Aircraft dynamic oil level warning method and system

Abstract

The present invention relates to a method and system for warning a dynamic oil level of an aircraft, the method comprising: S1. combining the actual composition of each hydraulic source system of the aircraft hydraulic system, constructing a function expression of the oil level of the oil tank and the temperature of the oil tank; S2. constructing a low oil level warning condition; S3. combining the actual composition of each hydraulic source system of the aircraft hydraulic system, constructing a function expression of the oil level warning of the oil tank and the temperature of the oil tank; S4. detecting whether the oil level of the aircraft hydraulic oil tank is less than or equal to the warning value, if it is less than or equal to the warning value, then warning is issued, otherwise no warning is issued. The method determines a dynamic warning threshold by linking the warning threshold of the low oil level with the oil temperature and through a functional relationship, the threshold can improve the availability of the system and the attendance rate under the condition of ensuring the safety of the system.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft control, and in particular relates to an aircraft dynamic oil level alarm method and system. Background Art

[0002] At present, the aircraft hydraulic energy system needs oil to participate in the system circulation during operation. In order to ensure that the system can operate normally under various expected environments, it is necessary to ensure that the oil volume in the hydraulic oil tank must be more than a certain amount. If it is less than a certain amount, the crew must immediately take measures to deal with it. In order to prevent the crew from not dealing with it in time, a low oil level alarm will generally be given when the system oil volume is lower than a given value. However, the existing oil level alarm system designs the oil level alarm value as a fixed value, and the system design is simple. Due to the characteristics of oil expansion / contraction with temperature, in order to envelope the oil level changes at high and low temperatures of the aircraft oil and ensure system safety, when it is designed as a fixed value, the alarm value threshold can only be large, increasing the alarm threshold, thereby reducing the availability of the system. Summary of the invention

[0003] In order to solve the above problems existing in the prior art, the present invention provides an aircraft dynamic oil level warning method and system.

[0004] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0005] In a first aspect, a method for dynamic oil level warning of an aircraft according to the present invention comprises:

[0006] S1. Combine the actual composition of each hydraulic source system of the aircraft hydraulic system to construct a functional expression of the fuel tank refueling level and the fuel tank temperature;

[0007] S2. Construct low oil level alarm conditions, including:

[0008] According to the operating conditions of the aircraft in the entire flight profile, combined with the working state of the aircraft hydraulic system in the entire flight profile, considering the boundary conditions of the aircraft hydraulic system, calculate the difference between the amount of refueling during operation and the sum of all possible volume reductions of each hydraulic source system, and use this value as one of the alarm conditions;

[0009] According to the operating conditions of the aircraft in the entire flight profile, combined with the working status of the hydraulic system in the entire flight profile, considering the boundary conditions of the aircraft hydraulic system, calculate the minimum oil volume required for each hydraulic source system to maintain operation during operation, and use this value as one of the alarm conditions;

[0010] S3. Combined with the actual composition of each hydraulic source system of the aircraft hydraulic system, a function expression of the fuel tank alarm oil level and the fuel tank temperature is constructed;

[0011] S4. Check whether the oil level in the aircraft hydraulic oil tank is less than or equal to the alarm value. If so, an alarm is issued, otherwise no alarm is issued.

[0012] Further, step S4 includes:

[0013] Collect the oil temperature signal and hydraulic oil level signal in the hydraulic oil tank of each hydraulic source system of the aircraft, and determine whether to output the hydraulic oil tank low oil level alarm in combination with the built-in alarm oil level threshold that changes with temperature or the set fixed threshold;

[0014] When the oil temperature is determined to be lower than a set threshold according to the oil temperature signal, and the oil level is determined to be lower than a set fixed threshold according to the hydraulic oil level signal, a low oil level alarm is output;

[0015] When the oil temperature is higher than the set threshold value according to the oil temperature signal, and when the oil level is lower than the built-in warning oil level threshold value that changes with temperature according to the hydraulic oil level signal, a low oil level alarm is output.

[0016] Furthermore, in step S1, the process of constructing a function expression of the refueling oil level and the fuel tank temperature includes:

[0017] S1-1. Park the aircraft on the ground and establish the following fuel level calculation formula with reference to the fuel tank filling quantity standard;

[0018] ,

[0019] ,

[0020] ,

[0021] ,

[0022] ;

[0023] In the formula, is the total oil filling volume of the oil tank which changes with the hydraulic oil temperature of the oil tank; It is the change in oil volume in the oil tank caused by charging all accumulators from a fully depressurized state to the system design pressure state when one accumulator is not charged and other accumulators are charged to the specified minimum charging pressure. The unit is L. The change in oil volume in the oil tank caused by the volume difference of the actuator retraction and extension chamber between the ground state and the flight state is based on the normal position of each actuator on the ground. The unit is L. The minimum circulating oil volume for the oil tank to ensure the normal operation of the system - 2% of the maximum oil volume flowing through the oil tank per minute, in L; It is the amount of oil required for oil compression, in L; It is the expansion volume caused by the hydraulic parts under pressure, the unit is L; The system reserve oil volume is 1.5L for each hydraulic source system, in L; It is the volume of oil that is equal to the maximum cold shrinkage of all oil in the aircraft hydraulic system, in L; It is the volume of oil equal to 130% of the quantitative capacity of the largest hydraulic doser in the aircraft hydraulic system, in L; The oil volume from the left hydraulic source system to the middle hydraulic source system and the right hydraulic source system, in L; is the total volume of the accumulator, in L; The volume of the oil under high pressure, in L; is the inflation pressure at temperature t, in MPa; is the maximum pressure of the hydraulic system, in MPa. ; is the oil compressibility coefficient; t is the refueling and charging temperature of the hydraulic system, and the refueling and charging temperature of the hydraulic system is taken as room temperature, that is, t =30℃; The minimum operating temperature of the hydraulic system, the minimum operating temperature of the type II hydraulic system is t=-40℃; is the oil volume of the hydraulic system; is the volume expansion coefficient of the oil, ;

[0024] S1-2. Calculate all parameter values ​​in the above formula that are not related to the oil temperature, taking into account the status and conditions of each hydraulic source system of the aircraft;

[0025] S1-3. According to the minimum operating temperature requirement of the hydraulic system -40℃, calculate The initial value of; then combined with the definition of volume expansion rate, according to The initial value of is used, and the numerical solution is used to obtain the functional expression of the oil level of each hydraulic source and the oil temperature t in the oil tank.

[0026] Further, in step S2, (1) the difference between the amount of oil added during operation and the sum of all possible volume reductions of each hydraulic source system is calculated by the following formula;

[0027] ;

[0028] In the formula, is the total oil filling volume of the tank that changes with temperature; It is the change in oil volume in the oil tank caused by charging all accumulators from a fully depressurized state to the system design pressure state when one accumulator is not charged and other accumulators are charged to the specified minimum charging pressure. The unit is L. The change in oil volume in the oil tank caused by the volume difference of the actuator retraction and extension chamber between the ground state and the flight state is based on the normal position of each actuator on the ground. The unit is L. It is the amount of oil required for oil compression, in L; For the system reserve oil volume, take 1.5L for each hydraulic source system;

[0029] (2) Calculate the minimum amount of oil required for each hydraulic source system to maintain operation during operation using the following formula;

[0030] + + The increase in the accumulator's liquid chamber volume from the charging pressure to the system's rated pressure;

[0031] In the formula, Based on the normal position of each actuator on the ground, the change in the oil volume in the oil tank caused by the volume difference of the actuator retraction and extension chamber in the ground state and the flight state, the unit is L; The minimum circulating oil volume in the oil tank to ensure the normal operation of the system, calculated as 2% of the maximum oil volume flowing through the oil tank per minute, in L.

[0032] Furthermore, when constructing the function expression of the fuel tank alarm oil level and the fuel tank temperature in step S3, the larger value of the two alarm conditions is taken; specifically:

[0033] Take the function expression of the oil level and oil temperature t of the hydraulic source system as condition one and the fixed value as condition two, establish an equivalent relationship, and solve the corresponding temperature value when the two are equal;

[0034] According to the temperature value solved above, the entire alarm function is divided into segments. Above this temperature value, the actual oil level is lower than condition one, and an alarm is issued. Below this temperature value, the actual oil level is lower than condition two, and an alarm is issued.

[0035] In a second aspect, the aircraft dynamic oil level warning system of the present invention comprises:

[0036] The oil temperature sensor is installed on the oil tank of each hydraulic source system of the aircraft, and obtains the current oil temperature information in the hydraulic oil tank through contact with the hydraulic oil;

[0037] The oil level sensor is installed on the oil tank of each hydraulic source system of the aircraft, and is connected to the piston in the system oil tank to obtain the current oil level information in the hydraulic oil tank;

[0038] The acquisition system is connected to the oil temperature sensor and the oil level sensor, converts the voltage signals representing the oil temperature and oil level transmitted by the oil temperature sensor and the oil level sensor into corresponding digital signals, and communicates with the management computer;

[0039] The management computer has the above-mentioned aircraft dynamic oil level alarm method built in, and substitutes the oil temperature and oil level signals sent by the acquisition system into the function expression of the oil tank alarm oil level and the oil tank temperature to determine whether to output a low oil level alarm instruction;

[0040] The IDU interactive display gives a corresponding alarm display by solving the low oil level command output by the management computer.

[0041] Beneficial effects of the present invention:

[0042] The above technical solution of the present invention realizes the dynamic oil level alarm of the aircraft, improves the availability of the hydraulic system, and improves the attendance rate. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 It is a flow chart of the aircraft dynamic oil level warning method of the present invention;

[0044] Figure 2 It is a schematic block diagram of the structure of the aircraft dynamic oil level warning system of the present invention;

[0045] Figure 3 It is a curve diagram of the relationship between the left hydraulic source oil tank and the temperature in the process of constructing a functional expression of the oil tank warning oil level and the oil tank temperature in the aircraft dynamic oil level warning method of the present invention;

[0046] Figure 4 It is a curve diagram of the relationship between the hydraulic source oil tank and the temperature in the process of constructing a functional expression of the oil tank warning oil level and the oil tank temperature in the aircraft dynamic oil level warning method of the present invention. DETAILED DESCRIPTION

[0047] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0048] like Figure 1 As shown, the aircraft dynamic oil level warning method described in the present invention comprises the following steps:

[0049] Step S1. Based on the actual composition of each hydraulic source system of the aircraft hydraulic system, a function expression of the oil tank refueling level and the oil tank temperature is constructed (the aircraft is a large aircraft, including more than two hydraulic source systems, for example, the aircraft in the embodiment of the table below includes a left hydraulic source system, a middle hydraulic source system and a right hydraulic source system); the specific process includes:

[0050] S1-1. Park the aircraft on the ground and establish the following oil filling level calculation formula with reference to the oil filling amount standard of the oil tank (National Military Standard GJB 3223-98 "General Specification for Aircraft Hydraulic System Isolation Oil Tanks"), and clarify the factors that need to be considered in the calculation process: the minimum oil volume required for the hydraulic pump cycle, the oil level difference in different states of the actuation system, the volume change in the oil tank caused by the accumulator being completely unloaded to the state of being filled to the design pressure, the change of oil with temperature, the allowable volume difference, the dead oil volume, etc.;

[0051] ,

[0052] ,

[0053] ,

[0054] ,

[0055] ;

[0056] In the formula, is the total oil filling volume of the tank that changes with temperature; It is the change in oil volume in the oil tank caused by charging all accumulators from a fully depressurized state to the system design pressure state when one accumulator is not charged and other accumulators are charged to the specified minimum charging pressure. The unit is L. The change in oil volume in the oil tank caused by the volume difference of the actuator retraction and extension chamber between the ground state and the flight state is based on the normal position of each actuator on the ground. The unit is L. The minimum circulating oil volume for the oil tank to ensure the normal operation of the system - 2% of the maximum oil volume flowing through the oil tank per minute, in L; It is the amount of oil required for oil compression, in L; It is the expansion volume caused by the hydraulic parts under pressure, the unit is L; The system reserve oil volume (considering the full leakage volume), 1.5L for each hydraulic source system, unit is L; It is the volume of oil that is equal to the maximum cold shrinkage of all oil in the aircraft hydraulic system, in L; It is the volume of oil equal to 130% of the quantitative capacity of the largest hydraulic doser in the aircraft hydraulic system, in L; The oil volume from the left hydraulic source system to the middle hydraulic source system and the right hydraulic source system, in L; is the total volume of the accumulator, in L; The volume of the oil under high pressure, in L; is the inflation pressure at temperature t, in MPa; is the maximum pressure of the hydraulic system, in MPa. ; is the oil compressibility coefficient; t is the refueling and charging temperature of the hydraulic system, and the refueling and charging temperature of the hydraulic system is taken as room temperature, that is, t =30℃; The minimum operating temperature of the hydraulic system, the minimum operating temperature of the type II hydraulic system is t=-40℃; is the oil volume of the hydraulic system; is the volume expansion coefficient of the oil, ;

[0057] S1-2. Combine the status and conditions of each hydraulic source system of the aircraft hydraulic source to calculate all parameter values ​​in the above formula that are not related to the oil temperature, that is, combine the design status and conditions of each aircraft system to calculate the above formula In ~ The specific calculation process belongs to the common knowledge in this field and will not be described in detail here;

[0058] S1-3. According to the minimum operating temperature requirement of the hydraulic system -40℃, calculate The initial value of; then combined with the definition of volume expansion rate, according to The initial value of is used, and the numerical solution is used to obtain the function expression of the oil filling level and the oil tank oil temperature t of each hydraulic source system; that is, combining the formula of S1-1 above and the value calculated in S1-2, substituting the calculation of the expansion rate and the definition of -40 degrees Celsius oil, combined with the numerical solution, the expression of the oil level and temperature of each hydraulic source system is obtained.

[0059] Step S2. Constructing low oil level warning conditions, including:

[0060] S2-1. According to the operating conditions of the aircraft in the entire flight profile, combined with the working state of the hydraulic system in the entire flight profile, considering the boundary conditions of the hydraulic system, calculate the difference between the amount of refueling during operation and the sum of all possible volume reductions of each hydraulic source system, and use this value as one of the alarm conditions; wherein the difference between the amount of refueling during operation and the sum of all possible volume reductions of each hydraulic source system is calculated by the following formula (alarm condition one expression):

[0061] ;

[0062] In the formula, is the total oil filling volume of the tank that changes with temperature; It is the change in oil volume in the oil tank caused by charging all accumulators from a fully depressurized state to the system design pressure state when one accumulator is not charged and other accumulators are charged to the specified minimum charging pressure. The unit is L. The change in oil volume in the oil tank caused by the volume difference of the actuator retraction and extension chamber between the ground state and the flight state is based on the normal position of each actuator on the ground. The unit is L. It is the amount of oil required for oil compression, in L; For the system reserve oil volume (considering the full leakage volume), take 1.5L for each hydraulic source system;

[0063] S2-2. According to the operating conditions of the aircraft in the entire flight profile, combined with the working state of the hydraulic system in the entire flight profile, considering the boundary conditions of the hydraulic system, calculate the minimum amount of oil required for each hydraulic source system to maintain operation during operation, and use this value as one of the alarm conditions; wherein, the minimum amount of oil required for each hydraulic source system to maintain operation during operation is calculated by the following formula (alarm condition 2 expression):

[0064] + + The increase in the accumulator's liquid chamber volume from the charging pressure to the system's rated pressure;

[0065] In the formula, Based on the normal position of each actuator on the ground, the change in the oil volume in the oil tank caused by the volume difference of the actuator retraction and extension chamber in the ground state and the flight state, the unit is L; The minimum circulating oil volume in the oil tank to ensure the normal operation of the system, calculated as 2% of the maximum oil volume flowing through the oil tank per minute, in L.

[0066] Step S3. In combination with the actual composition of each hydraulic source system of the aircraft hydraulic system, a function expression of the oil tank warning oil level and the oil tank temperature is constructed; specifically: when constructing the function expression of the oil tank warning oil level and the oil tank temperature, the larger value of the two warning conditions is taken; specifically:

[0067] First, take the function expression of the hydraulic source oil level and the oil temperature t as condition one, and the fixed value (different for each hydraulic source system) as condition two, establish an equivalent relationship, and solve the corresponding temperature value when the two are equal;

[0068] Then, according to the temperature value solved above, the entire warning function is segmented (for example, according to the parameter values ​​of each hydraulic system oil tank of the aircraft obtained by simulation and calculation, see Table 1 below). Above this temperature value, the actual oil level is lower than condition 1, and an alarm is issued. Below this temperature value, the actual oil level is lower than condition 2, and an alarm is issued. For example, see Figure 3 and Figure 4 Graph of the curve.

[0069]

[0070] Step S4. Detect whether the oil level of the aircraft hydraulic oil tank is less than or equal to the alarm value. If it is less than or equal to the alarm value, an alarm is issued, otherwise no alarm is issued; including:

[0071] Collect the oil temperature signal and hydraulic oil level signal in the hydraulic oil tank of each hydraulic source system of the aircraft, and determine whether to output the hydraulic oil tank low oil level alarm in combination with the built-in alarm oil level threshold that changes with temperature or the set fixed threshold;

[0072] When the oil temperature is determined to be lower than a set threshold according to the oil temperature signal, and the oil level is determined to be lower than a set fixed threshold according to the hydraulic oil level signal, a low oil level alarm is output;

[0073] When the oil temperature is higher than the set threshold value according to the oil temperature signal, and when the oil level is lower than the built-in warning oil level threshold value that changes with temperature according to the hydraulic oil level signal, a low oil level alarm is output.

[0074] The aircraft dynamic oil level warning method of the present invention relates the low oil level warning threshold to the oil temperature and determines the dynamic warning threshold through a functional relationship. The threshold can improve the availability of the system and the attendance rate while ensuring the safety of the system.

[0075] In a second aspect, the aircraft dynamic oil level warning system described in the present invention includes an oil temperature sensor 100 , an oil level sensor 200 , a collection system 300 , a management computer 400 and an IDU interactive display 500 . Among them, the oil temperature sensor 100 is installed on the oil tank of each hydraulic source system of the aircraft, and obtains the oil temperature information in the current hydraulic oil tank by contacting with the hydraulic oil; the oil level sensor 200 is installed on the oil tank of each hydraulic source system of the aircraft, and obtains the oil level information in the current hydraulic oil tank by connecting with the piston in the system oil tank; the acquisition system 300 is connected to the oil temperature sensor 100 and the oil level sensor 200, converts the voltage signals representing the oil temperature and oil level transmitted by the oil temperature sensor 100 and the oil level sensor 200 into corresponding digital signals, and communicates with the management computer 400; the management computer 400 is equipped with the above-mentioned aircraft dynamic oil level alarm method, and substitutes the oil temperature and oil level signals received from the acquisition system 300 into the function expression of the oil tank alarm oil level and the oil tank temperature to determine whether to output a low oil level alarm instruction; the IDU interactive display 500 gives a corresponding alarm display by solving the low oil level instruction output by the management computer 400.

[0076] The above is a preferred embodiment of the present invention. It should be pointed out that a person skilled in the art can make several improvements and modifications without departing from the principle of the present invention. These improvements and modifications are also considered to be within the scope of protection of the present invention.

Claims

1. An aircraft dynamic oil level warning method, characterized in that: include: S1. Based on the actual composition of each hydraulic source system of the aircraft hydraulic system, a function expression of the fuel tank refueling level and the fuel tank temperature is constructed; the process of constructing the function expression of the fuel tank refueling level and the fuel tank temperature includes: S1-1. Park the aircraft on the ground and establish the following fuel level calculation formula with reference to the fuel tank filling quantity standard; ， ， ， ， ； In the formula, is the total oil filling volume of the oil tank which changes with the hydraulic oil temperature of the oil tank; It is the change in oil volume in the oil tank caused by charging all accumulators from a fully depressurized state to the system design pressure state when one accumulator is not charged and other accumulators are charged to the specified minimum charging pressure. The unit is L. The change in oil volume in the oil tank caused by the volume difference of the actuator retraction and extension chamber between the ground state and the flight state is based on the normal position of each actuator on the ground. The unit is L. The minimum circulating oil volume for the oil tank to ensure the normal operation of the system - 2% of the maximum oil volume flowing through the oil tank per minute, in L; It is the amount of oil required for oil compression, in L; It is the expansion volume caused by the hydraulic parts under pressure, the unit is L; The system reserve oil volume is 1.5L for each hydraulic source system, in L; It is the volume of oil that is equal to the maximum cold shrinkage of all oil in the aircraft hydraulic system, in L; It is the volume of oil equal to 130% of the quantitative capacity of the largest hydraulic doser in the aircraft hydraulic system, in L; The oil volume from the left hydraulic source system to the middle hydraulic source system and the right hydraulic source system, in L; is the total volume of the accumulator, in L; The volume of the oil under high pressure, in L; is the inflation pressure at temperature t, in MPa; is the maximum pressure of the hydraulic system, in MPa. ; is the oil compressibility coefficient; t is the refueling and charging temperature of the aircraft hydraulic system, and the refueling and charging temperature of the aircraft hydraulic system is taken as room temperature, that is, t =30℃; The minimum operating temperature of the aircraft hydraulic system is -40℃. is the volume of oil in the aircraft hydraulic system; is the volume expansion coefficient of the oil, ; S1-2. Calculate all parameter values ​​in the above formula that are not related to the oil temperature, taking into account the status and conditions of each hydraulic source system of the aircraft; S1-3. According to the minimum operating temperature requirement of the aircraft hydraulic system -40℃, calculate The initial value of; then combined with the definition of volume expansion rate, according to The initial value of is used, and the functional expression of the oil level of each hydraulic source and the oil temperature t of the oil tank is obtained by numerical solution; S2. Construct low oil level alarm conditions, including: According to the operating conditions of the aircraft in the entire flight profile, combined with the working state of the aircraft hydraulic system in the entire flight profile, considering the boundary conditions of the aircraft hydraulic system, calculate the difference between the amount of refueling during operation and the sum of all possible volume reductions of each hydraulic source system, and use this value as one of the alarm conditions; According to the operating conditions of the aircraft in the entire flight profile, combined with the working status of the hydraulic system in the entire flight profile, considering the boundary conditions of the aircraft hydraulic system, calculate the minimum oil volume required for each hydraulic source system to maintain operation during operation, and use this value as one of the alarm conditions; S3. Combined with the actual composition of each hydraulic source system of the aircraft hydraulic system, a function expression of the fuel tank alarm oil level and the fuel tank temperature is constructed; S4. Check whether the oil level in the aircraft hydraulic oil tank is less than or equal to the alarm value. If so, an alarm is issued, otherwise no alarm is issued.

2. The method according to claim 1, characterized in that Step S4 includes: Collect the oil temperature signal and hydraulic oil level signal in the hydraulic oil tank of each hydraulic source system of the aircraft, and determine whether to output the hydraulic oil tank low oil level alarm in combination with the built-in alarm oil level threshold that changes with temperature or the set fixed threshold; When the oil temperature is determined to be lower than a set threshold according to the oil temperature signal, and the oil level is determined to be lower than a set fixed threshold according to the hydraulic oil level signal, a low oil level alarm is output; When the oil temperature is higher than the set threshold value according to the oil temperature signal, and when the oil level is lower than the built-in warning oil level threshold value that changes with temperature according to the hydraulic oil level signal, a low oil level alarm is output.

3. The method according to any one of claims 1-2, characterized in that: In step S2, (1) the difference between the amount of oil added during operation and the sum of all possible volume reductions of each hydraulic source system is calculated by the following formula; ； In the formula, is the total oil filling volume of the tank that changes with temperature; It is the change in oil volume in the oil tank caused by charging all accumulators from a fully depressurized state to the system design pressure state when one accumulator is not charged and other accumulators are charged to the specified minimum charging pressure. The unit is L. The change in oil volume in the oil tank caused by the volume difference of the actuator retraction and extension chamber between the ground state and the flight state is based on the normal position of each actuator on the ground. The unit is L. It is the amount of oil required for oil compression, in L; Take the system reserve oil quantity, 1.5L for each hydraulic source system; (2) Calculate the minimum amount of oil required for each hydraulic source system to maintain operation during operation using the following formula; + + The increase in the accumulator's liquid chamber volume from the charging pressure to the system's rated pressure; In the formula, Based on the normal position of each actuator on the ground, the change in the oil volume in the oil tank caused by the volume difference of the actuator retraction and extension chamber in the ground state and the flight state, the unit is L; The minimum circulating oil volume in the oil tank to ensure the normal operation of the system, calculated as 2% of the maximum oil volume flowing through the oil tank per minute, in L.

4. An aircraft dynamic oil level warning system, characterized in that: include: An oil temperature sensor (100) is installed on the oil tank of each hydraulic source system of the aircraft, and obtains information on the current oil temperature in the hydraulic oil tank by contacting the hydraulic oil; An oil level sensor (200) is installed on the oil tank of each hydraulic source system of the aircraft, and is connected to a piston in the system oil tank to obtain information about the current oil level in the hydraulic oil tank; The data collection system (300) is connected to the oil temperature sensor (100) and the oil level sensor (200), converts the voltage signals representing the oil temperature and the oil level transmitted by the oil temperature sensor (100) and the oil level sensor (200) into corresponding digital signals, and communicates with the management computer (400); A management computer (400) is built with the aircraft dynamic oil level warning method as described in any one of claims 1 to 3, and substitutes the oil temperature and oil level signals received from the acquisition system (300) into the function expression of the oil tank warning oil level and the oil tank temperature to determine whether to output a low oil level warning instruction; The IDU interactive display (500) provides a corresponding alarm display by solving the low oil level instruction output by the management computer (400).

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