Aircraft demand conversion method, device, equipment and medium based on engine characteristics

Abstract

The present application discloses a method, device, equipment and medium for converting aircraft demand based on engine characteristics. The method provides a target demand power conversion model for engine power based on actual test data characteristics of a certain type of turboshaft turboprop engine that is similar to the target engine configuration and has been verified by high-altitude platform tests. The target demand power conversion model can be used to more accurately evaluate the actual power capacity of the engine, and can be used for engine design based on aircraft requirements, so that in the early stage of engine design, it can be determined whether the designed state point can meet the requirements of the aircraft's full envelope, and the maximum power state point can be determined by the aircraft requirements to guide the selection of engine design points, ensuring that the result after the engine completes the design scheme is basically consistent with the evaluated converted power, thereby improving the accuracy and reliability of engine design parameters and meeting the requirements of the aircraft's full envelope.

Description

Technical Field

[0001] The present application relates to the field of aviation engine technology, and in particular, to a method, device, equipment and medium for converting aircraft demand based on engine characteristics. Background Art

[0002] Helicopters and turboprop aircraft often have different power requirements at different altitudes, temperatures, and flight conditions. For turboshaft and turboprop engines, the maximum output power decreases with increasing altitude and temperature. However, when an aircraft has power requirements at different altitudes, temperatures, speeds, etc., it is difficult to compare which state has a higher power requirement.

[0003] In the design of a turboshaft turboprop engine, the power requirements of the aircraft must be met first, and the aircraft will propose different powers under different states according to its flight envelope. Under the existing technology, a design point is selected through experience. After the preliminary design of the engine is completed, other state points in the flight envelope are checked. If the requirements are not met, the parameter selection of the design point needs to be re-conducted. The existing engine power conversion method calculates the converted power based on the inlet conditions. It is an aerodynamic parameter conversion method. Under this conversion method, the higher the inlet temperature, the higher the converted power, which is contrary to the actual engine capacity and cannot represent the engine capacity. Therefore, the existing scheme cannot determine whether the designed state point can meet the requirements of the aircraft's full envelope at the beginning of the design, and cannot determine the maximum power state point through aircraft requirements to guide the selection of engine design points. Summary of the invention

[0004] On the one hand, the present application provides an aircraft demand conversion method based on engine characteristics to solve the technical problem that the prior art is unable to determine whether the designed state point can meet the aircraft's full envelope requirements in the early stage of design, and is unable to determine the maximum power state point through aircraft requirements to guide the selection of engine design points.

[0005] The technical solutions adopted in this application are as follows:

[0006] A method for converting aircraft demand based on engine characteristics comprises the steps of:

[0007] S1. Obtain test data of a turboshaft turboprop engine that is similar to the target engine and has been verified by high-altitude test benches, define this type of engine as the benchmark engine, define the power demand of the aircraft as the target power demand, and define the engine that meets the target power demand as the target engine;

[0008] S2. Preprocess the data to obtain the power characteristic data of the engine at different altitudes, temperatures and speeds at the same gas generator speed;

[0009] S3, performing linear fitting on the power characteristic data to obtain the characteristic change slopes of power with the three parameters of height, temperature and speed, and defining them as height coefficient X1, temperature coefficient X2 and speed coefficient X3 respectively;

[0010] S4. Establish a calculation model for the height, speed, and temperature power characteristics of the scale engine, namely:

[0011] P=P0+H*X1+T*X2+M*X3 (1)

[0012] Wherein, P is the power of the scale engine at the calculation state point, P0 is the power value of the scale engine at the ground standard day and the Mach number is 0, H is the height of the calculation state point, T is the deviation between the temperature of the calculation state point and the standard temperature, and M is the flight Mach number of the target state;

[0013] S5. Select a state point as a scaling reference point, divide the power of the target engine and the scale engine at the scaling reference point, obtain a proportionality coefficient K, scale the characteristics according to the proportionality coefficient K, and obtain a target demand power conversion model:

[0014] Pc=Ps-H*X1*KT*X2*KM*X3*K (2)

[0015] Among them, Pc is the power value of the target required power converted to the ground standard day and the Mach number is 0, and Ps is the actual power value of the target required power;

[0016] S6. Select a target state point, substitute the target required power into the required power conversion model, and obtain the converted power, wherein the target state point is a state when the ground standard day and the Mach number is 0;

[0017] S7. Select the state point with the largest converted power as the engine design point.

[0018] Furthermore, in step S1, the turboshaft turboprop engine test data includes engine gas generator speed, power, flight altitude, speed, and temperature, wherein the engine output power should be the power without aircraft bleed air and power extraction, and the flight altitude, speed, and temperature cover the design operating envelope of the engine.

[0019] Furthermore, in step S2, the data is preprocessed, including being unified into the international system of units, and all data are retained to integer digits.

[0020] Furthermore, in step S3, the power characteristic data is linearly fitted using the least squares method.

[0021] Furthermore, in the step S5, the maximum take-off state point of the ground standard day is selected as the scaling reference point.

[0022] On the other hand, the present application also provides an aircraft demand conversion device based on engine characteristics, comprising:

[0023] A test data acquisition module is used to acquire test data of a turboshaft turboprop engine that is similar to the target engine configuration and has been tested and verified on a high-altitude platform, and the engine is defined as a benchmark engine, the power demand of the aircraft is defined as a target power demand, and the engine that meets the target power demand is defined as a target engine;

[0024] The data preprocessing module is used to preprocess the data, unify it into the international system of units, retain all data to integers, and obtain the power characteristic data of the engine at different altitudes, temperatures, and speeds at the same gas generator speed;

[0025] A coefficient obtaining module is used to perform linear fitting on the power characteristic data to obtain the characteristic change slopes of power as the three parameters of height, temperature and speed change, and define them as height coefficient X1, temperature coefficient X2 and speed coefficient X3 respectively;

[0026] Characteristic calculation model establishment module, used to establish the standard engine height, speed, temperature power characteristic calculation model:

[0027] P=P0+H*X1+T*X2+M*X3 (1)

[0028] Wherein, P is the power of the scale engine at the calculation state point, P0 is the power value of the scale engine at the ground standard day and the Mach number is 0, H is the height of the calculation state point, T is the deviation between the temperature of the calculation state point and the standard temperature, and M is the flight Mach number of the target state;

[0029] The target demand power conversion model establishment module is used to select a state point as the scaling reference point, divide the power of the target engine and the scale engine at the scaling reference point, obtain the proportionality coefficient K, scale the characteristics according to the proportionality coefficient K, and obtain the target demand power conversion model:

[0030] Pc=Ps-H*X1*KT*X2*KM*X3*K (2)

[0031] Among them, Pc is the power value of the target required power converted to the ground standard day and the Mach number is 0, and Ps is the actual power value of the target required power;

[0032] A conversion module is used to select a target state point, substitute the target required power into the required power conversion model, and obtain the converted power, wherein the target state point is a state when the ground standard day and the Mach number is 0;

[0033] The engine design point determination module is used to select the state point with the largest converted power as the engine design point.

[0034] On the other hand, the present application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the method for converting aircraft demand based on engine characteristics when executing the computer program.

[0035] On the other hand, the present application further provides a storage medium, which includes a stored program, and when the program is run, controls the device where the storage medium is located to execute the steps of the aircraft demand conversion method based on engine characteristics.

[0036] Compared with the prior art, this application has the following beneficial effects:

[0037] The present application provides an aircraft demand conversion method based on engine characteristics. The method provides a target demand power conversion model for engine power based on actual test data characteristics of a certain type of turboshaft turboprop engine that is similar to the target engine configuration and has been verified by high-altitude bench tests. The target demand power conversion model can be used to more accurately evaluate the actual power capability of the engine, and can be used for engine design based on aircraft requirements, so that in the early stage of engine design, it can be determined whether the designed state point can meet the requirements of the aircraft's full envelope, and the maximum power state point can be determined through the aircraft requirements to guide the selection of engine design points, ensuring that the result after the engine completes the design scheme is basically consistent with the evaluated converted power, thereby improving the accuracy and reliability of engine design parameters and meeting the requirements of the aircraft's full envelope.

[0038] In addition to the above-described purposes, features and advantages, the present application also has other purposes, features and advantages. The present application will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The illustrative embodiments and descriptions of the present application are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0040] Figure 1 It is a flow chart of an aircraft demand conversion method based on engine characteristics according to a preferred embodiment of the present application;

[0041] Figure 2 It is a schematic diagram of a module of an aircraft demand conversion device based on engine characteristics in a preferred embodiment of the present application;

[0042] Figure 3 is a schematic block diagram of an electronic device entity in a preferred embodiment of the present application;

[0043] Figure 4 It is a schematic diagram of the internal structure of a computer device according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0044] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0045] Reference Figure 1 The preferred embodiment of the present application provides an aircraft demand conversion method based on engine characteristics, comprising the steps of:

[0046] S1. Obtain test data of a turboshaft turboprop engine that is similar to the target engine configuration and has been verified by high-altitude test benches, including engine gas generator speed, power, flight altitude, speed, and temperature. The engine output power should be the power without aircraft bleed air and power extraction. The flight altitude, speed, and temperature cover the design operating envelope of the engine. This type of engine is defined as the benchmark engine, the aircraft power demand is defined as the target demand power, and the engine that meets the target demand power is defined as the target engine;

[0047] S2. Preprocess the data, unify them into the international system of units, retain all data to integers, and obtain the power characteristic data of the engine at different altitudes, temperatures, and speeds at the same gas generator speed;

[0048] S3, using the least square method to perform linear fitting on the power characteristic data, to obtain the characteristic change slopes of power with the three parameters of height, temperature and speed, and define them as height coefficient X1, temperature coefficient X2 and speed coefficient X3 respectively;

[0049] S4. Establish a calculation model for the height, speed, and temperature power characteristics of a scale engine:

[0050] P=P0+H*X1+T*X2+M*X3 (1)

[0051] Wherein, P is the power of the scale engine at the calculation state point, P0 is the power value of the scale engine at the ground standard day and the Mach number is 0, H is the height of the calculation state point, T is the deviation between the temperature of the calculation state point and the standard temperature, and M is the flight Mach number of the target state;

[0052] S5. Select a state point as a scaling reference point, divide the power of the target engine and the scale engine at the scaling reference point, obtain a proportionality coefficient K, scale the characteristics according to the proportionality coefficient K, and obtain a target demand power conversion model:

[0053] Pc=Ps-H*X1*KT*X2*KM*X3*K (2)

[0054] Among them, Pc is the power value of the target required power converted to the ground standard day and the Mach number is 0, and Ps is the actual power value of the target required power;

[0055] S6. Select a target state point, substitute the target required power into the required power conversion model, and obtain the converted power, wherein the target state point is a state when the ground standard day and the Mach number is 0;

[0056] S7. Select the state point with the largest converted power as the engine design point.

[0057] The present application provides an aircraft demand conversion method based on engine characteristics. The method provides a target demand power conversion model for engine power based on actual test data characteristics of a certain type of turboshaft turboprop engine that is similar to the target engine configuration and has been verified by high-altitude bench tests. The target demand power conversion model can be used to more accurately evaluate the actual power capability of the engine, and can be used for engine design based on aircraft requirements, so that in the early stage of engine design, it can be determined whether the designed state point can meet the requirements of the aircraft's full envelope, and the maximum power state point can be determined through the aircraft requirements to guide the selection of engine design points, ensuring that the result after the engine completes the design scheme is basically consistent with the evaluated converted power, thereby improving the accuracy and reliability of engine design parameters and meeting the requirements of the aircraft's full envelope.

[0058] Specifically, in step S5, the maximum takeoff state point on the ground standard day is selected as the scaling reference point. Its purpose and advantage are: most aircraft will make power requirements for this state point. Selecting this state point can facilitate the comparison of the power sizes of different engines. At the same time, this state is also the state that is best verified by bench testing.

[0059] Implementation Cases:

[0060] The power requirements of a certain type of aircraft for the engine are shown in Table 1:

[0061] Table 1

[0062]

[0063] The test data of a turboshaft turboprop engine with a similar configuration to the target engine and which has been verified by high-altitude test benches are obtained. After analyzing and fitting the test data at the same gas generator speed of this type of engine, it is found that its power characteristic data at altitude, speed, and temperature conform to the following rules:

[0064] 1) The maximum take-off power on a standard ground day is 3500 kW, i.e. P0 = 3500;

[0065] 2) When the altitude increases by 1000m, the power decreases by 90kW, i.e. X1 = -90;

[0066] 3) When the temperature rises by 1 degree, the power decreases by 80kW, that is, X2 = -80;

[0067] 4) The Mach number increases by 0.1, and the power increases by 30kW, that is, X3 = 30;

[0068] According to the above rules, a power characteristic calculation model of a certain engine is established, that is, the above formula (1) can be written as:

[0069] P=3500+H*(-90)+T*(-80)+M*30

[0070] The conversion ratio between the target demand power conversion model and the power characteristic calculation model adopts the power ratio under the ground standard day condition, that is, the proportionality coefficient is K=3000 / 3500.

[0071] Then the target demand power conversion model, that is, the above formula (2) can be written as:

[0072] Pc=Ps-H*(-30)*30 / 35-T*(-80)*30 / 35-M*30*30 / 35

[0073] The results of aircraft power conversion are shown in Table 2:

[0074] Table 2

[0075]

[0076] According to the conversion results under different working conditions, it can be judged that the highest aerodynamic state point required by this type of aircraft is 2, and its converted power is the largest, reaching 4746kw. The power capacity of this state point should be considered when selecting the engine design point, so as to maximize the satisfaction of the aircraft's full envelope requirements.

[0077] like Figure 2 As shown, the present application also provides an aircraft demand conversion device based on engine characteristics, including:

[0078] A test data acquisition module is used to acquire test data of a turboshaft turboprop engine that is similar to the target engine configuration and has been tested and verified on a high-altitude platform, and the engine is defined as a benchmark engine, the power demand of the aircraft is defined as a target power demand, and the engine that meets the target power demand is defined as a target engine;

[0079] The data preprocessing module is used to preprocess the data, unify it into the international system of units, retain all data to integers, and obtain the power characteristic data of the engine at different altitudes, temperatures, and speeds at the same gas generator speed;

[0080] A coefficient obtaining module is used to perform linear fitting on the power characteristic data to obtain the characteristic change slopes of power as the three parameters of height, temperature and speed change, and define them as height coefficient X1, temperature coefficient X2 and speed coefficient X3 respectively;

[0081] Characteristic calculation model establishment module, used to establish the standard engine height, speed, temperature power characteristic calculation model:

[0082] P=P0+H*X1+T*X2+M*X3 (1)

[0083] Wherein, P is the power of the scale engine at the calculation state point, P0 is the power value of the scale engine at the ground standard day and the Mach number is 0, H is the height of the calculation state point, T is the deviation between the temperature of the calculation state point and the standard temperature, and M is the flight Mach number of the target state;

[0084] The target demand power conversion model establishment module is used to select a state point as the scaling reference point, divide the power of the target engine and the scale engine at the scaling reference point, obtain the proportionality coefficient K, scale the characteristics according to the proportionality coefficient K, and obtain the target demand power conversion model:

[0085] Pc=Ps-H*X1*KT*X2*KM*X3*K (2)

[0086] Among them, Pc is the power value of the target required power converted to the ground standard day and the Mach number is 0, and Ps is the actual power value of the target required power;

[0087] A conversion module is used to select a target state point, substitute the target required power into the required power conversion model, and obtain the converted power, wherein the target state point is a state when the ground standard day and the Mach number is 0;

[0088] The engine design point determination module is used to select the state point with the largest converted power as the engine design point.

[0089] like Figure 3 As shown, a preferred embodiment of the present application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the aircraft demand conversion method based on engine characteristics in the above-mentioned embodiment when executing the program.

[0090] like Figure 4 As shown, the preferred embodiment of the present application also provides a computer device, which can be a terminal or a liveness detection server, and its internal structure diagram can be as shown in Figure 4As shown. The computer device includes a processor, a memory and a network interface connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with other external computer devices through a network connection. When the computer program is executed by the processor, the steps of the above-mentioned aircraft demand conversion method based on engine characteristics are implemented.

[0091] Those skilled in the art will understand that Figure 4 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components.

[0092] A preferred embodiment of the present application further provides a storage medium, which includes a stored program, and when the program is executed, controls the device where the storage medium is located to execute the steps of the aircraft demand conversion method based on engine characteristics in the above embodiment.

[0093] It can be seen that the technical solution of this application has two core focuses:

[0094] 1) Establish an engine power characteristic calculation model based on existing engines;

[0095] 2) According to the model, convert the aircraft power demand to the same state for comparison.

[0096] The present invention provides a power conversion method based on actual test characteristics of existing engines, which can more accurately evaluate the actual power capacity of the engine and can be used for engine design based on aircraft requirements.

[0097] The method of this application has been used to evaluate the engine requirements of three types of aircraft, and the maximum power requirements of the engine design have been given. The requirements are compared with the characteristics of the engine after the design scheme is completed. The results show that the results after the engine design scheme is completed are basically consistent with the evaluated converted power, proving that this method is effective.

[0098] It should be noted that the steps shown in the flowcharts of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and that, although a logical order is shown in the flowcharts, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0099] If the functions described in the method of this embodiment are implemented in the form of software functional units and sold or used as independent products, they can be stored in one or more computing devices readable storage media. Based on this understanding, the part of the embodiment of the present application that contributes to the prior art or the part of the technical solution can be embodied in the form of a software product, which is stored in a storage medium and includes several instructions to enable a computing device (which can be a personal computer, server, mobile computing device or network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present application. 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 and other media that can store program code.

[0100] Those skilled in the art will appreciate that the embodiments of the present application can be provided as methods, systems, or computer program products. Therefore, the present application can adopt the form of complete hardware embodiments, complete software embodiments, or embodiments in combination with software and hardware. Moreover, the present application can adopt the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) that contain computer-usable program code. The scheme in the embodiments of the present application can be implemented in various computer languages, for example, object-oriented programming language Java and literal scripting language JavaScript, etc.

[0101] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or box in the flowchart and / or block diagram, as well as the combination of the processes and / or boxes in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0102] These computer program instructions may also be stored in a computer readable memory capable of directing a computer or other programmable data processing device to operate in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture including an instruction device, which implements the process Figure 1 A process or multiple processes and / or boxes Figure 1A function specified in one or more boxes.

[0103] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing instructions for implementing the process in the computer or other programmable device. Figure 1 A process or multiple processes and / or boxes Figure 1 The steps for the functions specified in one or more boxes.

[0104] Although the preferred embodiments of the present application have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications falling within the scope of the present application.

[0105] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

Claims

1. A method for converting aircraft demand based on engine characteristics, characterized in that: Includes steps: S1. Obtain test data of a turboshaft turboprop engine that is similar to the target engine and has been verified by high-altitude test benches, define this type of engine as the benchmark engine, define the power demand of the aircraft as the target power demand, and define the engine that meets the target power demand as the target engine; S2. Preprocess the data to obtain the power characteristic data of the engine at different altitudes, temperatures and speeds at the same gas generator speed; S3, performing linear fitting on the power characteristic data to obtain the characteristic change slopes of power with the three parameters of height, temperature and speed, and defining them as height coefficient X1, temperature coefficient X2 and speed coefficient X3 respectively; S4. Establish a calculation model for the height, speed, and temperature power characteristics of a scale engine: P=P0+H*X1+T*X2+M*X3 (1) Wherein, P is the power of the scale engine at the calculation state point, P0 is the power value of the scale engine at the ground standard day and the Mach number is 0, H is the height of the calculation state point, T is the deviation between the temperature of the calculation state point and the standard temperature, and M is the flight Mach number of the target state; S5. Select a state point as a scaling reference point, divide the power of the target engine and the scale engine at the scaling reference point, obtain a proportionality coefficient K, scale the characteristics according to the proportionality coefficient K, and obtain a target demand power conversion model: Pc=Ps-H*X1*KT*X2*KM*X3*K (2) Among them, Pc is the power value of the target required power converted to the ground standard day and the Mach number is 0, and Ps is the actual power value of the target required power; S6. Select a target state point, substitute the target required power into the required power conversion model, and obtain the converted power, wherein the target state point is a state when the ground standard day and the Mach number is 0; S7. Select the state point with the largest converted power as the engine design point.

2. The aircraft demand conversion method based on engine characteristics according to claim 1, characterized in that: In step S1, the turboshaft turboprop engine test data includes the engine gas generator speed, power, flight altitude, speed, and temperature, wherein the engine output power should be the power without aircraft bleed air and power extraction, and the flight altitude, speed, and temperature cover the design operating envelope of the engine.

3. The aircraft demand conversion method based on engine characteristics according to claim 1, characterized in that: In step S2, the data is preprocessed, including being unified into the international system of units, and all data are retained to integer digits.

4. The aircraft demand conversion method based on engine characteristics according to claim 1, characterized in that: In step S3, a least square method is used to perform linear fitting on the power characteristic data.

5. The aircraft demand conversion method based on engine characteristics according to claim 1, characterized in that: In the step S5, the maximum take-off state point of the ground standard day is selected as the scaling reference point.

6. An aircraft demand conversion device based on engine characteristics, characterized in that: include: A test data acquisition module is used to acquire test data of a turboshaft turboprop engine that is similar to the target engine configuration and has been tested and verified on a high-altitude platform, and the engine is defined as a benchmark engine, the power demand of the aircraft is defined as a target power demand, and the engine that meets the target power demand is defined as a target engine; The data preprocessing module is used to preprocess the data, unify it into the international system of units, retain all data to integers, and obtain the power characteristic data of the engine at different altitudes, temperatures, and speeds at the same gas generator speed; A coefficient obtaining module is used to perform linear fitting on the power characteristic data to obtain the characteristic change slopes of power as the three parameters of height, temperature and speed change, and define them as height coefficient X1, temperature coefficient X2 and speed coefficient X3 respectively; The characteristic calculation model establishment module is used to establish the standard engine height, speed, temperature power characteristic calculation model, namely: P=P0+H*X1+T*X2+M*X3 (1) Wherein, P is the power of the scale engine at the calculation state point, P0 is the power value of the scale engine at the ground standard day and the Mach number is 0, H is the height of the calculation state point, T is the deviation between the temperature of the calculation state point and the standard temperature, and M is the flight Mach number of the target state; The target demand power conversion model establishment module is used to select a state point as the scaling reference point, divide the power of the target engine and the scale engine at the scaling reference point, obtain the proportionality coefficient K, scale the characteristics according to the proportionality coefficient K, and obtain the target demand power conversion model: Pc=Ps-H*X1*KT*X2*KM*X3*K (2) Among them, Pc is the power value of the target required power converted to the ground standard day and the Mach number is 0, and Ps is the actual power value of the target required power; A conversion module is used to select a target state point, substitute the target required power into the required power conversion model, and obtain the converted power, wherein the target state point is a state when the ground standard day and the Mach number is 0; The engine design point determination module is used to select the state point with the largest converted power as the engine design point.

7. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the program, the steps of the aircraft demand conversion method based on engine characteristics as described in any one of claims 1 to 5 are implemented.

8. A storage medium comprising a stored program, characterized in that: When the program is running, the device where the storage medium is located is controlled to execute the steps of the aircraft demand conversion method based on engine characteristics as described in any one of claims 1 to 5.

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