Motor power determination method and device for electric fixed-wing unmanned transport plane

Abstract

The invention belongs to the technical field of aircraft system design, and relates to a motor power determination method and device for an electric fixed-wing unmanned transport plane. The method comprises the following steps: S1, determining a weight coefficient of a battery; s2, calculating the maximum weight and the wing area of the aircraft; and S3, first motor power is calculated according to the lift limit constraint, second motor power is calculated according to the take-off and lift gradient standard of the single-motor failure aircraft, third motor power is calculated according to the take-off ground takeoff distance, and the maximum value of the first motor power, the second motor power and the third motor power is selected as final motor power. According to the method, the motor top-layer parameter calculation time of aircraft system design is shortened, and the top-layer parameter iteration speed is increased.

Description

Technical Field

[0001] This application belongs to the field of aircraft system design technology, and specifically relates to a method and apparatus for determining the motor power of an electric fixed-wing unmanned transport aircraft. Background Technology

[0002] Unmanned transport aircraft are a core technology supporting the future low-altitude economy and the development of the logistics industry. Compared to traditional fuel-powered aircraft, electric aircraft are pollution-free and have advantages such as low noise, simple aerodynamic shape, high aerodynamic efficiency, good handling performance, and high reliability. Compared to electric rotorcraft, electric fixed-wing aircraft have the advantages of high speed, high efficiency, and good economy. Current top-level parameter design methods for transport aircraft are only applicable to traditional fuel-powered aircraft and cannot be applied to the top-level parameter design of electric fixed-wing unmanned transport aircraft. Summary of the Invention

[0003] To address the aforementioned issues, this application provides a method and apparatus for determining the motor power of an electric fixed-wing unmanned transport aircraft, providing technical support for the top-level parameter design of the electric fixed-wing unmanned transport aircraft.

[0004] The first aspect of this application provides a method for determining the motor power of an electric fixed-wing unmanned transport aircraft, mainly including:

[0005] Step S1: Determine the weight coefficient of the battery;

[0006] Step S2: Calculate the maximum weight and wing area of ​​the aircraft;

[0007] Step S3: Calculate the first motor power based on the service ceiling constraint, calculate the second motor power based on the takeoff climb gradient standard for aircraft with a single motor failure, calculate the third motor power based on the takeoff ground taxi distance, and select the maximum value among the first motor power, the second motor power, and the third motor power as the final motor power.

[0008] Preferably, step S1 further includes:

[0009] Step S11: Obtain the input performance indicators, including range. With cruising speed ;

[0010] Step S12: Calculate the battery's weight coefficient according to the following formula. :

[0011] ;

[0012] in, The lift-to-drag ratio during cruise. For the energy density of the battery, For the design margin factor, The efficiency of the propeller in cruise mode. This refers to the efficiency of the motor.

[0013] Preferably, in step S2, the maximum weight W of the aircraft is calculated using the following formula:

[0014] ;

[0015] in, For commercial purposes, This is the empty weight factor of the aircraft.

[0016] Preferably, step S2 further includes:

[0017] Step S21: Calculate cruise speed pressure ;

[0018] Step S22: Calculate the wing area S using the following formula:

[0019] ;

[0020] in, The lift coefficient is used for cruise.

[0021] Preferably, in step S21, the cruise pressure is calculated using the following formula:

[0022] ;

[0023] in, This refers to atmospheric density.

[0024] Preferably, in step S3, the power of the first motor is calculated according to the following formula. :

[0025] ;

[0026] in, The cruising speed of an aircraft at its service ceiling. Number of engines;

[0027] ;

[0028] in, This refers to the atmospheric density at the service ceiling.

[0029] Preferably, in step S3, the power of the second motor is calculated according to the following formula. :

[0030] ;

[0031] in, The standard specifies the aircraft takeoff climb gradient constraint in the event of a single motor failure. This represents the lift-to-drag ratio corresponding to the aircraft's angle of attack at takeoff. This refers to the aircraft's takeoff speed.

[0032] ;

[0033] in, This represents the maximum lift coefficient for the aircraft's takeoff configuration.

[0034] Preferably, in step S3, the power of the third motor is calculated according to the following formula. :

[0035] ;

[0036] in, The thrust-to-weight ratio required for takeoff;

[0037] ;

[0038] in, ;

[0039] ;

[0040] in, This refers to the ground takeoff distance of an aircraft. Let be the coefficient of friction of the tire, and assume the angle of attack on the ground is 0°. The drag coefficient at zero angle of attack. The lift coefficient is zero angle of attack.

[0041] The second aspect of this application provides a device for determining the motor power of an electric fixed-wing unmanned transport aircraft, mainly comprising:

[0042] Battery weight coefficient determination module, used to determine the weight coefficient of the battery;

[0043] The aircraft weight and wing area determination module is used to calculate the maximum weight and wing area of ​​the aircraft.

[0044] The motor power determination module is used to calculate the first motor power based on the service ceiling constraint, the second motor power based on the takeoff climb gradient standard of an aircraft with a single motor failure, and the third motor power based on the takeoff ground taxi distance. The maximum value among the first motor power, the second motor power, and the third motor power is selected as the final motor power.

[0045] Preferably, the battery weight coefficient determination module includes:

[0046] Performance indicator acquisition unit, used to acquire input performance indicators, including range With cruising speed ;

[0047] The weight factor calculation unit is used to calculate the battery's weight factor according to the following formula. :

[0048] ;

[0049] in, The lift-to-drag ratio during cruise. For the energy density of the battery, For the design margin factor, The efficiency of the propeller in cruise mode. This refers to the efficiency of the motor.

[0050] Preferably, the aircraft weight and wing area determination module includes:

[0051] The maximum weight calculation unit is used to calculate the aircraft's maximum weight W using the following formula:

[0052] ;

[0053] in, For commercial purposes, This is the empty weight factor of the aircraft.

[0054] Preferably, the aircraft weight and wing area determination module includes:

[0055] Cruise pressure calculation unit, used to calculate cruise pressure ;

[0056] The wing area calculation unit is used to calculate the wing area S using the following formula:

[0057] ;

[0058] in, The lift coefficient is used for cruise.

[0059] Preferably, the cruise pressure is calculated in the cruise pressure calculation unit using the following formula:

[0060] ;

[0061] in, This refers to atmospheric density.

[0062] Preferably, the motor power determination module includes a first motor power calculation unit, used to calculate the first motor power according to the following formula. :

[0063] ;

[0064] in, The cruising speed of an aircraft at its service ceiling. Number of engines;

[0065] ;

[0066] in, This refers to the atmospheric density at the service ceiling.

[0067] Preferably, the motor power determination module includes a second motor power calculation unit, used to calculate the second motor power according to the following formula. :

[0068] ;

[0069] in, The standard specifies the aircraft takeoff climb gradient constraint in the event of a single motor failure. This represents the lift-to-drag ratio corresponding to the aircraft's angle of attack at takeoff. This refers to the aircraft's takeoff speed.

[0070] ;

[0071] in, This represents the maximum lift coefficient for the aircraft's takeoff configuration.

[0072] Preferably, the motor power determination module in step [1] includes a third motor power calculation unit, used to calculate the third motor power according to the following formula. :

[0073] ;

[0074] in, The thrust-to-weight ratio required for takeoff;

[0075] ;

[0076] in, ;

[0077] ;

[0078] in, This refers to the ground takeoff distance of an aircraft. Let be the coefficient of friction of the tire, and assume the angle of attack on the ground is 0°. The drag coefficient at zero angle of attack. The lift coefficient is zero angle of attack.

[0079] A third aspect of this application provides a computer device including a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for determining the motor power of an electric fixed-wing unmanned transport aircraft as described above.

[0080] A fourth aspect of this application provides a readable storage medium storing a computer program that, when executed by a processor, is used to implement the method for determining the motor power of an electric fixed-wing unmanned transport aircraft as described above.

[0081] This application shortens the calculation time for the top-level parameters of the motor in aircraft system design and accelerates the iteration speed of the top-level parameters. Attached Figure Description

[0082] Figure 1 This is a flowchart of a preferred embodiment of the method for determining the motor power of the electric fixed-wing unmanned transport aircraft of this application.

[0083] Figure 2 This is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of this application. Detailed Implementation

[0084] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0085] The first aspect of this application provides a method for determining the motor power of an electric fixed-wing unmanned transport aircraft, such as... Figure 1 As shown, it mainly includes:

[0086] Step S1: Determine the weight coefficient of the battery;

[0087] Step S2: Calculate the maximum weight and wing area of ​​the aircraft;

[0088] Step S3: Calculate the first motor power based on the service ceiling constraint, calculate the second motor power based on the takeoff climb gradient standard for aircraft with a single motor failure, calculate the third motor power based on the takeoff ground taxi distance, and select the maximum value among the first motor power, the second motor power, and the third motor power as the final motor power.

[0089] This application references traditional aircraft airworthiness standards and design specifications, and considers the design characteristics of electric propeller-powered fixed-wing aircraft. It establishes calculation models for the battery weight coefficient, maximum aircraft weight and wing area, and required motor power for electric fixed-wing aircraft. Furthermore, it provides a method and process for designing the top-level parameters of an electric fixed-wing unmanned transport aircraft. The calculation models reflect performance indicators such as payload, range, flight speed, service ceiling, and takeoff distance; aerodynamic performance parameters such as cruise lift-to-drag ratio, maximum lift coefficient of takeoff configuration, and drag characteristics; and the influence of battery energy density, motor efficiency, propeller efficiency, and design standards on the top-level parameters of the electric fixed-wing unmanned transport aircraft. This application is used for the top-level parameter design of electric propeller-powered fixed-wing aircraft.

[0090] In some alternative implementations, step S1 further includes:

[0091] Step S11: Obtain the input performance indicators, including range. With cruising speed ;

[0092] Step S12: Calculate the battery's weight coefficient according to the following formula. :

[0093] ;

[0094] in, The lift-to-drag ratio during cruise. For the energy density of the battery, For the design margin factor, The efficiency of the propeller in cruise mode. This refers to the efficiency of the motor.

[0095] In some alternative implementations, in step S2, the maximum weight W of the aircraft is calculated using the following formula:

[0096] ;

[0097] in, For commercial purposes, This is the empty weight factor of the aircraft.

[0098] In some alternative implementations, step S2 further includes:

[0099] Step S21: Calculate cruise speed pressure ;

[0100] Step S22: Calculate the wing area S using the following formula:

[0101] ;

[0102] in, The lift coefficient is used for cruise.

[0103] In some alternative implementations, in step S21, the cruise pressure is calculated using the following formula:

[0104] ;

[0105] in, This refers to atmospheric density.

[0106] In some alternative implementations, in step S3, the power of the first motor is calculated according to the following formula. :

[0107] ;

[0108] in, The cruising speed of an aircraft at its service ceiling. Number of engines;

[0109] ;

[0110] in, This refers to the atmospheric density at the service ceiling.

[0111] In some alternative implementations, in step S3, the power of the second motor is calculated according to the following formula. :

[0112] ;

[0113] in, The standard specifies the aircraft takeoff climb gradient constraint in the event of a single motor failure. This represents the lift-to-drag ratio corresponding to the aircraft's angle of attack at takeoff. This refers to the aircraft's takeoff speed.

[0114] ;

[0115] in, This represents the maximum lift coefficient for the aircraft's takeoff configuration.

[0116] In some alternative implementations, in step S3, the power of the third motor is calculated according to the following formula. :

[0117] ;

[0118] in, The thrust-to-weight ratio required for takeoff;

[0119] ;

[0120] in, ;

[0121] ;

[0122] in, This refers to the ground takeoff distance of an aircraft. Let be the coefficient of friction of the tire, and assume the angle of attack on the ground is 0°. The drag coefficient at zero angle of attack. The lift coefficient is zero angle of attack.

[0123] Design a four-engine electric propeller-driven fixed-wing unmanned transport aircraft with the following performance specifications: payload 260kg, range 500km, cruising speed 200km / h, cruising altitude 2000m, service ceiling 3000m, and takeoff distance 150m. Calculate the maximum weight of the aircraft, wing area, and required motor power. The calculation process is as follows:

[0124] 1) Calculate the battery weight factor .

[0125] The relevant parameters are calculated as shown in Appendix 1.

[0126] Appendix 1: Relevant parameters for calculating battery weight coefficient

[0127]

[0128] 2) Calculate the maximum weight W of the aircraft and the wing area S.

[0129] The relevant parameters are calculated as shown in Appendix 2.

[0130] Appendix 2: Relevant parameters for calculating aircraft weight and wing area

[0131]

[0132] 3) Calculate the required motor power .

[0133] The relevant parameters are calculated as shown in Appendix Table 3.

[0134] Appendix 3 Relevant parameters for motor power calculation

[0135]

[0136] As shown in Table 3, the final calculated motor power is 38.23 kW.

[0137] The second aspect of this application provides a motor power determination device for an electric fixed-wing unmanned transport aircraft corresponding to the above method, mainly comprising:

[0138] Battery weight coefficient determination module, used to determine the weight coefficient of the battery;

[0139] The aircraft weight and wing area determination module is used to calculate the maximum weight and wing area of ​​the aircraft.

[0140] The motor power determination module is used to calculate the first motor power based on the service ceiling constraint, the second motor power based on the takeoff climb gradient standard of an aircraft with a single motor failure, and the third motor power based on the takeoff ground taxi distance. The maximum value among the first motor power, the second motor power, and the third motor power is selected as the final motor power.

[0141] In some alternative implementations, the battery weight coefficient determination module includes:

[0142] Performance indicator acquisition unit, used to acquire input performance indicators, including range With cruising speed ;

[0143] The weight factor calculation unit is used to calculate the battery's weight factor according to the following formula. :

[0144] ;

[0145] in, The lift-to-drag ratio during cruise. For the energy density of the battery, For the design margin factor, The efficiency of the propeller in cruise mode. This refers to the efficiency of the motor.

[0146] In some alternative implementations, the aircraft weight and wing area determination module includes:

[0147] The maximum weight calculation unit is used to calculate the aircraft's maximum weight W using the following formula:

[0148] ;

[0149] in, For commercial purposes, This is the empty weight factor of the aircraft.

[0150] In some alternative implementations, the aircraft weight and wing area determination module includes:

[0151] Cruise pressure calculation unit, used to calculate cruise pressure ;

[0152] The wing area calculation unit is used to calculate the wing area S using the following formula:

[0153] ;

[0154] in, The lift coefficient is used for cruise.

[0155] In some alternative implementations, the cruise pressure is calculated in the cruise pressure calculation unit using the following formula:

[0156] ;

[0157] in, This refers to atmospheric density.

[0158] In some optional embodiments, the motor power determination module includes a first motor power calculation unit, used to calculate the first motor power according to the following formula. :

[0159] ;

[0160] in, The cruising speed of an aircraft at its service ceiling. Number of engines;

[0161] ;

[0162] in, This refers to the atmospheric density at the service ceiling.

[0163] In some optional embodiments, the motor power determination module includes a second motor power calculation unit, used to calculate the second motor power according to the following formula. :

[0164] ;

[0165] in, The standard specifies the aircraft takeoff climb gradient constraint in the event of a single motor failure. This represents the lift-to-drag ratio corresponding to the aircraft's angle of attack at takeoff. This refers to the aircraft's takeoff speed.

[0166] ;

[0167] in, This represents the maximum lift coefficient for the aircraft's takeoff configuration.

[0168] In some optional embodiments, the motor power determination module in step [1] includes a third motor power calculation unit for calculating the third motor power according to the following formula. :

[0169] ;

[0170] in, The thrust-to-weight ratio required for takeoff;

[0171] ;

[0172] in, ;

[0173] ;

[0174] in, This refers to the ground takeoff distance of an aircraft. Let be the coefficient of friction of the tire, and assume the angle of attack on the ground is 0°. The drag coefficient at zero angle of attack. The lift coefficient is zero angle of attack.

[0175] In a third aspect of this application, a computer device is provided, comprising a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for determining the motor power of an electric fixed-wing unmanned transport aircraft as described above.

[0176] In a fourth aspect, this application provides a readable storage medium storing a computer program that, when executed by a processor, implements the motor power determination method for an electric fixed-wing unmanned transport aircraft as described above. This computer-readable storage medium may be included in the apparatus described in the above embodiments; or it may exist independently and not incorporated into the apparatus. The aforementioned computer-readable storage medium carries one or more programs that, when executed by the apparatus, process data according to the described method.

[0177] The following is for reference. Figure 2 It shows a schematic diagram of the structure of a computer device 400 suitable for implementing the embodiments of this application. Figure 2 The computer device shown is merely an example and should not impose any limitation on the functionality and scope of use of the embodiments described in this application.

[0178] like Figure 2As shown, the computer device 400 includes a central processing unit (CPU) 401, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 402 or a program loaded from a storage section 408 into a random access memory (RAM) 403. The RAM 403 also stores various programs and data required for the operation of the device 400. The CPU 401, ROM 402, and RAM 403 are interconnected via a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0179] The following components are connected to I / O interface 405: an input section 406 including a keyboard, mouse, etc.; an output section 407 including a cathode ray tube (CRT), liquid crystal display (LCD), etc., and speakers, etc.; a storage section 408 including a hard disk, etc.; and a communication section 409 including a network interface card such as a LAN card, modem, etc. The communication section 409 performs communication processing via a network such as the Internet. A drive 410 is also connected to I / O interface 405 as needed. A removable medium 411, such as a disk, optical disk, magneto-optical disk, semiconductor memory, etc., is installed on drive 410 as needed so that computer programs read from it can be installed into storage section 408 as needed.

[0180] Specifically, according to embodiments of this application, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of this application include a computer program product comprising a computer program carried on a computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via communication section 409, and / or installed from removable medium 411. When the computer program is executed by central processing unit (CPU) 401, it performs the functions defined in the methods of this application. It should be noted that the computer storage medium of this application can be a computer-readable signal medium or a computer-readable storage medium, or any combination thereof. A computer-readable storage medium can be, for example,—but not limited to—an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of computer-readable storage media may include, but are not limited to: electrical connections having one or more wires, portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof. In this application, a computer-readable storage medium can be any tangible medium containing or storing a program that can be used by or in connection with an instruction execution system, apparatus, or device. In this application, a computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, carrying computer-readable program code. Such propagated data signals can take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium can also be any computer-readable medium other than a computer-readable storage medium, which can send, propagate, or transmit a program for use by or in connection with an instruction execution system, apparatus, or device. The program code contained on a computer-readable medium can be transmitted using any suitable medium, including but not limited to: wireless, wire, optical fiber, RF, etc., or any suitable combination thereof.

[0181] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of this application. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing the specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, can be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0182] The modules or units described in the embodiments of this application can be implemented in software or hardware. The described modules or units can also be located in a processor, and the names of these modules or units do not necessarily constitute a limitation on the module or unit itself.

[0183] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for determining the motor power of an electric fixed-wing unmanned transport aircraft, characterized in that, include: Step S1: Determine the weight coefficient of the battery; Step S2: Calculate the maximum weight and wing area of ​​the aircraft; Step S3: Calculate the first motor power based on the service ceiling constraint, calculate the second motor power based on the takeoff climb gradient standard for aircraft with a single motor failure, calculate the third motor power based on the takeoff ground taxi distance, and select the maximum value among the first motor power, the second motor power, and the third motor power as the final motor power.

2. The method for determining the motor power of an electric fixed-wing unmanned transport aircraft as described in claim 1, characterized in that, Step S1 further includes: Step S11: Obtain the input performance indicators, including range. With cruising speed ; Step S12: Calculate the battery's weight coefficient according to the following formula. : ； in, The lift-to-drag ratio during cruise. For the energy density of the battery, For the design margin factor, The efficiency of the propeller in cruise mode. This refers to the efficiency of the motor.

3. The method for determining the motor power of an electric fixed-wing unmanned transport aircraft as described in claim 2, characterized in that, In step S2, the maximum weight W of the aircraft is calculated using the following formula: ； in, For commercial purposes, This is the empty weight factor of the aircraft.

4. The method for determining the motor power of an electric fixed-wing unmanned transport aircraft as described in claim 3, characterized in that, Step S2 further includes: Step S21: Calculate cruise speed pressure ; Step S22: Calculate the wing area S using the following formula: ； in, The lift coefficient is used for cruise.

5. The method for determining the motor power of an electric fixed-wing unmanned transport aircraft as described in claim 4, characterized in that, In step S21, the cruise pressure is calculated using the following formula: ； in, This refers to atmospheric density.

6. The method for determining the motor power of an electric fixed-wing unmanned transport aircraft as described in claim 5, characterized in that, In step S3, the power of the first motor is calculated according to the following formula. : ； in, The cruising speed of an aircraft at its service ceiling. Number of engines; ； in, This refers to the atmospheric density at the service ceiling.

7. The method for determining the motor power of an electric fixed-wing unmanned transport aircraft as described in claim 5, characterized in that, In step S3, the power of the second motor is calculated according to the following formula. : ； in, The standard specifies the aircraft takeoff climb gradient constraint in the event of a single motor failure. This represents the lift-to-drag ratio corresponding to the aircraft's angle of attack at takeoff. This refers to the aircraft's takeoff speed. ； in, This represents the maximum lift coefficient for the aircraft's takeoff configuration.

8. The method for determining the motor power of an electric fixed-wing unmanned transport aircraft as described in claim 5, characterized in that, In step S3, the power of the third motor is calculated according to the following formula. : ； in, The thrust-to-weight ratio required for takeoff; ； in, ; ； in, This refers to the ground takeoff distance of an aircraft. Let be the coefficient of friction of the tire, and assume the angle of attack on the ground is 0°. The drag coefficient at zero angle of attack. The lift coefficient at zero angle of attack.

9. A device for determining the motor power of an electric fixed-wing unmanned transport aircraft, characterized in that, include: Battery weight coefficient determination module, used to determine the weight coefficient of the battery; The aircraft weight and wing area determination module is used to calculate the maximum weight and wing area of ​​the aircraft. The motor power determination module is used to calculate the first motor power based on the service ceiling constraint, the second motor power based on the takeoff climb gradient standard of an aircraft with a single motor failure, and the third motor power based on the takeoff ground taxi distance. The maximum value among the first motor power, the second motor power, and the third motor power is selected as the final motor power.

10. The motor power determination device for an electric fixed-wing unmanned transport aircraft as described in claim 9, characterized in that, The battery weight coefficient determination module includes: Performance indicator acquisition unit, used to acquire input performance indicators, including range With cruising speed ; The weight factor calculation unit is used to calculate the battery's weight factor according to the following formula. : ； in, The lift-to-drag ratio during cruise. For the energy density of the battery, For the design margin factor, The efficiency of the propeller in cruise mode. This refers to the efficiency of the motor.

11. The motor power determination device for an electric fixed-wing unmanned transport aircraft as described in claim 10, characterized in that, The aircraft weight and wing area determination module includes: The maximum weight calculation unit is used to calculate the aircraft's maximum weight W using the following formula: ； in, For commercial purposes, This is the empty weight factor of the aircraft.

12. The motor power determination device for an electric fixed-wing unmanned transport aircraft as described in claim 11, characterized in that, The aircraft weight and wing area determination module includes: Cruise pressure calculation unit, used to calculate cruise pressure ; The wing area calculation unit is used to calculate the wing area S using the following formula: ； in, The lift coefficient is used for cruise.

13. The motor power determination device for an electric fixed-wing unmanned transport aircraft as described in claim 12, characterized in that, In the cruise pressure calculation unit, the cruise pressure is calculated using the following formula: ； in, This refers to atmospheric density.

14. The motor power determination device for an electric fixed-wing unmanned transport aircraft as described in claim 13, characterized in that, The motor power determination module includes a first motor power calculation unit, used to calculate the first motor power according to the following formula. : ； in, The cruising speed of an aircraft at its service ceiling. Number of engines; ； in, This refers to the atmospheric density at the service ceiling.

15. The motor power determination device for an electric fixed-wing unmanned transport aircraft as described in claim 13, characterized in that, The motor power determination module includes a second motor power calculation unit, used to calculate the second motor power according to the following formula. : ； in, The standard specifies the aircraft takeoff climb gradient constraint in the event of a single motor failure. This represents the lift-to-drag ratio corresponding to the aircraft's angle of attack at takeoff. This refers to the aircraft's takeoff speed. ； in, This represents the maximum lift coefficient for the aircraft's takeoff configuration.

16. The motor power determination device for an electric fixed-wing unmanned transport aircraft as described in claim 13, characterized in that, The motor power determination module mentioned above includes a third motor power calculation unit, used to calculate the third motor power according to the following formula. : ； in, The thrust-to-weight ratio required for takeoff; ； in, ; ； in, This refers to the ground takeoff distance of an aircraft. Let be the coefficient of friction of the tire, and assume the angle of attack on the ground is 0°. The drag coefficient at zero angle of attack. The lift coefficient at zero angle of attack.

17. A computer device, characterized in that, It includes a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for determining the motor power of an electric fixed-wing unmanned transport aircraft as described in any one of claims 1-8.

18. A readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it is used to implement the method for determining the motor power of the electric fixed-wing unmanned transport aircraft as described in any one of claims 1-8.

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