method to filter the original ultrasonic pulse signal, and obtain the filtered ultrasonic pulse signal.

3. An airborne fuel level measurement method according to claim 2, characterised in that, The step S2 specifically comprises the following steps: Step S21: according to the set power parameter, perform power operation on the filtered ultrasonic pulse signal to obtain the power operated ultrasonic pulse signal; Step S22: calculate the echo phase difference according to the ultrasonic wave length, call the envelope superposition method to superimpose the ultrasonic pulse signals at different times according to the phase difference, and obtain the envelope superimposed ultrasonic pulse signal; Step S23: call the comparison method to identify the envelope wave peak time point of the envelope superimposed ultrasonic pulse signal, and obtain the time point sequence.

4. An airborne fuel level measurement method according to claim 3, characterised in that, The step S3 specifically comprises the following steps: Step S31: according to the time point sequence and the set liquid level partition, judge the current liquid level area, if the current liquid level area is a low liquid level area, calculate the liquid level height according to the ultrasonic wave flight time, the float ball immersion fuel height, the sound speed, and the mechanical blind area of the transducer; if the current liquid level area is a high liquid level area, calculate the liquid level height according to the ultrasonic wave flight time, the secondary wave guide tube length, the secondary wave guide tube mechanical blind area, the float ball immersion fuel height, and the main wave guide tube mechanical blind area; Step S32: correct the liquid level height value according to the set temperature parameter, and obtain the corrected liquid level height.

5. The airborne fuel level measurement method of claim 1, wherein, Before collecting the ultrasonic pulse signal in step S1, the system parameters are initialized, including the default sound speed, the baud rate, and the set IO port.

6. The airborne fuel level measurement method of claim 1, wherein, The airborne fuel liquid level measurement method further comprises: Step S4: perform median calculation on the liquid level heights obtained by multiple measurements to obtain the liquid level height value.

7. An on-board fuel level measurement system for performing the on-board fuel level measurement method of claim 1; characterized by, It comprises a collection unit, a timing unit, and a calculation unit; The collection unit is used for setting the number of excitation waves according to the temperature value, and collecting the ultrasonic pulse signal; The timing unit is used for calculating the time point sequence according to the collected ultrasonic pulse signal; The computing unit is configured to determine a current liquid level zone according to the time point sequence and the set liquid level zone, and calculate the liquid level height according to the ultrasonic wave flight time, the fuel immersion height of the float ball, the sound speed and the mechanical blind zone of the transducer if the current liquid level zone is a low liquid level zone; and calculate the liquid level height according to the ultrasonic wave flight time, the length of the auxiliary wave guide tube, the mechanical blind zone of the auxiliary wave guide tube, the fuel immersion height of the float ball and the mechanical blind zone of the main wave guide tube if the current liquid level zone is a high liquid level zone.

8. An electronic device, comprising: The method comprises a memory and a processor; the memory stores a computer program; when the computer program is executed on the processor, the method for measuring the fuel level on the aircraft as claimed in any one of claims 1-6 is realized.

9. A computer-readable storage medium, characterized in that, The computer readable storage medium stores computer instructions; when the computer instructions are executed on the processor, the method for measuring the fuel level on the aircraft as claimed in any one of claims 1-6 is realized.

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