Method and system for adaptive measurement of aircraft fuel quantity

Abstract

The application discloses an airplane fuel oil adaptive measurement method and system, comprising: obtaining the flight time of an airplane and the oil consumption rate of each engine of the airplane, constructing a first oil measurement model, calculating the change amount and the current fuel oil of the fuel tank within a set time based on the first oil measurement model, which are respectively a first fuel change amount and a first fuel oil; obtaining the measurement data of the oil sensor of each fuel tank of the airplane, constructing a second oil measurement model, calculating the change amount and the current fuel oil of the fuel tank within a set time based on the second oil measurement model, which are respectively a second fuel change amount and a second fuel oil; and performing confidence evaluation on the first oil measurement model and the second oil measurement model to obtain the measurement value of the current airplane fuel oil. The application improves the accuracy and reliability of the fuel oil measurement, and improves the reliability of the airplane fuel oil measurement.

Description

Technical Field

[0001] This invention belongs to the field of automated measurement technology, specifically relating to an adaptive measurement method and system for aircraft fuel quantity. Background Technology

[0002] Aircraft fuel measurement has a significant impact on aircraft flight range and fuel control, and in recent years, the reliability and accuracy of aircraft fuel measurement have received increasing attention. Currently, aircraft fuel measurement mainly relies on direct measurement using fuel level sensors installed inside the fuel tank. This single data source makes it difficult to guarantee the accuracy and reliability of the measurements. Furthermore, when the fuel level sensor malfunctions, it will lead to abnormal measurement data, affecting the normal operation of the fuel measurement system and consequently impacting the normal execution of aircraft missions. Summary of the Invention

[0003] The purpose of this invention is to provide an adaptive measurement method and system for aircraft fuel quantity, so as to solve the problems of low measurement accuracy and reliability of existing fuel measurement systems and the difficulty in measuring fuel quantity normally when the fuel quantity sensor fails.

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

[0005] An adaptive measurement method for aircraft fuel quantity includes:

[0006] The flight time of the aircraft and the fuel consumption rate of each engine of the aircraft are obtained, and a first fuel quantity measurement model is constructed. Based on the first fuel quantity measurement model, the change in the fuel quantity in the fuel tank and the current fuel quantity are calculated within a set time, which are respectively the first fuel change and the first fuel quantity.

[0007] Acquire the measurement data of the fuel level sensors in each fuel tank of the aircraft, construct a second fuel level measurement model, and calculate the change in fuel level in the fuel tank and the current fuel level within a set time based on the second fuel level measurement model, which are the second fuel level change and the second fuel level, respectively.

[0008] The confidence levels of the first and second fuel quantity measurement models are evaluated to obtain the current fuel quantity of the aircraft.

[0009] In some embodiments, when all fuel level sensors in each fuel tank are functioning normally, the logic for evaluating the confidence level of the first fuel level measurement model and the second fuel level measurement model is as follows:

[0010] When the aircraft is determined to be in level flight, the second fuel level is used as the current fuel level measurement.

[0011] When the aircraft is determined to be in a large attitude state, the first fuel change and the second fuel change are compared. When the first fuel change is greater than the second fuel change, the first fuel quantity is used as the current fuel quantity of the aircraft. When the first fuel change is less than the second fuel change, the second fuel quantity is used as the current fuel quantity of the aircraft.

[0012] In some embodiments, when the fuel level sensor in fuel tank 0 is functioning normally, but one or more of the fuel level sensors in other fuel tanks malfunction, the judgment logic for evaluating the confidence level of the first fuel level measurement model and the second fuel level measurement model is as follows:

[0013] Determine the fuel level in fuel tank #0;

[0014] When the fuel in tank 0 is not depleted, the current fuel level of the aircraft is obtained by evaluating the confidence of the first and second fuel level measurement models based on the judgment logic that the fuel level sensors of each tank are working normally.

[0015] When the fuel in fuel tank 0 is depleted, the first fuel quantity calculated based on the first fuel quantity measurement model will be used as the current fuel quantity of the aircraft.

[0016] In some embodiments, when the fuel level sensor in fuel tank 0 malfunctions while the fuel level sensors in other fuel tanks function normally, the judgment logic for evaluating the confidence level of the first fuel level measurement model and the second fuel level measurement model is as follows:

[0017] Determine the fuel level in fuel tank #0;

[0018] When the fuel in fuel tank 0 is not depleted, the first fuel quantity calculated based on the first fuel quantity measurement model will be used as the current fuel quantity of the aircraft.

[0019] When the fuel in tank 0 is depleted, the current fuel level of the aircraft is obtained by evaluating the confidence level of the first and second fuel level measurement models based on the judgment logic that assumes all fuel level sensors in each tank are working normally.

[0020] In some embodiments, when the fuel level sensor in fuel tank 0 malfunctions and one or more of the fuel level sensors in other fuel tanks malfunction, the judgment logic for evaluating the confidence level of the first fuel level measurement model and the second fuel level measurement model is as follows:

[0021] The first fuel quantity calculated based on the first fuel quantity measurement model is used as the current fuel quantity measurement value of the aircraft.

[0022] In some embodiments, the working status information of the oil pump in tank 0 is obtained, and the oil level in tank 0 is determined based on the working status of the oil pump in tank 0.

[0023] In some embodiments, the aircraft load and flight altitude are obtained to correct the fuel consumption rate of each engine, and a first fuel quantity measurement model is constructed based on the corrected engine fuel consumption rate.

[0024] In some embodiments, the aircraft attitude angle and acceleration are acquired, and a second fuel measurement model is constructed based on the measurement data from the aircraft attitude angle, acceleration, and fuel level sensors.

[0025] In some embodiments, fuel level alarm information and fuel pump status control information are acquired, and a confidence evaluation is performed on the first fuel quantity measurement model and the second fuel quantity measurement model. When the first fuel quantity is used as the measurement value of the current aircraft fuel quantity, the first fuel quantity is corrected according to the fuel level alarm information and the fuel pump status control information.

[0026] On the other hand, the present invention also provides an adaptive measurement system for aircraft fuel quantity, comprising:

[0027] The data acquisition unit is used to acquire flight status data and fuel level sensor measurement data of the aircraft.

[0028] The first fuel quantity measurement unit is used to calculate the change in fuel quantity in the fuel tank and the current fuel quantity within a set time according to the first fuel quantity measurement model.

[0029] The second fuel quantity measurement unit is used to calculate the change in fuel quantity in the fuel tank and the current fuel quantity within a set time period based on the second fuel quantity measurement model.

[0030] The fuel quantity calculation unit is used to calculate the current fuel quantity of the aircraft based on the confidence evaluation results of the first fuel quantity measurement model and the second fuel quantity measurement model.

[0031] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0032] This invention fully utilizes data collected by various sensors on the aircraft, and acquires various flight status data and fuel quantity sensor measurement data. It constructs a fuel quantity measurement model from multiple dimensions to calculate the current fuel quantity of the aircraft, and evaluates the confidence level of each measurement value to obtain the final fuel quantity measurement value. This improves the accuracy and reliability of fuel quantity measurement and ensures flight safety.

[0033] This invention constructs different fuel quantity measurement models from two dimensions: fuel consumption and fuel level. Based on the judgment logic of confidence evaluation, it can still achieve accurate measurement of aircraft fuel quantity when the fuel quantity sensor fails, thus improving the reliability of aircraft fuel quantity measurement. Attached Figure Description

[0034] 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.

[0035] Figure 1 This is a schematic diagram of the measurement system of the present invention.

[0036] Figure 2 This is a block diagram of the measurement system structure of the present invention.

[0037] Figure 3 This is a flowchart illustrating the judgment logic for evaluating the confidence level of the first oil quantity measurement model and the second oil quantity measurement model in this invention. Detailed Implementation

[0038] 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.

[0039] Currently, aircraft have achieved digital and intelligent design and application, and various types of sensors are deployed on aircraft to achieve precise measurement and control of flight status.

[0040] Based on the above-mentioned features, this invention acquires measurement data from various sensors on the aircraft and flight status information through a data bus, enabling multi-dimensional measurement of the aircraft's fuel level. By comparing the multi-dimensional measurement data, the accuracy and reliability of fuel level measurement are improved, ensuring flight safety. At the same time, when the fuel level sensor in the fuel measurement system malfunctions or experiences measurement errors, it ensures that the aircraft's fuel level can be measured and fed back normally, improving the reliability of the fuel level measurement system.

[0041] The following describes the specific implementation of the adaptive measurement method of the present invention for measuring aircraft fuel quantity, with reference to specific embodiments.

[0042] Reference Figure 1 This is a system structure design block diagram for measuring aircraft fuel quantity in this embodiment. Taking the measurement of fuel quantity in five fuel tanks on an aircraft as an example, generally, when the five fuel tanks supply fuel to the four engines of the aircraft via fuel pumps, fuel is supplied first from tank 0, followed by fuel from tanks 1-4. The adaptive measurement method in this embodiment is explained below, taking into account this characteristic of aircraft fuel supply, and includes the following steps:

[0043] Acquire the aircraft's flight status data and the measurement values ​​of the fuel level sensors in each fuel tank. The flight status data includes flight duration, fuel consumption rate of the four engines, aircraft load, flight altitude, fuel pump status control information, aircraft attitude angle, acceleration, fuel level warning information, etc.

[0044] Based on the aircraft's flight duration and the fuel consumption rate of the four engines, a first fuel quantity measurement model is constructed. Based on the first fuel quantity measurement model, the change in fuel quantity in the fuel tank and the current fuel quantity within a set time are calculated, which are respectively the first fuel quantity change and the first fuel quantity.

[0045] Specifically, based on the flight duration h and the engine fuel consumption rate υ j (j = 1, 2, 3, 4, representing the engine fuel consumption rate of the j-th path), the fuel consumption calculation formula based on the first fuel quantity measurement model can be obtained as follows:

[0046]

[0047] According to formula (1), the change in the amount of fuel in the tank within a set time period can be obtained, that is, the first change in fuel quantity.

[0048] By recording the total fuel level of the aircraft before takeoff, the formula for calculating the total fuel level is as follows:

[0049]

[0050] Among them, M 油i This represents the amount of fuel in the i-th fuel tank.

[0051] According to equations (1) and (2), the current fuel quantity based on the first fuel quantity measurement model can be obtained, namely the first fuel quantity.

[0052] When calculating aircraft fuel quantity using engine fuel consumption rate, to improve measurement accuracy, the current aircraft load and flight altitude can be used to compensate and correct the engine fuel consumption rate, and the corrected engine fuel consumption rate can be used to construct the first fuel quantity measurement model.

[0053] Based on the measurement data of the fuel level sensors in each fuel tank of the aircraft, a second fuel level measurement model is constructed. Based on the second fuel level measurement model, the change in fuel level in the fuel tank and the current fuel level are calculated within a set time, which are the second fuel level change and the second fuel level, respectively.

[0054] To improve the accuracy of fuel quantity calculation when calculating aircraft fuel quantity based on fuel quantity sensor measurements, aircraft attitude angles (pitch angle α, roll angle β) and aircraft acceleration can be introduced and used together with fuel quantity sensor measurements to construct a second fuel quantity measurement model.

[0055] The formula for calculating the fuel level in each fuel tank is as follows:

[0056] M 油i =H i *Q(H, α, β)*ρ i ……(3)

[0057] Among them, H i Let H be the current fuel level measured by the fuel level sensor, and Q(H, α, β) be the mathematical model of the fuel tank constructed from the total height H of the fuel level sensor and the attitude angle. ρ i This refers to the density of the fuel.

[0058] According to formula (3), the change in fuel quantity in the tank over a certain period of time can be obtained, which is the second fuel quantity change.

[0059] According to formulas (3) and (2), the current fuel quantity based on the second fuel quantity measurement model can be obtained, that is, the second fuel quantity.

[0060] Based on the first fuel quantity measurement model and the second fuel quantity measurement model, the confidence level of the current fuel quantity measurement value obtained based on the first fuel quantity measurement model and the second fuel quantity measurement model is evaluated to obtain the current aircraft fuel quantity measurement value.

[0061] In this embodiment, the judgment logic for evaluating the confidence level of the first oil quantity measurement model and the second oil quantity measurement model varies in different scenarios, as described above. Figure 3 This includes the following situations:

[0062] 1) The fuel level sensors in all fuel tanks are functioning normally.

[0063] The judgment logic for evaluating the confidence level of the first and second oil quantity measurement models is as follows:

[0064] When the aircraft is determined to be in level flight, the second fuel level is used as the current fuel level measurement.

[0065] When the aircraft is determined to be in a large attitude state, the first fuel change and the second fuel change are compared. When the first fuel change is greater than the second fuel change, the first fuel quantity is used as the current fuel quantity of the aircraft. When the first fuel change is less than the second fuel change, the second fuel quantity is used as the current fuel quantity of the aircraft.

[0066] The aircraft's flight attitude here refers to a "large attitude" state, which is usually relative to level flight. This means the aircraft has certain pitch, yaw, and roll angles during flight. Because the fuel level in the tanks is more complex in this state compared to level flight, a confidence level assessment method is introduced to measure the fuel level to improve the reliability of the measurements. Determining whether the aircraft is in a large attitude state by obtaining its pitch, yaw, and roll angles is relatively easy.

[0067] 2) The fuel level sensor in fuel tank 0 is normal, but one or more of the fuel level sensors in fuel tanks 1-4 are faulty.

[0068] The judgment logic for evaluating the confidence level of the first and second oil quantity measurement models is as follows:

[0069] Determine the fuel level in fuel tank #0; the fuel level in fuel tank #0 can be determined based on the measurement data from the fuel level sensor in fuel tank #0 or the fuel pump status control information in fuel tank #0.

[0070] When the fuel in tank 0 is not depleted, the fuel level measurement values ​​of tanks 1-4 at the time of the malfunction are obtained and remain unchanged until the fuel in tank 0 is depleted. Since only tank 0 is supplying fuel at this time, and the fuel in tanks 1-4 is not consumed, the current fuel level measurement value of the aircraft is obtained by judging the confidence of the first fuel level measurement model and the second fuel level measurement model when the fuel level sensors of each tank are working normally.

[0071] When the fuel in tank 0 is depleted, the first fuel level is used as the current fuel level of the aircraft. That is, the first fuel level measurement model is used to calculate the current fuel level of the aircraft.

[0072] 3) The fuel level sensor in fuel tank #0 is faulty, while the fuel level sensors in fuel tanks #1-#4 are functioning normally.

[0073] The judgment logic for evaluating the confidence level of the first and second oil quantity measurement models is as follows:

[0074] Determine the fuel level in tank 0; Since the fuel level sensor in tank 0 is malfunctioning, the method to determine the fuel level in tank 0 is to obtain the working status information of the fuel pump in tank 0, and then determine the fuel level in tank 0 based on the working status of the fuel pump in tank 0.

[0075] When the fuel in fuel tank 0 is not depleted, the first fuel quantity calculated based on the first fuel quantity measurement model will be used as the current fuel quantity of the aircraft.

[0076] When the fuel in tank 0 is depleted, since the fuel level sensors in the other tanks are all functioning normally, the fuel levels in tanks 1-4 are calculated based on the first fuel level measurement model and the second fuel level measurement model, respectively. At this point, the current fuel level of the aircraft can be obtained by using the judgment logic of evaluating the confidence level of the first and second fuel level measurement models when the fuel level sensors in each tank are functioning normally.

[0077] 4) The fuel level sensor in fuel tank 0 is faulty, and one or more of the fuel level sensors in fuel tanks 1-4 are also faulty.

[0078] The confidence evaluation logic for the first and second oil quantity change curves is as follows:

[0079] The first fuel quantity calculated based on the first fuel quantity measurement model is used as the current fuel quantity measurement value of the aircraft.

[0080] In this embodiment, the aircraft fuel quantity is measured from two different dimensions based on the first fuel quantity measurement model and the second fuel quantity measurement model, making it applicable to fuel quantity measurement when the fuel quantity sensor fails during flight, thereby improving the reliability of aircraft fuel quantity measurement.

[0081] On the other hand, this invention also provides an adaptive measurement system for aircraft fuel quantity based on the adaptive measurement method in the above embodiments, referring to... Figure 2 ,include:

[0082] The data acquisition unit is used to acquire flight status data and fuel level sensor measurement data of the aircraft.

[0083] The first fuel quantity measurement unit is used to calculate the change in fuel quantity in the fuel tank and the current fuel quantity within a set time according to the first fuel quantity measurement model.

[0084] The second fuel quantity measurement unit is used to calculate the change in fuel quantity in the fuel tank and the current fuel quantity within a set time period based on the second fuel quantity measurement model.

[0085] The fuel quantity calculation unit is used to calculate the current fuel quantity of the aircraft based on the confidence evaluation results of the first fuel quantity measurement model and the second fuel quantity measurement model.

[0086] The system can utilize various existing sensors on the aircraft, as well as RS422A, HB6096, and 1553B data buses, to collect various flight status data and fuel quantity sensor measurement data. This data is then applied to the measurement of aircraft fuel quantity, which not only improves the accuracy and reliability of aircraft fuel quantity measurement but also greatly enhances the ability to utilize aircraft flight status data, providing a new approach to aircraft fuel quantity measurement.

[0087] 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. An adaptive measurement method for aircraft fuel quantity, characterized in that, include: The flight time of the aircraft and the fuel consumption rate of each engine of the aircraft are obtained, and a first fuel quantity measurement model is constructed. Based on the first fuel quantity measurement model, the change in the fuel quantity in the fuel tank and the current fuel quantity are calculated within a set time, which are respectively the first fuel change and the first fuel quantity. Acquire the measurement data of the fuel level sensors in each fuel tank of the aircraft, construct a second fuel level measurement model, and calculate the change in fuel level in the fuel tank and the current fuel level within a set time based on the second fuel level measurement model, which are the second fuel level change and the second fuel level, respectively. The confidence levels of the first and second fuel quantity measurement models are evaluated to obtain the current fuel quantity of the aircraft. When all fuel level sensors in each fuel tank are functioning normally, the logic for evaluating the confidence level of the first and second fuel level measurement models is as follows: When the aircraft is determined to be in level flight, the second fuel level is used as the current fuel level measurement. When the aircraft is determined to be in a large attitude state, the first fuel change and the second fuel change are compared; when the first fuel change is greater than the second fuel change, the first fuel quantity is used as the current fuel quantity of the aircraft; when the first fuel change is less than the second fuel change, the second fuel quantity is used as the current fuel quantity of the aircraft. The aircraft load and flight altitude are used to correct the fuel consumption rate of each engine. The corrected engine fuel consumption rate is used to construct the first fuel quantity measurement model. The aircraft attitude angle and acceleration are acquired, and a second fuel measurement model is constructed based on the measurement data of the aircraft attitude angle, acceleration and fuel level sensors.

2. The adaptive measurement method for aircraft fuel quantity according to claim 1, characterized in that, When the fuel level sensor in fuel tank 0 is functioning normally, but one or more of the fuel level sensors in other fuel tanks malfunction, the logic for evaluating the confidence level of the first and second fuel level measurement models is as follows: Determine the fuel level in fuel tank #0; When the fuel in tank 0 is not depleted, the current fuel level of the aircraft is obtained by evaluating the confidence of the first and second fuel level measurement models based on the judgment logic that the fuel level sensors of each tank are working normally. When the fuel in fuel tank 0 is depleted, the first fuel quantity calculated based on the first fuel quantity measurement model will be used as the current fuel quantity of the aircraft.

3. The adaptive measurement method for aircraft fuel quantity according to claim 1, characterized in that, When the fuel level sensor in fuel tank 0 malfunctions, while the fuel level sensors in other fuel tanks are functioning normally, the logic for evaluating the confidence level of the first and second fuel level measurement models is as follows: Determine the fuel level in fuel tank #0; When the fuel in fuel tank 0 is not depleted, the first fuel quantity calculated based on the first fuel quantity measurement model will be used as the current fuel quantity of the aircraft. When the fuel in tank 0 is depleted, the current fuel level of the aircraft is obtained by evaluating the confidence level of the first and second fuel level measurement models based on the judgment logic that assumes all fuel level sensors in each tank are working normally.

4. The adaptive measurement method for aircraft fuel quantity according to claim 1, characterized in that, When the fuel level sensor in fuel tank 0 malfunctions and one or more of the fuel level sensors in other fuel tanks malfunction, the confidence evaluation logic for the first fuel level measurement model and the second fuel level measurement model is as follows: The first fuel quantity calculated based on the first fuel quantity measurement model is used as the current fuel quantity measurement value of the aircraft.

5. The adaptive measurement method for aircraft fuel quantity according to any one of claims 1-4, characterized in that, Obtain the working status information of the oil pump in oil tank No. 0, and determine the oil level in oil tank No. 0 based on the working status of the oil pump in oil tank No.

0.

6. The adaptive measurement method for aircraft fuel quantity according to any one of claims 1-4, characterized in that, The system acquires fuel level alarm information and fuel pump status control information, evaluates the confidence level of the first fuel quantity measurement model and the second fuel quantity measurement model, and corrects the first fuel quantity based on the fuel level alarm information and fuel pump status control information when using the first fuel quantity as the current aircraft fuel quantity measurement value.

7. An adaptive measurement system for aircraft fuel quantity, characterized in that, include: The data acquisition unit is used to acquire flight status data, fuel level sensor measurement data, aircraft load, flight altitude, aircraft attitude angle, and acceleration. The first fuel quantity measurement unit is used to correct the fuel consumption rate of each engine according to the aircraft load and flight altitude, and to construct the first fuel quantity measurement model with the corrected engine fuel consumption rate; it is also used to calculate the change in fuel quantity in the fuel tank and the current fuel quantity within a set time according to the first fuel quantity measurement model, which are respectively the first fuel change and the first fuel quantity. The second fuel quantity measurement unit is used to construct a second fuel quantity measurement model based on the aircraft attitude angle, acceleration and fuel quantity sensor measurement data; it is also used to calculate the change in fuel quantity in the fuel tank and the current fuel quantity within a set time period based on the second fuel quantity measurement model, which are respectively the second fuel quantity change and the second fuel quantity. The fuel quantity calculation unit is used to calculate the current fuel quantity of the aircraft based on the confidence evaluation results of the first fuel quantity measurement model and the second fuel quantity measurement model. When all fuel level sensors in each fuel tank are functioning normally, the confidence evaluation logic for the first and second fuel level measurement models is as follows: if the aircraft is in level flight, the second fuel level is used as the current fuel level measurement; if the aircraft is in a high-attitude flight, the first fuel level change and the second fuel level change are compared; if the first fuel level change is greater than the second fuel level change, the first fuel level is used as the current fuel level measurement; if the first fuel level change is less than the second fuel level change, the second fuel level is used as the current fuel level measurement.

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