Civil aircraft fuel temperature simulation method, system, equipment, medium and product

Abstract

The present invention provides a fuel temperature simulation method, system, equipment, medium and product for civil aircraft, and relates to the field of aviation simulation technology. The method includes: calculating the fuel tank buffer temperature of each fuel tank in the current cycle during simulated flight training according to multiple fuel flow parameters; obtaining the real-time fuel quantity of each fuel tank in the current cycle during simulated flight training; determining the target cooling rate function according to the comparison result between the real-time fuel quantity of the fuel tank in the current cycle and the minimum fuel quantity; based on the target cooling rate function, calculating the fuel tank temperature difference of each fuel tank in the current cycle according to the fuel tank buffer temperature of the current cycle; obtaining the fuel tank simulation temperature of each fuel tank in the current cycle according to the fuel tank buffer temperature of the current cycle and the fuel tank temperature difference of the current cycle. The present invention simulates the fuel temperature during simulated training of civil aircraft more comprehensively, so that the simulation result has high authenticity and accuracy.

Description

Technical Field

[0001] The present invention relates to the field of aviation simulation technology, and in particular to a method, system, equipment, medium and product for simulating fuel temperature of a civil aircraft. Background Art

[0002] Fuel temperature is an important output parameter of the fuel system and is used to display on the main instrument of the civil flight simulation training device. In simulation training, the accuracy of the fuel temperature simulated by the fuel temperature simulation model directly affects the objective judgment of flight training.

[0003] The existing fuel temperature is modeled based on only two variables: the outside temperature and the engine's operating status, which results in the modeling method being too simple and the final simulation result being of low authenticity and accuracy.

[0004] Therefore, there is an urgent need for a fuel temperature simulation method, system, equipment, medium and product for civil aircraft to solve the above problems. Summary of the invention

[0005] In view of the problems existing in the prior art, the present invention provides a fuel temperature simulation method, system, equipment, medium and product for a civil aircraft.

[0006] The present invention provides a fuel temperature simulation method for a civil aircraft, comprising:

[0007] Calculating the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to a plurality of fuel flow parameters, wherein the plurality of fuel flow parameters are constructed based on the pressure relief valve flow, the transfer valve flow, the ejector pump flow and the engine hot fuel flow corresponding to the fuel tank;

[0008] Acquire the real-time fuel quantity of each fuel tank in the current cycle during the simulated flight training;

[0009] Determine a target cooling rate function according to a comparison result between the real-time fuel amount in the fuel tank and the minimum fuel amount in the current cycle, wherein the target cooling rate function is constructed based on a fuel tank buffer temperature, a fuel burning rate, a maximum fuel amount in the fuel tank, and a real-time fuel amount in the fuel tank;

[0010] Based on the target cooling rate function, according to the fuel tank buffer temperature of the current cycle, the fuel tank temperature difference value of each fuel tank in the current cycle is calculated, wherein the fuel tank temperature difference value is the temperature difference value between the fuel tank temperature and the total temperature data;

[0011] The fuel tank simulation temperature of each fuel tank in the current cycle is obtained according to the fuel tank buffer temperature in the current cycle and the fuel tank temperature difference in the current cycle.

[0012] According to a fuel temperature simulation method for a civil aircraft provided by the present invention, the wings of the civil simulated aircraft in the simulated flight training process are provided with an outer fuel tank and an inner fuel tank, wherein the outer fuel tank is a fuel tank away from a side of the fuselage, and the inner fuel tank is a fuel tank close to a side of the fuselage, and the method further includes:

[0013] When it is determined that the pressure relief valve of the fuel tank is in an open state, a fuel flow parameter of the pressure relief valve is obtained according to the product between the pressure relief valve flow and the preset boost pump temperature rise value;

[0014] Acquire the fuel flow rate and flow temperature of the engine when transmitting hot fuel, and obtain the engine fuel flow parameter according to the product between the fuel flow rate and the flow temperature;

[0015] When it is determined that the transfer valve between the outer fuel tank and the inner fuel tank is in a closed state, the fuel flow parameter of the ejector pump is obtained according to the product of the total flow of the ejector pump between the outer fuel tank and the inner fuel tank and the fuel tank buffer temperature of the inner fuel tank in the previous cycle;

[0016] When it is determined that the transfer valve between the outer fuel tank and the inner fuel tank is in an open state and the ejector pump is in a closed state, the total flow of the transfer valve is obtained according to the gravity flow when the fuel in the outer fuel tank is transferred to the inner fuel tank under the action of gravity, and the transfer valve fuel parameter is obtained according to the product between the total flow of the transfer valve and the tank buffer temperature of the outer fuel tank in the previous cycle;

[0017] The multiple fuel flow parameters are obtained according to the pressure relief valve fuel flow parameter, the engine fuel flow parameter, the ejector pump fuel flow parameter and the transfer valve fuel parameter.

[0018] According to a fuel temperature simulation method for a civil aircraft provided by the present invention, the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training is calculated according to multiple fuel flow parameters, including:

[0019] When it is determined that the fuel tank is the outer fuel tank, summing the fuel flow parameter of the engine and the fuel flow parameter of the ejector pump to obtain a first summing result;

[0020] Obtaining a first product result according to the product of the real-time oil volume of the outer oil tank in the current cycle and the oil tank buffer temperature of the outer oil tank in the previous cycle;

[0021] Obtaining a second summation result according to a summation result between the first summation processing result and the first product result;

[0022] A third summation result is obtained by summing the values ​​corresponding to the real-time oil volume of the outer oil tank in the current cycle and the total flow of the ejector pump;

[0023] According to the ratio between the second summation result and the third summation result, the fuel tank buffer temperature of the outer fuel tank in the current cycle during the simulated flight training is obtained.

[0024] According to a fuel temperature simulation method for a civil aircraft provided by the present invention, the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training is calculated according to multiple fuel flow parameters, and further includes:

[0025] When it is determined that the fuel tank is the inner fuel tank, summing the fuel parameter of the transmission valve and the fuel flow parameter of the pressure relief valve to obtain a fourth summing result;

[0026] Obtaining a second product result according to the product of the real-time oil volume of the inner oil tank in the current cycle and the oil tank buffer temperature of the inner oil tank in the previous cycle;

[0027] Obtaining a fifth summation result according to a summation result between the fourth summation processing result and the second multiplication result;

[0028] A sixth summation result is obtained by summing the values ​​corresponding to the real-time oil volume of the inner oil tank in the current cycle and the total flow of the transfer valve;

[0029] According to the ratio between the fifth summation result and the sixth summation result, the fuel tank buffer temperature of the inner fuel tank in the current cycle during the simulated flight training is obtained.

[0030] According to a fuel temperature simulation method for a civil aircraft provided by the present invention, the target cooling rate function is determined according to the comparison result between the real-time fuel amount in the fuel tank of the current cycle and the minimum fuel amount, including:

[0031] In the case where it is determined that the real-time fuel amount in the fuel tank of the current cycle is greater than the minimum fuel amount, taking the first cooling rate function as the target cooling rate function;

[0032] In the case where it is determined that the real-time fuel amount in the fuel tank of the current cycle is less than or equal to the minimum fuel amount, using the second cooling rate function as the target cooling rate function;

[0033] The first cooling rate function is constructed based on the total temperature data, the fuel tank buffer temperature of the current cycle, the fuel burning rate, the maximum fuel amount of the fuel tank, and the real-time fuel amount of the fuel tank of the current cycle;

[0034] The second cooling rate function is constructed based on the total temperature data, the fuel tank buffer temperature of the current cycle, the fuel combustion rate, and the maximum fuel amount in the fuel tank.

[0035] According to a fuel temperature simulation method for a civil aircraft provided by the present invention, obtaining the fuel tank simulation temperature of each fuel tank in the current cycle according to the fuel tank buffer temperature of the current cycle and the fuel tank temperature difference value of the current cycle, comprises:

[0036] When it is determined that the fuel tank buffer temperature of the current cycle is less than the maximum fuel tank temperature, or greater than the minimum fuel tank temperature, the fuel tank buffer temperature of the current cycle and the fuel tank temperature difference of the current cycle are summed to obtain the fuel tank simulation temperature of the fuel tank in the current cycle;

[0037] When it is determined that the fuel tank buffer temperature of the current cycle is greater than the maximum fuel tank temperature, the maximum fuel tank temperature is used as the fuel tank buffer temperature of the current cycle, and the difference between the maximum fuel tank temperature and the fuel tank temperature of the current cycle is summed to obtain the fuel tank simulation temperature of the fuel tank in the current cycle;

[0038] When it is determined that the fuel tank buffer temperature of the current cycle is less than the fuel tank minimum temperature, the fuel tank minimum temperature is used as the fuel tank buffer temperature of the current cycle, and the fuel tank minimum temperature and the fuel tank temperature difference of the current cycle are summed to obtain the fuel tank simulation temperature of the current cycle.

[0039] The present invention also provides a fuel temperature simulation system for a civil aircraft, comprising:

[0040] A buffer temperature calculation module, used to calculate the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to a plurality of fuel flow parameters, wherein the plurality of fuel flow parameters are constructed based on the pressure relief valve flow, the transfer valve flow, the ejector pump flow and the engine hot fuel flow corresponding to the fuel tank;

[0041] A fuel quantity acquisition module, used for acquiring the real-time fuel quantity of each fuel tank in the current cycle during the simulated flight training;

[0042] a processing module, configured to determine a target cooling rate function according to a comparison result between the real-time fuel amount in the fuel tank and the minimum fuel amount in the current cycle, wherein the target cooling rate function is constructed based on a fuel tank buffer temperature, a fuel burning rate, a maximum fuel amount in the fuel tank, and a real-time fuel amount in the fuel tank;

[0043] A temperature difference calculation module, configured to calculate the fuel tank temperature difference value of each fuel tank in the current cycle based on the target cooling rate function and the fuel tank buffer temperature of the current cycle, wherein the fuel tank temperature difference value is the temperature difference value between the fuel tank temperature and the total temperature data;

[0044] The simulation temperature calculation module is used to obtain the fuel tank simulation temperature of each fuel tank in the current cycle according to the fuel tank buffer temperature in the current cycle and the fuel tank temperature difference value in the current cycle.

[0045] The present invention also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, the fuel temperature simulation method for a civil aircraft as described in any one of the above is implemented.

[0046] The present invention also provides a non-transitory computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the fuel temperature simulation method of a civil aircraft as described in any one of the above methods is implemented.

[0047] The present invention also provides a computer program product, comprising a computer program, wherein when the computer program is executed by a processor, the computer program implements any of the above-mentioned methods for simulating fuel temperature of a civil aircraft.

[0048] The civil aircraft fuel temperature simulation method, system, equipment, medium and product provided by the present invention, when modeling the aircraft fuel temperature simulation model, take into account factors such as the fuel tank valve, priming pump, engine, etc. in the actual aircraft to model the fuel temperature, thereby more comprehensively simulating the fuel temperature during the civil aircraft simulation training, so that the simulation result has higher authenticity and accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0050] Figure 1 A schematic flow chart of a fuel temperature simulation method for a civil aircraft provided by the present invention;

[0051] Figure 2 A schematic diagram of the location of a fuel tank for a civil aircraft provided by the present invention;

[0052] Figure 3 A schematic diagram of the structure of a fuel temperature simulation system for a civil aircraft provided by the present invention;

[0053] Figure 4 This is a schematic structural diagram of an electronic device provided by the present invention. DETAILED DESCRIPTION

[0054] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0055] The existing fuel temperature modeling and simulation technology for civil aircraft cannot accurately simulate the fuel temperature of the entire flight phase due to insufficient data for fuel temperature modeling. In some civil aircraft flight training devices, the modeling method for fuel temperature is too simple, which also leads to low accuracy of simulation results.

[0056] In view of the fact that the existing civil aircraft flight training devices do not take into account comprehensive factors when modeling fuel temperature, the present invention takes into account factors such as valve position, the status of the boost pump and the ejector pump, the available fuel amount, the fuel flow and flow temperature calculated by the engine, and the total temperature when modeling fuel temperature, and provides a complete set of algorithm models, thereby solving the modeling difficulties caused by incomplete data and the problem that the current existing models are too simple, resulting in low accuracy of simulation results.

[0057] Figure 1 The schematic diagram of the flow chart of the fuel temperature simulation method for civil aircraft provided by the present invention is as follows: Figure 1 As shown, the present invention provides a fuel temperature simulation method for a civil aircraft, comprising:

[0058] Step 101, calculate the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to multiple fuel flow parameters, wherein the multiple fuel flow parameters are constructed based on the pressure relief valve flow, transfer valve flow, ejector pump flow and engine hot fuel flow corresponding to the fuel tank.

[0059] Figure 2 The schematic diagram of the location of the fuel tank of a civil aircraft provided by the present invention can be referred to Figure 2 As shown, for the types of civil aircraft used in existing civil aircraft simulation training devices, the present invention, when performing fuel temperature simulation, is mainly explained for a civil simulation aircraft with 5 fuel tanks, namely outer fuel tank No. 1, outer fuel tank No. 2, inner fuel tank No. 3, inner fuel tank No. 4 and central fuel tank No. 5, wherein the two outer fuel tanks are respectively arranged on both sides of the wing and away from the fuselage, the two inner fuel tanks are respectively arranged on both sides of the wing and close to the fuselage, and the central fuel tank is arranged on one side of the fuselage.

[0060] Furthermore, in the present invention, the fuel simulation result in the aircraft simulation training process is to perform periodic fuel temperature simulation based on the changes in the fuel amount in the fuel tank, the fuel tank buffer temperature, the temperature and flow-related data of the engine, the transmission valve, and the priming pump. Therefore, when calculating the fuel tank buffer temperature of the current cycle, the present invention needs to combine multiple fuel flow parameters of the previous cycle to first calculate the fuel tank buffer temperature in the previous cycle, including the buffer temperature of the outer fuel tank and the inner fuel tank, and then iteratively calculate the fuel tank buffer temperature of the current cycle based on the fuel tank buffer temperature of the previous cycle.

[0061] Step 102, obtaining the real-time fuel quantity of each fuel tank in the current cycle during the simulated flight training process.

[0062] When the amount of oil in the fuel tank is large, the overall heat capacity of the fuel tank system will also increase accordingly, which means that under the same heat input or output conditions, the change speed of the fuel tank temperature will be relatively slow, so it is necessary to consider the impact of the amount of oil in the fuel tank on the fuel tank temperature. For each fuel temperature simulation cycle, the present invention needs to obtain the remaining oil amount of each fuel tank in the current cycle, that is, the real-time fuel amount of the fuel tank, so that in the subsequent fuel temperature simulation process, the impact of the fuel amount in the fuel tank on the fuel temperature is also added to the simulation conditions.

[0063] Step 103, determining a target cooling rate function based on a comparison result between the real-time fuel quantity in the fuel tank and the minimum fuel quantity in the current cycle, wherein the target cooling rate function is constructed based on a fuel tank buffer temperature, a fuel combustion rate, a maximum fuel quantity in the fuel tank, and the real-time fuel quantity in the fuel tank.

[0064] In the present invention, the minimum fuel level is a preset threshold value, which is used to indicate the safe lower limit of the fuel level in the fuel tank. When the fuel level in the fuel tank is lower than this threshold value, it means that the remaining fuel level in the fuel tank is in an unusable state and fuel replenishment is required.

[0065] The real-time fuel amount in the fuel tank (i.e., the amount of remaining fuel in the fuel tank) directly affects the thermal capacity and heat dissipation efficiency of the fuel tank. When the remaining amount in the fuel tank is large, the thermal capacity of the fuel is large, and it can absorb or release more heat, thereby slowing down the change in the fuel tank temperature. On the contrary, when the remaining amount in the fuel tank is small, the thermal capacity decreases, and the fuel tank temperature is more sensitive to changes in the external environment. Therefore, the present invention uses different cooling rate functions to calculate the fuel tank temperature difference according to the remaining amount in the fuel tank, which can more accurately reflect the actual temperature difference between the fuel tank and the total temperature, and improve the accuracy of the calculation.

[0066] Step 104, based on the target cooling rate function and according to the fuel tank buffer temperature of the current cycle, calculate the fuel tank temperature difference of each fuel tank in the current cycle, wherein the fuel tank temperature difference is the temperature difference between the fuel tank temperature and the total temperature data.

[0067] In the present invention, based on the target cooling rate function determined in the above embodiment, the fuel tank temperature difference value of the current cycle is calculated according to various parameters of the fuel tank (such as the fuel tank buffer temperature, the fuel combustion rate, the maximum fuel amount in the fuel tank and the real-time fuel amount in the fuel tank), wherein the fuel tank temperature difference value refers to the difference between the current temperature of the fuel tank and the total temperature data.

[0068] Step 105, obtaining the fuel tank simulation temperature of each fuel tank in the current cycle according to the fuel tank buffer temperature in the current cycle and the fuel tank temperature difference in the current cycle.

[0069] In the present invention, the final temperature of the fuel tank, i.e., the fuel tank simulation temperature, is the sum of the fuel tank buffer temperature and the fuel tank temperature difference. If the total temperature of the current cycle is less than the fuel tank buffer temperature, the fuel tank temperature difference will be calculated as a negative value, and the fuel tank temperature of the current cycle will decrease. The calculation formula of the fuel tank simulation temperature is specifically:

[0070] ;

[0071] Wherein, TKFINLT is the tank simulation temperature, unit is ℃; TKBUFT is the tank buffer temperature of the current cycle, AMBFDT is the tank temperature difference of the current cycle; K represents the tank number, in the present invention, when K=1 and 2, it represents outer tank 1 and outer tank 2 respectively; when K=3 and 4, it represents inner tank 3 and outer tank 4 respectively. It should be noted that when K=5, it represents the central tank, in the present invention, the temperature simulation of the central tank in the fuel temperature simulation process can be obtained by modeling using the existing technology, and the tank simulation process provided by the present invention does not consider the temperature simulation of the central tank.

[0072] The fuel temperature simulation method for a civil aircraft provided by the present invention, when building a fuel temperature simulation model for an aircraft, takes into account factors such as a fuel tank valve, an ejector pump, and an engine in an actual aircraft to build a model, thereby more comprehensively simulating the fuel temperature during simulation training of a civil aircraft, and making the simulation result have higher authenticity and accuracy.

[0073] On the basis of the above embodiment, the wings of the civil simulated aircraft in the simulated flight training process are provided with an outer fuel tank and an inner fuel tank, wherein the outer fuel tank is a fuel tank away from a side of the fuselage, and the inner fuel tank is a fuel tank close to a side of the fuselage, and the method further includes:

[0074] When it is determined that the pressure relief valve of the fuel tank is in an open state, a fuel flow parameter of the pressure relief valve is obtained according to the product between the pressure relief valve flow and the preset boost pump temperature rise value;

[0075] Acquire the fuel flow rate and flow temperature of the engine when transmitting hot fuel, and obtain the engine fuel flow parameter according to the product between the fuel flow rate and the flow temperature;

[0076] When it is determined that the transfer valve between the outer fuel tank and the inner fuel tank is in a closed state, the fuel flow parameter of the ejector pump is obtained according to the product of the total flow of the ejector pump between the outer fuel tank and the inner fuel tank and the fuel tank buffer temperature of the inner fuel tank in the previous cycle;

[0077] When it is determined that the transfer valve between the outer fuel tank and the inner fuel tank is in an open state and the ejector pump is in a closed state, the total flow of the transfer valve is obtained according to the gravity flow when the fuel in the outer fuel tank is transferred to the inner fuel tank under the action of gravity, and the transfer valve fuel parameter is obtained according to the product between the total flow of the transfer valve and the tank buffer temperature of the outer fuel tank in the previous cycle;

[0078] The multiple fuel flow parameters are obtained according to the pressure relief valve fuel flow parameter, the engine fuel flow parameter, the ejector pump fuel flow parameter and the transfer valve fuel parameter.

[0079] In the present invention, when simulating the fuel temperature of the inner and outer fuel tanks, multiple fuel flow parameters are involved, which can be referred to Figure 2 As shown, when the boost pump of the wing tank is turned on, the pressure relief valve of the boost pump will work and generate fuel reflux, causing the refluxed fuel to splash back to the inner tank. Affected by this, the temperature of the inner tank on the corresponding side will rise. It should be noted that the central tank pump of narrow-body aircraft is currently not equipped with a pressure relief valve, so in the present invention, the central tank pump can be ignored when it is working. When the central tank pump is turned on, it will provide full flow fuel to the engine at full pressure. In response to the temperature rise caused by the opening of the pressure relief valve of the fuel tank, the present invention obtains the pressure relief valve fuel flow parameter based on the product between the pressure relief valve flow and the preset boost pump temperature rise value. For pressure relief valve No. 1 and pressure relief valve No. 2, the calculation formula of the pressure relief valve fuel flow parameter DFDT (KL) is specifically:

[0080] ;

[0081] For pressure relief valve No. 3 and pressure relief valve No. 4, the calculation formula of the pressure relief valve fuel flow parameter DFDT (KL) is as follows:

[0082] ;

[0083] Among them, RELIEFVLVF is the flow rate corresponding to the wing tank pressure relief valve, with a total of 1 to 4 pressure relief valves, in kg / m, pressure relief valve No. 1 and pressure relief valve No. 2 are located on the left wing, and pressure relief valve No. 3 and pressure relief valve No. 4 are located on the right wing; TKPMPDT is the boost pump temperature rise constant value, which is 0.001; DFDT (KL) is the corresponding pressure relief valve fuel flow parameter, which is used in the subsequent buffer temperature difference calculation process of the inner wing tank.

[0084] Furthermore, during the simulated flight training, the engine system can be controlled by the Full Authority Digital Engine Control (FADEC) model to transfer the flow of hot fuel from the engine. The calculation formula of the engine fuel flow parameter is as follows:

[0085] ;

[0086] Wherein, ENGFF is the fuel flow calculated by the engine, in kg / h; ENGFT is the flow temperature calculated by the engine, in °C; DFDT (E) is the engine fuel flow parameter. When E=1, it indicates the engine on the left wing; when E=2, it indicates the engine on the right wing.

[0087] During the simulated flight training, if the transfer valve is closed, the fuel is transferred from the inner tank to the outer tank through the ejector pump, and its flow rate is the sum of the flow rates of the two ejector pumps (i.e. ejector pump No. 1 and ejector pump No. 2) in the outer tanks on both sides of the wing. The calculation formula of the ejector pump fuel flow parameter DFDT (KJ) is as follows:

[0088] ;

[0089] ;

[0090] Among them, XJFLOW is the flow rate of a single ejector pump, that is, when the transfer valve is closed, the fuel is transported from the inner tank to the outer tank by the ejector pump, unit kg / h; JFLOW is the sum of the flow rates of the two ejector pumps at the outer tank, unit kg / h; is the fuel tank buffer temperature of the inner tank in the previous cycle, that is, inner tank No. 3 or inner tank No. 4; DFDT (KJ) is the fuel flow parameter of the ejector pump of the corresponding inner tank.

[0091] During simulated flight training, when the transfer valve is open, the fuel needs to be transferred from the outer tank to the inner tank through the ejector pump. At this time, if the transfer valve is open and the ejector pump is closed, gravity flow will occur, and the relative tank oil level allows the fuel to be transferred by gravity, and its flow rate is the sum of the flow rate generated by gravity and the flow rate when the ejector pump is turned on. The calculation formula of the transfer valve fuel parameters is as follows:

[0092] ;

[0093] ;

[0094] ;

[0095] ;

[0096] Where XXFLOW is the flow rate of the transfer valve, in kg / h; XFLOW is the sum of the flow rate generated by gravity and the flow rate when the ejector pump is turned on, in kg / h; is the tank buffer temperature of the outer tank in the previous cycle, and DFDT (KK) is the corresponding outer tank transfer valve fuel parameter. DFDTS (K) is the flow parameter of the product entering the outer tank due to the flow difference and temperature difference factors, that is, the first summation processing result in the subsequent steps, wherein DFDT (K) is equivalent to DFDT (E) in the above embodiment; DFDTS (KJ) is the flow parameter of the product entering the inner tank due to the flow difference and temperature difference factors, that is, the fourth summation processing result in the subsequent steps.

[0097] Based on the above embodiment, the calculation of the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to multiple fuel flow parameters includes:

[0098] When it is determined that the fuel tank is the outer fuel tank, summing the fuel flow parameter of the engine and the fuel flow parameter of the ejector pump to obtain a first summing result;

[0099] Obtaining a first product result according to the product of the real-time oil volume of the outer oil tank in the current cycle and the oil tank buffer temperature of the outer oil tank in the previous cycle;

[0100] Obtaining a second summation result according to a summation result between the first summation processing result and the first product result;

[0101] A third summation result is obtained by summing the values ​​corresponding to the real-time oil volume of the outer oil tank in the current cycle and the total flow of the ejector pump;

[0102] According to the ratio between the second summation result and the third summation result, the fuel tank buffer temperature of the outer fuel tank in the current cycle during the simulated flight training is obtained.

[0103] In the present invention, according to the multiple fuel flow parameters obtained in the above embodiments, according to the calculation formula of the buffer temperature difference of the outer tank, the buffer temperature difference of the outer tank in each cycle is obtained through iterative calculation. The calculation formula of the buffer temperature difference of the outer tank is specifically:

[0104] ;

[0105] in, It is the fuel tank buffer temperature of the outer fuel tank in the current cycle, that is, the fuel tank buffer temperature of outer fuel tank No. 1 or outer fuel tank No. 2 in the current cycle. HRTOSEC is hours converted to seconds, and its value is 1 / 3600. Based on the above calculation formula, a more accurate and real outer fuel tank buffer temperature can be obtained.

[0106] On the basis of the above embodiment, the calculation of the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to the multiple fuel flow parameters also includes:

[0107] When it is determined that the fuel tank is the inner fuel tank, summing the fuel parameter of the transmission valve and the fuel flow parameter of the pressure relief valve to obtain a fourth summing result;

[0108] Obtaining a second product result according to the product of the real-time oil volume of the inner oil tank in the current cycle and the oil tank buffer temperature of the inner oil tank in the previous cycle;

[0109] Obtaining a fifth summation result according to a summation result between the fourth summation processing result and the second multiplication result;

[0110] A sixth summation result is obtained by summing the values ​​corresponding to the real-time oil volume of the inner oil tank in the current cycle and the total flow of the transfer valve;

[0111] According to the ratio between the fifth summation result and the sixth summation result, the fuel tank buffer temperature of the inner fuel tank in the current cycle during the simulated flight training is obtained.

[0112] In the present invention, according to the multiple fuel flow parameters obtained in the above embodiments, according to the calculation formula of the inner tank buffer temperature difference, the buffer temperature difference of the inner tank in each cycle is obtained through iterative calculation. The calculation formula of the inner tank buffer temperature difference is specifically:

[0113] ;

[0114] in, is the fuel tank buffer temperature of the inner fuel tank in the current cycle, that is, the fuel tank buffer temperature of inner fuel tank No. 3 or inner fuel tank No. 4 in the current cycle, HRTOSEC is hours converted to seconds, and the value is 1 / 3600. Based on the above calculation formula, a more accurate and real inner fuel tank buffer temperature can be obtained.

[0115] Based on the above embodiment, the target cooling rate function is determined according to the comparison result between the real-time fuel amount in the fuel tank of the current cycle and the minimum fuel amount, including:

[0116] In the case where it is determined that the real-time fuel amount in the fuel tank of the current cycle is greater than the minimum fuel amount, taking the first cooling rate function as the target cooling rate function;

[0117] In the case where it is determined that the real-time fuel amount in the fuel tank of the current cycle is less than or equal to the minimum fuel amount, using the second cooling rate function as the target cooling rate function;

[0118] The first cooling rate function is constructed based on the total temperature data, the fuel tank buffer temperature of the current cycle, the fuel burning rate, the maximum fuel amount of the fuel tank, and the real-time fuel amount of the fuel tank of the current cycle;

[0119] The second cooling rate function is constructed based on the total temperature data, the fuel tank buffer temperature of the current cycle, the fuel combustion rate, and the maximum fuel amount in the fuel tank.

[0120] In the present invention, different methods are used to calculate the fuel tank temperature difference value based on the real-time fuel amount in the fuel tank. Specifically, when the real-time fuel amount in the fuel tank is greater than the unavailable fuel amount (i.e., the minimum fuel amount), a cooling rate function related to the fuel amount, i.e., a first cooling rate function, is executed:

[0121] ;

[0122] When the real-time fuel amount in the fuel tank is less than or equal to the unavailable fuel amount, the cooling rate function related to the ambient temperature is executed, that is, the second cooling rate function:

[0123] ;

[0124] In the present invention, the fuel is stored in the wings on both sides and the central tank, and the wings have inner tanks and outer tanks. At this time, K=1 to 5, wherein AMBFDT is the temperature difference between the tank and the total temperature, in °C; TAT is the total temperature, in °C; TKBUFT is the tank buffer temperature of the current cycle, in °C; FTLAG is the lag constant, with a value of 5.3419E-5; FBURNRT is the fuel burning rate, with a value of 1.0; TKMAXF is the maximum fuel amount in the tank, in kg; VOLTK is the real-time fuel amount in the tank of the current cycle, in kg; CTIME is the system cycle time, in sec.

[0125] On the basis of the above embodiment, obtaining the fuel tank simulation temperature of each fuel tank in the current cycle according to the fuel tank buffer temperature of the current cycle and the fuel tank temperature difference value of the current cycle includes:

[0126] When it is determined that the fuel tank buffer temperature of the current cycle is less than the maximum fuel tank temperature, or greater than the minimum fuel tank temperature, the fuel tank buffer temperature of the current cycle and the fuel tank temperature difference of the current cycle are summed to obtain the fuel tank simulation temperature of the fuel tank in the current cycle;

[0127] When it is determined that the fuel tank buffer temperature of the current cycle is greater than the maximum fuel tank temperature, the maximum fuel tank temperature is used as the fuel tank buffer temperature of the current cycle, and the difference between the maximum fuel tank temperature and the fuel tank temperature of the current cycle is summed to obtain the fuel tank simulation temperature of the fuel tank in the current cycle;

[0128] When it is determined that the fuel tank buffer temperature of the current cycle is less than the fuel tank minimum temperature, the fuel tank minimum temperature is used as the fuel tank buffer temperature of the current cycle, and the fuel tank minimum temperature and the fuel tank temperature difference of the current cycle are summed to obtain the fuel tank simulation temperature of the current cycle.

[0129] In the present invention, when the fuel tank buffer temperature exceeds the maximum fuel tank temperature, the value corresponding to the fuel tank buffer temperature is directly set to the maximum fuel tank temperature, in order to prevent the fuel tank temperature from continuing to rise, thereby protecting the fuel tank and fuel from damage. Subsequently, the maximum fuel tank temperature and the fuel tank temperature difference value of the current cycle are summed to obtain the fuel tank simulation temperature of the fuel tank in the current cycle.

[0130] When the buffer temperature of the fuel tank is lower than the minimum temperature of the fuel tank, the buffer temperature of the fuel tank is adjusted to the minimum temperature of the fuel tank to prevent the fuel tank temperature from being too low. Then, the minimum temperature of the fuel tank is summed with the fuel tank temperature difference of the current cycle to obtain the fuel tank simulation temperature of the current cycle under this condition.

[0131] The fuel temperature simulation system for a civil aircraft provided by the present invention is described below. The fuel temperature simulation system for a civil aircraft described below and the fuel temperature simulation method for a civil aircraft described above can be referred to each other.

[0132] Figure 3 The schematic diagram of the structure of the fuel temperature simulation system for civil aircraft provided by the present invention is as follows: Figure 3 As shown, the present invention provides a fuel temperature simulation system for a civil aircraft, comprising a buffer temperature calculation module 301, a fuel quantity acquisition module 302, a processing module 303, a temperature difference calculation module 304 and a simulation temperature calculation module 305, wherein the buffer temperature calculation module 301 is used to calculate the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to a plurality of fuel flow parameters, wherein the plurality of fuel flow parameters are constructed based on the pressure relief valve flow, the transmission valve flow, the ejector pump flow and the engine hot fuel flow corresponding to the fuel tank; the fuel quantity acquisition module 302 is used to obtain the real-time fuel quantity of each fuel tank in the current cycle during the simulated flight training; the processing module 303 is used to calculate the fuel tank buffer temperature of each fuel tank in the current cycle according to a plurality of fuel flow parameters. According to the comparison result between the real-time fuel quantity in the fuel tank of the current cycle and the minimum fuel quantity, a target cooling rate function is determined, wherein the target cooling rate function is constructed based on the fuel tank buffer temperature, fuel combustion rate, maximum fuel quantity in the fuel tank and real-time fuel quantity in the fuel tank; the temperature difference calculation module 304 is used to calculate the fuel tank temperature difference value of each fuel tank in the current cycle based on the target cooling rate function and the fuel tank buffer temperature of the current cycle, wherein the fuel tank temperature difference value is the temperature difference value between the fuel tank temperature and the total temperature data; the simulation temperature calculation module 305 is used to obtain the fuel tank simulation temperature of each fuel tank in the current cycle according to the fuel tank buffer temperature of the current cycle and the fuel tank temperature difference value of the current cycle.

[0133] The fuel temperature simulation system for civil aircraft provided by the present invention, when modeling the aircraft fuel temperature simulation model, takes into account factors such as the fuel tank valve, the priming pump, and the engine in the actual aircraft to model the fuel temperature, thereby more comprehensively simulating the fuel temperature during the simulation training of the civil aircraft, so that the simulation result has higher authenticity and accuracy.

[0134] The system provided by the present invention is used to execute the above-mentioned method embodiments. Please refer to the above-mentioned embodiments for the specific processes and detailed contents, which will not be repeated here.

[0135] Figure 4 A schematic diagram of the structure of an electronic device provided by the present invention, such as Figure 4As shown, the electronic device may include: a processor (Processor) 401, a communication interface (Communications Interface) 402, a memory (Memory) 403 and a communication bus 404, wherein the processor 401, the communication interface 402, and the memory 403 communicate with each other through the communication bus 404. The processor 401 can call the logic instructions in the memory 403 to execute the fuel temperature simulation method of the civil aircraft, which includes: calculating the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to multiple fuel flow parameters, wherein the multiple fuel flow parameters are constructed based on the pressure relief valve flow, transmission valve flow, ejector pump flow and engine hot fuel flow corresponding to the fuel tank; obtaining the real-time fuel amount of each fuel tank in the current cycle during the simulated flight training; determining the target cooling rate function according to the comparison result between the real-time fuel amount of the fuel tank in the current cycle and the minimum fuel amount, wherein the target cooling rate function is constructed based on the fuel tank buffer temperature, fuel burning rate, maximum fuel amount of the fuel tank and real-time fuel amount of the fuel tank; based on the target cooling rate function, according to the fuel tank buffer temperature of the current cycle, calculating the fuel tank temperature difference value of each fuel tank in the current cycle, wherein the fuel tank temperature difference value is the temperature difference value between the fuel tank temperature and the total temperature data; according to the fuel tank buffer temperature of the current cycle and the fuel tank temperature difference value of the current cycle, obtaining the fuel tank simulation temperature of each fuel tank in the current cycle.

[0136] In addition, the logic instructions in the above-mentioned memory 403 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, etc. Various media that can store program codes.

[0137] On the other hand, the present invention also provides a computer program product, which includes a computer program stored on a non-transitory computer-readable storage medium, and the computer program includes program instructions. When the program instructions are executed by a computer, the computer can execute the fuel temperature simulation method for a civil aircraft provided by the above-mentioned methods, and the method includes: calculating the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training process according to multiple fuel flow parameters, wherein the multiple fuel flow parameters are constructed based on the pressure relief valve flow, transfer valve flow, ejector pump flow and engine hot fuel flow corresponding to the fuel tank; obtaining the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training process The real-time fuel amount in the fuel tank of the previous cycle; according to the comparison result between the real-time fuel amount in the fuel tank of the current cycle and the minimum fuel amount, determine the target cooling rate function, wherein the target cooling rate function is constructed based on the fuel tank buffer temperature, fuel combustion rate, maximum fuel amount in the fuel tank and real-time fuel amount in the fuel tank; based on the target cooling rate function, according to the fuel tank buffer temperature of the current cycle, calculate the fuel tank temperature difference value of each fuel tank in the current cycle, wherein the fuel tank temperature difference value is the temperature difference value between the fuel tank temperature and the total temperature data; according to the fuel tank buffer temperature of the current cycle and the fuel tank temperature difference value of the current cycle, obtain the fuel tank simulation temperature of each fuel tank in the current cycle.

[0138] On the other hand, the present invention further provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, is implemented to execute the fuel temperature simulation method for a civil aircraft provided in the above-mentioned embodiments, the method comprising: calculating the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to a plurality of fuel flow parameters, wherein the plurality of fuel flow parameters are constructed based on the pressure relief valve flow, the transmission valve flow, the ejector pump flow and the engine hot fuel flow corresponding to the fuel tank; obtaining the real-time fuel quantity of each fuel tank in the current cycle during the simulated flight training; and obtaining the real-time fuel quantity of each fuel tank in the current cycle according to the current fuel flow parameters. The target cooling rate function is determined based on the comparison result between the real-time fuel amount in the fuel tank of the current cycle and the minimum fuel amount, wherein the target cooling rate function is constructed based on the fuel tank buffer temperature, fuel combustion rate, maximum fuel amount in the fuel tank and real-time fuel amount in the fuel tank; based on the target cooling rate function, according to the fuel tank buffer temperature of the current cycle, the fuel tank temperature difference value of each fuel tank in the current cycle is calculated, wherein the fuel tank temperature difference value is the temperature difference value between the fuel tank temperature and the total temperature data; according to the fuel tank buffer temperature of the current cycle and the fuel tank temperature difference value of the current cycle, the fuel tank simulation temperature of each fuel tank in the current cycle is obtained.

[0139] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0140] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0141] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for simulating fuel temperature of a civil aircraft, characterized in that: include: Calculating the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to a plurality of fuel flow parameters, wherein the plurality of fuel flow parameters are constructed based on the pressure relief valve flow, the transfer valve flow, the ejector pump flow and the engine hot fuel flow corresponding to the fuel tank; Acquire the real-time fuel quantity of each fuel tank in the current cycle during the simulated flight training; Determine a target cooling rate function according to a comparison result between the real-time fuel amount in the fuel tank and the minimum fuel amount in the current cycle, wherein the target cooling rate function is constructed based on a fuel tank buffer temperature, a fuel burning rate, a maximum fuel amount in the fuel tank, and a real-time fuel amount in the fuel tank; Based on the target cooling rate function, according to the fuel tank buffer temperature of the current cycle, the fuel tank temperature difference value of each fuel tank in the current cycle is calculated, wherein the fuel tank temperature difference value is the temperature difference value between the fuel tank temperature and the total temperature data; The fuel tank simulation temperature of each fuel tank in the current cycle is obtained according to the fuel tank buffer temperature in the current cycle and the fuel tank temperature difference in the current cycle.

2. The method for simulating fuel temperature of a civil aircraft according to claim 1, characterized in that: The wings of the civil simulated aircraft in the simulated flight training process are provided with an outer fuel tank and an inner fuel tank, wherein the outer fuel tank is a fuel tank away from a side of the fuselage, and the inner fuel tank is a fuel tank close to a side of the fuselage, and the method further includes: When it is determined that the pressure relief valve of the fuel tank is in an open state, a fuel flow parameter of the pressure relief valve is obtained according to the product between the pressure relief valve flow and the preset boost pump temperature rise value; Acquire the fuel flow rate and flow temperature of the engine when transmitting hot fuel, and obtain the engine fuel flow parameter according to the product between the fuel flow rate and the flow temperature; When it is determined that the transfer valve between the outer fuel tank and the inner fuel tank is in a closed state, the fuel flow parameter of the ejector pump is obtained according to the product of the total flow of the ejector pump between the outer fuel tank and the inner fuel tank and the fuel tank buffer temperature of the inner fuel tank in the previous cycle; When it is determined that the transfer valve between the outer fuel tank and the inner fuel tank is in an open state and the ejector pump is in a closed state, the total flow of the transfer valve is obtained according to the gravity flow when the fuel in the outer fuel tank is transferred to the inner fuel tank under the action of gravity, and the transfer valve fuel parameter is obtained according to the product between the total flow of the transfer valve and the tank buffer temperature of the outer fuel tank in the previous cycle; The multiple fuel flow parameters are obtained according to the pressure relief valve fuel flow parameter, the engine fuel flow parameter, the ejector pump fuel flow parameter and the transfer valve fuel parameter.

3. The method for simulating fuel temperature of a civil aircraft according to claim 2, characterized in that: The step of calculating the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to the multiple fuel flow parameters includes: When it is determined that the fuel tank is the outer fuel tank, summing the fuel flow parameter of the engine and the fuel flow parameter of the ejector pump to obtain a first summing result; Obtaining a first product result according to the product of the real-time oil volume of the outer oil tank in the current cycle and the oil tank buffer temperature of the outer oil tank in the previous cycle; Obtaining a second summation result according to a summation result between the first summation processing result and the first product result; A third summation result is obtained by summing the values ​​corresponding to the real-time oil volume of the outer oil tank in the current cycle and the total flow of the ejector pump; According to the ratio between the second summation result and the third summation result, the fuel tank buffer temperature of the outer fuel tank in the current cycle during the simulated flight training is obtained.

4. The method for simulating fuel temperature of a civil aircraft according to claim 2, characterized in that: The step of calculating the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to the multiple fuel flow parameters also includes: When it is determined that the fuel tank is the inner fuel tank, summing the fuel parameter of the transmission valve and the fuel flow parameter of the pressure relief valve to obtain a fourth summing result; Obtaining a second product result according to the product of the real-time oil volume of the inner oil tank in the current cycle and the oil tank buffer temperature of the inner oil tank in the previous cycle; Obtaining a fifth summation result according to a summation result between the fourth summation processing result and the second multiplication result; A sixth summation result is obtained by summing the values ​​corresponding to the real-time oil volume of the inner oil tank in the current cycle and the total flow of the transfer valve; According to the ratio between the fifth summation result and the sixth summation result, the fuel tank buffer temperature of the inner fuel tank in the current cycle during the simulated flight training is obtained.

5. The method for simulating fuel temperature of a civil aircraft according to claim 2, characterized in that: The step of determining the target cooling rate function according to the comparison result between the real-time fuel amount in the fuel tank and the minimum fuel amount in the current cycle comprises: In the case where it is determined that the real-time fuel amount in the fuel tank of the current cycle is greater than the minimum fuel amount, taking the first cooling rate function as the target cooling rate function; In the case where it is determined that the real-time fuel amount in the fuel tank of the current cycle is less than or equal to the minimum fuel amount, using the second cooling rate function as the target cooling rate function; The first cooling rate function is constructed based on the total temperature data, the fuel tank buffer temperature of the current cycle, the fuel burning rate, the maximum fuel amount of the fuel tank, and the real-time fuel amount of the fuel tank of the current cycle; The second cooling rate function is constructed based on the total temperature data, the fuel tank buffer temperature of the current cycle, the fuel combustion rate, and the maximum fuel amount in the fuel tank.

6. The method for simulating fuel temperature of a civil aircraft according to any one of claims 1 to 5, characterized in that: The step of obtaining the fuel tank simulation temperature of each fuel tank in the current cycle according to the fuel tank buffer temperature in the current cycle and the fuel tank temperature difference value in the current cycle includes: When it is determined that the fuel tank buffer temperature of the current cycle is less than the maximum fuel tank temperature, or greater than the minimum fuel tank temperature, the fuel tank buffer temperature of the current cycle and the fuel tank temperature difference of the current cycle are summed to obtain the fuel tank simulation temperature of the fuel tank in the current cycle; When it is determined that the fuel tank buffer temperature of the current cycle is greater than the maximum fuel tank temperature, the maximum fuel tank temperature is used as the fuel tank buffer temperature of the current cycle, and the difference between the maximum fuel tank temperature and the fuel tank temperature of the current cycle is summed to obtain the fuel tank simulation temperature of the fuel tank in the current cycle; When it is determined that the fuel tank buffer temperature of the current cycle is less than the fuel tank minimum temperature, the fuel tank minimum temperature is used as the fuel tank buffer temperature of the current cycle, and the fuel tank minimum temperature and the fuel tank temperature difference of the current cycle are summed to obtain the fuel tank simulation temperature of the current cycle.

7. A fuel temperature simulation system for civil aircraft, characterized in that: include: A buffer temperature calculation module, used to calculate the fuel tank buffer temperature of each fuel tank in the current cycle during the simulated flight training according to a plurality of fuel flow parameters, wherein the plurality of fuel flow parameters are constructed based on the pressure relief valve flow, the transfer valve flow, the ejector pump flow and the engine hot fuel flow corresponding to the fuel tank; A fuel quantity acquisition module, used for acquiring the real-time fuel quantity of each fuel tank in the current cycle during the simulated flight training; a processing module, configured to determine a target cooling rate function according to a comparison result between the real-time fuel amount in the fuel tank and the minimum fuel amount in the current cycle, wherein the target cooling rate function is constructed based on a fuel tank buffer temperature, a fuel burning rate, a maximum fuel amount in the fuel tank, and a real-time fuel amount in the fuel tank; A temperature difference calculation module, configured to calculate the fuel tank temperature difference value of each fuel tank in the current cycle based on the target cooling rate function and the fuel tank buffer temperature of the current cycle, wherein the fuel tank temperature difference value is the temperature difference value between the fuel tank temperature and the total temperature data; The simulation temperature calculation module is used to obtain the fuel tank simulation temperature of each fuel tank in the current cycle according to the fuel tank buffer temperature in the current cycle and the fuel tank temperature difference value in the current cycle.

8. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the computer program, the fuel temperature simulation method for a civil aircraft according to any one of claims 1 to 6 is implemented.

9. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the fuel temperature simulation method for a civil aircraft as claimed in any one of claims 1 to 6 is implemented.

10. A computer program product, comprising a computer program, characterized in that When the computer program is executed by a processor, the fuel temperature simulation method for a civil aircraft as claimed in any one of claims 1 to 6 is implemented.

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