Aircraft electric propulsion method and system based on wide bandgap semiconductor

Abstract

The invention discloses an aircraft electric propulsion method and system based on a wide bandgap semiconductor, and relates to the technical field of wide bandgap semiconductors. The method comprises the steps of obtaining an aircraft electric propulsion requirement according to a flight task, constructing an electric propulsion model based on the aircraft electric propulsion requirement and wide bandgap semiconductor characteristics, and constructing an electric intelligent control propulsion system based on the electric propulsion model and a wide bandgap semiconductor. And performing a flight simulation test on the electric intelligent control propulsion system to obtain a visual flight simulation test report, and optimizing the electric intelligent control propulsion system according to the visual flight simulation test report. The characteristics of the wide bandgap semiconductor can be fully exerted, the energy utilization efficiency is remarkably improved, the aircraft can accurately execute control instructions when taking off and landing under the complex meteorological condition and high-difficulty maneuvering actions in the air, the precision and flexibility of flight operation are remarkably improved, and the flight experience of the aircraft is improved. And the aircraft can better adapt to diversified flight mission requirements.

Description

Technical Field

[0001] The present invention relates to the technical field of wide bandgap semiconductors, and in particular to an aircraft electric propulsion method and system based on wide bandgap semiconductors. Background Art

[0002] In today's aviation sector, there are many challenges in improving the performance of aircraft. Traditional electric propulsion systems use conventional semiconductor devices, which have significant limitations in terms of power density, efficiency, and adaptability to high-temperature environments. As aircraft missions become increasingly complex and diverse, higher requirements are placed on electric propulsion systems, such as higher thrust output to meet the load requirements of large aircraft, better energy efficiency to extend the range, and greater stability to adapt to harsh flight conditions. Conventional semiconductor technology has difficulty breaking through these bottlenecks, resulting in aircraft electric propulsion systems being unable to meet future aviation development trends in terms of performance. New technologies and methods are urgently needed to achieve a qualitative leap. Against this background, aircraft electric propulsion methods and systems based on wide-bandgap semiconductors have emerged. Summary of the Invention

[0003] The present invention provides an aircraft electric propulsion method based on wide bandgap semiconductors, comprising:

[0004] Step S1: The electric propulsion center obtains the electric propulsion requirements of the aircraft according to the flight mission;

[0005] Step S2: The electric propulsion center constructs an electric propulsion model based on the electric propulsion requirements of the aircraft and the characteristics of wide bandgap semiconductors;

[0006] Step S3: The electric propulsion center constructs an electric intelligent control propulsion system based on the electric propulsion model and wide bandgap semiconductors;

[0007] Step S4: The electric propulsion center performs a flight simulation test on the electric intelligent control propulsion system to obtain a visual flight simulation test report;

[0008] Step S5: The electric propulsion center optimizes the electric intelligent control propulsion system according to the visualized flight test report.

[0009] In the above-mentioned wide bandgap semiconductor-based aircraft electric propulsion method, the electric propulsion center obtains the aircraft electric propulsion requirements according to the flight mission, including the following sub-steps:

[0010] Step S11: The electric propulsion center obtains environmental information and geographic information of the mission area according to the flight mission;

[0011] Step S12: The electric propulsion center obtains specific mission information of the aircraft according to the flight mission;

[0012] Step S13: The electric propulsion center integrates and analyzes the specific mission information of the aircraft, the environmental information of the mission area, and the geographic information to generate the electric propulsion requirements of the aircraft.

[0013] In the above-mentioned aircraft electric propulsion method based on wide bandgap semiconductors, the electric propulsion center constructs an electric propulsion model based on the aircraft electric propulsion requirements and the wide bandgap semiconductor characteristics, including the following sub-steps:

[0014] Step S21: The electric propulsion center obtains electric propulsion parameters according to the electric propulsion requirements of the aircraft;

[0015] Step S22: The electric propulsion center generates energy-saving and high-efficiency electric propulsion parameters according to the wide bandgap semiconductor characteristics and the electric propulsion parameters;

[0016] Step S23: The electric propulsion center constructs an electric propulsion model according to energy-saving and high-efficiency electric propulsion parameters.

[0017] In the above-mentioned aircraft electric propulsion method based on wide bandgap semiconductors, the electric propulsion center constructs an electric intelligent control propulsion system based on the electric propulsion model and wide bandgap semiconductors, including the following sub-steps:

[0018] Step S31: The electric propulsion center constructs an intelligent control model based on the electric propulsion model and wide bandgap semiconductor characteristics;

[0019] Step S32: The electric propulsion center constructs an electric intelligent control propulsion system based on the electric propulsion model, the intelligent control model, and the wide bandgap semiconductor.

[0020] In the above-mentioned aircraft electric propulsion method based on wide bandgap semiconductors, the electric propulsion center performs a flight simulation test on the electric intelligent control propulsion system to obtain a visual flight simulation test report, which includes the following sub-steps:

[0021] Step S41: The electric propulsion center builds a simulation test environment according to the flight mission;

[0022] Step S42: The electric propulsion center performs a flight simulation test on the electric intelligent control propulsion system in a simulated test environment to obtain simulation test data;

[0023] Step S43: The electric propulsion center generates a visual flight simulation test report based on the simulation test data.

[0024] The present invention also provides an aircraft electric propulsion system based on wide bandgap semiconductors, comprising:

[0025] Aircraft electric propulsion requirement acquisition module, which obtains the aircraft electric propulsion requirement according to the flight mission;

[0026] Electric propulsion model building module, which builds an electric propulsion model based on the aircraft's electric propulsion requirements and wide-bandgap semiconductor characteristics;

[0027] Electric intelligent control propulsion system building module, which builds an electric intelligent control propulsion system based on electric propulsion model and wide bandgap semiconductors;

[0028] The electric intelligent control propulsion system simulation test module performs flight simulation tests on the electric intelligent control propulsion system and obtains visual flight simulation test reports;

[0029] The electric intelligent control propulsion system optimization module optimizes the electric intelligent control propulsion system based on the visual flight test report.

[0030] In the above-mentioned aircraft electric propulsion system based on wide bandgap semiconductors, the aircraft electric propulsion requirement acquisition module specifically includes:

[0031] The environmental information and geographic information acquisition submodule obtains the environmental information and geographic information of the mission area according to the flight mission;

[0032] The specific mission information acquisition submodule obtains the specific mission information of the aircraft according to the flight mission;

[0033] The electric propulsion requirement generation submodule integrates and analyzes the specific mission information of the aircraft, the environmental information of the mission area, and the geographic information to generate the electric propulsion requirements of the aircraft.

[0034] In the above-mentioned aircraft electric propulsion system based on wide bandgap semiconductors, the electric propulsion model construction module specifically includes:

[0035] The electric propulsion parameter acquisition submodule obtains the electric propulsion parameters according to the electric propulsion requirements of the aircraft;

[0036] Energy-saving and high-efficiency electric propulsion parameter generation submodule, which generates energy-saving and high-efficiency electric propulsion parameters based on wide bandgap semiconductor characteristics and electric propulsion parameters;

[0037] The electric propulsion model construction submodule constructs the electric propulsion model based on energy-saving and efficient electric propulsion parameters.

[0038] In the above-mentioned aircraft electric propulsion system based on wide bandgap semiconductors, the electric intelligent control propulsion system building module specifically includes:

[0039] Intelligent control model construction submodule, which builds an intelligent control model based on the electric propulsion model and wide bandgap semiconductor characteristics;

[0040] The electric intelligent control propulsion system construction sub-module constructs the electric intelligent control propulsion system based on the electric propulsion model, intelligent control model and wide bandgap semiconductors.

[0041] In the above-mentioned aircraft electric propulsion system based on wide bandgap semiconductors, the electric intelligent control propulsion system simulation test module specifically includes:

[0042] The simulation test environment construction submodule builds a simulation test environment according to the flight mission;

[0043] The simulation test data acquisition submodule performs flight simulation tests on the electric intelligent control propulsion system in a simulation test environment to obtain simulation test data;

[0044] The visual flight simulation test report generation submodule generates a visual flight simulation test report based on the simulation test data.

[0045] The present invention achieves the following beneficial effects: It fully leverages the properties of wide-bandgap semiconductors, significantly improving energy efficiency. It also enables aircraft to accurately execute control commands during takeoff and landing in complex weather conditions and difficult aerial maneuvers, significantly improving the accuracy and flexibility of flight operations and enabling aircraft to better adapt to diverse flight mission requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments described in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0047] Figure 1 This is a flow chart of an aircraft electric propulsion method based on wide bandgap semiconductors provided in Example 1 of the present application;

[0048] Figure 2 This is a schematic diagram of an aircraft electric propulsion system based on wide bandgap semiconductors provided in Example 2 of the present application. DETAILED DESCRIPTION

[0049] The following is a clear and complete description of the technical solutions in the embodiments of the present invention, in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0050] Example 1

[0051] like Figure 1 As shown, the first embodiment of the present application provides an aircraft electric propulsion method based on wide bandgap semiconductors, the method comprising the following steps:

[0052] Step S1: The electric propulsion center obtains the electric propulsion requirements of the aircraft according to the flight mission;

[0053] Furthermore, the electric propulsion center obtains the electric propulsion requirements of the aircraft according to the flight mission, including the following sub-steps:

[0054] Step S11: The electric propulsion center obtains environmental information and geographic information of the mission area according to the flight mission;

[0055] Specifically, the mission area in which the aircraft performs the flight mission is obtained according to the flight mission, and the environmental information of the mission area is collected through the environmental sensors carried by the aircraft. The environmental sensors include but are not limited to temperature sensors, humidity sensors, pressure sensors, and magnetic field sensors. The geographic information of the mission area is obtained through geographic environment information collection tools such as GPS and optical cameras.

[0056] Step S12: The electric propulsion center obtains specific mission information of the aircraft according to the flight mission;

[0057] Specifically, the specific mission information of the aircraft includes but is not limited to mission type, mission objective, mission route range, mission time requirement, and mission constraints.

[0058] Step S13: The electric propulsion center integrates and analyzes the specific mission information of the aircraft, the environmental information of the mission area, and the geographical information to generate the electric propulsion requirements of the aircraft.

[0059] Specifically, the specific mission information of the aircraft, the environmental information of the mission area and the geographic information are integrated and analyzed to extract the flight requirements of each flight phase of the aircraft during take-off, ascent, cruising, trajectory change, maneuvering flight, descent and landing. According to the flight requirements of each flight phase, the thrust control requirements, flight attitude control requirements, orbit control requirements and other aircraft electric propulsion requirements for each flight phase are generated.

[0060] Step S2: The electric propulsion center constructs an electric propulsion model based on the electric propulsion requirements of the aircraft and the characteristics of wide bandgap semiconductors;

[0061] Furthermore, the Electric Propulsion Center constructs an electric propulsion model based on the aircraft electric propulsion requirements and wide bandgap semiconductor characteristics, including the following sub-steps:

[0062] Step S21: The electric propulsion center obtains electric propulsion parameters according to the electric propulsion requirements of the aircraft;

[0063] Specifically, electric propulsion parameters for each flight phase are generated according to the electric propulsion requirements of the aircraft in each flight phase. The electric propulsion parameters include but are not limited to performance parameters, electrical parameters, thermal management parameters, mechanical parameters, dynamic response parameters, and reliability parameters.

[0064] Step S22: The electric propulsion center generates energy-saving and high-efficiency electric propulsion parameters according to the wide bandgap semiconductor characteristics and the electric propulsion parameters;

[0065] Specifically, the characteristic parameters of the wide bandgap semiconductor are obtained according to the characteristics of the wide bandgap semiconductor, and the electric propulsion optimization formula is used according to the characteristic parameters of the wide bandgap semiconductor and the electric propulsion parameters. Obtain the energy-saving and efficient electric propulsion parameters of the aircraft, where DTC is the energy-saving and efficient electric propulsion parameter, n is the number of flight phases of the aircraft, im is the number of electric propulsion parameters in the i-th flight phase, ijR is the number of sub-parameters of the j-th electric propulsion parameter in the i-th flight phase, μ ijr is the weight coefficient of the rth sub-parameter of the jth electric propulsion parameter in the i-th flight phase, dc ijr is the rth sub-parameter value of the jth electric propulsion parameter in the i-th flight phase, ijrT is the number of wide bandgap semiconductor optimized characteristic parameters of the rth sub-parameter of the jth electric propulsion parameter in the i-th flight phase, α ijrt kt is the weight coefficient of the t-th wide bandgap semiconductor optimized characteristic parameter of the r-th sub-parameter of the j-th electric propulsion parameter in the i-th flight phase, ijrt is the optimized characteristic parameter value of the t-th wide bandgap semiconductor of the r-th sub-parameter of the j-th electric propulsion parameter in the i-th flight phase, yh ijr is the rth sub-parameter optimization factor of the jth electric propulsion parameter in the i-th flight phase.

[0066] Step S23: The electric propulsion center constructs an electric propulsion model according to energy-saving and high-efficiency electric propulsion parameters;

[0067] Specifically, the flight control optimization parameters DTC are generated based on the energy-saving and efficient electric propulsion parameters DTC kt , Energy Optimization Parameters DTC nt and power optimization parameters DTC dt , building algorithms through electric propulsion models Construct an electric propulsion model, where DJM is the electric propulsion model, α1 is the connection weight coefficient between the electric propulsion model and the flight control system, dk is the connection factor between the electric propulsion model and the flight control system, n is the number of flight control optimization parameters, i ranges from [1, n], and fk i is the i-th initial flight control parameter, is the i-th flight control optimization parameter, α2 is the connection weight coefficient between the electric propulsion model and the energy system, dn is the connection factor between the electric propulsion model and the energy system, m is the number of energy optimization parameters, j ranges from [1, m], ny j is the jth initial energy parameter, is the jth energy optimization parameter, RC(DTC dt ) is the electric propulsion model fusion function based on power optimization parameters.

[0068] Step S3: The electric propulsion center constructs an electric intelligent control propulsion system based on the electric propulsion model and wide bandgap semiconductors;

[0069] Furthermore, the Electric Propulsion Center constructs an electric intelligent control propulsion system based on the electric propulsion model and wide bandgap semiconductors, including the following sub-steps:

[0070] Step S31: The electric propulsion center constructs an intelligent control model based on the electric propulsion model and wide bandgap semiconductor characteristics;

[0071] Specifically, the electric propulsion model DJM is used to obtain the electric propulsion data of the aircraft under various working conditions, and the algorithm is adjusted through intelligent control. Get the intelligent control adjustment value of the electric propulsion data of the aircraft under different constraints, where ZKZ is the intelligent control adjustment value, G is the number of electric propulsion data, and ls g is the g-th electric propulsion data value, tz g is the constraint control adjustment coefficient of the g-th electric propulsion data, gT is the number of environmental constraint adjustment factors of the g-th electric propulsion data, α gt is the weight of the t-th environmental constraint adjustment factor of the g-th electric propulsion data, hj gt is the tth environmental constraint adjustment factor for the gth electric propulsion data, hy gt is the control adjustment index of the t-th environmental constraint adjustment factor of the g-th electric propulsion data, gQ is the number of flight mission constraint adjustment factors of the g-th electric propulsion data, β gq is the weight of the qth mission constraint adjustment factor for the gth electric propulsion data, gr gq is the qth mission constraint adjustment factor for the gth electric propulsion data, gy gq is the control adjustment index of the qth mission constraint adjustment factor of the gth electric propulsion data, gR is the number of wide bandgap semiconductor characteristic constraint adjustment factors of the gth electric propulsion data, δ gr is the weight of the rth wide bandgap semiconductor characteristic constraint adjustment factor for the gth electric propulsion data, tx gr is the rth wide bandgap semiconductor characteristic constraint adjustment factor for the gth electric propulsion data, tygr is the control adjustment index of the rth wide bandgap semiconductor characteristic constraint adjustment factor for the gth electric propulsion data.

[0072] An intelligent control adjustment value dataset is constructed based on the intelligent control adjustment value ZKZ of electric propulsion data under various constraint conditions, and an intelligent control model is constructed based on the intelligent adjustment value dataset using machine learning technology.

[0073] Step S32: The electric propulsion center constructs an electric intelligent control propulsion system based on the electric propulsion model, the intelligent control model, and the wide bandgap semiconductor;

[0074] Specifically, the electric propulsion model, intelligent control model and wide bandgap semiconductors are deeply integrated to construct an electric intelligent control propulsion system, and the electric intelligent control propulsion system is connected with the aircraft's power system, flight control system, energy system and other aircraft onboard systems, so that the electric intelligent control propulsion system can be deployed on the aircraft.

[0075] Step S4: The electric propulsion center performs a flight simulation test on the electric intelligent control propulsion system to obtain a visual flight simulation test report;

[0076] Furthermore, the electric propulsion center performs a flight simulation test on the electric intelligent control propulsion system to obtain a visual flight simulation test report, which includes the following sub-steps:

[0077] Step S41: The electric propulsion center builds a simulation test environment according to the flight mission;

[0078] Specifically, the relevant mission environment of the aircraft when performing the flight mission is obtained according to the flight mission, and a simulation test environment is constructed through three-dimensional modeling and virtual reality technology to accurately reproduce the flight environment such as high altitude, low temperature, low pressure, and complex airflow. For example, the execution environment of the corresponding mission is simulated according to the type of flight mission, different meteorological conditions are simulated according to the route of the flight mission, and the endurance pressure is simulated according to the mission duration.

[0079] Step S42: The electric propulsion center performs a flight simulation test on the electric intelligent control propulsion system in a simulated test environment to obtain simulation test data;

[0080] Specifically, the aircraft's electric intelligent control propulsion system is connected to a simulation test environment to simulate flight processes such as takeoff, cruising, and landing, and different flight constraints and environmental conditions are added in real time during the flight. Through various high-precision sensors, key indicators such as the electric intelligent control propulsion system's thrust output, motor speed, energy consumption, and dynamic switching loss are monitored in all directions to obtain detailed simulation test data.

[0081] Step S43: The electric propulsion center generates a visual flight simulation test report based on the simulation test data;

[0082] Specifically, the simulation test data is deeply analyzed, and line graphs are selected according to the characteristics of the data to show the trend of parameter changes over time. Bar graphs are used to compare performance indicators at different stages. Combined with the flight mission objectives, the performance of the electric intelligent control propulsion system is evaluated, and the system's strengths and weaknesses are presented in the report, accompanied by intuitive charts, to generate a highly visual and detailed flight simulation test report.

[0083] Step S5: The electric propulsion center optimizes the electric intelligent control propulsion system according to the visual flight test report;

[0084] Specifically, we conduct in-depth analysis of the visual flight test report to identify the performance shortcomings presented in the report. Based on the data trends and performance shortcomings in the report, we make targeted improvements to key components and conduct multiple rounds of testing and optimization to improve the overall performance of the electric intelligent control propulsion system.

[0085] Example 2

[0086] like Figure 2 As shown, the second embodiment of the present application provides an aircraft electric propulsion system based on wide bandgap semiconductors, including:

[0087] An aircraft electric propulsion requirement acquisition module 21 acquires the aircraft electric propulsion requirement according to the flight mission;

[0088] Furthermore, the aircraft electric propulsion requirement acquisition module 21 includes the following submodules:

[0089] The environmental information and geographic information acquisition submodule obtains the environmental information and geographic information of the mission area according to the flight mission;

[0090] Specifically, the mission area in which the aircraft performs the flight mission is obtained according to the flight mission, and the environmental information of the mission area is collected through the environmental sensors carried by the aircraft. The environmental sensors include but are not limited to temperature sensors, humidity sensors, pressure sensors, and magnetic field sensors. The geographic information of the mission area is obtained through geographic environment information collection tools such as GPS and optical cameras.

[0091] The specific mission information acquisition submodule obtains the specific mission information of the aircraft according to the flight mission;

[0092] Specifically, the specific mission information of the aircraft includes but is not limited to mission type, mission objective, mission route range, mission time requirement, and mission constraints.

[0093] The electric propulsion requirement generation submodule integrates and analyzes the specific mission information of the aircraft, the environmental information of the mission area, and the geographic information to generate the electric propulsion requirements of the aircraft;

[0094] Specifically, the specific mission information of the aircraft, the environmental information of the mission area and the geographic information are integrated and analyzed to extract the flight requirements of each flight phase of the aircraft during take-off, ascent, cruising, trajectory change, maneuvering flight, descent and landing. According to the flight requirements of each flight phase, the thrust control requirements, flight attitude control requirements, orbit control requirements and other aircraft electric propulsion requirements for each flight phase are generated.

[0095] An electric propulsion model building module 22 builds an electric propulsion model based on the electric propulsion requirements of the aircraft and the characteristics of wide bandgap semiconductors;

[0096] Furthermore, the electric propulsion model building module 22 includes the following submodules:

[0097] The electric propulsion parameter acquisition submodule obtains the electric propulsion parameters according to the electric propulsion requirements of the aircraft;

[0098] Specifically, electric propulsion parameters for each flight phase are generated according to the electric propulsion requirements of the aircraft in each flight phase. The electric propulsion parameters include but are not limited to performance parameters, electrical parameters, thermal management parameters, mechanical parameters, dynamic response parameters, and reliability parameters.

[0099] Energy-saving and high-efficiency electric propulsion parameter generation submodule, which generates energy-saving and high-efficiency electric propulsion parameters based on wide bandgap semiconductor characteristics and electric propulsion parameters;

[0100] Specifically, the characteristic parameters of the wide bandgap semiconductor are obtained according to the characteristics of the wide bandgap semiconductor, and the electric propulsion optimization formula is used according to the characteristic parameters of the wide bandgap semiconductor and the electric propulsion parameters. Obtain the energy-saving and efficient electric propulsion parameters of the aircraft, where DTC is the energy-saving and efficient electric propulsion parameter, n is the number of flight phases of the aircraft, im is the number of electric propulsion parameters in the i-th flight phase, ijR is the number of sub-parameters of the j-th electric propulsion parameter in the i-th flight phase, μ ijr is the weight coefficient of the rth sub-parameter of the jth electric propulsion parameter in the i-th flight phase, dc ijr is the rth sub-parameter value of the jth electric propulsion parameter in the i-th flight phase, ijrT is the number of wide bandgap semiconductor optimized characteristic parameters of the rth sub-parameter of the jth electric propulsion parameter in the i-th flight phase, α ijrt kt is the weight coefficient of the t-th wide bandgap semiconductor optimized characteristic parameter of the r-th sub-parameter of the j-th electric propulsion parameter in the i-th flight phase, ijrt is the optimized characteristic parameter value of the t-th wide bandgap semiconductor of the r-th sub-parameter of the j-th electric propulsion parameter in the i-th flight phase, yh ijr is the rth sub-parameter optimization factor of the jth electric propulsion parameter in the i-th flight phase.

[0101] The electric propulsion model construction submodule constructs the electric propulsion model based on energy-saving and efficient electric propulsion parameters;

[0102] Specifically, the flight control optimization parameters DTC are generated based on the energy-saving and efficient electric propulsion parameters DTC kt , Energy Optimization Parameters DTC nt and power optimization parameters DTC dt , building algorithms through electric propulsion models Construct an electric propulsion model, where DJM is the electric propulsion model, α1 is the connection weight coefficient between the electric propulsion model and the flight control system, dk is the connection factor between the electric propulsion model and the flight control system, n is the number of flight control optimization parameters, i ranges from [1, n], and fk i is the i-th initial flight control parameter, is the i-th flight control optimization parameter, α2 is the connection weight coefficient between the electric propulsion model and the energy system, dn is the connection factor between the electric propulsion model and the energy system, m is the number of energy optimization parameters, j ranges from [1, m], ny j is the jth initial energy parameter, is the jth energy optimization parameter, RC(DTC dt ) is the electric propulsion model fusion function based on power optimization parameters.

[0103] Electric intelligent control propulsion system construction module 23, constructing an electric intelligent control propulsion system based on an electric propulsion model and wide bandgap semiconductors;

[0104] Furthermore, the electric intelligent control propulsion system building module 23 includes the following submodules:

[0105] Intelligent control model construction submodule, which builds an intelligent control model based on the electric propulsion model and wide bandgap semiconductor characteristics;

[0106] Specifically, the electric propulsion model DJM is used to obtain the electric propulsion data of the aircraft under various working conditions, and the algorithm is adjusted through intelligent control. Get the intelligent control adjustment value of the electric propulsion data of the aircraft under different constraints, where ZKZ is the intelligent control adjustment value, G is the number of electric propulsion data, and ls g is the g-th electric propulsion data value, tz g is the constraint control adjustment coefficient of the g-th electric propulsion data, gT is the number of environmental constraint adjustment factors of the g-th electric propulsion data, α gt is the weight of the t-th environmental constraint adjustment factor of the g-th electric propulsion data, hj gt is the tth environmental constraint adjustment factor for the gth electric propulsion data, hy gtis the control adjustment index of the t-th environmental constraint adjustment factor of the g-th electric propulsion data, gQ is the number of flight mission constraint adjustment factors of the g-th electric propulsion data, β gq is the weight of the qth mission constraint adjustment factor for the gth electric propulsion data, gr gq is the qth mission constraint adjustment factor for the gth electric propulsion data, gy gq is the control adjustment index of the qth mission constraint adjustment factor of the gth electric propulsion data, gR is the number of wide bandgap semiconductor characteristic constraint adjustment factors of the gth electric propulsion data, δ gr is the weight of the rth wide bandgap semiconductor characteristic constraint adjustment factor for the gth electric propulsion data, tx gr is the rth wide bandgap semiconductor characteristic constraint adjustment factor for the gth electric propulsion data, ty gr is the control adjustment index of the rth wide bandgap semiconductor characteristic constraint adjustment factor for the gth electric propulsion data.

[0107] An intelligent control adjustment value dataset is constructed based on the intelligent control adjustment value ZKZ of electric propulsion data under various constraint conditions, and an intelligent control model is constructed based on the intelligent adjustment value dataset using machine learning technology.

[0108] The electric intelligent control propulsion system construction submodule builds the electric intelligent control propulsion system based on the electric propulsion model, intelligent control model and wide bandgap semiconductors;

[0109] Specifically, the electric propulsion model, intelligent control model and wide bandgap semiconductors are deeply integrated to construct an electric intelligent control propulsion system, and the electric intelligent control propulsion system is connected with the aircraft's power system, flight control system, energy system and other aircraft onboard systems, so that the electric intelligent control propulsion system can be deployed on the aircraft.

[0110] The electric intelligent control propulsion system simulation test module 24 performs a flight simulation test on the electric intelligent control propulsion system to obtain a visual flight simulation test report;

[0111] Furthermore, the electric intelligent control propulsion system simulation test module 24 includes the following submodules:

[0112] The simulation test environment construction submodule builds a simulation test environment according to the flight mission;

[0113] Specifically, the relevant mission environment of the aircraft when performing the flight mission is obtained according to the flight mission, and a simulation test environment is constructed through three-dimensional modeling and virtual reality technology to accurately reproduce the flight environment such as high altitude, low temperature, low pressure, and complex airflow. For example, the execution environment of the corresponding mission is simulated according to the type of flight mission, different meteorological conditions are simulated according to the route of the flight mission, and the endurance pressure is simulated according to the mission duration.

[0114] The simulation test data acquisition submodule performs flight simulation tests on the electric intelligent control propulsion system in a simulation test environment to obtain simulation test data;

[0115] Specifically, the aircraft's electric intelligent control propulsion system is connected to a simulation test environment to simulate flight processes such as takeoff, cruising, and landing, and different flight constraints and environmental conditions are added in real time during the flight. Through various high-precision sensors, key indicators such as the electric intelligent control propulsion system's thrust output, motor speed, energy consumption, and dynamic switching loss are monitored in all directions to obtain detailed simulation test data.

[0116] Visual flight simulation test report generation submodule generates a visual flight simulation test report based on simulation test data;

[0117] Specifically, the simulation test data is deeply analyzed, and line graphs are selected according to the characteristics of the data to show the trend of parameter changes over time. Bar graphs are used to compare performance indicators at different stages. Combined with the flight mission objectives, the performance of the electric intelligent control propulsion system is evaluated, and the system's strengths and weaknesses are presented in the report, accompanied by intuitive charts, to generate a highly visual and detailed flight simulation test report.

[0118] An electric intelligent control propulsion system optimization module 25 is used to optimize the electric intelligent control propulsion system according to the visual flight test report;

[0119] Specifically, we conduct in-depth analysis of the visual flight test report to identify the performance shortcomings presented in the report. Based on the data trends and performance shortcomings in the report, we make targeted improvements to key components and conduct multiple rounds of testing and optimization to improve the overall performance of the electric intelligent control propulsion system.

[0120] Corresponding to the above embodiment, an embodiment of the present invention provides a computer storage medium, comprising: at least one memory and at least one processor;

[0121] The memory is used to store one or more program instructions;

[0122] A processor is used for running one or more program instructions to implement an aircraft electric propulsion method based on wide bandgap semiconductors.

[0123] Corresponding to the above embodiments, an embodiment of the present invention provides a computer-readable storage medium, which contains one or more program instructions, and the one or more program instructions are used by a processor to execute a method for implementing a simulated management port of an industrial control firewall without a hardware management port.

[0124] The embodiments disclosed in the present invention provide a computer-readable storage medium, in which computer program instructions are stored. When the computer program instructions are executed on a computer, the computer executes the above-mentioned method for implementing a simulated management port of an industrial control firewall without a hardware management port.

[0125] In the embodiments of the present invention, the processor may be an integrated circuit chip having signal processing capabilities. The processor may be a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field programmable gate array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components.

[0126] The methods, steps, and logic diagrams disclosed in the embodiments of the present invention can be implemented or executed. A general-purpose processor can be a microprocessor or any conventional processor. The steps of the methods disclosed in the embodiments of the present invention can be directly implemented and executed by a hardware decoding processor, or by a combination of hardware and software modules within the decoding processor. The software modules can be located in a storage medium well-established in the art, such as random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, or registers. The processor reads the information from the storage medium and, in conjunction with its hardware, completes the steps of the aforementioned methods.

[0127] The storage medium may be a memory and may be, for example, a volatile memory or a nonvolatile memory, or may include both volatile and nonvolatile memory.

[0128] Among them, the non-volatile memory can be a read-only memory (ROM), a programmable read-only memory (PROM), an erasable programmable read-only memory (EPROM), an electrically erasable programmable read-only memory (EEPROM), or a flash memory.

[0129] Volatile memory may be random access memory (RAM), which is used as an external cache memory. By way of example and not limitation, many forms of RAM are available, such as static random access memory (SRAM), dynamic random access memory (DRAM), synchronous dynamic random access memory (SDRAM), double data rate synchronous dynamic random access memory (DDRSDRAM), enhanced synchronous dynamic random access memory (ESDRAM), synchronous link dynamic random access memory (SLDRAM), and direct RAM bus random access memory (DRRAM).

[0130] The storage media described in the embodiments of the present invention are intended to include, but are not limited to, these and any other suitable types of memory.

[0131] Those skilled in the art will appreciate that in one or more of the above examples, the functions described herein can be implemented using a combination of hardware and software. When software is used, the corresponding functions can be stored in a computer-readable medium or transmitted as one or more instructions or codes on a computer-readable medium. Computer-readable media include computer storage media and communication media, wherein communication media includes any medium that facilitates the transmission of computer programs from one place to another. The storage medium can be any available medium that can be accessed by a general-purpose or special-purpose computer.

[0132] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent replacements, improvements, etc. made on the basis of the technical solution of the present invention should be included in the scope of protection of the present invention.

Claims

1. A method for electric propulsion of an aircraft based on wide bandgap semiconductors, characterized in that: include: Step S1: The electric propulsion center obtains the electric propulsion requirements of the aircraft according to the flight mission; Step S2: The electric propulsion center constructs an electric propulsion model based on the electric propulsion requirements of the aircraft and the characteristics of wide bandgap semiconductors; Step S3: The electric propulsion center constructs an electric intelligent control propulsion system based on the electric propulsion model and wide bandgap semiconductors; Step S4: The electric propulsion center performs a flight simulation test on the electric intelligent control propulsion system to obtain a visual flight simulation test report; Step S5: The electric propulsion center optimizes the electric intelligent control propulsion system according to the visualized flight test report.

2. The aircraft electric propulsion method based on wide bandgap semiconductors according to claim 1, characterized in that: The electric propulsion center obtains the electric propulsion requirements of the aircraft based on the flight mission, including the following sub-steps: Step S11: The electric propulsion center obtains environmental information and geographic information of the mission area according to the flight mission; Step S12: The electric propulsion center obtains specific mission information of the aircraft according to the flight mission; Step S13: The electric propulsion center integrates and analyzes the specific mission information of the aircraft, the environmental information of the mission area, and the geographic information to generate the electric propulsion requirements of the aircraft.

3. The aircraft electric propulsion method based on wide bandgap semiconductors according to claim 1, characterized in that: The Electric Propulsion Center builds an electric propulsion model based on the aircraft's electric propulsion requirements and the characteristics of wide-bandgap semiconductors, including the following sub-steps: Step S21: The electric propulsion center obtains electric propulsion parameters according to the electric propulsion requirements of the aircraft; Step S22: The electric propulsion center generates energy-saving and high-efficiency electric propulsion parameters according to the wide bandgap semiconductor characteristics and the electric propulsion parameters; Step S23: The electric propulsion center constructs an electric propulsion model according to energy-saving and high-efficiency electric propulsion parameters.

4. The aircraft electric propulsion method based on wide bandgap semiconductors according to claim 1, characterized in that: The Electric Propulsion Center builds an electric intelligent control propulsion system based on the electric propulsion model and wide bandgap semiconductors, including the following sub-steps: Step S31: The electric propulsion center constructs an intelligent control model based on the electric propulsion model and wide bandgap semiconductor characteristics; Step S32: The electric propulsion center constructs an electric intelligent control propulsion system based on the electric propulsion model, the intelligent control model, and the wide bandgap semiconductor.

5. The aircraft electric propulsion method based on wide bandgap semiconductors according to claim 1, characterized in that: The Electric Propulsion Center conducts flight simulation tests on the electric intelligent control propulsion system to obtain a visual flight simulation test report, which includes the following sub-steps: Step S41: The electric propulsion center builds a simulation test environment according to the flight mission; Step S42: The electric propulsion center performs a flight simulation test on the electric intelligent control propulsion system in a simulated test environment to obtain simulation test data; Step S43: The electric propulsion center generates a visual flight simulation test report based on the simulation test data.

6. An aircraft electric propulsion system based on wide bandgap semiconductors, characterized in that: include: Aircraft electric propulsion requirement acquisition module, which obtains the aircraft electric propulsion requirement according to the flight mission; Electric propulsion model building module, which builds an electric propulsion model based on the aircraft's electric propulsion requirements and wide-bandgap semiconductor characteristics; Electric intelligent control propulsion system building module, which builds an electric intelligent control propulsion system based on electric propulsion model and wide bandgap semiconductors; The electric intelligent control propulsion system simulation test module performs flight simulation tests on the electric intelligent control propulsion system and obtains visual flight simulation test reports; The electric intelligent control propulsion system optimization module optimizes the electric intelligent control propulsion system based on the visual flight test report.

7. The aircraft electric propulsion system based on wide bandgap semiconductors according to claim 6, characterized in that: Aircraft electric propulsion requirements acquisition module, specifically including: The environmental information and geographic information acquisition submodule obtains the environmental information and geographic information of the mission area according to the flight mission; The specific mission information acquisition submodule obtains the specific mission information of the aircraft according to the flight mission; The electric propulsion requirement generation submodule integrates and analyzes the specific mission information of the aircraft, the environmental information of the mission area, and the geographic information to generate the electric propulsion requirements of the aircraft.

8. The aircraft electric propulsion system based on wide bandgap semiconductors according to claim 6, characterized in that: Electric propulsion model building modules, including: The electric propulsion parameter acquisition submodule obtains the electric propulsion parameters according to the electric propulsion requirements of the aircraft; Energy-saving and high-efficiency electric propulsion parameter generation submodule, which generates energy-saving and high-efficiency electric propulsion parameters based on wide bandgap semiconductor characteristics and electric propulsion parameters; The electric propulsion model construction submodule constructs the electric propulsion model based on energy-saving and efficient electric propulsion parameters.

9. The aircraft electric propulsion system based on wide bandgap semiconductors according to claim 6, characterized in that: The building blocks of the electric intelligent control propulsion system include: Intelligent control model construction submodule, which builds an intelligent control model based on the electric propulsion model and wide bandgap semiconductor characteristics; The electric intelligent control propulsion system construction sub-module constructs the electric intelligent control propulsion system based on the electric propulsion model, intelligent control model and wide bandgap semiconductors.

10. The aircraft electric propulsion system based on wide bandgap semiconductors according to claim 6, characterized in that: The electric intelligent control propulsion system simulation test module includes: The simulation test environment construction submodule builds a simulation test environment according to the flight mission; The simulation test data acquisition submodule performs flight simulation tests on the electric intelligent control propulsion system in a simulation test environment to obtain simulation test data; The visual flight simulation test report generation submodule generates a visual flight simulation test report based on the simulation test data.

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