A method, device, equipment and medium for determining design parameters of a propeller

Abstract

This application provides a method, apparatus, device, and medium for determining propeller design parameters, applicable to the field of propeller design technology. It addresses the technical problems of inaccurate parameters and low design precision caused by neglecting propeller motor torque. The method includes: determining the corresponding target hovering Mach value; obtaining the load correspondence between hovering disk load and solidity based on the target hovering thrust value and the target hovering Mach value; calculating the corresponding solidity interval and substituting it into the load correspondence to obtain the corresponding initial hovering disk load interval; calculating the critical disk radius value; determining the target hovering disk load value based on the critical disk radius value and the target hovering thrust value; obtaining the target hovering disk load interval based on the target hovering disk load value; and calculating the target disk radius value, target chord length value, and target solidity value based on the ratio between the target hovering thrust value and the target hovering disk load interval. This improves the propeller design precision.

Description

Technical Field

[0001] This application relates to the field of propeller design technology, and in particular to a method, apparatus, equipment and medium for determining propeller design parameters. Background Technology

[0002] The propeller is a core component of an aircraft's propulsion system, capable of converting the rotational mechanical energy output by an engine or motor into thrust. Therefore, it is the core actuator for the power output of aircraft such as eVTOL. In practical applications, the propeller's radius, chord length, solidity, pitch angle, and rotational speed are not independent but coupled together. By determining the corresponding parameters of the propeller, the aerodynamic performance of the propeller can be kept within the design target, thereby accurately outputting the thrust required for hovering and cruise, while avoiding aerodynamic problems such as shock waves and stall.

[0003] Existing methods for determining propeller design parameters typically treat the motor as an ideal "power source," ignoring the limitations of its torque output capability. For example, based on a given blade thrust distribution, the minimum energy loss and different thrust distribution patterns are applied to the propeller design to directly determine the propeller design parameters.

[0004] However, existing methods for determining propeller design parameters suffer from low design accuracy due to inaccurate parameters. Summary of the Invention

[0005] This application provides a method, apparatus, equipment, and medium for determining propeller design parameters, in order to solve the problem of low design accuracy caused by inaccurate parameters in existing methods for determining propeller design parameters.

[0006] In a first aspect, this application provides a method for determining propeller design parameters, the method comprising:

[0007] Based on the initial airfoil parameter values ​​and the target motor torque value, the corresponding target hovering Mach value is determined. Based on the target hovering thrust value and the target hovering Mach value, the solidity corresponding to the hovering rotor disk load is calculated, and the load correspondence between the hovering rotor disk load and the solidity is obtained.

[0008] Based on the target blade slenderness ratio and the target number of blades, the corresponding solidity interval is calculated, and the solidity interval is substituted into the load correspondence to obtain the corresponding initial hovering disk load interval.

[0009] Based on the target cruise thrust value, target hovering Mach value, and cruise Mach number, calculate the corresponding critical propeller disk radius value, and determine the target hovering propeller disk load value according to the critical propeller disk radius value and the target hovering thrust value.

[0010] Based on the target hovering disk load value, the initial hovering disk load range is divided to obtain the target hovering disk load range. Then, based on the ratio between the target hovering thrust value and the target hovering disk load range, the target disk radius value, target chord length value, and target solidity value are calculated.

[0011] In some embodiments of this application, the corresponding target hovering Mach value is determined based on the initial airfoil parameter values ​​and the target motor torque value, including:

[0012] Based on the initial airfoil parameter values, the Mach number correspondence between the hovering Mach value and the blade element lift coefficient is determined, and the target blade element lift coefficient range is substituted into the Mach number correspondence to obtain the corresponding Mach number range.

[0013] The target hovering Mach number is determined based on the Mach number range and the target motor torque value.

[0014] In some embodiments of this application, the target hovering Mach value is determined based on the Mach number range and the target motor torque value, including:

[0015] Based on the target hovering pull value and the target motor torque value, calculate the corresponding target torque load value, and based on the target torque load value, determine the corresponding target hovering Mach value.

[0016] In some embodiments of this application, based on the target hovering pull value and the target hovering Mach value, the realism corresponding to the hovering rotor disk load is calculated to obtain the load correspondence between the hovering rotor disk load and the realism, including:

[0017] Based on the target hovering thrust value and the target hovering Mach value, the propeller thrust coefficient and the equivalent thrust coefficient of the propeller blade corresponding to the hovering propeller disk load and their corresponding coefficient ratios are calculated. Based on the coefficient ratios, the solidity is calculated to obtain the load correspondence between the hovering propeller disk load and the solidity.

[0018] In some embodiments of this application, the corresponding critical propeller disk radius value is calculated based on the target cruise thrust value, the target hovering Mach value, and the cruise Mach number, including:

[0019] Based on the target hovering Mach value and hovering speed, the corresponding propeller disk radius is determined, and the cruise speed corresponding to the hovering speed is determined according to the ratio between the target cruise thrust value and the target hovering thrust value.

[0020] The critical disk radius value is calculated based on the cruise speed, cruise Mach number, and disk radius.

[0021] In some embodiments of this application, the initial hovering disk load range is divided based on the target hovering disk load value to obtain the target hovering disk load range, including:

[0022] Based on the initial hover disk load range, the maximum initial hover disk load value is determined, and based on the maximum initial hover disk load value and the target hover disk load value, the target hover disk load range is determined.

[0023] In some embodiments of this application, the target rotor radius, target chord length, and target solidity are calculated based on the ratio between the target hovering pull value and the target hovering rotor disk load range, including:

[0024] Based on the target hovering pull value and the target hovering propeller disk load range, calculate the corresponding target propeller disk radius value, and determine the corresponding target chord length value based on the ratio between the target propeller disk radius value and the target blade slenderness ratio.

[0025] Calculate the target solidity value based on the target chord length, target propeller disk radius, and number of propeller blades.

[0026] Secondly, this application provides a device for determining propeller design parameters, the device comprising:

[0027] The calculation module is used to determine the corresponding target hovering Mach value based on the initial airfoil parameter value and the target motor torque value, and to calculate the solidity corresponding to the hovering rotor disk load based on the target hovering thrust value and the target hovering Mach value, so as to obtain the load correspondence between the hovering rotor disk load and the solidity.

[0028] The input module is used to calculate the corresponding solidity interval based on the target blade slenderness ratio and the target number of blades, and then substitute the solidity interval into the load correspondence to obtain the corresponding initial hovering disk load interval.

[0029] The determination module is used to calculate the corresponding critical propeller disk radius value based on the target cruise thrust value, the target hovering Mach value, and the cruise Mach number, and to determine the target hovering propeller disk load value based on the critical propeller disk radius value and the target hovering thrust value.

[0030] The segmentation module is used to divide the initial hovering disk load range based on the target hovering disk load value to obtain the target hovering disk load range, and calculate the target disk radius value, target chord length value and target solidity value according to the ratio between the target hovering thrust value and the target hovering disk load range.

[0031] Thirdly, this application provides a computer device, including: a processor, and a memory communicatively connected to the processor;

[0032] The memory stores instructions that the computer executes;

[0033] The processor executes computer execution instructions stored in memory to implement the method of this application.

[0034] Fourthly, this application provides a computer-readable storage medium storing program code, which, when executed by a processor, is used to implement the method of this application.

[0035] Compared with existing technologies, the method of this application determines the target hovering Mach value by using initial airfoil parameter values ​​and target motor torque values, and calculates the solidity corresponding to the hovering disk load by combining the target hovering thrust value, thereby obtaining the load correspondence between the two. This achieves the combination of airfoil aerodynamic characteristics, motor torque hard constraints, and hovering aerodynamic loads, constructing a quantitative correspondence between the disk load constrained by torque and the solidity, solving the problem of neglecting the motor torque boundary in traditional designs, and improving the accuracy of subsequent design parameter determination, so as to further improve the design precision of the propeller. Furthermore, the method calculates the solidity interval based on the target blade slenderness ratio and the target number of blades, and substitutes it into the load correspondence to obtain the initial hovering disk load interval. This achieves the determination of the solidity design range by using structural parameters (slenderness ratio, number of blades), and then reverses to determine the disk load interval matching the structural constraints, realizing the correspondence between aerodynamic load parameters and structural parameters, narrowing the parameter range of propeller design. Finally, the method calculates the critical disk radius value based on the target cruise thrust value, the target hovering Mach value, and the cruise Mach number, and determines the target solidity design range by combining the target hovering thrust value. By setting the target hovering propeller disk load value, and based on the characteristics of hovering and cruise speeds of a fixed-pitch propeller, the Mach number of the cruise condition, i.e., the shock wave constraint, is transformed into the corresponding critical propeller disk radius. This allows for further determination of the accurate lower limit constraint of the hovering propeller disk load, improving the parameter accuracy of the hovering propeller disk load. It also enables reverse verification of the hovering design parameters under cruise conditions, ensuring that the design parameters simultaneously meet the aerodynamic performance requirements of both operating conditions, and avoiding problems such as cruise shock waves and aerodynamic instability caused by single-condition design. Based on the target hovering propeller disk load value, the initial... The hovering rotor disk load range is divided to obtain the target hovering rotor disk load range. The target rotor disk radius, target chord length, and target solidity are calculated based on the ratio of the target hovering thrust value to the range. This achieves the division of the initial load range by the lower limit of the cruise constraint, resulting in an accurate load range that simultaneously satisfies motor torque constraints, structural parameter constraints, and dual-condition aerodynamic constraints. Furthermore, the parameter values ​​take into account both the engineering feasibility and design margin of manufacturing, thereby improving the safety, accuracy, and aerodynamic efficiency of the electric vertical take-off and landing aircraft's power system. Attached Figure Description

[0036] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0037] Figure 1 A flowchart illustrating a method for determining propeller design parameters provided in an embodiment of this application;

[0038] Figure 2 A shock wave diagram illustrating a method for determining propeller design parameters provided in an embodiment of this application;

[0039] Figure 3 A schematic diagram illustrating the correspondence between torque load and disk load in a method for determining propeller design parameters provided in this application embodiment;

[0040] Figure 4 A schematic diagram showing the correspondence between the realism of a method for determining propeller design parameters provided in this application and the unit torque load;

[0041] Figure 5 A schematic diagram illustrating the relationship between rotational speed and thrust in a method for determining propeller design parameters provided in this application embodiment;

[0042] Figure 6 A schematic diagram illustrating the relationship between rotational speed and torque in a method for determining propeller design parameters provided in this application embodiment;

[0043] Figure 7 A schematic diagram of a device for determining propeller design parameters provided in an embodiment of this application;

[0044] Figure 8 This is a structural block diagram of an apparatus for performing a method for determining propeller design parameters according to an embodiment of this application. Detailed Implementation

[0045] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this application as detailed in the appended claims.

[0046] The technical solution of this application and how the technical solution of this application solves the above-mentioned technical problems are described in detail below with specific embodiments. These specific embodiments can be combined with each other, and the same or similar concepts or processes may not be described again in some embodiments. The embodiments of this application will now be described with reference to the accompanying drawings.

[0047] Figure 1 This is a flowchart illustrating a method for determining propeller design parameters provided in an embodiment of this application. Figure 1 As shown, the method for determining the design parameters of this type of propeller may include the following steps:

[0048] S110. Based on the initial airfoil parameter values ​​and the target motor torque value, determine the corresponding target hovering Mach value, and based on the target hovering thrust value and the target hovering Mach value, calculate the solidity corresponding to the hovering rotor disk load, and obtain the load correspondence between the hovering rotor disk load and the solidity.

[0049] The initial airfoil parameters refer to the geometric and aerodynamic characteristics of the propeller blade cross-section, which mainly include: relative thickness (the ratio of the maximum airfoil thickness to the chord length); sweep angle (the sweep angle at the half-chord line of the blade); and airfoil coefficient (an empirical coefficient reflecting the pressure distribution characteristics of the airfoil). These initial airfoil parameters can be used to calculate the critical Mach number, thereby determining the upper limit of the tip Mach number and preventing shock wave generation.

[0050] The target motor torque value refers to the maximum torque that the motor can continuously output in the design requirements. It is a value given in the actual propeller design scenario. For example, given the design requirement that "the electric propeller has a limited rated output torque, so the propeller torque should not exceed 250 Nm", the corresponding target motor torque value is 250 Nm.

[0051] The target hovering Mach number refers to the design target value corresponding to the airflow Mach number at the propeller tip during hovering. It is one of the propeller design parameters determined by calculation, representing the ratio of the airflow velocity at the propeller tip to the local speed of sound during hovering. In practical applications, the target hovering Mach number cannot be arbitrarily selected. It must simultaneously meet the following requirements: not exceeding the critical tip Mach number calculated from the initial airfoil parameters (to avoid tip shock waves); matching the unit torque load requirement corresponding to the target motor torque value; and leaving a margin for the cruise Mach number design.

[0052] The target hovering thrust value refers to the minimum limit thrust value that a single propeller needs to provide in the vertical takeoff and landing / hovering conditions of an eVTOL aircraft. It is a value given in the actual propeller design scenario. For example, given the design requirement that "the tilting propeller needs to provide no less than 2500N of thrust in the vertical takeoff and landing state", the corresponding target hovering thrust value is 2500N.

[0053] Hover disk load refers to the load per unit disk of a propeller under hovering conditions. Specifically, it is the ratio of the propeller hovering thrust to the disk sweep area. This converts the overall thrust target into a load requirement per unit area, facilitating load performance comparisons of propellers of different sizes and layouts. In practical applications, momentum theory is the most fundamental part of typical aerodynamic propeller theory. This theory treats the propeller rotation as a disk, assuming an inflow velocity of... In the axial inflow state, the airflow velocity is uniformly distributed in this circular region (hereinafter referred to as the propeller disk plane). At this time, there are differences in velocity and pressure before and after the propeller disk. After the airflow passes through the propeller disk plane, an induced velocity is added. And the pressure increment, while the propeller thrust can be considered as the rate of change of normal momentum of the propeller disk plane, which can be divided by the propeller disk area to obtain the expression for the unit propeller disk load:

[0054] ;

[0055] Where ρ is the air density and V is the inflow velocity. Let T be the induced velocity, T be the target hovering thrust, and A be the disk area; then the hovering disk load is T / A. Here, air density, inflow velocity, and disk area are conditional parameters for propeller operation, and the propeller induced velocity is the active factor generating propeller thrust. The above formula cannot provide the specific values ​​of the unit disk load and induced velocity, failing to meet design requirements. Therefore, a propeller blade element theoretical model is further introduced.

[0056] Furthermore, according to the lift formula, taking into account the number of blades... After normalization, the total thrust of the propeller in axial inflow condition can be obtained. Similarly, dividing by the disk area yields the expression for the unit disk load under blade element theory:

[0057] ；

[0058] In the formula, π can be taken as 3.14. Let be the slope of the airfoil's lift line at the infinitesimal element, where 'a' and 'y' have no specific meaning and are only used to represent the overall lift line slope; N is the number of propeller blades. C is the reference chord length of the propeller blade; R is the radius of the propeller disk; η is the dimensionless radius of the infinitesimal element of the propeller blade, η=r / R; η0 is the minimum dimensionless radius of the blade section with a non-zero chord length; λ is the propeller inflow ratio, λ=V / (ΩR), Ω is the propeller rotational speed; λi is the propeller downwash ratio, λi=Vi / (ΩR), Vi is the induced velocity; For the integral with respect to η; It is the propeller pitch angle.

[0059] This allows us to calculate the unit disk load of the propeller.

[0060] Solidity refers to the ratio of the sum of the projected areas of all propeller blades on the plane of rotation to the swept area of ​​the propeller disk. It characterizes the degree to which the blades cover the plane of the propeller disk and is an important structural aerodynamic indicator of the propeller. The larger the solidity, the higher the degree of blade coverage on the propeller disk and the stronger the thrust output capability, but the blade drag and weight will also increase. The smaller the solidity, the more slender the blades and the higher the aerodynamic efficiency, but the more difficult it is to ensure structural strength and the limited thrust output capability.

[0061] The load correspondence refers to the quantitative functional / curve relationship between hover disk load and solidity. It is a correlation determined under constraints such as initial airfoil parameters, target motor torque, target hovering Mach value, and target hovering thrust value. Moreover, this relationship is not a single numerical correspondence, but a range-based quantitative correlation. That is, under the premise of satisfying motor torque constraints, hovering thrust targets, and no shock wave constraints, it defines the reasonable range of solidity corresponding to different hover disk loads, as well as the allowable range of hover disk loads under different solidities.

[0062] Based on this, the corresponding Mach number range is calculated by using the initial airfoil parameters and blade element lift coefficient range given in the actual design requirements. Furthermore, based on the given target motor torque value, the corresponding target hovering Mach value is determined from the Mach number range. Thus, based on the target hovering thrust value and the target hovering Mach value, the solidity corresponding to each hovering rotor disk load is determined, thereby constructing the load correspondence between hovering rotor disk load and solidity.

[0063] S120. Based on the target blade slenderness ratio and the target number of blades, calculate the corresponding solidity interval, and substitute the solidity interval into the load correspondence to obtain the corresponding initial hovering disk load interval.

[0064] The target blade slenderness ratio and target number of blades are values ​​given in the actual propeller design scenario. The target blade slenderness ratio can be given in the range of 4-6. Since the blade slenderness ratio is defined as the ratio of the blade radius to the chord length, the blade slenderness ratio under different numbers of blades can be compared based on the propeller solidity to design the required number of propeller blades. If the propeller solidity is too high, the blade slenderness ratio will decrease. At this time, the blade area occupies most of the propeller disk plane, which is meaningless in actual design. If the solidity is too low, the blade slenderness ratio will increase. The blades will be too thin and long, which makes it difficult to guarantee the structural strength of the propeller under the design conditions of high speed and high thrust, and it is also meaningless in design. The number of blades has a limited impact on the propeller solidity and slenderness ratio. Therefore, considering the reduction of propeller weight and simplification of manufacturing and assembly, a two-bladed propeller is preferred in the preliminary design, that is, the target number of blades is 2.

[0065] The solidity range refers to the reasonable range of propeller solidity values ​​derived from the target blade slenderness ratio, the target number of blades, and the corresponding solidity quantification formula. For example:

[0066] ;

[0067] Where R is the propeller disk radius, C is the propeller blade chord length, N is the number of blades, and for a two-bladed propeller N is 2, S is the propeller solidity. Since the blade slenderness ratio = R / C and N is 2, the range of S can be calculated.

[0068] The initial hovering disk load range refers to the reasonable range of hovering disk load values ​​obtained by substituting the real range derived from the structural constraints into the previously obtained correspondence between the hovering disk load and the real load.

[0069] Based on this, by determining the given target blade slenderness ratio and the target number of blades, the corresponding solidity interval is calculated. The solidity interval is then substituted into the load correspondence to obtain the corresponding initial hovering disk load interval. This allows for further subdivision of the hovering disk load interval based on the cruise state, resulting in a more accurate hovering disk load interval range.

[0070] S130. Based on the target cruise thrust value, target hovering Mach value, and cruise Mach number, calculate the corresponding critical propeller disk radius value, and determine the target hovering propeller disk load value according to the critical propeller disk radius value and the target hovering thrust value.

[0071] The target cruise thrust value refers to the minimum thrust design target value that a single propeller needs to provide at the maximum design cruise speed of an eVTOL aircraft. It is a value given in the actual propeller design scenario. For example, given the design requirement that "at the maximum cruise speed of 50m / s, a thrust of not less than 1000N needs to be generated" during cruise motion, the corresponding target cruise thrust value is 1000N.

[0072] Cruise Mach number refers to the design value of the airflow Mach number at the propeller tip at the maximum design cruise speed. It represents the ratio of the airflow velocity at the propeller tip to the local speed of sound during cruise. This value is not independently selected but must be calculated based on the maximum cruise speed of eVTOL and the propeller speed requirements. It is numerically related to the target hovering Mach number; that is, if the cruise Mach number is higher than the target hovering Mach number, the speed needs to be increased during cruise, further increasing the tip Mach number. It must not exceed the cruise critical Mach number determined by the blade airfoil parameters to avoid shock waves at the propeller tip. A reasonable margin must also be reserved for aerodynamic efficiency and noise control during cruise. In practical applications, the propeller needs to provide high thrust in hovering, but in cruise, the propeller needs to increase its speed to counteract flight drag. Both of these critical propeller states must be considered during design. Assuming the initial design requires a cruise speed of 50 m / s, the propeller thrust is 0.4 times the hovering limit thrust. Within the hovering unit disk load range that meets the performance requirements of hovering, the cruise unit torque load is higher than the cutoff line level. It is particularly important to note that, since the propeller speed needs to be increased during cruise, the cruise tip Mach number is generally higher than the hover tip Mach number.

[0073] The critical propeller disk radius value refers to the critical design value of the propeller disk radius derived from the target cruise thrust, target hovering Mach number, and cruise Mach number, combined with propeller aerodynamic theory and load calculation model. In other words, it is the critical value of the propeller radius under the shock wave constraint in cruise state. This value is the limit value of the propeller disk radius under dual operating condition constraints. If the propeller disk radius is less than this value, it will cause the cruise tip Mach number to exceed the critical value and generate a shock wave, or the cruise thrust will not meet the design requirements. If the propeller disk radius is greater than this value, it will cause the hovering speed to be too low, the torque to exceed the limit, or the overall size of the propeller to be too large, affecting the spatial layout of the eVTOL.

[0074] The target hovering disk load value refers to the hovering disk load value calculated based on the critical disk radius value and the target hovering thrust value, combined with the hovering disk load formula. It is a limitation on the hovering disk load value under cruise conditions. In practical applications, the blade performance in cruise mode limits the selection of the hovering unit disk load, that is, the hovering disk load value needs to be higher than the target hovering disk load value.

[0075] Based on this, the range of hovering propeller disk load values ​​is further restricted by the cruise state. That is, based on the target cruise thrust value, the target hovering Mach value, and the cruise Mach number, since the cruise Mach number needs to be greater than the calculated target hovering Mach value, the critical propeller disk radius value corresponding to the critical cruise Mach number can be calculated, and the maximum propeller disk radius value under cruise state can be obtained. Then, based on the critical propeller disk radius value and the target hovering thrust value, the target hovering propeller disk load value corresponding to the critical propeller disk radius can be calculated. That is, the minimum hovering propeller disk load value that meets the requirements of the given cruise thrust and target cruise Mach number under cruise conditions.

[0076] S140. Based on the target hovering disk load value, the initial hovering disk load range is divided to obtain the target hovering disk load range. Based on the ratio between the target hovering thrust value and the target hovering disk load range, the target disk radius value, target chord length value, and target solidity value are calculated.

[0077] Among them, the target disk radius, target chord length, and target solidity are the calculated propeller design parameters that meet the actual requirements.

[0078] Based on this, by determining the initial hovering disk load range in the hovering state, and then further obtaining the target hovering disk load range after secondary division based on the target hovering disk load value determined in the cruise state, since the disk load is the ratio of the thrust to the disk area, the range of the disk radius can be determined, and the target disk radius value can be obtained by rounding. Based on the target disk radius value, the target chord length value and the target solidity value can be calculated respectively.

[0079] Based on the feasible implementation of S110 described above, this application further provides a method for determining the corresponding target hovering Mach value based on the initial airfoil parameter value and the target motor torque value, including:

[0080] Based on the initial airfoil parameter values, the Mach number correspondence between the hovering Mach value and the blade element lift coefficient is determined, and the target blade element lift coefficient range is substituted into the Mach number correspondence to obtain the corresponding Mach number range.

[0081] The target hovering Mach number is determined based on the Mach number range and the target motor torque value.

[0082] The target blade element lift coefficient range refers to the reasonable range of blade element lift coefficient values ​​that are predetermined for the eVTOL hovering condition, taking into account the propeller blade aerodynamic performance requirements, stall constraints, and noise control (shock wave avoidance). For example, it is determined to be 1-1.2.

[0083] The Mach number correspondence refers to the quantitative function / curve relationship between the tip Mach number and the blade element lift coefficient under hovering conditions, established based on initial airfoil parameters (airfoil coefficient, relative thickness, sweep angle, etc.) through propeller aerodynamic theory (blade element theory) and tip shock wave analysis. In other words, it represents the maximum permissible tip Mach number at which the blades do not generate shock waves under different blade element lift coefficients. In practical applications, the Mach number correspondence can be expressed as:

[0084] ;

[0085] Among them, the airfoil coefficient The relative thickness of the airfoil is 0.95. The value is 12%, where t is the airfoil thickness and c is the airfoil chord length. The angle is 30°, and the swept-back configuration is 0.8. R - R Within the region, R is the propeller disk radius. Therefore, the lift coefficient can be determined based on the blade element. The critical Mach number at the blade tip, calculated to be 1.0-1.2, is the minimum allowable number for the blade to not generate shock waves. The value is 0.644-0.675, please refer to [the relevant documentation]. Figure 2 , Figure 2 A shock wave diagram illustrating a method for determining propeller design parameters provided in this application embodiment, as shown below. Figure 2 As shown, the critical Mach number of the blade is directly related to the lift coefficient of the blade section. C LA higher lift coefficient results in a narrower shock wave boundary and a lower critical Mach number, which is detrimental to blade design. At the same propeller speed, the blade tip will enter the shock wave state first, so a higher lift coefficient will cause the blades to stall prematurely. Conversely, a lower lift coefficient will result in insufficient resistance to overcome flight drag during cruise, leading to poor propeller performance during cruise.

[0086] Based on this, by substituting the given target blade lift coefficient range into the Mach number correspondence, the corresponding Mach number range is obtained; thus, the target hovering Mach value is determined according to the Mach number range and the target motor torque value.

[0087] Based on the feasible implementation of S110 described above, this application further provides a method for determining a target hovering Mach value based on a Mach number range and a target motor torque value, including:

[0088] Based on the target hovering pull value and the target motor torque value, calculate the corresponding target torque load value, and based on the target torque load value, determine the corresponding target hovering Mach value.

[0089] Among them, the target torque load value refers to the design target value of unit torque load under hovering conditions calculated based on the target hovering pull value and the target motor torque value. It represents the magnitude of the hovering pull that can be output per unit torque under the target motor torque. In practical applications, propeller power consists of two parts, namely effective power and drag power.

[0090] To characterize the thrust provided by a propeller per unit power, the ratio of propeller thrust to propeller power is further defined as the unit power load:

[0091] ；

[0092] In the formula: The propeller tip speed, P is power. Zero-lift drag coefficient, The coefficient for induced velocity non-uniformity. S Where V is the propeller solidity, V is the inflow velocity, and ρ is the air density.

[0093] Furthermore, since the propeller lift decomposes into components within the propeller disk plane, and due to the effects of blade friction, airfoil drag, shock wave drag, and induced drag, tangential loads are generated within the propeller disk plane. The resultant torque of these loads about the shaft is the propeller torque. Therefore, the propeller torque can be derived from blade element theory. However, since the calculation of airfoil drag and shock wave drag is too complex, we consider using the correspondence between power and torque to deduce the torque magnitude from the propeller power model.

[0094] The unit torque load is the ratio between the propeller disk thrust and the propeller torque, characterizing the magnitude of the thrust that the propeller can provide under unit torque conditions. The unit torque load of the propeller is shown below:

[0095] ；

[0096] In the formula, Q represents the motor torque.

[0097] Compared to traditional piston engines, electric motors offer a wider range of speed adjustments. While increasing the speed can effectively boost power output, electric motor torque has a lower correlation with speed, and different motors have different torque limits. Due to the limitations of motor torque, a conservative maximum output torque of 250 Nm is chosen based on current motor performance parameters. The unit torque load cutoff line for hovering / cruising can be obtained using the formula for unit torque load. A value above this cutoff line is considered to meet the motor's torque characteristics. Combining this with the aforementioned propeller tip Mach number range, the variation in unit torque load during hovering is presented. Please refer to [reference needed]. Figure 3 , Figure 3 A schematic diagram illustrating the correspondence between torque load and propeller disk load in a method for determining propeller design parameters provided in this application embodiment is shown below. Figure 3 As shown, the induced velocity non-uniformity coefficient is taken as the recommended value of 1.1, and the air density is taken as 1.225 kg / m³. 3 The zero-lift drag coefficient is recommended to be 0.02, and the propeller solidity S is taken as a commonly available value of 0.1-0.2. As the unit disk load increases, the higher the unit torque load of the propeller, the better the performance. However, excessive disk load requires a higher rotational speed for a given propeller radius, which can lead to shock wave problems. Therefore, the region near the cutoff line is analyzed. Under the same solidity, the higher the hovering tip Mach number, the better. However, due to the tip shock wave problem and the need to leave a certain design margin for cruise state design, the hovering tip Mach number can be set to 0.65, and the corresponding hovering blade element lift coefficient cannot exceed 1.15.

[0098] Based on the feasible implementation of S110 described above, this application further provides a method for calculating the realism corresponding to the hovering rotor disk load based on the target hovering pull value and the target hovering Mach value, thereby obtaining the load correspondence between the hovering rotor disk load and the realism, including:

[0099] Based on the target hovering thrust value and the target hovering Mach value, the propeller thrust coefficient and the equivalent thrust coefficient of the propeller blade corresponding to the hovering propeller disk load and their corresponding coefficient ratios are calculated. Based on the coefficient ratios, the solidity is calculated to obtain the load correspondence between the hovering propeller disk load and the solidity.

[0100] Among them, the propeller thrust coefficient is a dimensionless characteristic coefficient in propeller aerodynamic design. It is a core aerodynamic index characterizing the overall thrust output capability of the propeller. Its calculation formula is derived from propeller blade element theory and momentum theory, and is closely related to parameters such as propeller hovering thrust, air density, propeller speed, and propeller disk radius.

[0101]

[0102] In the formula, This is the propeller thrust coefficient. It is the equivalent thrust coefficient of the propeller blade.

[0103] The equivalent thrust coefficient of a propeller blade is a core aerodynamic indicator characterizing the comprehensive thrust output capability of local micro-elements of a propeller blade. Unlike the overall propeller thrust coefficient, which is at the engine level, this coefficient focuses on the airfoil aerodynamic characteristics of the blade micro-elements (such as blade element lift coefficient and airfoil lift line slope). It is derived by combining the blade element lift coefficient constraint corresponding to the target hovering Mach number. It represents the contribution coefficient of the local thrust characteristics of the blade to the overall propeller thrust, obtained by equivalently integrating the thrust output capabilities of all spanwise micro-elements of the blade. The magnitude of the value reflects the quality of the airfoil aerodynamic characteristics of the blade micro-elements; the larger the value, the stronger the lift output capability of the local airfoil of the blade, and the greater the thrust contribution to the overall propeller under the same realism.

[0104]

[0105] In the formula, the equivalent thrust coefficient of the propeller blade is... Mainly related to the inflow ratio of the blades and the ratio of washing Related to, and also to, the slope of the lift line of leaf element. and pitch angle Relevant. Based on the inherent aerodynamic characteristics of the blade element airfoil, if we assume the lift line slope of the blade element is 5.7, then the blade element's pitch angle can be determined by the maximum lift coefficient of the blade element. If the reverse is determined, then the blade element's pitch angle can be determined based on the set maximum lift coefficient of the blade element, and thus the blade's equivalent thrust coefficient can be obtained.

[0106] Based on this, by determining the propeller tip Mach number, the unit disk load of the propeller can be mapped to the propeller thrust coefficient. Then, combined with the equivalent thrust coefficient of the blades, the solidity of the propeller can be calculated. Assuming the design requirement is a maximum hovering thrust of 2500 N, the corresponding unit torque load of the propeller can be calculated. Please refer to [reference needed]. Figure 4 , Figure 4 A schematic diagram illustrating the correspondence between the realism of a method for determining propeller design parameters and unit torque load, provided in an embodiment of this application; as shown. Figure 4As shown, the unit propeller load required to meet the hovering unit torque load requirement must be higher than 120 kg / m. 2 At this point, the propeller solidity is higher than 0.1.

[0107] Based on the feasible implementation of S130 described above, this application further provides a method for calculating the corresponding critical propeller disk radius value based on the target cruise thrust value, the target hovering Mach value, and the cruise Mach number, including:

[0108] Based on the target hovering Mach value and hovering speed, the corresponding propeller disk radius is determined, and the cruise speed corresponding to the hovering speed is determined according to the ratio between the target cruise thrust value and the target hovering thrust value.

[0109] The critical disk radius value is calculated based on the cruise speed, cruise Mach number, and disk radius.

[0110] Among them, hovering speed refers to the propeller rotation speed required to provide the target hovering thrust value when the eVTOL is in vertical hovering condition, under the constraints of matching motor torque boundary and hovering tip Mach number. In practical applications, this speed is the core operating parameter of the propeller in hovering state, and it must simultaneously meet the requirements that the tip Mach number does not exceed the target hovering Mach value, and the propeller torque does not exceed the rated torque of the motor.

[0111] Cruise speed refers to the propeller rotation speed constrained by hover speed and cruise tip Mach number when the eVTOL is in horizontal cruise mode, in order to provide the target cruise thrust value.

[0112] For further details, please refer to Figure 5 and Figure 6 , Figure 5 This diagram illustrates the relationship between rotational speed and thrust in a method for determining propeller design parameters provided in this application. Figure 6 A schematic diagram illustrating the relationship between rotational speed and torque in a method for determining propeller design parameters provided in this application embodiment; as shown. Figure 5 and Figure 6 As shown, the thrust reaches the minimum requirement for hovering at a speed of 2932 RPM, with a propeller torque of 232 Nm. Compared to the motor's rated torque, there is still some design margin. At maximum cruising speed, the propeller thrust requirement is approximately 0.4 times that at hovering, meaning the thrust meets the design requirements at a speed of 3420 RPM, with a propeller torque of 184 Nm. Both propeller thrust and torque meet the requirements. In summary, the designed propeller structural parameters can well meet the performance requirements for hovering and cruising under critical conditions.

[0113] Based on this, the relationship between hovering speed and propeller disk radius is determined by using the thrust and Mach number corresponding to the hovering state. This involves substituting the thrust and Mach number corresponding to the hovering state into the propeller thrust coefficient formula, and determining the proportional relationship between hovering speed and cruise speed based on the ratio between the target cruise thrust value and the target hovering thrust value. This determines the cruise speed corresponding to the hovering speed, allowing the hovering speed in the relationship to be expressed as the corresponding cruise speed, thus obtaining the relationship between cruise speed and propeller disk radius. Since there is a direct quantitative relationship between Mach number and speed, the propeller disk radius corresponding to the cruise speed is substituted into the cruise Mach number to obtain the quantitative relationship between propeller disk radius and cruise Mach number. Because the Mach number in the cruise state is greater than the Mach number in the hovering state, meaning the critical value of the cruise Mach number is the same as the hovering Mach number, the critical value of the propeller disk radius in the cruise state can be calculated based on the critical value of the cruise Mach number and the quantitative relationship between the propeller disk radius and the cruise Mach number, thus determining the critical propeller disk radius value.

[0114] Based on the feasible implementation of S140 described above, this application further provides a method for dividing the initial hovering disk load range based on the target hovering disk load value to obtain the target hovering disk load range, including:

[0115] Based on the initial hover disk load range, the maximum initial hover disk load value is determined, and based on the maximum initial hover disk load value and the target hover disk load value, the target hover disk load range is determined.

[0116] Based on this, when considering the tip shock wave problem in cruise mode, the minimum hovering disk load value that must be satisfied in hovering mode can be determined, i.e., the target hovering disk load value. This narrows down the initial hovering disk load range in hovering mode, resulting in the target hovering disk load range composed of the maximum initial hovering disk load value and the target hovering disk load value. Since the target hovering disk load range satisfies both hovering and cruise conditions, it is a relatively accurate range and can be used to determine the precise range of the disk radius, so as to further round down to determine the disk radius value.

[0117] Based on the feasible implementation of S140 described above, this application further provides a method for calculating the target rotor disk radius, target chord length, and target solidity value based on the ratio between the target hovering pull value and the target hovering rotor disk load range, including:

[0118] Based on the target hovering pull value and the target hovering propeller disk load range, calculate the corresponding target propeller disk radius value, and determine the corresponding target chord length value based on the ratio between the target propeller disk radius value and the target blade slenderness ratio.

[0119] Calculate the target solidity value based on the target chord length, target propeller disk radius, and number of propeller blades.

[0120] Based on this, according to the given target hovering pull value and the determined target hovering disk load range, the range corresponding to the disk area is determined based on the hovering disk load of T / A, so as to further determine the range of the target disk radius, and the target disk radius value is obtained by rounding down from it. Then, the corresponding target chord length value is determined based on the ratio between the target disk radius value and the target blade slenderness ratio. Based on the target chord length value, the target disk radius value and the number of blades, the target solidity value is calculated.

[0121] Based on the above steps, it can be seen that this application determines the target hovering Mach value by using the initial airfoil parameter values ​​and the target motor torque value, and calculates the solidity corresponding to the hovering rotor disk load by combining the target hovering thrust value, thereby obtaining the load correspondence between the two. This realizes the combination of airfoil aerodynamic characteristics, motor torque hard constraints, and hovering aerodynamic loads, constructing a quantitative correspondence between the rotor disk load constrained by torque and the solidity, solving the problem of ignoring the motor torque boundary in traditional design, and improving the accuracy of subsequent design parameter determination, so as to further improve the design precision of the propeller. Furthermore, the solidity interval is calculated based on the target blade slenderness ratio and the target number of blades, and the initial hovering rotor disk load interval is obtained by substituting it into the load correspondence. This realizes the determination of the solidity design range by using structural parameters (slenderness ratio, number of blades), and then the determination of the rotor disk load interval matching the structural constraints in reverse, realizing the correspondence between aerodynamic load parameters and structural parameters, and narrowing the parameter range of propeller design. The critical rotor disk radius value is calculated based on the target cruise thrust value, the target hovering Mach value, and the cruise Mach number, and determined by combining the target hovering thrust value. The target hovering propeller disk load value is used to convert the Mach number of the cruise condition, i.e., the shock wave constraint, into the corresponding critical propeller disk radius based on the characteristics of hovering and cruise speeds of a fixed-pitch propeller. This allows for further determination of the accurate lower limit constraint of the hovering propeller disk load, improving the parameter accuracy of the hovering propeller disk load. It also enables reverse verification of the hovering design parameters under cruise conditions, ensuring that the design parameters simultaneously meet the aerodynamic performance requirements of both operating conditions, and avoiding problems such as cruise shock waves and aerodynamic instability caused by single-condition design. Based on the target hovering propeller disk load value, the initial... The initial hovering rotor disk load range is divided to obtain the target hovering rotor disk load range. The target rotor disk radius, target chord length, and target solidity are calculated based on the ratio of the target hovering thrust value to the range. This achieves the division of the initial load range by the lower limit of the cruise constraint, resulting in an accurate load range that simultaneously satisfies motor torque constraints, structural parameter constraints, and dual-condition aerodynamic constraints. Furthermore, the parameter values ​​take into account both the engineering feasibility and design margin of manufacturing, thereby improving the safety, accuracy, and aerodynamic efficiency of the electric vertical take-off and landing aircraft's power system.

[0122] Figure 7This is a schematic diagram of a device for determining propeller design parameters provided in an embodiment of this application. Figure 7 As shown, the device for determining the design parameters of this propeller includes: a calculation module, a substitution module, a determination module, and a partitioning module; wherein:

[0123] The calculation module is used to determine the corresponding target hovering Mach value based on the initial airfoil parameter value and the target motor torque value, and to calculate the solidity corresponding to the hovering rotor disk load based on the target hovering thrust value and the target hovering Mach value, so as to obtain the load correspondence between the hovering rotor disk load and the solidity.

[0124] The input module is used to calculate the corresponding solidity interval based on the target blade slenderness ratio and the target number of blades, and then substitute the solidity interval into the load correspondence to obtain the corresponding initial hovering disk load interval.

[0125] The determination module is used to calculate the corresponding critical propeller disk radius value based on the target cruise thrust value, the target hovering Mach value, and the cruise Mach number, and to determine the target hovering propeller disk load value based on the critical propeller disk radius value and the target hovering thrust value.

[0126] The segmentation module is used to divide the initial hovering disk load range based on the target hovering disk load value to obtain the target hovering disk load range, and calculate the target disk radius value, target chord length value and target solidity value according to the ratio between the target hovering thrust value and the target hovering disk load range.

[0127] In this embodiment of the application, the calculation module can also be specifically used for:

[0128] Based on the initial airfoil parameter values, the Mach number correspondence between the hovering Mach value and the blade element lift coefficient is determined, and the target blade element lift coefficient range is substituted into the Mach number correspondence to obtain the corresponding Mach number range.

[0129] The target hovering Mach number is determined based on the Mach number range and the target motor torque value.

[0130] In this embodiment of the application, the calculation module can also be specifically used for:

[0131] Based on the target hovering pull value and the target motor torque value, calculate the corresponding target torque load value, and based on the target torque load value, determine the corresponding target hovering Mach value.

[0132] In this embodiment of the application, the calculation module can also be specifically used for:

[0133] Based on the target hovering thrust value and the target hovering Mach value, the propeller thrust coefficient and the equivalent thrust coefficient of the propeller blade corresponding to the hovering propeller disk load and their corresponding coefficient ratios are calculated. Based on the coefficient ratios, the solidity is calculated to obtain the load correspondence between the hovering propeller disk load and the solidity.

[0134] In this embodiment of the application, the determining module can also be specifically used for:

[0135] Based on the target hovering Mach value and hovering speed, the corresponding propeller disk radius is determined, and the cruise speed corresponding to the hovering speed is determined according to the ratio between the target cruise thrust value and the target hovering thrust value.

[0136] The critical disk radius value is calculated based on the cruise speed, cruise Mach number, and disk radius.

[0137] In this embodiment of the application, the partitioning module can also be specifically used for:

[0138] Based on the initial hover disk load range, the maximum initial hover disk load value is determined, and based on the maximum initial hover disk load value and the target hover disk load value, the target hover disk load range is determined.

[0139] In this embodiment of the application, the partitioning module can also be specifically used for:

[0140] Based on the target hovering pull value and the target hovering propeller disk load range, calculate the corresponding target propeller disk radius value, and determine the corresponding target chord length value based on the ratio between the target propeller disk radius value and the target blade slenderness ratio.

[0141] Calculate the target solidity value based on the target chord length, target propeller disk radius, and number of propeller blades.

[0142] Figure 8 This is a schematic diagram of a device for performing a method for determining propeller design parameters according to an embodiment of this application. Figure 8 As shown, the device includes:

[0143] The device may include one or more processors with processing cores, one or more computer-readable storage media such as memory, communication components, etc. The processor, memory, and communication components are connected via a bus.

[0144] In the specific implementation process, at least one processor executes computer execution instructions stored in memory, causing at least one processor to execute the above method for determining propeller design parameters.

[0145] The specific implementation process of the processor can be found in the above method embodiments, and its implementation principle and technical effect are similar, so it will not be repeated here.

[0146] Furthermore, the processor can be a Central Processing Unit (CPU), or other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), etc. A general-purpose processor can be a microprocessor or any conventional processor. The steps of the method disclosed in this application can be directly manifested as being executed by a hardware processor, or executed by a combination of hardware and software modules within the processor.

[0147] The memory may include random access memory (RAM) and may also include non-volatile memory (NVM), such as at least one disk storage device.

[0148] The bus can be an Industry Standard Architecture (ISA) bus, a Peripheral Component Interconnect (PCI) bus, or an Extended Industry Standard Architecture (EISA) bus, etc. Buses can be categorized as address buses, data buses, control buses, etc. For ease of illustration, the buses shown in the accompanying drawings are not limited to a single bus or a single type of bus.

[0149] In some embodiments, a computer program product is also provided, comprising a computer program or instructions that, when executed by a processor, implement the steps in any of the methods for determining propeller design parameters described above.

[0150] For details on the implementation of each of the above operations, please refer to the previous examples, which will not be repeated here.

[0151] Those skilled in the art will understand that all or part of the steps in the various methods of the above embodiments can be performed by instructions, or by instructions controlling related hardware. These instructions can be stored in a computer-readable storage medium and loaded and executed by a processor.

[0152] Therefore, embodiments of this application provide a computer-readable storage medium storing a plurality of program codes, which can be loaded by a processor to execute the steps in any of the propeller design parameter determination methods provided in embodiments of this application.

[0153] The storage medium may include: read-only memory (ROM), random access memory (RAM), disk or optical disk, etc.

[0154] According to one aspect of this application, a computer program product or computer program is provided, the computer program product or computer program including computer instructions stored in a computer-readable storage medium.

[0155] Since the instructions stored in the storage medium can execute the steps in any of the propeller design parameter determination methods provided in the embodiments of this application, the beneficial effects that any of the propeller design parameter determination methods provided in the embodiments of this application can achieve can be realized. For details, please refer to the previous embodiments, which will not be repeated here.

[0156] Other embodiments of this application will readily occur to those skilled in the art upon consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of this application that follow the general principles of this application and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only, and the true scope of this application is indicated by the appended claims.

[0157] It should be understood that this application is not limited to the precise structure described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope.

Claims

1. A method of determining design parameters of a propeller, characterized by, The method includes: Based on the initial airfoil parameter values ​​and the target motor torque value, the corresponding target hovering Mach value is determined, and based on the target hovering thrust value and the target hovering Mach value, the solidity corresponding to the hovering rotor disk load is calculated to obtain the load correspondence between the hovering rotor disk load and the solidity. Based on the target blade slenderness ratio and the target number of blades, the corresponding solidity interval is calculated, and the solidity interval is substituted into the load correspondence to obtain the corresponding initial hovering disk load interval. Based on the target cruise thrust value, the target hovering Mach value, and the cruise Mach number, the corresponding critical propeller disk radius value is calculated, and the target hovering propeller disk load value is determined according to the critical propeller disk radius value and the target hovering thrust value. Based on the target hovering disk load value, the initial hovering disk load range is divided to obtain the target hovering disk load range. Then, based on the ratio between the target hovering thrust value and the target hovering disk load range, the target disk radius value, target chord length value, and target solidity value are calculated.

2. The method according to claim 1, characterized in that, The step of determining the corresponding target hovering Mach value based on the initial airfoil parameter values ​​and the target motor torque value includes: Based on the initial airfoil parameter values, the Mach number correspondence between the hovering Mach value and the blade element lift coefficient is determined, and the target blade element lift coefficient interval is substituted into the Mach number correspondence to obtain the corresponding Mach number interval. The target hovering Mach number is determined based on the Mach number range and the target motor torque value.

3. The method according to claim 2, characterized in that, Determining the target hovering Mach value based on the Mach number range and the target motor torque value includes: Based on the target hovering pull value and the target motor torque value, the corresponding target torque load value is calculated, and based on the target torque load value, the corresponding target hovering Mach value is determined.

4. The method according to claim 1, characterized in that, The step of calculating the solidity corresponding to the hovering rotor disk load based on the target hovering pull value and the target hovering Mach value, and obtaining the load correspondence between the hovering rotor disk load and the solidity, includes: Based on the target hovering thrust value and the target hovering Mach value, the propeller thrust coefficient and the propeller blade equivalent thrust coefficient corresponding to the hovering propeller disk load and their corresponding coefficient ratios are calculated, and the solidity is calculated according to the coefficient ratios to obtain the load correspondence between the hovering propeller disk load and the solidity.

5. The method according to claim 1, characterized in that, The calculation of the corresponding critical propeller disk radius based on the target cruise thrust value, the target hovering Mach value, and the cruise Mach number includes: Based on the target hovering Mach value and hovering speed, the corresponding propeller disk radius is determined, and the cruise speed corresponding to the hovering speed is determined according to the ratio between the target cruise thrust value and the target hovering thrust value. The critical propeller disk radius value is calculated based on the cruise speed, the cruise Mach number, and the propeller disk radius.

6. The method according to claim 1, characterized in that, The initial hovering rotor disk load range is divided based on the target hovering rotor disk load value to obtain the target hovering rotor disk load range, including: Based on the initial hovering disk load range, the maximum initial hovering disk load value is determined, and based on the maximum initial hovering disk load value and the target hovering disk load value, the target hovering disk load range is determined.

7. The method according to claim 1, characterized in that, The step of calculating the target rotor radius, target chord length, and target solidity value based on the ratio between the target hovering pull force value and the target hovering rotor disk load range includes: Based on the target hovering pull value and the target hovering propeller disk load range, calculate the corresponding target propeller disk radius value, and determine the corresponding target chord length value based on the ratio between the target propeller disk radius value and the target blade slenderness ratio; The target solidity value is calculated based on the target chord length, the target propeller disk radius, and the number of propeller blades.

8. A device for determining propeller design parameters, characterized in that, The device includes: The calculation module is used to determine the corresponding target hovering Mach value based on the initial airfoil parameter value and the target motor torque value, and to calculate the solidity corresponding to the hovering rotor disk load based on the target hovering thrust value and the target hovering Mach value, so as to obtain the load correspondence between the hovering rotor disk load and the solidity. The substitution module is used to calculate the corresponding solidity interval based on the target blade slenderness ratio and the target number of blades, and substitute the solidity interval into the load correspondence to obtain the corresponding initial hovering disk load interval. The determination module is used to calculate the corresponding critical propeller disk radius value based on the target cruise thrust value, the target hovering Mach value, and the cruise Mach number, and to determine the target hovering propeller disk load value based on the critical propeller disk radius value and the target hovering thrust value. The segmentation module is used to segment the initial hovering disk load range based on the target hovering disk load value to obtain the target hovering disk load range, and to calculate the target disk radius value, target chord length value and target solidity value according to the ratio between the target hovering thrust value and the target hovering disk load range.

9. A computer device, characterized in that, include: One or more processors; Memory; One or more programs, wherein the one or more programs are stored in memory and configured to be executed by one or more processors, the one or more programs being configured to perform the method as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores program code that can be called by a processor to perform the method as described in any one of claims 1 to 7.

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