Fuel oil measuring method, system and equipment based on two-dimensional dynamic weight adjustment and medium

Abstract

The invention discloses a fuel oil measurement method, system and device based on two-dimensional dynamic weight adjustment and a medium. The method comprises the following steps: S01, acquiring flight state data and fuel oil distribution data; s02, obtaining a time dimension dynamic weight and a space dimension dynamic weight; and S03, respectively carrying out weighted fusion processing on the fuel value calculated based on the flight state and the fuel value calculated based on the fuel distribution by adopting the time dimension dynamic weight and the space dimension dynamic weight to obtain an optimized fuel measurement value. According to the method, the measurement method based on two-dimensional dynamic weight adjustment is adopted, fuel measurement errors caused by aircraft flight attitude changes and fuel shaking can be reduced, the accuracy of fuel measurement data is guaranteed, the reliability of flight control system decision making is improved, and the flight range planning is optimized by reducing the fuel measurement errors and improving the fuel consumption calculation precision.

Description

Technical Field

[0001] This invention belongs to the field of aviation fuel measurement technology, specifically relating to a fuel measurement method, system, equipment, and medium based on dual-dimensional dynamic weight adjustment. Background Technology

[0002] Fuel measurement is a critical aspect of the operation of many devices (such as automobiles, ships, generators, etc.). However, traditional fuel measurement methods typically use a single sensor, which has the following problems: 1) Measurement accuracy is greatly affected by environmental factors (such as temperature, fuel level fluctuations, and fuel density changes); 2) The limitations of a single sensor lead to high measurement errors; 3) Static weighting methods cannot adapt to changes in dynamic operating conditions. Summary of the Invention

[0003] The purpose of this invention is to provide a fuel measurement method, system, device and medium based on dual-dimensional dynamic weight adjustment, so as to solve the problems that the fuel measurement accuracy is easily affected by external factors and the measurement error is large.

[0004] This invention is achieved through the following technical solution:

[0005] The fuel measurement method based on two-dimensional dynamic weight adjustment includes the following steps:

[0006] S01. Acquire flight status data and fuel distribution data;

[0007] S02. Obtain the dynamic weights of the time dimension and the dynamic weights of the spatial dimension, including:

[0008] S021. Define time dimension weights and spatial dimension weights. Time dimension weights are used to characterize the impact of different stages of the aircraft on the reliability of fuel measurement values. Spatial dimension weights are used to dynamically adjust the weights of fuel sensor measurement values ​​at different locations of the aircraft as the flight attitude changes.

[0009] S022. Obtain the confidence level of flight status data and the confidence level of fuel distribution data. The confidence level of flight status data is used to weigh the reliability of the fuel quantity calculated based on the current flight status, and the confidence level of fuel distribution data is used to weigh the reliability of the current fuel sensor measurement data.

[0010] S023. Obtain the dynamic weight of the time dimension based on the weight of the time dimension and the confidence level of the flight status data, and obtain the weight of the space dimension based on the weight of the space dimension and the confidence level of the fuel distribution data.

[0011] S03. The fuel values ​​calculated based on flight status and fuel distribution are weighted and fused using dynamic weights in the time dimension and spatial dimension, respectively, to obtain optimized fuel measurement values.

[0012] In some embodiments of the present invention, the flight status data includes flight altitude, speed, pitch angle, roll angle, and wheel load status.

[0013] In some embodiments of the present invention, the fuel distribution data includes fuel measurement values ​​of each fuel tank and the position of the fuel center of gravity.

[0014] In some embodiments of the present invention, a step of preprocessing the acquired flight status data and fuel distribution data is also included.

[0015] In some embodiments of the present invention, data preprocessing includes noise reduction using Kalman filtering, time synchronization using timestamps to align sensor data, and standardization of data from different units.

[0016] In some embodiments of the present invention, flight state confidence is calculated using the rate of change of flight speed, the rate of change of acceleration, the deviation of the current pitch angle from normal level flight, and the change in altitude.

[0017] The fuel distribution confidence level was calculated using fuel level fluctuation rate, the degree of unevenness in fuel distribution between fuel tanks, and the offset of the fuel center of gravity within the fuel tanks.

[0018] In some embodiments of the present invention, in step S03, the dynamic weights of the time dimension and the dynamic weights of the spatial dimension are normalized, and the normalized dynamic weights of the time dimension and the dynamic weights of the spatial dimension are weighted and fused to obtain optimized fuel measurement values.

[0019] On the other hand, the present invention also provides a fuel measurement system based on dual-dimensional dynamic weight adjustment, which uses the aforementioned fuel measurement method to measure fuel quantity; including:

[0020] The data acquisition module is used to acquire flight status data and fuel distribution data;

[0021] The dynamic weight acquisition module is used to acquire dynamic weights in the time dimension and dynamic weights in the spatial dimension.

[0022] The weighted fusion optimization module is used to perform weighted fusion processing on the fuel value calculated based on flight status and the fuel value calculated based on fuel distribution, respectively, according to the dynamic weights of the time dimension and the dynamic weights of the spatial dimension, to obtain the optimized fuel measurement value.

[0023] On the other hand, the present invention also provides an electronic device, comprising:

[0024] Processor; and,

[0025] Memory for storing the executable instructions of the processor;

[0026] The processor is configured to execute the fuel measurement method by executing the executable instructions.

[0027] On the other hand, the present invention also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the fuel measurement method described above.

[0028] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0029] This invention employs a measurement method based on dual-dimensional dynamic weight adjustment, which can reduce fuel measurement errors caused by changes in aircraft flight attitude and fuel sloshing, ensure the accuracy of fuel measurement data, improve the reliability of flight control system decisions, and improve the accuracy of fuel consumption calculation by reducing fuel measurement errors, thereby optimizing flight route planning. Attached Figure Description

[0030] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings in the embodiments will be briefly described below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0031] Figure 1 This is a flowchart of the fuel measurement method based on two-dimensional dynamic weight adjustment according to an embodiment of the present invention.

[0032] Figure 2 This is a schematic diagram of the two-dimensional dynamic weight adjustment process in an embodiment of the present invention.

[0033] Figure 3 This is a block diagram of the fuel measurement system according to an embodiment of the present invention. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of this application clearer, specific embodiments of this application will be described in further detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are merely for explaining this application and not for limiting it. It should also be noted that, for ease of description, only the parts relevant to this application are shown in the drawings, not all of them. Before discussing exemplary embodiments in more detail, it should be mentioned that some exemplary embodiments are described as processes or methods depicted as flowcharts. Although the flowcharts describe operations (or steps) as sequential processes, many of these operations can be performed in parallel, concurrently, or simultaneously. Furthermore, the order of the operations can be rearranged. The process can be terminated when its operation is completed, but may also have additional steps not included in the drawings. The process can correspond to a method, function, procedure, subroutine, subprogram, etc.

[0035] Capacitive fuel sensors calculate fuel level by measuring changes in capacitance, and their accuracy is affected by factors such as temperature, changes in the dielectric constant of the fuel, tank tilt, and fuel sloshing.

[0036] To improve the accuracy, precision, and reliability of fuel measurement, this invention provides a measurement method that can combine multiple data and dynamically adjust the weight of fuel sensor measurements according to actual operating conditions. By simultaneously adjusting the weight of measurements in two dimensions, the accuracy of fuel measurement is improved.

[0037] This invention employs a weighted fusion method, combining the time dimension (flight status) and the spatial dimension (fuel distribution) to dynamically adjust the fuel measurement weights of the two dimensions.

[0038] In terms of time, the fuel sensors are dynamically adjusted as the flight phases (takeoff, cruise, and landing) change. During takeoff and landing, when fuel sloshing is severe, the measurement weight of affected fuel sensors is reduced to avoid errors. During cruise, when fuel is stable, the measurement weight of fuel sensors can be increased to improve measurement accuracy.

[0039] In the spatial dimension, the weights of measurement points in fuel tanks at different locations or with different shapes on the aircraft are dynamically adjusted, taking into account the fuel distribution. The weights of different measurement locations are optimized based on factors such as the aircraft's pitch angle, roll angle, and fuel tank shape.

[0040] By employing a two-dimensional dynamic weight adjustment fuel measurement method, the measurement accuracy and reliability of the fuel measurement system can be improved, making it particularly suitable for accurate fuel measurement in applications such as aviation, automobiles, and ships.

[0041] In some embodiments of the present invention, reference is made to Figure 1 and Figure 2The fuel measurement method based on two-dimensional dynamic weight adjustment includes the following steps:

[0042] S01, Data Acquisition

[0043] Sensors are used to collect relevant data, including:

[0044] Flight status data, including flight altitude, speed, pitch angle, roll angle, wheel load status, etc.

[0045] Fuel distribution data, including fuel measurements in each tank and the location of the fuel center of gravity.

[0046] S02, Data Preprocessing

[0047] The collected data is preprocessed, including:

[0048] Noise reduction: Kalman filtering is used to reduce sensor noise interference.

[0049] Time synchronization processing; use timestamps to align data from each sensor to ensure consistent data timing.

[0050] Normalization: Standardize data from different units to calculate weights.

[0051] S03, Dynamic Weight Calculation

[0052] The calculation of dynamic weights includes:

[0053] 1) Calculation of time dimension weights; the time dimension weights represent the impact of different flight phases on the reliability of fuel measurement values, expressed as:

[0054]

[0055] Among them, W t k1 represents the time dimension weight, and k1 is the flight state adjustment parameter.

[0056] 2) Spatial dimension weight calculation; Spatial dimension weight is used to dynamically adjust the weight of fuel sensor measurements at different locations on the aircraft as the flight attitude changes, and is expressed as:

[0057]

[0058] Among them, W f k1 represents the spatial dimension weight, and k2 represents the fuel distribution adjustment parameter.

[0059] 3) Confidence calculation

[0060] Based on the fuel quantity error calculated from flight data and the fuel sensor data error, the confidence levels of flight status data and fuel distribution data are calculated.

[0061] Confidence is used to dynamically optimize fuel measurement data, weighing the reliability between fuel quantity calculated from flight conditions and fuel quantity measured by fuel sensors, including:

[0062] a) Flight status confidence, which weighs the reliability of the fuel quantity calculated based on the current flight status; expressed as:

[0063]

[0064] Where, σ v The flight speed change rate is used as the confidence level of the flight status decreases when the flight speed changes significantly.

[0065] σ a The flight acceleration rate is the rate of change. When the aircraft's motion changes drastically, the confidence level of the flight status decreases.

[0066] |θ-θ0| represents the deviation between the current pitch angle and normal level flight. When the pitch angle of the aircraft nose is too large, the confidence level of the flight status decreases.

[0067] Δh is the change in altitude. When the aircraft climbs or descends too quickly, the confidence level of the flight status decreases.

[0068] kt is the flight state confidence adjustment coefficient, used to control the sensitivity of the flight state confidence.

[0069] During the cruise phase, the aircraft's flight status is stable, and Ct remains basically unchanged, indicating that the fuel measurement data of the current flight status is highly reliable.

[0070] During takeoff and landing, the aircraft's flight status changes drastically, with large variations in flight speed and pitch angle, resulting in a decrease in Ct (fuel consumption). This makes fuel measurement data representing the current flight status less reliable.

[0071] b) Fuel distribution reliability, which weighs the reliability of current fuel sensor measurement data; expressed as:

[0072]

[0073] Where, σ l The fuel level fluctuation rate is the fuel distribution confidence level decreases when the fuel in the tank sloshes.

[0074] σ b The degree of unevenness in fuel distribution between fuel tanks is considered. When the fuel distribution is uneven, the fuel distribution reliability decreases.

[0075] |G-G0| represents the offset of the fuel center of gravity within the fuel tank. When the fuel center of gravity deviates from the normal value, the fuel distribution reliability decreases.

[0076] kf is the fuel distribution reliability adjustment coefficient, used to control the sensitivity of fuel distribution reliability.

[0077] During the cruise phase, the aircraft's flight status was stable, C f If the value remains basically unchanged, it indicates that the fuel measurement data is highly reliable under the current condition.

[0078] During takeoff and landing, the aircraft's flight status changes drastically. f A decrease indicates that the reliability of fuel measurement data is low under the current conditions.

[0079] 4) Dynamic weight calculation for the time dimension, expressed as:

[0080] W′ t =W t ×C t .

[0081] 5) Dynamic weight calculation for spatial dimensions, expressed as:

[0082] W′ f =W f ×C f .

[0083] S04, Weighted Fuel Measurement Value Fusion Processing

[0084] S041, Dynamic Weight Normalization Processing

[0085] The dynamic weights are normalized to obtain the normalized time-dimensional dynamic weights W. tg The dynamic weight W of the spatial dimension after normalization fg , respectively represented as:

[0086]

[0087]

[0088] S042. Dynamic weights W for the time dimension after normalization. tg The dynamic weight W of the spatial dimension after normalization fg The fuel sensor measurement data is weighted and fused to obtain the optimized fuel measurement value, which is represented as:

[0089] F final =W tg ×F state +W fg ×F fuel ;

[0090] Among them, F final The optimized fuel measurement value; F state Fuel quantity calculated based on flight conditions; Ffuel This is the amount of fuel calculated based on fuel distribution.

[0091] F state The fuel quantity calculated based on flight conditions can be obtained by calculating fuel consumption from flight parameters, and is expressed as:

[0092] F state =F m *K(h, v, θ, a);

[0093] Where Fm is the fuel measurement value obtained by the fuel sensor;

[0094] K(h, v, θ, a) is the flight state correction coefficient, which is related to the flight state.

[0095] K=C1v+C2a+C3cos(θ)+C4Δh;

[0096] Where C1, C2, C3, and C4 are coefficients determined through experiments;

[0097] v represents flight speed, which affects engine fuel consumption;

[0098] 'a' represents flight acceleration, which affects fuel sloshing within the fuel tank and indirectly affects the calculation of fuel consumption.

[0099] θ is the flight pitch angle, which affects engine intake efficiency and thus fuel consumption;

[0100] Δh represents the change in flight altitude, which affects the current air pressure and thus the amount of fuel injected.

[0101] F fuel The fuel quantity calculated based on fuel distribution can be directly measured using fuel sensors (fuel level sensor, fuel center of gravity sensor), and expressed as:

[0102]

[0103] Where n is the number of fuel tanks;

[0104] h i Let i be the fuel level in the i-th fuel tank;

[0105] A i Let be the cross-sectional area of ​​the i-th fuel tank, which is affected by the flight attitude;

[0106] ρ is the fuel density, which is affected by temperature and can be corrected according to temperature.

[0107] On the other hand, in some embodiments of the present invention, reference is made to Figure 3A fuel measurement system based on dual-dimensional dynamic weight adjustment, employing the aforementioned fuel measurement method to measure fuel quantity; comprising:

[0108] The data acquisition module is used to acquire flight status data and fuel distribution data. The data acquisition module includes sensors, sensor interface modules, multiplexers, and ADC modules to realize data acquisition and transmission.

[0109] The dynamic weight acquisition module is used to acquire dynamic weights in the time dimension and dynamic weights in the spatial dimension.

[0110] The weighted fusion optimization module is used to perform weighted fusion processing on the fuel value calculated based on flight status and the fuel value calculated based on fuel distribution according to the dynamic weights of the time dimension and the spatial dimension, respectively, to obtain the optimized fuel measurement value. The weighted fusion optimization module is electrically connected to the avionics DMC through the communication interface module and outputs the optimized fuel measurement value.

[0111] The fuel measurement system also includes a data preprocessing module for preprocessing the collected data.

[0112] On the other hand, the present invention also provides an electronic device, comprising:

[0113] Processor; and,

[0114] Memory for storing the executable instructions of the processor;

[0115] The processor is configured to execute the fuel measurement method by executing the executable instructions.

[0116] On the other hand, the present invention also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the fuel measurement method described above.

[0117] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A fuel measurement method based on dual-dimensional dynamic weight adjustment, characterized in that, Includes the following steps: S01. Acquire flight status data and fuel distribution data; S02. Obtain the dynamic weights of the time dimension and the dynamic weights of the spatial dimension, including: S021. Define time dimension weights and spatial dimension weights. Time dimension weights are used to characterize the impact of different stages of the aircraft on the reliability of fuel measurement values. Spatial dimension weights are used to dynamically adjust the weights of fuel sensor measurement values ​​at different locations of the aircraft as the flight attitude changes. S022. Obtain the confidence level of flight status data and the confidence level of fuel distribution data. The confidence level of flight status data is used to weigh the reliability of the fuel quantity calculated based on the current flight status, and the confidence level of fuel distribution data is used to weigh the reliability of the current fuel sensor measurement data. S023. Obtain the dynamic weight of the time dimension based on the weight of the time dimension and the confidence level of the flight status data, and obtain the weight of the space dimension based on the weight of the space dimension and the confidence level of the fuel distribution data. S03. The fuel values ​​calculated based on flight status and fuel distribution are weighted and fused using dynamic weights in the time dimension and spatial dimension, respectively, to obtain optimized fuel measurement values.

2. The fuel measurement method based on dual-dimensional dynamic weight adjustment according to claim 1, characterized in that, The flight status data includes flight altitude, speed, pitch angle, roll angle, and wheel load status.

3. The fuel measurement method based on dual-dimensional dynamic weight adjustment according to claim 1, characterized in that, The fuel distribution data includes fuel measurement values ​​from each fuel tank and the location of the fuel center of gravity.

4. The fuel measurement method based on dual-dimensional dynamic weight adjustment according to claim 1, characterized in that, It also includes steps for preprocessing the acquired flight status data and fuel distribution data.

5. The fuel measurement method based on dual-dimensional dynamic weight adjustment according to claim 4, characterized in that, Data preprocessing includes noise reduction using Kalman filtering, time synchronization using timestamps to align data from different sensors, and standardization of data from different units.

6. The fuel measurement method based on dual-dimensional dynamic weight adjustment according to claim 1, characterized in that, Flight status confidence is calculated using the rate of change of flight speed, the rate of change of acceleration, the deviation of the current pitch angle from normal level flight, and the change in altitude. The fuel distribution confidence level was calculated using fuel level fluctuation rate, the degree of unevenness in fuel distribution between fuel tanks, and the offset of the fuel center of gravity within the fuel tanks.

7. The fuel measurement method based on dual-dimensional dynamic weight adjustment according to claim 1, characterized in that, In step S03, the dynamic weights of the time dimension and the dynamic weights of the spatial dimension are normalized. The normalized dynamic weights of the time dimension and the dynamic weights of the spatial dimension are then weighted and fused to obtain the optimized fuel measurement value.

8. A fuel measurement system based on dual-dimensional dynamic weight adjustment, characterized in that, The fuel quantity is measured using the fuel measurement method according to any one of claims 1-7; comprising: The data acquisition module is used to acquire flight status data and fuel distribution data; The dynamic weight acquisition module is used to acquire dynamic weights in the time dimension and dynamic weights in the spatial dimension. The weighted fusion optimization module is used to perform weighted fusion processing on the fuel value calculated based on flight status and the fuel value calculated based on fuel distribution, respectively, according to the dynamic weights of the time dimension and the dynamic weights of the spatial dimension, to obtain the optimized fuel measurement value.

9. An electronic device, characterized in that, include: processor; as well as, Memory for storing the executable instructions of the processor; The processor is configured to execute the fuel measurement method of any one of claims 1-7 by executing the executable instructions.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the fuel measurement method according to any one of claims 1-7.

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