Fuel consumption model processing method and system based on flight control data table and storage medium

Abstract

The application discloses a fuel consumption model processing method and system based on a flight control data table and a storage medium. The method can be widely applied to the technical field of model application. The method of the application analyzes the physical logic of each influencing factor and fuel consumption through physics, constructs a fuel consumption model according to the physical logic, determines model parameters of the fuel consumption model according to obtained aircraft performance data, then, substitutes the model parameters into the fuel consumption model, and verifies the feasibility of the fuel consumption model according to the data of the obtained flight control data table, so that the application end can understand each influencing factor of the aircraft through the fuel consumption model that passes the verification, and thus can improve the flight safety and reduce the flight cost by improving specific problems.

Description

Technical Field

[0001] The present invention relates to the field of model application technology, and in particular to a fuel consumption model processing method, system and storage medium based on a flight control data table. Background Art

[0002] Fuel consumption is the most important cost metric in the aviation industry. The amount of fuel an aircraft carries is crucial to flight safety and costs. Currently, the planning systems used by the international aviation industry only provide input and output, with intermediate processing acting like a black box. Models, algorithms, and logic are unknown. Consequently, when data fitting accuracy is poor, the application side cannot understand the cause, making it impossible to address the issue, thereby improving flight safety and reducing costs. Furthermore, one of the prerequisites for establishing an accurate route planning system is to accurately characterize the changing patterns of fuel consumption (a key cost) under varying weather conditions and flight states. Summary of the Invention

[0003] The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, the present invention proposes a fuel consumption model processing method, system and storage medium based on a flight control data table, which can effectively improve flight safety and reduce flight costs.

[0004] In one aspect, an embodiment of the present invention provides a method for processing a fuel consumption model based on a flight control data table, comprising the following steps:

[0005] Obtain aircraft performance data;

[0006] By physically analyzing the physical logic of various influencing factors and fuel consumption, the influencing factors include at least one of temperature, flight altitude, takeoff weight, weather conditions, climb speed, ground speed, roll speed, high-altitude wind speed, and flight attitude;

[0007] Constructing a fuel consumption model according to the physical logic;

[0008] determining model parameters of the fuel consumption model based on the aircraft performance data;

[0009] Get the data from the flight control data table;

[0010] The feasibility of the fuel consumption model after substituting the model parameters is checked based on the data in the flight control data table.

[0011] In some embodiments, the physical analysis of the physical logic of various influencing factors and fuel consumption includes:

[0012] Analyze kinetic energy increment and potential energy increment;

[0013] Analyze the approximate value of instantaneous air pressure based on the pressure height formula of static meteorology;

[0014] Analyze the work done by friction according to the flight attitude;

[0015] Analyze lift work based on flight dynamics.

[0016] In some embodiments, analyzing the kinetic energy increment and the potential energy increment includes:

[0017] determining a kinetic energy increment based on the gross weight, flight speed, and high-altitude wind speed of the aircraft at a target time, wherein the flight speed is determined by the climb speed, ground speed, and roll speed;

[0018] The potential energy increment is determined according to the total weight of the aircraft at the target time point, the flight altitude of the aircraft at the target time point, the total weight of the aircraft at the previous time point, and the flight altitude of the aircraft at the previous time point.

[0019] In some embodiments, analyzing the friction work according to the flight attitude includes:

[0020] Determine the atmospheric pressure acting on the aircraft surface;

[0021] Determine the direction of the outer normal of the positive pressure on the aircraft surface;

[0022] The work done by friction is determined according to the pressure, the external normal direction, the flight speed, the high-altitude wind speed and the flight lift coefficient.

[0023] In some embodiments, analyzing the approximate instantaneous air pressure of the aircraft according to a pressure-height formula of static meteorology includes:

[0024] Analyze aircraft roll based on the pressure height formula and Rodrigues rotation formula in static meteorology.

[0025] In some embodiments, analyzing lift work based on flight dynamics includes:

[0026] The lift effect caused by wind resistance is analyzed based on the horizontal flight speed, aircraft pitch angle and flight attitude parameters.

[0027] In some embodiments, the fuel consumption model is formulated as follows:

[0028]

[0029] Among them, K1 represents the fuel energy conversion rate; K2 represents the lift effect coefficient caused by wind resistance during flight; K3 represents the flight attitude parameter; U represents the horizontal flight speed; g represents the acceleration of gravity; h represents the flight altitude; M1(t) represents the fuel load at time t; M0(t) represents the total weight at time t; UR(t) represents the flight speed at time t; e r Represents the coordinate components in the spherical coordinate system; P represents the pressure of the atmosphere on the aircraft surface; represents the external normal direction of the aircraft surface; θ1 represents the elevation angle at time t.

[0030] On the other hand, an embodiment of the present invention provides a fuel consumption model processing system based on a flight control data table, comprising:

[0031] A first acquisition module is used to acquire aircraft performance data;

[0032] an analysis module, configured to perform physical analysis on the physical logic of various influencing factors and fuel consumption, wherein the influencing factors include at least one of temperature, flight altitude, takeoff weight, weather conditions, climb speed, ground speed, roll speed, high-altitude wind speed, and flight attitude;

[0033] A construction module, configured to construct a fuel consumption model according to the physical logic;

[0034] a determination module, configured to determine model parameters of the fuel consumption model based on the aircraft performance data;

[0035] The second acquisition module is used to obtain data from the flight control data table;

[0036] The testing module is used to test the feasibility of the fuel consumption model after the model parameters are substituted according to the data of the flight control data table.

[0037] On the other hand, an embodiment of the present invention provides a fuel consumption model processing system based on a flight control data table, comprising:

[0038] at least one memory for storing a program;

[0039] At least one processor is used to load the program to execute the fuel consumption model processing method based on the flight control data table.

[0040] On the other hand, an embodiment of the present invention provides a storage medium storing a computer-executable program, wherein the computer-executable program is used to implement the fuel consumption model processing method based on the flight control data table when executed by a processor.

[0041] The fuel consumption model processing method based on the flight control data table provided by the embodiment of the present invention has the following beneficial effects:

[0042] This embodiment physically analyzes the physical logic of various influencing factors and fuel consumption, and constructs a fuel consumption model based on the physical logic. Then, the model parameters of the fuel consumption model are determined based on the acquired aircraft performance data. After substituting the model parameters into the fuel consumption model, the feasibility of the fuel consumption model is verified based on the data obtained from the flight control data table. This allows the application end to understand the various influencing factors of the aircraft through the verified fuel consumption model, so that improvements can be made to specific problems to improve flight safety and reduce flight costs.

[0043] Additional aspects and advantages of the present application will be given in part in the following description, become apparent from the following description, or be learned by practice of the present application. BRIEF DESCRIPTION OF DRAWINGS

[0044] The present application will be further described with reference to the accompanying drawings and examples in which:

[0045] Figure 1 A flow chart of a fuel consumption model processing method based on a flight control data table for an embodiment of the present application;

[0046] Figure 2 A schematic diagram of an aircraft external normal direction and high altitude speed and flight speed for an embodiment of the present application;

[0047] Figure 3 A lift decomposition schematic diagram for an embodiment of the present application;

[0048] Figure 4 A verification result schematic diagram for an embodiment of the present application;

[0049] Figure 5 Another verification result schematic diagram for an embodiment of the present application;

[0050] Figure 6 Another verification result schematic diagram for an embodiment of the present application. DETAILED DESCRIPTION

[0051] Embodiments of the present application are described in detail below, examples of which are shown in the accompanying drawings, in which the same or similar reference numerals represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by reference to the accompanying drawings are exemplary and are only used to explain the present application, and cannot be understood as limiting the present application.

[0052] In the description of the present application, the meaning of several is more than one, the meaning of multiple is more than two, greater than, less than, more than, etc. are understood as not including the number, above, below, etc. are understood as including the number. If it is described that the first, the second is only used for the purpose of distinguishing technical features, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features or implicitly indicating the order of indicated technical features.

[0053] In the description of the present application, unless otherwise explicitly limited, the setting words such as words should be broadly understood, and those skilled in the art can reasonably determine the specific meaning of the above words in the present application in combination with the specific content of the technical solution.

[0054] In the description of the present application, the description of the terms "one embodiment", "some embodiments", "exemplary embodiment", "example", "specific example", or "some examples" and the like means that the specific features or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the exemplary description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features or characteristics described can be combined in any suitable manner in one or more embodiments or examples.

[0055] With reference to Figure 1 , the present embodiment provides a fuel consumption model processing method based on flight control data table. The method of the present embodiment can be applied to a server, a processor of an aircraft data processing platform or a cloud.

[0056] Specifically, based on the data of the aircraft flight control data table, the present embodiment establishes a general differential equation mathematical model as a fuel consumption model from the energy conservation in the flight process, and makes appropriate simplification of the model on a reasonable basis for calculation. Then, through numerical fitting of the model, the model constructed by the present embodiment depends on temperature, climb height, take-off weight, weather conditions, ground speed, wind speed, flight attitude and other factors. In numerical simulation, the fuel consumption of the model of the present embodiment and the fuel consumption provided by the Boeing 777 flight data table have excellent approximation, for example, under the condition of 200 tons and -5C, steady climb and flight for 150km, the maximum error of the theoretically simulated fuel consumption of the present embodiment and the actual fuel consumption is only 2kg, and on the basis of the total fuel consumption of 3864kg, the data calculated from the established model has extremely high precision compared with the data of the aircraft flight manual.

[0057] The following will be described with reference to the accompanying drawings. For example, as shown in Figure 1 , the present embodiment includes but is not limited to the following steps:

[0058] Step 110, acquiring aircraft performance data;

[0059] Step 120, analyzing the physical logic of each influencing factor and fuel consumption through physical analysis, the influencing factors including at least one of temperature, flight height, take-off weight, weather conditions, climb speed, ground speed, roll speed, high altitude wind speed and flight attitude;

[0060] Step 130, constructing a fuel consumption model according to the physical logic;

[0061] Step 140, determining the model parameters of the fuel consumption model according to the aircraft performance data;

[0062] Step 150, acquiring the data of the flight control data table;

[0063] Step 160: Check the feasibility of the fuel consumption model after substituting the model parameters according to the data in the flight control data table.

[0064] In the embodiment of the present application, the aircraft performance data can be obtained from the aircraft performance manual. At the same time, the physical logic of the various influencing factors and fuel consumption through physical analysis includes but is not limited to the following:

[0065] Analyze kinetic energy increment and potential energy increment;

[0066] Analyze the approximate value of instantaneous air pressure based on the pressure height formula of static meteorology;

[0067] Analyze the work done by friction according to the flight attitude;

[0068] Analyze lift work based on flight dynamics.

[0069] The analysis of the kinetic energy increment and the potential energy increment includes:

[0070] determining a kinetic energy increment based on the gross weight, flight speed, and high-altitude wind speed of the aircraft at a target time, wherein the flight speed is determined by the climb speed, ground speed, and roll speed;

[0071] The potential energy increment is determined according to the total weight of the aircraft at the target time point, the flight altitude of the aircraft at the target time point, the total weight of the aircraft at the previous time point, and the flight altitude of the aircraft at the previous time point.

[0072] Specifically, based on the law of conservation of energy, during the period [t, t+Δt], the fuel consumption is M1(t+Δt)-M1(t). Since K1 is the fuel conversion rate, the power consumption generated by the fuel during this period is K1*[M1(t+Δt)-M1(t)].

[0073] The energy generated in the previous step is mainly reflected in: the kinetic energy increment and potential energy increment in the period [t, t+Δt], the negative work done by the friction force, and the positive work done by the wind resistance lift caused by the flight pitch angle.

[0074] The kinetic energy increment can be expressed as shown in formula (1):

[0075]

[0076] The potential energy increment can be expressed as shown in formula (2):

[0077] M0(t+Δt)*g*h(t+Δt)-M0(t)*g*h(t) Formula (2)

[0078] In this process, K1 represents the fuel energy conversion rate, which depends on the aircraft starting configuration and engine performance; M1(t+Δt) represents the aircraft fuel load at time t+Δt; M1(t) represents the fuel load at time t; M0(t+Δt) represents the total weight of the aircraft at time t+Δt; M0(t) represents the total weight of the aircraft at time t; UR(t+Δt) represents the flight speed at t+Δt; UR(t) represents the flight speed at time t; UB(t+Δt) represents the high-altitude wind speed at t+Δt; UB(t) represents the high-altitude wind speed at time t; g represents the acceleration of gravity; h(t+Δt) represents the flight altitude at time t+Δt; h(t) represents the flight altitude at time t.

[0079] Analyzing the friction work according to the flight attitude includes:

[0080] The pressure of the atmosphere on the surface of the aircraft and the direction of the outer normal of the positive pressure on the surface of the aircraft are determined; and then the work done by friction is determined based on the pressure, the direction of the outer normal, the flight speed, the high-altitude wind speed and the flight lift coefficient.

[0081] Specifically, when the aircraft is in the climbing phase, the atmospheric pressure acting on the aircraft surface at time t is set to P; is the direction of the outer normal of the aircraft surface, then the work done by the friction force in the period [t, t+Δt] is as shown in formula (3):

[0082]

[0083] Among them, K2 represents the lift effect coefficient caused by wind resistance during flight, which depends on the instantaneous state of the aircraft, such as pitch angle, flight speed, high-altitude wind, etc.

[0084] The instantaneous fuselage pressure approximation value is analyzed according to the pressure height formula of static meteorology, and the aircraft roll can be analyzed according to the pressure height formula of static meteorology and the Rodrigues rotation formula.

[0085] Specifically, when P and The specific expression of ρ is simplified. In this embodiment, atmospheric pressure can be used as ρ γ However, it is necessary to establish an equation for the air density ρ to close the model. This requires the introduction of a set of partial differential equations, which increases the complexity of the numerical calculation.

[0086] Since civil aviation flights always take place under relatively stable meteorological conditions, this embodiment uses the static meteorological empirical pressure-height formula shown in formula (4) for the atmospheric pressure P:

[0087]

[0088] for This embodiment is explained by Figure 2

[0089] From Figure 2 It can be seen that it is assumed that the flight is first flown horizontally at speed U; then U is rotated by θ1(t) (describing the pitch angle) about e r ; and then rotated by θ2(t) (describing the roll angle) about e θ .

[0090]

[0091] Then, the relationship shown in equation (5) is obtained by the Rodrigues' Rotation formula:

[0092]

[0093] where e r , e θ , and e φ represent three coordinate components in the spherical coordinate system; θ1 and θ2 represent the pitch angle and roll angle of the aircraft.

[0094] The lift work is analyzed according to the flight dynamics, and the lift effect of the wind resistance can be analyzed according to the horizontal flight speed, the pitch angle of the aircraft, and the flight attitude parameters.

[0095] Specifically, the effect of the wind resistance is determined based on the different structures of the inclination angle. Taking the climbing stage as an example, the wind resistance delays the horizontal motion, as shown in equation (2), but at the same time provides a lift effect. Figure 3

[0096] In the lift effect, the effect of the F1 part is mainly considered; the effect of the other resistance part is embodied in the background wind speed part in the energy process.

[0097] where the F1 part is naturally proportional to the wind speed, and is related to the aerodynamic shape of the aircraft, the pitch angle, and the roll angle of the aircraft; the coefficient K3 is crucial to the flight attitude. In steady flight, the roll angle can be considered as a very small angle, so the lift work is shown in equation (6):

[0098] -K3*U 2 *sin(θ1) equation (6)

[0099] where K3 represents the flight attitude parameter, which mainly describes the corresponding parameter effect under different flight pitch angles; U represents the horizontal flight speed; and θ1 represents the pitch angle at time t.

[0100] Based on the foregoing, the fuel consumption model formula in the steady flight stage is shown in equation (7): ​​​

[0101]

[0102] Among them, K1 represents the fuel energy conversion rate, which depends on the aircraft starting configuration and engine performance; K2 represents the lift effect coefficient caused by wind resistance during flight, which depends on the instantaneous state of the aircraft, such as pitch angle, flight speed, high-altitude wind, etc.; K3 represents the flight attitude parameter, which mainly describes the corresponding parameter effects under different flight pitch angles; U represents the horizontal flight speed; g represents the acceleration of gravity; h represents the flight altitude; M1(t) represents the fuel load at time t; M0(t) represents the total weight at time t; UR represents the flight speed at time t; e r Represents the coordinate components in the spherical coordinate system; P represents the pressure of the atmosphere on the aircraft surface; represents the external normal direction of the aircraft surface; θ1 represents the elevation angle at time t.

[0103] After obtaining the fuel consumption model, this embodiment can use some data from the Boeing 777 flight control manual to fit the parameters. The model with the fitted parameters is then used to simulate and calculate subsequent data. This embodiment uses the flight data table of the Boeing 747 aircraft as a reference and verifies the feasibility of the model through numerical model fitting.

[0104] In some embodiments, taking a Boeing 777 as an example, the flight data of a flight of 150 km is compared under the weather conditions of -5°C temperature, takeoff weight of 200 tons, and wind speed of 40 kts. Figure 4 As shown, the horizontal axis is the flight distance, and the vertical axis is the fuel consumption (unit is kg), with an error within 2kg;

[0105] Take the Boeing 777 as an example, the flight data of 150km under the weather conditions of -5℃, take-off weight of 210 tons and wind speed of 40kts. Figure 5 As shown, the horizontal axis is the flight distance, and the vertical axis is the fuel consumption (in kg), with an error within 13kg;

[0106] Take the Boeing 777 as an example, the flight data of 150km under the weather conditions of -3℃, take-off weight of 250 tons and wind speed of 40kts. Figure 6 As shown, the horizontal axis is the flight distance and the vertical axis is the fuel consumption (unit is kg), with an error within 14kg.

[0107] In summary, this embodiment, based on physical principles, fundamentally establishes a mathematical model that correlates fuel consumption with flight attitude, flight distance, meteorological factors, flight weight, and other factors. This established mathematical model allows for a better analysis of the key fuel consumption factors at each stage of flight. This allows for an accurate prediction of the required fuel consumption for the entire flight, maximizing profitability. Furthermore, the model allows for analysis of the specific impact of various factors, such as meteorological factors and aircraft payload, on fuel. This allows for calculations to determine whether fuel reserves will meet the requirements for safe operation in the event of unexpected weather conditions during flight. Finally, the established model has the potential for further application in the civilian aircraft market: for example, it can be used to calculate the relationship between fuel load and cargo loading during drone flight, enabling more optimal flight planning.

[0108] An embodiment of the present invention provides a fuel consumption model processing system based on a flight control data table, comprising:

[0109] A first acquisition module is used to acquire aircraft performance data;

[0110] an analysis module, configured to perform physical analysis on the physical logic of various influencing factors and fuel consumption, wherein the influencing factors include at least one of temperature, flight altitude, takeoff weight, weather conditions, climb speed, ground speed, roll speed, high-altitude wind speed, and flight attitude;

[0111] A construction module, configured to construct a fuel consumption model according to the physical logic;

[0112] a determination module, configured to determine model parameters of the fuel consumption model based on the aircraft performance data;

[0113] The second acquisition module is used to obtain data from the flight control data table;

[0114] The testing module is used to test the feasibility of the fuel consumption model after the model parameters are substituted according to the data of the flight control data table.

[0115] The contents of the method embodiments of the present invention are all applicable to the system embodiments. The functions specifically implemented by the system embodiments are the same as those of the above method embodiments, and the beneficial effects achieved are also the same as those achieved by the above methods.

[0116] An embodiment of the present invention provides a fuel consumption model processing system based on a flight control data table, comprising:

[0117] at least one memory for storing a program;

[0118] At least one processor for loading the program to execute Figure 1 The fuel consumption model processing method based on the flight control data table is shown.

[0119] The content of the method embodiments of the present application is applicable to the system embodiments, the system embodiments specifically implement the same functions as the above method embodiments, and achieve the same beneficial effects as the above method.

[0120] The embodiment of the present application provides a storage medium, wherein the storage medium stores a computer executable program, and the computer executable program is executed by a processor to implement Figure 1 The fuel consumption model processing method based on the flight control data table.

[0121] The embodiment of the present application further provides a computer program product or a computer program, the computer program product or the computer program comprising computer instructions stored in a computer readable storage medium. The processor of the computer equipment can read the computer instructions from the computer readable storage medium, and the processor executes the computer instructions, so that the computer equipment executes Figure 1 The fuel consumption model processing method based on the flight control data table.

[0122] The above describes the embodiments of the present application in detail in combination with the drawings, but the present application is not limited to the above embodiments, and various changes can be made within the knowledge range of the ordinary skill in the art without departing from the purpose of the present application. In addition, the embodiments of the present application and the features in the embodiments can be combined with each other without conflict.

Claims

1. A fuel consumption model processing method based on flight control data table, characterized in that: The following steps are involved: Obtain aircraft performance data; By physically analyzing the physical logic of various influencing factors and fuel consumption, the influencing factors include at least one of temperature, flight altitude, takeoff weight, weather conditions, climb speed, ground speed, roll speed, high-altitude wind speed, and flight attitude; Constructing a fuel consumption model according to the physical logic; determining model parameters of the fuel consumption model based on the aircraft performance data; Get the data from the flight control data table; Testing the feasibility of the fuel consumption model after substituting the model parameters according to the data in the flight control data table; The formula of the fuel consumption model is as follows: ； Among them, K1 represents the fuel energy conversion rate; K2 represents the lift effect coefficient caused by wind resistance during flight; K3 represents the flight attitude parameter; U represents the horizontal flight speed; g represents the acceleration due to gravity; h represents the flight altitude; M1(t) represents the fuel load at time t; M0(t) represents the total weight at time t; UR represents the flight speed at time t; Represents the coordinate components in the spherical coordinate system; P represents the pressure of the atmosphere on the aircraft surface; Indicates the direction of the outer normal of the aircraft surface; represents the elevation angle at time t.

2. The method for processing a fuel consumption model based on a flight control data table according to claim 1, characterized in that: The physical analysis of various influencing factors and the physical logic of fuel consumption includes: Analyze kinetic energy increment and potential energy increment; Analyze the approximate value of instantaneous air pressure based on the pressure height formula of static meteorology; Analyze the work done by friction according to the flight attitude; Analyze lift work based on flight dynamics.

3. The method for processing a fuel consumption model based on a flight control data table according to claim 2, characterized in that: The analysis of kinetic energy increment and potential energy increment includes: determining a kinetic energy increment based on the gross weight, flight speed, and high-altitude wind speed of the aircraft at a target time, wherein the flight speed is determined by the climb speed, ground speed, and roll speed; The potential energy increment is determined according to the total weight of the aircraft at the target time point, the flight altitude of the aircraft at the target time point, the total weight of the aircraft at the previous time point, and the flight altitude of the aircraft at the previous time point.

4. The method for processing a fuel consumption model based on a flight control data table according to claim 3, characterized in that: Analyzing the friction work according to the flight attitude includes: Determine the atmospheric pressure acting on the aircraft surface; Determine the direction of the outer normal of the positive pressure on the aircraft surface; The work done by friction is determined according to the pressure, the external normal direction, the flight speed, the high-altitude wind speed and the flight lift coefficient.

5. The method for processing a fuel consumption model based on a flight control data table according to claim 2, characterized in that: The analysis of the approximate instantaneous air pressure of the fuselage according to the pressure height formula of static meteorology includes: Analyze aircraft roll based on the pressure height formula and Rodrigues rotation formula in static meteorology.

6. The method for processing a fuel consumption model based on a flight control data table according to claim 2, characterized in that: The lift work according to flight dynamics analysis includes: The lift effect caused by wind resistance is analyzed based on the horizontal flight speed, aircraft pitch angle and flight attitude parameters.

7. A fuel consumption model processing system based on flight control data table, characterized in that: include: A first acquisition module is used to acquire aircraft performance data; an analysis module, configured to perform physical analysis on the physical logic of various influencing factors and fuel consumption, wherein the influencing factors include at least one of temperature, flight altitude, takeoff weight, weather conditions, climb speed, ground speed, roll speed, high-altitude wind speed, and flight attitude; A construction module, configured to construct a fuel consumption model according to the physical logic; a determination module, configured to determine model parameters of the fuel consumption model based on the aircraft performance data; The second acquisition module is used to obtain data from the flight control data table; A testing module, configured to test the feasibility of the fuel consumption model after substituting the model parameters according to the data in the flight control data table; The formula of the fuel consumption model is as follows: ； Among them, K1 represents the fuel energy conversion rate; K2 represents the lift effect coefficient caused by wind resistance during flight; K3 represents the flight attitude parameter; U represents the horizontal flight speed; g represents the acceleration due to gravity; h represents the flight altitude; M1(t) represents the fuel load at time t; M0(t) represents the total weight at time t; UR represents the flight speed at time t; Represents the coordinate components in the spherical coordinate system; P represents the pressure of the atmosphere on the aircraft surface; Indicates the direction of the outer normal of the aircraft surface; represents the elevation angle at time t.

8. A fuel consumption model processing system based on flight control data table, characterized in that: include: at least one memory for storing a program; At least one processor is used to load the program to execute the fuel consumption model processing method based on the flight control data table according to any one of claims 1 to 6.

9. A storage medium, characterized in that: A computer-executable program is stored therein, and when the computer-executable program is executed by a processor, it is used to implement the fuel consumption model processing method based on the flight control data table according to any one of claims 1 to 6.

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