A method, system, aircraft, and storage medium for measuring an amount of fuel of an aircraft

Abstract

The application discloses a kind of aircraft oil quantity measurement method, system, aircraft and storage medium, belong to aircraft and oil quantity measurement technical field, comprising: the capacitance value of several capacitive sensors and the liquid level height of oil liquid that are measured in advance in aircraft fuel tank;Determine the oil-gas interface of local oil liquid surface corresponding to each capacitive sensor based on the capacitance value;Determine the inclination angle of each local oil liquid surface based on each oil-gas interface;The inclination angle of multiple local oil liquid surfaces is curved surface fitting, and the inclination angle of complete oil liquid surface in aircraft fuel tank is determined;Determine the available oil quantity in aircraft fuel tank based on the inclination angle of complete oil liquid surface and liquid level height.The scheme replaces the oil quantity calculated by traditional attitude angle by the inclination angle of oil liquid surface, and can ensure the accuracy and reliability of liquid surface inclination angle measurement by multiple capacitance value fusion and curved surface fitting.

Description

Technical Field

[0001] This application relates to the field of aircraft and fuel quantity measurement technology, specifically to a method, system, aircraft, and storage medium for measuring the fuel quantity of an aircraft. Background Technology

[0002] The fuel measurement system for civil aircraft is used to stably and accurately measure the remaining fuel in the fuel tanks and the distribution of fuel in each tank under different operating conditions. It is a key functional system to ensure safe flight and improve operational economy. On the one hand, the weight of aircraft fuel is variable and accounts for 30% to 60% of the total aircraft weight. Accurate and stable measurement of fuel fuel ensures that the aircraft can accurately adjust its center of gravity and balance flight drag, thereby reducing fuel consumption and increasing the aircraft's range. On the other hand, test data shows that every 0.5% improvement in fuel measurement accuracy can add at least 2 to 3 passengers, contributing to increased passenger transport profits.

[0003] However, the methods for measuring the remaining fuel weight of relevant aircraft generally rely on the aircraft's attitude angle. But the aircraft's attitude angle may not accurately reflect the actual fuel tank level under certain operating conditions. Especially when the aircraft's attitude changes dynamically or the fuel sloshes, there may be a deviation between the attitude angle and the actual fuel level tilt, which can easily lead to low accuracy in the calculation of the remaining fuel amount and make it difficult to meet the requirements of high performance and high economy for civil aircraft. Summary of the Invention

[0004] This invention provides a method, system, aircraft, and storage medium for measuring the fuel level of an aircraft, aiming to solve the problem of low accuracy in calculating the remaining fuel level in the fuel tank in existing aircraft fuel level measurement methods.

[0005] Firstly, a method for measuring the fuel level of an aircraft is provided, comprising the following steps: Measure the capacitance values ​​of several capacitive sensors pre-installed in the aircraft's fuel tank and the fuel level. Based on the capacitance value, the oil-gas interface of the local oil surface corresponding to each capacitance sensor is determined; Based on each of the oil and gas interfaces, the tilt angle of each of the local oil surfaces is determined; The tilt angles of the multiple local oil surfaces are fitted with a surface to determine the tilt angle of the complete oil surface inside the aircraft's fuel tank. The available amount of fuel in the aircraft's fuel tank is determined based on the tilt angle of the complete oil surface and the liquid level height.

[0006] In some embodiments, the step of determining the oil-gas interface of the local oil surface corresponding to each of the capacitance sensors based on the capacitance value includes: Using the capacitance values, construct the capacitor array corresponding to each of the capacitance sensors; Each of the capacitor arrays is converted into a dielectric constant distribution map using a preset image reconstruction algorithm; The dielectric constant distribution map is segmented and edge detected to determine the oil-gas interface of the local oil surface corresponding to each capacitive sensor.

[0007] In some embodiments, the step of determining the tilt angle of each local oil level based on each of the oil-gas interfaces includes: The tilt angle of each local oil surface is determined based on the angle between each oil-gas interface and the preset horizontal reference plane.

[0008] In some embodiments, the step of performing surface fitting on the tilt angles of the plurality of local oil levels to determine the tilt angle of the complete oil level in the aircraft fuel tank includes: The optimal fitting parameters are determined by performing surface fitting on the tilt angles of multiple local oil surfaces using a preset fitting model. Based on the best-fit parameters, the complete oil level of the aircraft's fuel tank is determined; Calculate the gradient vector of the complete oil surface, and determine the tilt angle of the complete oil surface in the aircraft's fuel tank based on the angle between the gradient vector and the preset horizontal reference plane.

[0009] In some embodiments, the step of determining the available fuel quantity in the aircraft fuel tank based on the tilt angle of the complete oil surface and the liquid level height includes: The remaining oil volume is determined based on the tilt angle of the complete oil surface and the liquid level height. The remaining oil quantity is filtered to obtain the filtered remaining oil quantity; The available fuel quantity in the aircraft's fuel tank is determined using the filtered remaining fuel quantity and the known unavailable fuel quantity.

[0010] In some embodiments, the capacitive sensor includes a plurality of inner electrodes and a plurality of outer electrodes. The plurality of inner electrodes are spaced apart along a circumferential direction, and the plurality of outer electrodes are disposed outside the plurality of inner electrodes and spaced apart along the circumferential direction. Each inner electrode is disposed opposite to at least one outer electrode to form an electrode pair, and the inner electrodes are combined in pairs to form an electrode pair.

[0011] In some embodiments, the step of measuring the capacitance values ​​of a plurality of capacitive sensors pre-deployed within the fuel tank of the aircraft and the fuel level includes: The internal electrodes of each capacitive sensor are sequentially excited to obtain the excitation signal of each capacitive sensor; Based on the excitation signal of each of the capacitive sensors, the capacitance value of the electrode pair in each of the capacitive sensors is determined.

[0012] In some embodiments, the step of determining the capacitance value of the electrode pair in each of the capacitive sensors based on the excitation signal of each of the capacitive sensors includes: Based on the excitation signal of each of the capacitive sensors, the original capacitance signal of the electrode pair in each of the capacitive sensors is measured; The original capacitor signals are amplified and filtered to obtain conditioned capacitor signals. The conditioned capacitance signal is converted from analog to digital to determine the capacitance value of the electrode pair in each capacitance sensor.

[0013] In some embodiments, the step of measuring the capacitance values ​​of a plurality of capacitive sensors pre-deployed within the fuel tank of the aircraft and the fuel level includes: The capacitance value of each electrode pair and the linearity between the preset capacitance and the liquid level are used to determine the liquid level height corresponding to each capacitance value.

[0014] In some embodiments, the capacitance sensor is a capacitance tomography capacitance sensor.

[0015] Secondly, a system for measuring the fuel level of an aircraft is also provided, the system comprising: The data acquisition module is used to measure the capacitance values ​​of several capacitive sensors pre-installed in the aircraft's fuel tank and the fuel level. The local oil level determination module is used to determine the oil-gas interface of the local oil level corresponding to each of the capacitance sensors based on the capacitance value. The local tilt angle determination module is used to determine the tilt angle of each local oil surface based on each of the oil-gas interfaces. The global tilt angle determination module is used to perform surface fitting on the tilt angles of multiple local oil surfaces to determine the tilt angle of the complete oil surface inside the aircraft's fuel tank. The available fuel quantity calculation module is used to determine the available fuel quantity in the aircraft's fuel tank based on the tilt angle of the complete fuel surface and the fuel level height.

[0016] In some embodiments, the capacitance sensor includes a plurality of inner electrodes and a plurality of outer electrodes. The plurality of inner electrodes are spaced apart along a circumferential direction, and the plurality of outer electrodes are disposed outside the plurality of inner electrodes and spaced apart along the circumferential direction. The inner electrodes are disposed opposite to at least one of the outer electrodes to form an electrode pair. The data acquisition module includes an excitation unit, a capacitance signal measurement unit, and a capacitance value calculation unit. The excitation unit is used to sequentially excite the internal electrodes of each of the capacitive sensors to obtain the excitation signal of each of the capacitive sensors. The capacitance determination unit is used to determine the capacitance value of the electrode pair in each of the capacitance sensors based on the excitation signal of each capacitance sensor.

[0017] In some embodiments, the capacitance determination unit includes a capacitance measurement subunit, a signal conditioning subunit, and an analog-to-digital conversion subunit; The capacitance measurement subunit is used to measure the original capacitance signal of the electrode pair in each capacitance sensor based on the excitation signal of each capacitance sensor. The signal conditioning subunit is used to amplify and filter each of the original capacitor signals to obtain the conditioned capacitor signal. The analog-to-digital conversion subunit is used to perform analog-to-digital conversion on the conditioned capacitance signal to determine the capacitance value of the electrode pair in each capacitance sensor.

[0018] Thirdly, an aircraft is also provided, including a memory and a processor, wherein the memory stores a computer program that, when executed by the processor, implements the steps of any of the methods described above.

[0019] Fourthly, a computer-readable storage medium is also provided, on which a computer program is stored, the computer program being loaded by a processor to perform the steps of any of the methods described above.

[0020] Beneficial effects: This application utilizes a distributed array of capacitive sensors within the aircraft's fuel tank to determine the capacitance value of each sensor. This allows for the identification of the corresponding local liquid-gas interface and tilt angle. Surface fitting is then used to obtain the tilt angle of the complete liquid surface, and finally, the available fuel quantity is calculated by combining this with the liquid level height. This scheme replaces traditional attitude angle calculations with the tilt angle of the fuel surface for fuel quantity calculation. The fusion of multiple capacitance values ​​and surface fitting ensures the accuracy and reliability of the liquid surface tilt angle measurement, thereby achieving a dual guarantee of flight safety and fuel economy. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the functional modules of the aircraft fuel quantity measurement system provided in an exemplary embodiment of this application; Figure 2 This is a schematic diagram of the electrode layer and electrode distribution of an ECT capacitive sensor provided in an exemplary embodiment of this application; Figure 3 This is a schematic diagram illustrating the working principle of the aircraft fuel quantity measurement system provided in an exemplary embodiment of this application; Figure 4 This is a simplified flowchart of an aircraft fuel quantity measurement method provided in an exemplary embodiment of this application; Figure 5 This is a dielectric constant distribution diagram of oil and air provided in an exemplary embodiment of this application; Figure 6 This is an overall flowchart of a method for measuring the fuel level of an aircraft provided by an exemplary embodiment of this application; Figure 7 This is an overall flowchart of another method for measuring aircraft fuel quantity provided by an exemplary embodiment of this application. Detailed Implementation

[0023] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0024] In the description of this application, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "a plurality of" means two or more, unless otherwise explicitly specified.

[0025] "A and / or B" includes the following three combinations: A only, B only, and a combination of A and B.

[0026] The use of "applies to" or "configured to" in this application implies open and inclusive language, which does not exclude the applicability to or configuration to devices performing additional tasks or steps. Additionally, the use of "based on" implies openness and inclusivity, because processes, steps, calculations, or other actions "based on" one or more of the stated conditions or values ​​may in practice be based on additional conditions or values ​​beyond those stated.

[0027] In this application, the term "exemplary" is used to mean "used as an example, illustration, or description." Any embodiment described as "exemplary" in this application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is provided to enable any person skilled in the art to make and use this application. Details are set forth in the following description for purposes of explanation. It should be understood that those skilled in the art will recognize that this application can be made without using these specific details. In other instances, well-known structures and processes are not described in detail to avoid obscuring the description of this application with unnecessary detail. Therefore, this application is not intended to be limited to the embodiments shown, but is consistent with the broadest scope of the principles and features disclosed in this application.

[0028] To address the issue of low measurement accuracy in existing aircraft fuel quantity measurement methods, this application proposes a new method for measuring aircraft fuel quantity. This method primarily utilizes Electrical Capacitance Tomography (ECT) technology. By measuring the capacitance values ​​between multiple electrode pairs, the dielectric constant distribution of the medium within the measured area is inverted. Based on the capacitance values ​​between the electrodes, the fuel distribution in the local area surrounding the electrodes within the fuel tank is calculated. Image fitting is then performed on the local fuel surfaces of multiple local areas within the fuel tank to generate a complete fuel surface for the entire tank, thereby obtaining the tilt angle of the complete fuel surface. Finally, based on the tilt angle of the complete fuel surface and the liquid level height measured by the ECT capacitance sensor, the remaining usable fuel quantity in the entire fuel tank is determined. This method enables real-time visual monitoring of the fuel cross-sectional distribution in the measurement area surrounding the electrodes within the fuel tank, effectively improving the measurement accuracy and reliability of the fuel in the tank.

[0029] On the one hand, this embodiment provides a system for measuring the fuel level of an aircraft, such as... Figure 1 As shown, the system includes a data acquisition module, a local oil level determination module, a local tilt angle determination module, a global tilt angle determination module, and an available oil quantity calculation module.

[0030] The system includes a data acquisition module for measuring the capacitance values ​​of several capacitive sensors pre-installed in the aircraft's fuel tank and the fuel level; a local fuel level determination module for determining the oil-gas interface of each local fuel level based on the capacitance values; a local tilt angle determination module for determining the tilt angle of each local fuel level based on each oil-gas interface; a global tilt angle determination module for performing surface fitting on the tilt angles of multiple local fuel levels to determine the tilt angle of the complete fuel level in the aircraft's fuel tank; and an available fuel quantity calculation module for determining the available fuel quantity in the aircraft's fuel tank based on the tilt angle and fuel level of the complete fuel level.

[0031] Furthermore, the capacitive sensor configured in the system is an ECT capacitive sensor, and its top view is shown below. Figure 2 As shown, the system includes an inner cylinder 1, an outer cylinder 2, inner electrodes 3 arranged on the inner cylinder 1, and outer electrodes 4 arranged on the outer cylinder 2, as well as a stabilizing bracket 7 for fixing the inner cylinder 1 and the outer cylinder 2. The bottom of the ECT capacitive sensor is connected to the oil in the tank. Multiple inner electrodes 3 are spaced apart along a circumferential direction, and multiple outer electrodes 4 are disposed outside the inner electrodes 3, also spaced apart along the aforementioned circumferential direction, forming a multi-electrode array layout. Each inner electrode 3 is positioned opposite to at least one outer electrode 4 to form an electrode pair. Preferably, the electrode pairs include pairs of any two inner electrodes 3 combined together, and also pairs of each inner electrode 3 with an adjacent and oppositely positioned outer electrode 4. These electrode pairs are used to measure the capacitance signal of a local area inside the tank monitored by the capacitive sensor.

[0032] Furthermore, the data acquisition module in the system includes an excitation unit, a capacitance signal measurement unit, and a capacitance value calculation unit.

[0033] The excitation unit is used to sequentially excite the internal electrodes of each capacitive sensor to obtain the excitation signal of each capacitive sensor; the capacitance determination unit is used to determine the capacitance value of the electrode pair in each capacitive sensor based on the excitation signal of each capacitive sensor.

[0034] Preferably, the capacitance determination unit includes a capacitance measurement subunit, a signal conditioning subunit, and an analog-to-digital conversion subunit; the capacitance measurement subunit is used to measure the original capacitance signal of the electrode pair in each capacitance sensor based on the excitation signal of each capacitance sensor; the signal conditioning subunit is used to amplify and filter each original capacitance signal to obtain a conditioned capacitance signal; the analog-to-digital conversion subunit is used to perform analog-to-digital conversion on the conditioned capacitance signal to determine the capacitance value of the electrode pair in each capacitance sensor.

[0035] In some embodiments, a fuel computer integrates the functions of a data acquisition module, a local fuel level determination module, a local tilt angle determination module, a global tilt angle determination module, and an available fuel quantity calculation module to obtain, as shown below. Figure 3 The aircraft fuel level measurement system shown works as follows: An ECT sensor collects real-time capacitance signal data of the fuel in the center wing fuel tank and each wing fuel tank at different positions. The ECT sensor and measurement sensors also collect real-time fuel level data in the center wing fuel tank and each wing fuel tank, respectively. This data is transmitted to a Fuel Remote Data Concentrator (FRDC). The FRDC processes the capacitance signals and fuel level data to determine the remaining fuel level in each tank. Simultaneously, the capacitance signals, fuel level data, and remaining fuel level output from the FRDC, along with the aircraft attitude angle data provided by the inertial navigation system, are sent to the fuel computer. The fuel computer then processes this data in conjunction with real-time flight status information such as the aircraft's operating conditions. Finally, the calculated capacitance signals, fuel level data, and remaining fuel level data are transmitted to a display for real-time monitoring and data interaction of the fuel tank status.

[0036] In this embodiment, the system is based on ECT capacitance tomography technology and a multi-electrode array layout. By accurately acquiring capacitance signals, it inverts the tilt angle of the local oil surface and fits it to the tilt angle of the complete oil surface. This enables real-time display and autonomous acquisition of the oil surface tilt angle without relying on external systems to provide attitude angle data. By using the tilt angle of the oil surface to replace the traditional attitude angle for calculating fuel quantity, the accuracy and real-time performance of fuel quantity measurement under complex flight conditions can be improved. At the same time, based on the safety characteristics and redundancy design of capacitance sensing, the system's reliability can be enhanced under sensor local failures and extreme attitudes. Furthermore, the real-time feedback of the oil surface tilt angle provides the pilot with an intuitive reference to the oil surface status, providing dual protection for aircraft flight safety and fuel economy.

[0037] On the other hand, this embodiment provides a method for measuring the fuel level of an aircraft, applied to scenarios where the remaining fuel level in the fuel tanks of an aircraft is measured. The implementation flow of the aircraft fuel level measurement method in this embodiment is as follows: Figure 4 As shown, the specific steps include: Step 100: Measure the capacitance values ​​of several capacitive sensors pre-installed in the aircraft's fuel tank and the fuel level.

[0038] Specifically, for several capacitive sensors pre-distributed evenly inside the aircraft's fuel tank, the diameter of each capacitive sensor is designed to match the size of the fuel tank, and the bottom of each capacitive sensor is connected to the fuel at the bottom of the tank. The data acquisition module of the aircraft's fuel level measurement system excites the electrodes of the capacitive sensors to measure the capacitance signals between different electrodes, and the capacitance value of each capacitive sensor is obtained by combining the multiple measured capacitance signals.

[0039] Simultaneously, the liquid level height data corresponding to the oil position monitored by each capacitive sensor is acquired. All capacitance values ​​and corresponding liquid level height data are stored by the data storage and interface module and transmitted to the remote data central FRDC unit.

[0040] In this embodiment, the shape of the aircraft fuel tank is not specifically limited, and it generally refers to any container that can hold aircraft fuel.

[0041] Step 200: Based on the capacitance value, determine the oil-gas interface of the local oil surface corresponding to each capacitance sensor.

[0042] Specifically, considering the significant difference in dielectric constant between the fuel and air in the aircraft's fuel tank, a clear distinction in characteristics will form at the fuel-air interface. This embodiment transmits the capacitance value to a local fuel level determination module integrated with an image reconstruction algorithm within the aircraft's fuel level measurement system. Utilizing the correlation between capacitance and dielectric constant, the image reconstruction algorithm analyzes and processes the capacitance value to construct a dielectric constant distribution map of the fuel and air within the aircraft's fuel tank cross-section, such as... Figure 5 As shown. Then, by segmenting and boundary detection of the dielectric constant distribution map, the boundary contours between oil and air in the local areas monitored by different capacitance sensors are accurately identified. This contour is the oil-air interface of the local oil surface corresponding to each capacitance sensor, so as to completely preserve the morphological characteristics of the local oil surface.

[0043] Step 300: Based on each oil-gas interface, determine the tilt angle of each local oil surface.

[0044] Specifically, for each local oil surface and its oil-gas interface, a reference coordinate system is established with the horizontal direction as the baseline. The local tilt angle determination module in the aircraft's oil quantity measurement system analyzes the morphological characteristics of the oil-gas interface in the coordinate system. By judging the height differences at different points on the interface, the tilt trend of the local oil surface is determined. Combining the contour data of the oil-gas interface, the tilt degree of the interface relative to the horizontal reference plane is calculated. Specifically, by identifying features such as the slope change of the interface and the height offset of key points, the angle between each local oil surface and the horizontal reference plane is derived. This angle is the tilt angle of the local oil surface corresponding to each capacitive sensor.

[0045] Step 400: Perform surface fitting on the tilt angles of multiple local oil surfaces to determine the tilt angle of the complete oil surface in the tank.

[0046] Specifically, firstly, the tilt angle data of multiple local oil surfaces are preprocessed to remove outliers caused by measurement noise, oil surface fluctuations, or capacitive sensor errors, ensuring data reliability and consistency. Then, based on the oil flow characteristics and the distribution features of the local tilt angle data, a suitable fitting model is selected through the global tilt angle determination module in the aircraft's fuel quantity measurement system. An optimization algorithm is then used to perform surface fitting on the preprocessed local tilt angle data, resulting in a fitted surface that best matches the overall shape of the actual oil surface within the fuel tank. Finally, by calculating the gradient direction of the fitted surface, the overall angle between the surface and the horizontal reference plane is determined, i.e., the tilt angle of the complete oil surface in the aircraft's fuel tank. The fitting model can be, but is not limited to, a linear model, a polynomial model, or a nonlinear model.

[0047] Step 500: Determine the amount of available fuel in the aircraft's fuel tank based on the tilt angle and level of the complete fuel surface.

[0048] Specifically, the available fuel quantity calculation module in the aircraft fuel quantity measurement system, based on the tilt angle of the complete fuel surface and the fuel level height data at various locations, fully considers the influence of the fuel surface tilt on the fuel quantity distribution in different areas, as well as the geometric dimensions and volume characteristics of the aircraft fuel tank, and accurately derives the available fuel quantity in the aircraft fuel tank through a fuel quantity calculation algorithm.

[0049] Furthermore, by calculating the amount of available fuel in each fuel tank on the aircraft, the distribution of the total available fuel in each fuel tank can be determined.

[0050] In this embodiment, multiple capacitive sensors are deployed in a distributed layout to determine the capacitance value of each sensor, thereby identifying the local liquid-gas interface and tilt angle corresponding to each sensor. The tilt angle of the complete liquid surface is then obtained through surface fitting, and finally, the available fuel quantity is calculated based on the liquid level height. This scheme uses the tilt angle of the liquid surface to replace the traditional attitude angle for fuel quantity calculation. It ensures the accuracy of the liquid surface tilt angle measurement through the fusion of multiple capacitance values ​​and surface fitting, effectively offsetting the fuel quantity measurement deviation caused by the liquid surface tilt. This improves the accuracy and reliability of fuel quantity measurement under complex flight conditions. Furthermore, the safety characteristics and redundancy design of capacitive sensors enhance the reliability of the measurement results. The real-time feedback of the liquid surface tilt angle provides the pilot with an intuitive reference to the liquid surface status, thus achieving a dual guarantee of flight safety and fuel economy.

[0051] In some embodiments, step 200, which involves determining the oil-gas interface of the local oil surface corresponding to each capacitance sensor based on the capacitance value, includes: Step 210: Construct the capacitor array corresponding to each capacitive sensor using the capacitance values.

[0052] Specifically, for each capacitive sensor, the capacitance values ​​of each electrode pair measured at all detection positions are collected. Based on the electrode arrangement logic of the capacitive sensor, the capacitance values ​​of all electrode pairs are integrated according to a preset arrangement rule. For example, the capacitive sensor includes multiple inner electrodes and multiple outer electrodes. The multiple inner electrodes are spaced apart along a circumferential direction, and the multiple outer electrodes are disposed outside the multiple inner electrodes and spaced apart along a circumferential direction. The inner electrodes are arranged opposite to at least one outer electrode to form an electrode pair. Preferably, the electrode pair includes an electrode pair formed by each inner electrode and the remaining inner electrodes, and also includes an electrode pair formed by each inner electrode and an adjacent and oppositely arranged outer electrode.

[0053] Based on the numbering order of the inner and outer electrodes and the correspondence between excitation and measurement, the capacitance values ​​of each electrode pair are systematically filled into the array structure. The rows and columns of the array correspond to different electrodes, and each element in the array corresponds to the capacitance measurement result of a different electrode pair, ultimately forming a capacitance array that represents the capacitance distribution within the local oil surface area monitored by each capacitance sensor.

[0054] Step 220: Use a preset image reconstruction algorithm to convert each capacitor array into a dielectric constant distribution map.

[0055] Specifically, due to the mapping relationship between the capacitor array corresponding to the capacitive sensor and the dielectric constant of media such as oil and air, the expression for this mapping relationship is as follows: ; in, It is a capacitor array; An array of dielectric constants composed of oil and air; The sensitivity coefficient. This is used to characterize the degree of change in capacitance caused by altering the distribution of the dielectric constant of a sensitive field. Here, the sensitive field specifically refers to the dielectric field composed of fuel and air in an aircraft fuel tank.

[0056] Based on this, this embodiment inputs each capacitor array one by one into a fuel computer integrated with an image reconstruction algorithm. The image reconstruction algorithm analyzes the numerical values ​​and distribution characteristics of each element in the capacitor array. Combining the mapping relationship between capacitance and dielectric constant, it inversely deduces the dielectric constant information at different locations within the local oil surface area monitored by the capacitor sensor. Finally, the derived dielectric constant data undergoes spatial mapping and visualization processing to generate a dielectric constant distribution map corresponding to each capacitor sensor, clearly presenting the spatial distribution differences of the dielectric constant within the local oil surface area monitored by each capacitor sensor. Here, the image reconstruction algorithm generally refers to an algorithm that can, based on the principle of capacitance sensing and the correlation law of dielectric properties, inversely deduce the dielectric constant characteristics of the sensitive field from the capacitor array corresponding to the capacitor sensor, thereby inferring the fluid characteristics and dielectric distribution within the sensitive field.

[0057] Step 230: Segment and edge detection of the dielectric constant distribution map to determine the oil-gas interface of the local oil surface corresponding to each capacitive sensor.

[0058] Specifically, considering the significant difference in dielectric constants between oil and air, a clear numerical boundary region will form in the dielectric constant distribution map. This embodiment first performs image segmentation processing on the dielectric constant distribution map based on the numerical difference in dielectric constant, dividing the map into different regions to initially distinguish between the high dielectric constant region corresponding to oil and the low dielectric constant region corresponding to air. Then, edge detection is used to accurately capture the boundary contours between adjacent regions, i.e., the contact interface between oil and air. Furthermore, interference noise in the boundary contours is removed, and the smoothness and integrity of the boundaries are optimized. Finally, the oil-air interface of the local oil surface region monitored by each capacitive sensor is determined, thus completely preserving the spatial morphological characteristics of this interface.

[0059] It should be noted that, based on the oil-gas interface of the local oil surface, which is derived from the capacitance value of the area monitored by the capacitance sensor, the corresponding liquid level height is determined according to the spatial location information of the oil-gas interface of the local oil surface.

[0060] In this embodiment, the original capacitance signal collected by the capacitance sensor is transformed into intuitive liquid-gas interface information through capacitance matrix construction, image reconstruction, and image segmentation detection. This process can accurately restore the local medium distribution of the structured capacitance matrix through image reconstruction algorithm, and ensure the accuracy of liquid-gas interface positioning through image segmentation and edge detection.

[0061] In some embodiments, step 300, which involves determining the tilt angle of each local oil level based on each oil-gas interface, includes: The tilt angle of each local oil surface is determined based on the angle between each oil-gas interface and the preset horizontal reference plane.

[0062] Specifically, a horizontal reference plane is first pre-defined as a standard, which is consistent with the installation reference plane or horizontal reference plane of the aircraft fuel tank. For each local oil surface and its gas-oil interface, complete contour morphology data is extracted, including the spatial location information of multiple key points on the interface. By analyzing the height differences of these key points relative to the horizontal reference plane, the overall tilt trend of the oil-gas interface is determined, thereby identifying the tilt direction. Key points refer to characteristic inflection points where the height change trend on the oil-gas interface reverses, and / or several sampling points evenly selected at preset intervals on the interface. Depending on requirements, characteristic inflection points can reflect the tilt direction of the local oil surface, such as the intersection point of the oil-gas interface and the electrode of the capacitive sensor, or the edge extreme points corresponding to the highest or lowest points of the interface within the sensor's monitoring area. By comprehensively capturing the overall morphology of the oil-gas interface through sampling points, distortion in tilt angle calculation due to local data deviations is avoided, ensuring accurate derivation of the local oil surface tilt state through point height differences.

[0063] Then, by combining the contour features and spatial location data of the oil-gas interface, the angle formed between the interface and the preset horizontal reference plane is calculated, that is, the tilt angle of the local oil surface corresponding to each capacitive sensor, so as to reflect the degree of tilt of the complete oil surface relative to the horizontal reference plane.

[0064] In some embodiments, step 400, which involves surface fitting to the tilt angles of multiple local oil surfaces to determine the tilt angle of the complete oil surface within the aircraft's fuel tank, includes: Step 410: Use a preset fitting model to perform surface fitting on the tilt angles of multiple local oil surfaces to determine the optimal fitting parameters.

[0065] Specifically, firstly, the collected tilt angles of all local oil surfaces are preprocessed to remove outliers and noise caused by oil surface sloshing, bubble interference, or capacitive sensor errors, thus obtaining preprocessed local tilt angles and ensuring data reliability and consistency. Then, based on the flow characteristics of the oil in the tank and the distribution characteristics of the preprocessed local tilt angles, a suitable fitting model is selected. The type of fitting model includes, but is not limited to, linear, polynomial, or nonlinear models.

[0066] The parameters of the selected fitting model are iteratively optimized by the optimization algorithm so that the fitting model can fit the oil surface morphology reflected by all local tilt angles to the greatest extent. Finally, a set of parameters that can make the fitting model match the actual oil surface characteristics to the highest degree is determined, namely the optimal fitting parameters.

[0067] Step 420: Determine the complete oil level in the tank based on the best-fit parameters.

[0068] Specifically, the optimal fitting parameters are substituted into the fitting model, and a surface, namely the complete oil surface of the fuel tank, is generated through the fitting model calculation. This complete oil surface, with the spatial structure of the fuel tank as a reference, integrates key information on the tilt angles of multiple local oil surfaces, and can comprehensively reflect the overall distribution of the oil surface within the fuel tank.

[0069] Furthermore, the generated surface is verified to check whether it matches the actual shape of each local oil surface and whether it can cover the entire oil area in the tank. If there is a deviation, the best fitting parameters are fine-tuned according to the verification results until the generated surface can accurately and completely simulate the real oil surface in the tank, thereby determining the complete oil surface of the tank.

[0070] Step 430: Calculate the gradient vector of the complete oil surface, and determine the tilt angle of the complete oil surface inside the aircraft fuel tank based on the angle between the gradient vector and the preset horizontal reference plane.

[0071] Specifically, using a preset horizontal reference plane as a reference, gradient analysis is performed on the complete oil surface of the aircraft's fuel tank to calculate the gradient vector of the oil surface. The direction of the gradient vector points to the direction of the fastest change in oil surface height, and its characteristics can intuitively reflect the tilt trend of the oil surface. By analyzing the direction and magnitude of the gradient vector, the angle formed between the vector and the preset horizontal reference plane is determined, which is the tilt angle of the complete oil surface of the fuel tank.

[0072] In this embodiment, the best fitting parameters are iteratively optimized using a fitting model to integrate discrete local liquid surface tilt angles into a complete liquid surface model and determine its tilt angle. This process can ensure the accuracy of the complete liquid surface shape restoration through the fitting algorithm, and accurately obtain the tilt angle of the oil surface by calculating the angle between the gradient vector and the horizontal reference plane. At the same time, it can improve the stability and reliability of liquid surface tilt angle measurement under complex flight conditions, thereby enhancing the independence and anti-interference capability of the entire aircraft oil quantity measurement system.

[0073] In some embodiments, step 500, which determines the amount of available fuel in the aircraft's fuel tank based on the tilt angle and level of the complete fuel surface, is as follows: Figure 6 As shown, it includes: Step 510: Determine the remaining oil volume based on the tilt angle and level of the complete oil surface.

[0074] Specifically, based on the tilt angle of the complete oil surface and the corresponding liquid level data from each capacitive sensor, the volume of remaining oil is determined by looking up a table. Simultaneously, the physical properties of the oil itself (such as density) and parameters such as the fuel tank's geometry and internal structure are fully considered. Using a weight calculation algorithm, the remaining fuel quantity in the aircraft's fuel tank, i.e., the weight of the remaining fuel, is calculated using the remaining oil volume, fuel density, and gravitational acceleration. The oil density can be directly measured using a densitometer or determined based on the measured dielectric constant of the oil.

[0075] Step 520: Filter the remaining oil quantity to obtain the filtered remaining oil quantity.

[0076] Specifically, to address potential noise issues in the remaining oil volume data, such as oil surface sloshing noise, air bubbles and foam interference from oil flow, electrical noise from the capacitive sensor and measurement circuit, and measurement errors like capacitive sensor drift and nonlinearity, an appropriate filtering algorithm is selected based on the actual operating conditions. Optional filtering algorithms include, but are not limited to, mean filtering, median filtering, low-pass filtering, Kalman filtering, or moving average filtering. Mean filtering smooths random noise, median filtering effectively removes spike pulse interference, low-pass filtering filters out high-frequency electrical noise, Kalman filtering is suitable for dynamically changing noise environments, and moving average filtering is suitable for continuous monitoring scenarios. By processing the remaining oil volume data using the corresponding filtering algorithm, abnormal interference signals are eliminated, measurement errors are compensated, and a more accurate filtered remaining oil volume is obtained.

[0077] Step 530: Determine the available fuel in the aircraft's fuel tanks using the filtered remaining fuel and the known unavailable fuel.

[0078] Specifically, the amount of unusable fuel in the tank is determined in advance based on the tank's structural design requirements, such as the residual area at the bottom and the minimum fuel level. Subtracting the known unusable fuel from the filtered remaining fuel yields the amount of usable fuel remaining in the tank.

[0079] In this embodiment, the accuracy of the remaining fuel quantity calculation is ensured by fully considering the influence of liquid surface tilt, and the interference of data fluctuation is eliminated by filtering. Furthermore, the usability of the usable fuel quantity result is ensured by removing unusable fuel quantity, thereby effectively improving the accuracy and reliability of usable fuel quantity measurement under complex flight conditions.

[0080] As another embodiment, such as Figure 7 As shown. This embodiment and Figure 6The difference in the illustrated embodiment is that this embodiment retains both the conventional aircraft attitude angle and the tilt angle of the complete oil surface calculated in this embodiment, and retains both the liquid level height measured by the conventional capacitive sensor (such as a coaxial cylindrical capacitive liquid level sensor) and the liquid level height measured by the ECT capacitive sensor in this embodiment. This can serve as redundant backup data for the oil level height, and the tilt angle measured by the ECT capacitive sensor can also be corrected using the liquid level height measured by the conventional measurement sensor to improve the safety of aircraft flight.

[0081] For example, the aircraft attitude angle and the tilt angle of the complete oil surface are compared to calculate whether the error between the two is within the error range; if it exceeds the error range, the tilt angle of the complete oil surface is corrected using the aircraft attitude angle. Specifically: The tilt angle of the complete oil surface is compared with the aircraft attitude angle, and the angle difference between the two is calculated. This angle difference is the tilt angle deviation of the complete oil surface.

[0082] When the tilt angle deviation is less than or equal to the preset tilt angle deviation threshold, the measurement result of the tilt angle of the complete oil surface is accurate and reliable.

[0083] If the tilt angle deviation exceeds a preset tilt angle deviation threshold, it is determined that there is a measurement anomaly in the tilt angle of the complete oil surface (such as interference from other types of sensors), and a correction mechanism is activated. Using the stable attitude angle output by the aircraft's inertial navigation system as a reference, and combining the positional characteristics of the complete oil surface with historical measurement patterns, the tilt angle of the complete oil surface is calibrated and corrected, updating the tilt angle of the complete oil surface. This eliminates errors caused by the deviation and ensures the reliability and accuracy of the tilt angle of the oil surface.

[0084] It is easy to understand that if either the aircraft's attitude angle or the tilt angle of the complete fuel level is abnormal, the tilt angle measured by the other can be used to calculate the available fuel weight in the fuel tank. This achieves a redundant design for measuring the aircraft's tilt angle, which helps improve the timeliness and reliability of the aircraft's available fuel weight data, and thus helps improve the safety of the aircraft's flight.

[0085] For example, the liquid level height measured by a traditional capacitive sensor is compared with that measured by an ECT capacitive sensor, and the error between the two is calculated to see if it is within the error range. If it exceeds the error range, the tilt angle of the complete oil surface is corrected using the aircraft attitude angle. Specifically: In this example, the oil tank is equipped with an equal number of ECT capacitive sensors and traditional capacitive sensors at corresponding locations. The liquid level measured by the traditional capacitive sensors at the same location is compared with the liquid level measured by the ECT capacitive sensors to obtain the liquid level deviation.

[0086] If the liquid level deviation is less than or equal to the preset liquid level deviation threshold, the liquid level measured by the ECT capacitive sensor is determined to be accurate and reliable.

[0087] If the liquid level deviation exceeds a preset threshold, the liquid level measured by the ECT capacitive sensor is deemed abnormal, and a correction mechanism is activated. Using the liquid level measured by a traditional capacitive sensor as a reference, and combining the positional characteristics of the intact oil surface with historical measurement patterns, the liquid level measured by the ECT capacitive sensor is calibrated and corrected, updating the liquid level measurement to ensure reliability and accuracy.

[0088] It is easy to understand that if either the traditional capacitive sensor or the ECT capacitive sensor malfunctions, the liquid level measured by the other sensor can be used to calculate the available fuel weight in the tank. This achieves a redundant design for measuring the liquid level in the tank, which helps improve the timeliness and reliability of the aircraft's available fuel weight data, and thus helps improve the safety of the aircraft's flight.

[0089] In some embodiments, Figure 2 As shown, the capacitive sensor employs a capacitance tomography (CTT) capacitive sensor array structure, comprising inner and outer electrode layers. Each electrode layer contains multiple electrodes, and the bottom of the capacitive sensor is connected to the oil in the tank. The electrode layers and the number of electrodes on each layer are determined based on the dielectric constant of the oil, the linearity between capacitance and liquid level, and the sensitivity of the capacitive sensor to changes in the tilt angle of the local oil surface in the tank.

[0090] Therefore, step 100, which involves measuring the capacitance values ​​of several capacitive sensors pre-installed within the fuel tank of the aircraft and the fuel level, includes: Step 110: Sequentially excite the internal electrodes of each capacitive sensor to obtain the excitation signal of each capacitive sensor.

[0091] Specifically, firstly, based on the circumferentially spaced distribution of multiple internal electrodes of the capacitance sensor, an excitation sequence is set. Then, through the excitation unit in the data acquisition module, excitation signals are sequentially applied to the multiple internal electrodes of each capacitance sensor according to the preset excitation sequence, ensuring that each internal electrode can obtain stable and suitable excitation energy, thereby generating an excitation signal that can drive the electrode pair to perform capacitance detection.

[0092] Step 120: Based on the excitation signal of each capacitive sensor, determine the capacitance value of the electrode pair in each capacitive sensor.

[0093] Specifically, while applying excitation signals sequentially to the inner electrodes of the capacitance sensor, the capacitance determination unit in the data acquisition module switches and selects all electrode pairs in the sensor and measures the capacitance signal. The electrode pairs include pairs of inner electrodes combined in pairs, and pairs of inner electrodes with adjacent and opposite outer electrodes, with the outer electrodes spaced apart along the circumference of the inner electrodes.

[0094] Furthermore, the capacitance determination unit includes a capacitance measurement subunit, a signal conditioning subunit, and an analog-to-digital conversion subunit. The processing flow of the capacitance determination unit for the original capacitance signal includes: first, the capacitance measurement subunit sequentially switches different electrode pairs according to preset logic, synchronously capturing the original capacitance signal generated by the difference between the dielectric constant of oil and air under the action of the excitation signal, ensuring comprehensive coverage of capacitance signal measurement for all electrode pairs; then, the signal conditioning subunit amplifies the weak original capacitance signal to enhance signal strength, and filters to remove electromagnetic interference, power fluctuations and other electrical noise, thereby improving the signal-to-noise ratio and stability, thus obtaining the conditioned capacitance signal; the analog-to-digital conversion subunit performs analog-to-digital conversion on the conditioned analog capacitance signal to obtain a digital capacitance signal, ensuring that the timing of the analog-to-digital conversion is synchronized with the entire data acquisition process, ensuring that the converted digital signal can truly and completely reflect the characteristics of the original conditioned capacitance signal; subsequently, signal processing methods such as Fourier transform are used to analyze the frequency components, amplitude and other characteristics of the digital signal to obtain the capacitance value corresponding to each electrode pair, and the capacitance values ​​of all electrode pairs are integrated to finally determine the capacitance value corresponding to each electrode pair in each capacitance sensor.

[0095] Furthermore, the data acquisition module also includes a control and synchronization unit and a data storage and interface unit. Throughout the process, the control and synchronization unit coordinates the timing of excitation signal generation, electrode pair switching, signal sampling, and processing to ensure precise synchronization of each stage, thereby guaranteeing the accuracy and efficiency of the capacitance value calculation results.

[0096] All capacitance values ​​and corresponding liquid level data are stored and transmitted to the remote data centralization unit (FRDC) through the storage and interface unit, so as to facilitate communication with external devices such as fuel computers and transmit measurement data.

[0097] In some embodiments, step 100, which involves measuring the capacitance values ​​of several capacitive sensors pre-installed within the fuel tank of the aircraft and the fuel level, further includes: The capacitance value of each electrode pair and the linearity between the preset capacitance and the liquid level are used to determine the liquid level height corresponding to each capacitance value.

[0098] Specifically, after obtaining the capacitance values ​​of each electrode pair, the corresponding liquid level height is determined by combining them with preset capacitance and liquid level linearity parameters. These linearity parameters are pre-calibrated experimentally, establishing a stable correspondence between capacitance values ​​and liquid level height, ensuring a reliable linear relationship between the two. Referring to the electrode arrangement of the capacitance sensor, the compatibility and installation parameters between the sensor and the aircraft fuel tank, and the influence of the oil dielectric constant on capacitance measurement, the capacitance value of each electrode pair is matched and analyzed against the preset linearity. During this process, minor deviations caused by slight fluctuations in the oil surface and differences in local medium distribution are eliminated. Through the derivation of the correspondence between capacitance values ​​and linearity, the actual oil level height corresponding to each capacitance value is accurately determined, ensuring the accuracy of the liquid level height data.

[0099] It should be noted that the measurements in this application embodiment are of the available fuel quantity in the aircraft's fuel tank, i.e., the measurement is of oil-phase fluids. Based on the same measurement principle, it is also applicable to measuring water-phase fluids stored in tanks configured on the aircraft. This application does not specifically limit the type of fluid measured. It is worth noting that the method of this application is applicable to fluids stored in tanks with dielectric constants that are significantly different from those of air, or to different types of water-phase or oil-phase fluids stored in tanks with significantly different dielectric constants, to ensure the accuracy of the oil-gas interface and liquid level height identified based on dielectric constants.

[0100] This embodiment also provides an aircraft, including a memory and a processor. In a specific example, the memory stores a computer program, and when the computer program is executed by the processor, it implements the method of any of the above embodiments.

[0101] This embodiment also provides a computer-readable storage medium having a computer program stored thereon, the computer program being loaded by a processor to perform the steps of any of the methods in the above embodiments.

[0102] In the embodiments of this application, the storage medium may be a magnetic disk, an optical disk, a read-only memory (ROM), or a random access memory (RAM), etc.

[0103] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0104] The foregoing has provided a detailed description of a method, system, aircraft, and storage medium for measuring aircraft fuel quantity according to embodiments of this application. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are only for the purpose of helping to understand the method and core ideas of this application. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of this application. Therefore, the content of this specification should not be construed as a limitation of this application.

Claims

1. A method for measuring the fuel level of an aircraft, characterized in that, Includes the following steps: Measure the capacitance values ​​of several capacitive sensors pre-installed in the aircraft's fuel tank and the fuel level. Based on the capacitance value, the oil-gas interface of the local oil surface corresponding to each capacitance sensor is determined; Based on each of the oil and gas interfaces, the tilt angle of each of the local oil surfaces is determined; The tilt angles of the multiple local oil surfaces are fitted with a surface to determine the tilt angle of the complete oil surface inside the aircraft's fuel tank. The available amount of fuel in the aircraft's fuel tank is determined based on the tilt angle of the complete oil surface and the liquid level height.

2. The method for measuring aircraft fuel quantity according to claim 1, characterized in that, The step of determining the oil-gas interface of the local oil surface corresponding to each of the capacitance sensors based on the capacitance value includes: Using the capacitance values, construct the capacitor array corresponding to each of the capacitance sensors; Each of the capacitor arrays is converted into a dielectric constant distribution map using a preset image reconstruction algorithm; The dielectric constant distribution map is segmented and edge detected to determine the oil-gas interface of the local oil surface corresponding to each capacitive sensor.

3. The method for measuring aircraft fuel quantity according to claim 1, characterized in that, The step of determining the tilt angle of each local oil level based on each oil-gas interface includes: The tilt angle of each local oil surface is determined based on the angle between each oil-gas interface and the preset horizontal reference plane.

4. The method for measuring aircraft fuel quantity according to claim 3, characterized in that, The step of performing surface fitting on the tilt angles of the multiple local oil surfaces to determine the tilt angle of the complete oil surface inside the aircraft fuel tank includes: The optimal fitting parameters are determined by performing surface fitting on the tilt angles of multiple local oil surfaces using a preset fitting model. Based on the best-fit parameters, the complete oil level of the aircraft's fuel tank is determined; Calculate the gradient vector of the complete oil surface, and determine the tilt angle of the complete oil surface in the aircraft's fuel tank based on the angle between the gradient vector and the preset horizontal reference plane.

5. The method for measuring aircraft fuel quantity according to claim 1, characterized in that, The step of determining the available fuel quantity in the aircraft's fuel tank based on the tilt angle of the complete oil surface and the liquid level height includes: The remaining oil volume is determined based on the tilt angle of the complete oil surface and the liquid level height. The remaining oil quantity is filtered to obtain the filtered remaining oil quantity; The available fuel quantity in the aircraft's fuel tank is determined using the filtered remaining fuel quantity and the known unavailable fuel quantity.

6. The method for measuring aircraft fuel quantity according to claim 1, characterized in that, The capacitive sensor includes multiple inner electrodes and multiple outer electrodes. The multiple inner electrodes are spaced apart along a circumferential direction. The multiple outer electrodes are disposed outside the multiple inner electrodes and spaced apart along the circumferential direction. Each inner electrode is disposed opposite to at least one outer electrode to form an electrode pair, and the inner electrodes are combined in pairs to form an electrode pair.

7. The method for measuring aircraft fuel quantity according to claim 6, characterized in that, The steps of measuring the capacitance values ​​of several capacitive sensors pre-installed in the aircraft's fuel tank and the fuel level include: The internal electrodes of each capacitive sensor are sequentially excited to obtain the excitation signal of each capacitive sensor; Based on the excitation signal of each of the capacitive sensors, the capacitance value of the electrode pair in each of the capacitive sensors is determined.

8. The method for measuring aircraft fuel quantity according to claim 7, characterized in that, The step of determining the capacitance value of the electrode pair in each of the capacitive sensors based on the excitation signal of each of the capacitive sensors includes: Based on the excitation signal of each of the capacitive sensors, the original capacitance signal of the electrode pair in each of the capacitive sensors is measured; The original capacitance signal is amplified and filtered to obtain a conditioned capacitance signal. The conditioned capacitance signal is converted from analog to digital to determine the capacitance value of the electrode pair in each capacitance sensor.

9. The method for measuring aircraft fuel quantity according to claim 7, characterized in that, The steps of measuring the capacitance values ​​of several capacitive sensors pre-installed in the aircraft's fuel tank and the fuel level include: Based on the capacitance values ​​of each electrode pair in the capacitance sensor and the preset mapping relationship between capacitance and liquid level, the liquid level height corresponding to the capacitance value of each electrode pair is determined.

10. The method for measuring aircraft fuel quantity according to claim 6, characterized in that, The capacitance sensor is a capacitance tomography capacitance sensor.

11. A system for measuring the fuel level of an aircraft, characterized in that, The system includes: The data acquisition module is used to measure the capacitance values ​​of several capacitive sensors pre-installed in the aircraft's fuel tank and the fuel level. The local oil level determination module is used to determine the oil-gas interface of the local oil level corresponding to each of the capacitance sensors based on the capacitance value. The local tilt angle determination module is used to determine the tilt angle of each local oil surface based on each of the oil-gas interfaces. The global tilt angle determination module is used to perform surface fitting on the tilt angles of multiple local oil surfaces to determine the tilt angle of the complete oil surface inside the aircraft's fuel tank. The available fuel quantity calculation module is used to determine the available fuel quantity in the aircraft's fuel tank based on the tilt angle of the complete fuel surface and the fuel level height.

12. The aircraft fuel quantity measurement system according to claim 11, characterized in that, The capacitive sensor includes multiple inner electrodes and multiple outer electrodes. The multiple inner electrodes are spaced apart along a circumferential direction. The multiple outer electrodes are disposed outside the multiple inner electrodes and are spaced apart along the circumferential direction. The inner electrodes are arranged opposite to at least one of the outer electrodes to form an electrode pair. The data acquisition module includes an excitation unit and a capacitance determination unit. The excitation unit is used to sequentially excite the internal electrodes of each of the capacitive sensors to obtain the excitation signal of each of the capacitive sensors. The capacitance determination unit is used to determine the capacitance value of the electrode pair in each of the capacitance sensors based on the excitation signal of each capacitance sensor.

13. The aircraft fuel quantity measurement system according to claim 12, characterized in that, The capacitance determination unit includes a capacitance measurement subunit, a signal conditioning subunit, and an analog-to-digital conversion subunit. The capacitance measurement subunit is used to measure the original capacitance signal of the electrode pair in each capacitance sensor based on the excitation signal of each capacitance sensor. The signal conditioning subunit is used to amplify and filter each of the original capacitor signals to obtain the conditioned capacitor signal. The analog-to-digital conversion subunit is used to perform analog-to-digital conversion on the conditioned capacitance signal to determine the capacitance value of the electrode pair in each capacitance sensor.

14. An aircraft, characterized in that, It includes a memory and a processor, wherein the memory stores a computer program that, when executed by the processor, implements the method as described in any one of claims 1-10.

15. A computer-readable storage medium, characterized in that, It stores a computer program, which is loaded by a processor to perform the steps of the method according to any one of claims 1-10.

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