Method, device, storage medium and electronic equipment for determining design parameters of a tiltrotor aircraft

Abstract

The present disclosure provides a method and device for determining design parameters of a tilt-rotor aircraft, a storage medium and an electronic device. The method comprises: considering a vertical take-off and landing mode and a flat flight mode of the tilt-rotor aircraft, and determining a maximum take-off weight of the tilt-rotor aircraft. The embodiments of the present disclosure can effectively guide the overall design of the tilt-rotor aircraft.

Description

Technical Field

[0001] This disclosure relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a method, apparatus, computer program product, non-transitory computer-readable storage medium, and electronic device for determining the design parameters of a tiltrotor aircraft. Background Technology

[0002] Tiltrotor aircraft, as a multi-functional aircraft, possess the capabilities of vertical takeoff and landing and horizontal flight, and have broad application prospects. When the rotor is in a vertical position, the aircraft is similar to a helicopter, capable of hovering, side-flying, rear-flying, and vertical takeoff and landing. When the rotor is in a horizontal position, the aircraft is similar to a fixed-wing aircraft, capable of high-speed, long-range flight.

[0003] Existing general design methods for fixed-wing aircraft are mainly for fixed-wing aircraft with horizontal take-off and landing configurations, while existing general design methods for helicopters are mainly for helicopters without fixed wings and whose rotors cannot be tilted. Neither of these conventional methods can be used to guide the design of tiltrotor aircraft, especially the maximum take-off weight of tiltrotor aircraft, resulting in a lack of guidance and low efficiency in the design of tiltrotor aircraft.

[0004] Therefore, it is necessary to propose a new technical solution to solve at least one of the above-mentioned technical problems. Summary of the Invention

[0005] This disclosure is made in order to overcome at least one aspect of the technical problems in the prior art.

[0006] According to one aspect of the embodiments of this disclosure, a method for determining the design parameters of a tiltrotor aircraft is proposed, comprising: determining the maximum takeoff weight of the tiltrotor aircraft by considering the vertical takeoff and landing mode and the level flight mode of the tiltrotor aircraft.

[0007] According to another aspect of the embodiments of this disclosure, a device for determining the design parameters of a tiltrotor aircraft is provided for: determining the maximum takeoff weight of the tiltrotor aircraft, taking into account the vertical takeoff and landing mode and the level flight mode of the tiltrotor aircraft.

[0008] According to another aspect of the embodiments of the present disclosure, a computer program product is provided, including program code instructions that, when executed by a computer, cause the computer to perform the method described according to the first aspect of the embodiments of the present disclosure.

[0009] According to another aspect of the embodiments of the present disclosure, a non-transitory computer-readable storage medium storing computer instructions, wherein the computer instructions are configured to cause the computer to perform the method described according to the first aspect of the embodiments of the present disclosure.

[0010] According to another aspect of the embodiments of the present disclosure, an electronic device is provided, comprising: a processor; a memory in electronic communication with the processor; and instructions stored in the memory and executable by the processor to cause the electronic device to perform the method according to the first aspect of the embodiments of the present disclosure. Attached Figure Description

[0011] The above and other aspects and features of this disclosure will become clear from the following description of embodiments taken in conjunction with the accompanying drawings, wherein:

[0012] Figure 1 This is a flowchart of a method for determining the design parameters of a tiltrotor aircraft according to an embodiment of the present disclosure;

[0013] Figure 2 This is a schematic diagram of the wing layout of a tiltrotor aircraft according to an embodiment of the present disclosure;

[0014] Figure 3 This is a flowchart illustrating a specific example of a method for determining design parameters of a tiltrotor aircraft according to an embodiment of the present disclosure;

[0015] Figure 4 This is a schematic block diagram of a device for determining the design parameters of a tiltrotor aircraft according to an embodiment of the present disclosure. Detailed Implementation

[0016] The following description of embodiments of the present disclosure with reference to the accompanying drawings is intended to explain the overall inventive concept of the present disclosure and should not be construed as a limitation thereof. All other embodiments obtained by those skilled in the art based on the embodiments in this disclosure are within the scope of protection of this disclosure.

[0017] The embodiments disclosed herein do not limit the execution order of each step, and the execution order of each step may be changed where feasible.

[0018] A tiltrotor aircraft is an aircraft that has both a fixed wing (also referred to as a "wing" in this disclosure) and a rotor, and the rotor's axis of rotation is tiltable relative to the fuselage. Figure 2 This is a schematic diagram of the wing configuration of a tiltrotor aircraft according to an embodiment of the present disclosure. Figure 2 As shown, the tiltrotor aircraft includes a fuselage 40, wings 10 and 20, and a rotor 30. Wings 10 and 20 are fixedly connected to the fuselage 40. The rotor 30 is mounted on the wings 10 and 20. The axis of the rotor 30 is tiltable relative to the fuselage 40, wings 10 and 20. In the figure, the axis of the rotor 30 is in a horizontal position, which can be used for level flight. Furthermore, although not shown, the axis of the rotor 30 can also be in a vertical position, which can be used for vertical takeoff and landing.

[0019] Optionally, there may be multiple rotors 30, distributed on wings 10 and 20, forming a distributed propulsion structure. Using multiple rotors 30 can achieve the following effects: (1) The diameter of each rotor is reduced, thereby reducing the downwash airflow of each rotor on the wing / fuselage, reducing thrust loss and adverse interference; (2) The pitch and roll control forces of the distributed rotors are stronger, and a reasonable tilt angle can also obtain a stronger yaw control force, resulting in stronger attitude control capability of the aircraft; (3) If some rotors fail, the remaining rotors can ensure safe flight, thereby achieving safety redundancy.

[0020] Optionally, the wing 10 includes two wings arranged along the length of the fuselage 40, namely the canard 10 and the aft 20, thus forming a "tandem wing" configuration. Furthermore, although not shown, the tiltrotor aircraft may include more pairs of wings. The tandem wing configuration achieves the following effects: (1) more flexible design of the center of gravity and wing positions, facilitating distributed power arrangement; (2) a smaller wingspan for the same takeoff weight, and the reduced overall dimensions are beneficial for the applicability of vertical takeoff and landing sites.

[0021] The overall design of an aircraft is the process of determining the overall design scheme of the aircraft based on known design requirements and design parameters.

[0022] In the prior art, there is a lack of methods to guide the overall design of tiltrotor aircraft. To address this, this disclosure provides a method for determining the design parameters of a tiltrotor aircraft, including: considering the vertical takeoff and landing (VTOL) mode and the horizontal flight mode of the tiltrotor aircraft, and determining the maximum takeoff weight of the tiltrotor aircraft. This method, based on the VTOL mode and the horizontal flight mode, determines the aircraft parameters and can effectively guide the overall design of the tiltrotor aircraft.

[0023] In the embodiments of this disclosure, vertical takeoff and landing mode refers to the operating state of a tiltrotor aircraft where the rotor is in or near a vertical position, and the corresponding flight phases include, for example, takeoff, landing, or hovering. Level flight mode refers to the operating state of a tiltrotor aircraft where the rotor is in or near a horizontal position, and the corresponding flight phases include, for example, cruise.

[0024] Figure 1 This is a flowchart of a method for determining the design parameters of a tiltrotor aircraft according to an embodiment of the present disclosure.

[0025] like Figure 1 As shown, the method 100 includes the following steps 110-130:

[0026] Step 110: Determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode, and determine the power requirement of the tiltrotor aircraft in level flight mode.

[0027] In embodiments of this disclosure, the power requirement of a tiltrotor aircraft in vertical takeoff and landing mode can be determined, exemplarily, based on the momentum blade element method. The power requirement of a tiltrotor aircraft in level flight mode can be determined, exemplarily, based on lift line theory.

[0028] In some embodiments of this disclosure, the tiltrotor aircraft employs a tandem wing configuration. In this regard, step 120 may further include: considering the effect of the downwash airflow caused by the canard on the aft wing of at least two wings, to determine the power requirement of the tiltrotor aircraft in level flight mode. This method enables a more accurate determination of the power requirement of the tiltrotor aircraft in level flight mode.

[0029] In some embodiments of this disclosure, the step of "considering the influence of the downwash airflow caused by the forewing of at least two wings on the rear wing and determining the required power of the tiltrotor aircraft in level flight mode" may further include: first, considering the influence of the downwash airflow caused by the forewing of at least two wings on the rear wing and determining the drag coefficient of the wing; second, determining the required power of the tiltrotor aircraft in level flight mode based on the drag coefficient of the wing.

[0030] In some embodiments of this disclosure, the step of "considering the influence of the downwash airflow caused by the canard in at least two wings on the aft wing and determining the drag coefficient of the wing" may further include: first, considering the influence of the free vortex of the canard on the aft wing and determining the first induced velocity of the aft wing; second, considering the influence of the attached vortex of the canard on the aft wing and determining the second induced velocity of the aft wing; then, determining the induced drag coefficient of the aft wing based on the first induced velocity and the second induced velocity; and finally, determining the drag coefficient of the wing based on the induced drag of the aft wing.

[0031] The steps described above, such as "determining the drag coefficient of the wing based on the induced drag of the rear wing", include, for example, obtaining the drag coefficient of the wing based on the induced drag coefficient of the rear wing, the induced drag coefficient of the canard (considering only the canard's own factors), and the zero-lift drag coefficient of the aircraft (obtained based on empirical values).

[0032] Step 120: Determine the weight of the power battery of the tiltrotor aircraft based on the power requirements of the tiltrotor aircraft in vertical take-off and landing mode and level flight mode, as well as the range index of the tiltrotor aircraft.

[0033] For example, the weight of the power battery can be determined according to the following formula:

[0034]

[0035] Among them, W bLet E be the weight of the power battery, E be the total output energy requirement of the power battery, and η be the total output energy requirement of the power battery. bto Here, e represents the depth of discharge of the power battery (exemplarily taken as 90%), and e represents the specific energy of the power battery pack. The total output energy requirement of the power battery can be determined based on the power demand of each flight phase in the flight profile.

[0036] In an optional embodiment, the weight of the power battery can be determined as follows: Based on the power requirements of the tiltrotor aircraft in vertical takeoff and landing mode and in level flight mode, and the flight profile of the tiltrotor aircraft, the required power for each flight phase is determined; based on the required power for each flight phase and the range index of the tiltrotor aircraft, the weight of the power battery is determined; and based on the weight of the power battery, the maximum takeoff weight is determined. Here, the flight profile is used to describe the flight path corresponding to a specific mission. Exemplarily, the aircraft's flight profile may include multiple flight phases, such as the pre-flight check phase, vertical takeoff and tilt transition phase, climb phase, cruise phase, descent phase, and tilt transition and vertical landing phase. Exemplarily, referring to step 110, the power consumption for each flight phase can be determined, thereby determining the weight of the power battery.

[0037] In one example, the power requirements for each flight phase are P1, P2, ..., P... n Based on the flight profile and the range specifications of the tiltrotor aircraft, the distances for each flight phase can be determined as S1, S2...S... n By combining the flight speeds of each flight phase, the flight times of each flight phase can be determined as t1, t2, ..., tt. n Therefore, the total output energy demand of the power battery can be obtained as P1t1 + P2t2 + ... + P n t n .

[0038] Step 130: Determine the maximum takeoff weight of the tiltrotor aircraft based on the weight of its power system.

[0039] In the embodiments of this disclosure, the maximum takeoff weight includes the power system weight. Furthermore, the maximum takeoff weight may also include the mission payload weight, structural weight, landing gear weight, power battery weight, avionics system weight, electrical system weight, tilt system weight, and unpredictable weight.

[0040] For example, the equipment models for the avionics system, electrical system, and tilt system are pre-selected, thereby determining the weights of the avionics system, electrical system, and tilt system. Landing gear and unpredictable weights can be calculated based on the maximum takeoff weight (determined as described below) and empirical weight coefficients. The weight coefficient for the landing gear is, for example, 1%-5%, specifically 1.5%. The weight coefficient for unpredictable weights is, for example, 1%-5%, specifically 2.5%. Structural weights include wing weight, fuselage weight, tail weight, and engine nacelle weight. The wing, fuselage, and tail weight models are determined using empirical formulas, while the engine nacelle weight is given based on the preliminary design. For example, the wing and fuselage weights refer to the USAF method in the section on weight estimation methods for general aviation aircraft in the Aircraft Design Manual, and the tail weight can refer to the migratory bird method. The engine nacelle weight can be taken as an empirical value, for example, 40 kg. The battery weight can be determined based on the energy consumption at each stage of the flight envelope.

[0041] In an optional embodiment, step 130 may further include: determining the power system weight of the tiltrotor aircraft based on the power requirements of the tiltrotor aircraft in vertical takeoff and landing mode and the power requirements of the tiltrotor aircraft in level flight mode; and determining the maximum takeoff weight based on the power system weight and the weight of the power battery.

[0042] In an optional embodiment, the propulsion system of the tiltrotor aircraft needs to meet the power requirements of the tiltrotor aircraft in vertical takeoff and landing mode and in level flight mode. The usable target propulsion system can be determined from one or more candidate propulsion systems by combining their output power.

[0043] For example, if the power requirement of a tiltrotor aircraft in vertical takeoff and landing mode is 15kW and the power requirement of a tiltrotor aircraft in level flight mode is 18kW, the output power of the three candidate power systems is 15kW, 20kW and 30kW respectively. The power system that meets the power requirement while having the smaller power, i.e. the power system with an output power of 20kW, can be selected as the target power system.

[0044] In an optional embodiment, the tiltrotor aircraft's propulsion system is a motor. Further optionally, the tiltrotor aircraft may include multiple motors. The required power for a single motor can be determined based on the total required power and the number of motors, thereby identifying the target motor.

[0045] In an optional embodiment, when determining the propulsion system, in addition to considering the aircraft's power requirements, its torque requirements can also be considered. These torque requirements can be determined based on the rotor tip speed. The rotor tip speed can be determined based on the rotor diameter (determined as described below) and the rotor speed (obtained empirically).

[0046] In an optional embodiment, when determining the power system, in addition to considering the aircraft's power requirements, the aircraft's hovering time requirements are also considered. For example, the relationship between temperature rise per unit time and motor torque can be fitted based on test data of candidate power motors, and the temperature rise per unit time of the candidate power motor can be determined based on the torque requirements mentioned above. Combined with a given hovering time, it can be determined whether the temperature rise of the candidate power motor exceeds a set threshold, thereby determining whether the candidate power motor meets the hovering time requirements.

[0047] Once the target power system is determined, its weight can be obtained.

[0048] In the embodiments of this disclosure, after determining the maximum takeoff weight, the wing area, wing aspect ratio, rotor diameter, and power system torque of the tiltrotor aircraft can be further determined.

[0049] In an optional embodiment, the method for determining the design parameters of the tiltrotor aircraft in this disclosure can be performed in a cyclic iterative manner, wherein each cycle includes the following steps:

[0050] Step 1: Set the initial value for the maximum takeoff weight.

[0051] For example, the initial value of the maximum takeoff weight can be determined based on an empirical range of the maximum takeoff weight, either by random selection or by selection according to specific rules.

[0052] The empirical range for maximum takeoff weight can be determined by combining factors such as range and payload, for example, it can be three times the payload specification. For example, the empirical range for maximum takeoff weight under a certain design mission is 100kg-500kg.

[0053] Step 2: Based on the initial value of the maximum takeoff weight, determine the power required by the tiltrotor aircraft in vertical takeoff and landing mode, and determine the power required by the tiltrotor aircraft in level flight mode.

[0054] Step 2 can be found in the description of step 110 above.

[0055] In an optional embodiment, step 2 may further include steps 2.1-2.3:

[0056] Step 2.1: Based on theoretical formulas, determine the wing area using the initial value of the maximum takeoff weight, and combine this with the given aspect ratio to obtain the wing span and chord length. Based on theoretical and empirical formulas, determine the rotor diameter using the initial value of the maximum takeoff weight.

[0057] For example, the wing area can be calculated using the following formula:

[0058] S=2W0g / (ρv c 2 C L )

[0059] Where S is the wing area, W0 is the initial value of the maximum takeoff weight, ρ is the air density, and v c For flight speed, C L This is the lift coefficient.

[0060] For example, the aspect ratio can range from 2 to 10, such as 3.

[0061] For example, the rotor diameter can be calculated using the following formula:

[0062]

[0063] Where D is the rotor diameter, n is the number of rotors, W0 is the initial value of the maximum takeoff weight, and p is the rotor disk load. The disk load can be determined by fitting a formula based on statistical data of rotor disk load and maximum takeoff weight for rotorcraft.

[0064] Step 2.2: Based on theoretical and empirical formulas, determine the induced drag coefficient and lift coefficient of the aircraft according to its span and chord length. For a tandem wing configuration, when determining the induced drag coefficient, consider the effect of the downwash airflow caused by the canard on the aft wing.

[0065] For example, the lift coefficient of an aircraft can be determined based on the Kuta-Zhukovsky lift theorem.

[0066] For example, the effects of the free vortex and attached vortex of the canard and the free vortex of the aft wing can be considered based on the Biot-Saffar law, and these can be superimposed to solve for the induced velocity of the aft wing, thereby determining the induced drag coefficient of the aircraft.

[0067] Step 2.3: Determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode based on the initial value of the maximum takeoff weight, rotor diameter, and flight altitude. Then, determine the required thrust based on the initial value of the maximum takeoff weight, the induced drag coefficient and lift coefficient of the aircraft, the given flight speed, and the given flight altitude. Finally, determine the power requirement of the tiltrotor aircraft in level flight mode based on the required thrust, rotor diameter, and flight altitude.

[0068] For example, the power requirement of a tiltrotor aircraft in vertical takeoff and landing mode can be determined based on the momentum blade element method. For example, the power requirement of a tiltrotor aircraft in level flight mode can be determined based on the lift line theory.

[0069] Step 3: Determine the weight of the tiltrotor's power battery based on the power requirements of the tiltrotor in vertical takeoff and landing mode, the power requirements of the tiltrotor in level flight mode, and the range of the tiltrotor.

[0070] For step 3, please refer to the description of step 120 above.

[0071] Step 4: Determine the iterative value of the maximum takeoff weight based on the weight of the power battery of the tiltrotor aircraft.

[0072] Step 4 can refer to the description of step 130 above.

[0073] Step 5: Determine whether the iterative value of the maximum takeoff weight meets the convergence requirement based on the difference between the initial value of the maximum takeoff weight and the iterative value of the maximum takeoff weight.

[0074] In the embodiments of this disclosure, the convergence requirement of the iterative value of the maximum takeoff weight means that the initial value of the maximum takeoff weight and the iterative value of the maximum takeoff weight are sufficiently close, and the iteration result achieves convergence.

[0075] For example, the relative difference between the iterative value of the maximum takeoff weight and the initial value of the maximum takeoff weight can be calculated (the difference between the iterative value and the initial value divided by the initial value). If the relative difference is less than a preset threshold (e.g., 0.00001), then the iterative value of the maximum takeoff weight is determined to meet the convergence requirement.

[0076] In an optional embodiment, step 6 may be included after step 5:

[0077] Based on the iterative value of the maximum takeoff weight that meets the convergence requirements, the wing area, wing aspect ratio, rotor diameter, and power system torque of the tiltrotor aircraft are determined. The methods for determining the wing area, wing aspect ratio, and rotor diameter can be found in step 2.1. The method for determining the power system torque can be found in the description of the aircraft's torque requirements above.

[0078] Figure 3 This is a flowchart illustrating a specific example of a method for determining design parameters of a tiltrotor aircraft according to an embodiment of the present disclosure. This example is used for the overall design of a tandem-wing tiltrotor aircraft, wherein the rotors are driven by electric motors.

[0079] like Figure 3As shown, in this example, the design requirements include: payload capacity, range, sea-level cruising speed, maximum level flight speed at sea level, maximum hovering altitude without ground effect, and sea-level hovering time. Design variables (i.e., design parameters) include: maximum takeoff weight, wing area, wing aspect ratio, rotor diameter, and required motor torque.

[0080] like Figure 3 As shown, this example is executed based on a loop iteration method, and each loop process includes the following steps:

[0081] (1) Input the initial value of the maximum takeoff weight.

[0082] (2) Establishing and running the dimensional model, including: determining the wing area and aspect ratio based on theoretical and empirical formulas and the initial value of the maximum takeoff weight, thereby obtaining the wing span and chord length. Determining the rotor diameter based on empirical formulas and the initial value of the maximum takeoff weight. This step can be found in the description of step 2.1 above.

[0083] (3) Establish and run a fixed-wing aerodynamic model, including: determining the induced drag coefficient and lift coefficient of the aircraft based on theoretical and empirical formulas, according to the span and chord length. For a tandem wing configuration, when determining the induced drag coefficient of the aircraft, the influence of the downwash airflow caused by the canard on the aft wing is considered.

[0084] (4) Establish and run the power model, including:

[0085] The characteristic point power calculation includes the subdivisions of hovering at sea level and hovering in high-altitude areas under the vertical takeoff and landing (VTOL) mode, and the subdivisions of cruise flight at sea level and maximum speed level flight under the level flight mode. For VTOL mode, the required power is determined based on the initial value of the maximum takeoff weight, rotor diameter, and flight altitude. For level flight mode, the required thrust is first determined based on the initial value of the maximum takeoff weight, the induced drag coefficient and lift coefficient of the aircraft, the given flight speed, and the given flight altitude. Then, the required power is determined based on the required thrust, rotor diameter, and flight altitude. This step is explained in the description of step 110 above.

[0086] Flight profile power calculation includes: calculating the required power for each stage of the pre-flight check phase, vertical takeoff and tilt transition phase, climb phase, cruise phase, descent phase, tilt transition and vertical landing phase, referring to the power calculation method of the above characteristic points.

[0087] The power calculation methods for each flight stage can be found in the power calculation steps for the characteristic points mentioned above. The corresponding climb and descent times are calculated based on the flight altitude and speed, and the level flight time is calculated based on the range requirements. Thus, the energy consumption for each stage is calculated, and the weight of the power battery is obtained by dividing by the battery specific energy.

[0088] The calculation of hovering time at sea level includes: fitting the relationship between temperature rise per unit time and motor torque based on the test data of candidate power motors, determining the temperature rise per unit time of candidate power motors based on the torque requirements mentioned above, and determining whether the temperature rise of candidate power motors exceeds the set threshold based on the given hovering time, thereby determining whether candidate power motors meet the hovering time requirements.

[0089] For example, since motor torque is proportional to current and approximately quadratic to heat generation per unit time, the relationship between temperature rise per unit time and motor torque can be fitted based on bench test results, thereby determining the hovering time in multi-rotor mode.

[0090] The target motor must meet the power requirements at each characteristic point, the power requirements at each stage of the flight profile, and the sea-level hovering time requirement. Based on the results of the power calculations for the characteristic points, the flight profile, and the sea-level hovering time, the target motor is determined. This step is described in the preceding section on step 120.

[0091] (5) Establishing and running the weight model, including: determining the iterative value of the maximum takeoff weight based on the weight of each system. The weights of the aforementioned systems include mission payload weight, structural weight, landing gear weight, power system weight, battery weight, avionics system weight, electrical system weight, tilt system weight, and unpredictable weight. The power system weight can be determined based on the weight of the selected target motor, and the battery weight can be determined based on the power requirements of each flight phase in the flight profile. This step is similar to the description of step 130 above.

[0092] For each iteration, determine whether the iterative value of the maximum takeoff weight satisfies the convergence condition (e.g., the relative difference is less than 0.00001). If convergence is achieved, the design value of the maximum takeoff weight is obtained; otherwise, the average of the iterative value of the maximum takeoff weight in this iteration and the initial value is used as the initial value of the maximum takeoff weight in the next iteration, and the iteration process continues.

[0093] It is easy to understand that in a single cycle that obtains the design value of the maximum takeoff weight, the design values ​​of other design parameters can be obtained simultaneously.

[0094] Figure 4 This is a schematic block diagram of a device for determining design parameters of a tiltrotor aircraft according to an embodiment of the present disclosure. The device 400 is used to: determine the maximum takeoff weight of the tiltrotor aircraft, taking into account its vertical takeoff and landing modes and level flight modes.

[0095] like Figure 4As shown, the device 400 includes: a power demand determination module 410, used to determine the power demand of the tiltrotor aircraft in vertical takeoff and landing mode and the power demand of the tiltrotor aircraft in level flight mode; a power battery determination module 420, used to determine the weight of the power battery of the tiltrotor aircraft based on the power demand of the tiltrotor aircraft in vertical takeoff and landing mode, the power demand of the tiltrotor aircraft in level flight mode, and the range index of the tiltrotor aircraft; and a maximum takeoff weight determination module 430, used to determine the maximum takeoff weight of the tiltrotor aircraft based on the weight of the power battery of the tiltrotor aircraft.

[0096] It should be understood that Figure 4 The various modules of the device 400 shown can be connected to the reference. Figure 1 The steps in method 100 described correspond to each other. Therefore, the operations, features, and advantages described above for method 100 also apply to device 400 and its included modules. For the sake of brevity, some operations, features, and advantages will not be repeated here.

[0097] In an optional embodiment, the power battery determination module 420 is further configured to: determine the required power for each flight stage based on the required power of the tiltrotor aircraft in vertical take-off and landing mode and the required power of the tiltrotor aircraft in level flight mode, as well as the flight profile of the tiltrotor aircraft; and determine the weight of the power battery based on the required power for each flight stage and the range index of the tiltrotor aircraft.

[0098] In an optional embodiment, the device 400 further includes a loop module for: setting an initial value for the maximum takeoff weight; determining the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode and the power requirement of the tiltrotor aircraft in level flight mode based on the initial value of the maximum takeoff weight; determining the weight of the tiltrotor aircraft's power battery based on the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode, the power requirement of the tiltrotor aircraft in level flight mode, and the range index of the tiltrotor aircraft; determining an iterative value of the maximum takeoff weight based on the weight of the tiltrotor aircraft's power battery; and determining whether the iterative value of the maximum takeoff weight meets the convergence requirement based on the difference between the initial value of the maximum takeoff weight and the iterative value of the maximum takeoff weight.

[0099] In an optional embodiment, the loop module is further configured to: determine the wing span and chord length, and the rotor diameter, based on an initial value of the maximum takeoff weight; determine the wing drag coefficient based on the wing span and chord length; determine the required power of the tiltrotor aircraft in vertical takeoff and landing mode based on the initial value of the maximum takeoff weight and the rotor diameter; and determine the required power of the tiltrotor aircraft in level flight mode based on the initial value of the maximum takeoff weight and the wing drag coefficient.

[0100] In an optional embodiment, the tiltrotor aircraft's wings include at least two wings distributed along the length of the fuselage; the power demand determination module 410 is further configured to: consider the influence of the downwash airflow caused by the forewing of the at least two wings on the rearwing, and determine the power demand of the tiltrotor aircraft in level flight mode.

[0101] In an optional embodiment, the power demand determination module 410 is further configured to: consider the influence of the downwash airflow caused by the canard on the aft wing of the at least two wings, and determine the drag coefficient of the wings; and determine the power demand of the tiltrotor aircraft in level flight mode based on the drag coefficient of the wings.

[0102] In an optional embodiment, the power demand determination module 410 is further configured to: determine a first induced velocity of the rear wing by considering the influence of the free vortex of the canard on the rear wing; determine a second induced velocity of the rear wing by considering the influence of the attached vortex of the canard on the rear wing; determine the induced drag coefficient of the rear wing based on the first induced velocity and the second induced velocity; and determine the drag coefficient of the wing based on the induced drag of the rear wing.

[0103] In an optional embodiment, the tiltrotor aircraft includes a power battery; the maximum takeoff weight determination module 430 is further configured to: determine the weight of the power system of the tiltrotor aircraft based on the power requirements of the tiltrotor aircraft in vertical takeoff and landing mode and the power requirements of the tiltrotor aircraft in level flight mode; and determine the maximum takeoff weight based on the weight of the power system and the weight of the power battery.

[0104] In an optional embodiment, the device 400 further includes a design parameter determination module for determining at least one of the following: wing area, wing aspect ratio, rotor diameter, and power system torque of the tiltrotor aircraft, based on the maximum takeoff weight of the tiltrotor aircraft.

[0105] In an optional embodiment, the flight profile described above includes at least one of the following flight phases: pre-flight inspection phase, vertical takeoff and tilt transition phase, climb phase, cruise phase, descent phase, tilt transition and vertical landing phase.

[0106] In optional embodiments, the design requirements of the above design method include at least one of the following: payload capacity, range, sea-level cruising speed, maximum level flight speed at sea level, maximum hovering altitude without ground effect, and sea-level hovering time; and / or the design parameters of the above method include at least one of the following: maximum takeoff weight, wing area, wing aspect ratio, rotor diameter, and motor torque required.

[0107] In optional embodiments, the above-mentioned vertical take-off and landing modes include hovering at sea level and hovering in high-altitude areas, and / or the above-mentioned level flight modes include cruising at sea level and level flight at maximum speed.

[0108] In an optional embodiment, the maximum takeoff weight determination module 430 is further configured to: fit the relationship between temperature rise per unit time and torque based on the test data of the candidate power system, determine the temperature rise per unit time of the candidate power system based on the torque requirement of the power system, determine whether the temperature rise of the candidate power system exceeds a set threshold in combination with the given hovering time, and then determine whether the candidate power system meets the hovering time requirement; if the candidate power system meets the hovering time requirement, obtain the power system weight of the tiltrotor aircraft based on the weight of the candidate power system.

[0109] This disclosure also provides a computer program product, including program code instructions, which, when executed by a computer, cause the computer to perform the method described above.

[0110] This disclosure also provides a non-transitory computer-readable storage medium storing computer instructions, wherein the computer instructions are used to cause the computer to perform the methods described above.

[0111] This disclosure also provides an electronic device, including: a processor, a memory that communicates electronically with the processor, and instructions stored in the memory and executable by the processor to cause the electronic device to perform the methods described above.

[0112] For details and technical effects of the computer program product, the non-transitory computer-readable storage medium storing computer instructions, and the electronic device of the present disclosure, please refer to the above description of the method for determining the design parameters of a tiltrotor aircraft, which will not be repeated here.

[0113] Based on the above, this disclosure proposes the following technical solution:

[0114] 1. A method for determining the design parameters of a tiltrotor aircraft, comprising:

[0115] Considering the vertical takeoff and landing mode and the level flight mode of the tiltrotor aircraft, determine the maximum takeoff weight of the tiltrotor aircraft.

[0116] 2. According to the method described in 1, the step of determining the maximum takeoff weight of the tiltrotor aircraft by considering its vertical takeoff and landing mode and level flight mode includes:

[0117] Determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode, and determine the power requirement of the tiltrotor aircraft in level flight mode;

[0118] The weight of the power battery of the tiltrotor aircraft is determined based on the power requirements of the tiltrotor aircraft in vertical take-off and landing mode, the power requirements of the tiltrotor aircraft in level flight mode, and the range index of the tiltrotor aircraft.

[0119] The maximum takeoff weight of the tiltrotor aircraft is determined based on the weight of its power battery.

[0120] 3. According to the method described in 2, wherein determining the weight of the power system battery of the tiltrotor aircraft based on the power requirements of the tiltrotor aircraft in vertical takeoff and landing mode, the power requirements of the tiltrotor aircraft in level flight mode, and the range index of the tiltrotor aircraft includes:

[0121] Based on the power requirements of the tiltrotor aircraft in vertical takeoff and landing mode and in level flight mode, as well as the flight profile of the tiltrotor aircraft, the power requirements for each flight stage are determined.

[0122] The weight of the power battery is determined based on the power requirements of each flight phase and the range of the tiltrotor aircraft.

[0123] 4. The method according to 1, wherein the step of determining the maximum takeoff weight of the tiltrotor aircraft, considering the vertical takeoff and landing mode and the level flight mode of the tiltrotor aircraft, is performed based on at least one cyclic process, each of the cyclic processes comprising:

[0124] Set the initial value for the maximum takeoff weight;

[0125] Based on the initial value of the maximum takeoff weight, determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode, and determine the power requirement of the tiltrotor aircraft in level flight mode;

[0126] The weight of the power battery of the tiltrotor aircraft is determined based on the power requirements of the tiltrotor aircraft in vertical take-off and landing mode, the power requirements of the tiltrotor aircraft in level flight mode, and the range index of the tiltrotor aircraft.

[0127] Based on the weight of the power battery of the tiltrotor aircraft, determine the iterative value of the maximum takeoff weight;

[0128] Based on the difference between the initial value of the maximum takeoff weight and the iterative value of the maximum takeoff weight, it is determined whether the iterative value of the maximum takeoff weight meets the convergence requirement.

[0129] 5. According to the method described in 4, determining the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode and determining the power requirement of the tiltrotor aircraft in level flight mode based on the initial value of the maximum takeoff weight includes:

[0130] Based on the initial value of the maximum takeoff weight, determine the wing span and chord length, as well as the rotor diameter;

[0131] The drag coefficient of the wing is determined based on its span and chord length.

[0132] Based on the initial value of the maximum takeoff weight and the rotor diameter, determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode;

[0133] Based on the initial value of the maximum takeoff weight and the drag coefficient of the wing, the power requirement of the tiltrotor aircraft in level flight mode is determined.

[0134] 6. The method according to any one of 1-2, wherein the wings of the tiltrotor aircraft include at least two wings distributed along the length of the fuselage;

[0135] Determining the power requirement of the tiltrotor aircraft in level flight mode includes:

[0136] Considering the effect of the downwash airflow caused by the forewing of the at least two wings on the aft wing, determine the power requirement of the tiltrotor aircraft in level flight mode.

[0137] 7. The method according to 6, wherein determining the power requirement of the tiltrotor aircraft in level flight mode by considering the effect of the downwash airflow caused by the canard of the at least two wings on the aft wing includes:

[0138] Considering the effect of the downwash airflow caused by the canard on the aft wing in the at least two wings, determine the drag coefficient of the wings;

[0139] Based on the drag coefficient of the wing, the power requirement of the tiltrotor aircraft in level flight mode is determined.

[0140] 8. The method according to 7, wherein determining the drag coefficient of the wing by considering the effect of the downwash airflow caused by the canard of the at least two wings on the aft wing includes:

[0141] Considering the effect of the free vortex of the canard on the aft wing, determine the first induced velocity of the aft wing;

[0142] Considering the effect of the attached vortex of the forewing on the aft wing, determine the second induced velocity of the aft wing;

[0143] The induced drag coefficient of the rear wing is determined based on the first induced velocity and the second induced velocity.

[0144] The drag coefficient of the wing is determined based on the induced drag of the rear wing.

[0145] 9. The method according to 2 or 3, wherein determining the maximum takeoff weight based on the weight of the power battery of the tiltrotor aircraft further includes:

[0146] The weight of the power system of the tiltrotor aircraft is determined based on the power requirements of the tiltrotor aircraft in vertical take-off and landing mode and the power requirements of the tiltrotor aircraft in level flight mode.

[0147] The maximum takeoff weight is determined based on the weight of the power system and the weight of the power battery.

[0148] 10. The method according to 3, wherein the flight profile includes at least one of the following flight phases: pre-flight inspection phase, vertical takeoff and tilt transition phase, climb phase, cruise phase, descent phase, tilt transition and vertical landing phase.

[0149] 11. The method according to 1, wherein after determining the maximum takeoff weight of the tiltrotor aircraft, the method further includes:

[0150] Based on the maximum takeoff weight of the tiltrotor aircraft, determine at least one of the following: wing area, wing aspect ratio, rotor diameter, and power system torque of the tiltrotor aircraft.

[0151] 12. The method according to 1, wherein the design requirements of the design method include at least one of the following: payload capacity, range, sea-level cruising speed, maximum level flight speed at sea level, maximum hovering altitude without ground effect, and sea-level hovering time; and / or

[0152] The design parameters of the method include at least one of the following: maximum takeoff weight, wing area, wing aspect ratio, rotor diameter, and motor torque required.

[0153] 13. According to the method described in 1, the vertical take-off and landing mode includes a hovering state at sea level and a hovering state in a plateau region, and / or the level flight mode includes a cruise flight state at sea level and a level flight state at maximum speed.

[0154] 14. The method according to 9, wherein determining the weight of the tiltrotor aircraft's power system based on the tiltrotor aircraft's power requirements in vertical takeoff and landing mode and the tiltrotor aircraft's power requirements in level flight mode includes:

[0155] The relationship between temperature rise per unit time and torque is fitted based on the test data of the candidate power system. The temperature rise per unit time of the candidate power system is determined based on the torque requirement of the power system. Combined with the given hovering time, it is determined whether the temperature rise of the candidate power system exceeds the set threshold, and then it is determined whether the candidate power system meets the hovering time requirement.

[0156] If the candidate propulsion system meets the hovering time requirement, the weight of the tiltrotor aircraft's propulsion system is obtained based on the weight of the candidate propulsion system.

[0157] 15. A device for determining the design parameters of a tiltrotor aircraft, used for:

[0158] Considering the vertical takeoff and landing mode and the level flight mode of the tiltrotor aircraft, determine the maximum takeoff weight of the tiltrotor aircraft.

[0159] 16. The apparatus according to claim 15, wherein the apparatus further comprises:

[0160] The power demand determination module is used to determine the power demand of the tiltrotor aircraft in vertical take-off and landing mode, and to determine the power demand of the tiltrotor aircraft in level flight mode.

[0161] The power battery determination module is used to determine the weight of the power battery of the tiltrotor aircraft based on the power requirements of the tiltrotor aircraft in vertical take-off and landing mode, the power requirements of the tiltrotor aircraft in level flight mode, and the range index of the tiltrotor aircraft.

[0162] The maximum takeoff weight determination module is used to determine the maximum takeoff weight of the tiltrotor aircraft based on the weight of its power battery.

[0163] 17. The apparatus according to claim 15, wherein the apparatus further comprises an iteration module, the iteration module being configured to:

[0164] Set the initial value for the maximum takeoff weight;

[0165] Based on the initial value of the maximum takeoff weight, determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode, and determine the power requirement of the tiltrotor aircraft in level flight mode;

[0166] The weight of the power battery of the tiltrotor aircraft is determined based on the power requirements of the tiltrotor aircraft in vertical take-off and landing mode, the power requirements of the tiltrotor aircraft in level flight mode, and the range index of the tiltrotor aircraft.

[0167] Based on the weight of the power battery of the tiltrotor aircraft, determine the iterative value of the maximum takeoff weight;

[0168] Based on the difference between the initial value of the maximum takeoff weight and the iterative value of the maximum takeoff weight, it is determined whether the iterative value of the maximum takeoff weight meets the convergence requirement.

[0169] 18. The apparatus according to 17, wherein the iteration module is further configured to:

[0170] Based on the initial value of the maximum takeoff weight, determine the wing span and chord length, as well as the rotor diameter;

[0171] The drag coefficient of the wing is determined based on its span and chord length.

[0172] Based on the initial value of the maximum takeoff weight and the rotor diameter, determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode;

[0173] Based on the initial value of the maximum takeoff weight and the drag coefficient of the wing, the power requirement of the tiltrotor aircraft in level flight mode is determined.

[0174] 19. A computer program product comprising program code instructions, wherein when the program product is executed by a computer, the program code instructions cause the computer to perform the method described in any one of 1-14.

[0175] 20. A non-transitory computer-readable storage medium storing computer instructions, wherein the computer instructions are configured to cause the computer to perform the method according to any one of 1-14.

[0176] 21. An electronic device, comprising:

[0177] processor,

[0178] A memory that communicates electronically with the processor; and

[0179] Instructions, which are stored in the memory and can be executed by the processor, to cause the electronic device to perform the method according to any one of 1-14.

[0180] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that variations may be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended text and its equivalents.

Claims

1. A method for determining the design parameters of a tiltrotor aircraft, comprising: Considering the vertical takeoff and landing mode and the level flight mode of the tiltrotor aircraft, determine the maximum takeoff weight of the tiltrotor aircraft; The process includes: Step S1: Determining the power requirements of the tiltrotor aircraft in vertical takeoff and landing mode and in level flight mode; Step S2: Determining the weight of the tiltrotor aircraft's power battery based on the power requirements of the tiltrotor aircraft in vertical takeoff and landing mode, the power requirements of the tiltrotor aircraft in level flight mode, and the range index of the tiltrotor aircraft; Step S3: Determining the maximum takeoff weight of the tiltrotor aircraft based on the weight of its power battery. Step S2 includes: Step S201: Determining the required power for each flight stage based on the power requirements of the tiltrotor aircraft in vertical takeoff and landing mode and in level flight mode, as well as the flight profile of the tiltrotor aircraft; Step S202: Determining the weight of the power battery based on the power requirements for each flight stage and the range index of the tiltrotor aircraft; Step S201 further includes: Determining the induced drag coefficient and lift coefficient of the tiltrotor aircraft based on its span and chord length; wherein, for a tandem wing configuration, the induced drag coefficient is determined based on the influence of the downwash airflow caused by the canard on the aft wing; Step S3 further includes: Step S301: Determine the power system weight of the tiltrotor aircraft based on the power requirements of the tiltrotor aircraft in vertical take-off and landing mode and the power requirements of the tiltrotor aircraft in level flight mode; Step S302: Determine the maximum take-off weight based on the power system weight and the weight of the power battery; The tiltrotor aircraft's wings include at least two wings distributed along the length of the fuselage; Step S1 further includes: considering the influence of the downwash airflow caused by the forewing of the at least two wings on the rear wing, determining the drag coefficient of the wing; and determining the power requirement of the tiltrotor aircraft in level flight mode based on the drag coefficient of the wing; including: step S101: determining the first induced velocity of the rear wing based on the influence of the free vortex of the forewing on the rear wing; step S102: determining the second induced velocity of the rear wing based on the influence of the attached vortex of the forewing on the rear wing; step S103: determining the induced drag coefficient of the rear wing based on the first induced velocity and the second induced velocity; and step S104: determining the drag coefficient of the wing based on the induced drag of the rear wing.

2. The method according to claim 1, wherein, The step of determining the maximum takeoff weight of the tiltrotor aircraft, taking into account its vertical takeoff and landing modes and level flight modes, is performed based on at least one cyclic process, each of which includes: Set the initial value for the maximum takeoff weight; Based on the initial value of the maximum takeoff weight, determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode, and determine the power requirement of the tiltrotor aircraft in level flight mode; The weight of the power battery of the tiltrotor aircraft is determined based on the power requirements of the tiltrotor aircraft in vertical take-off and landing mode, the power requirements of the tiltrotor aircraft in level flight mode, and the range index of the tiltrotor aircraft. Based on the weight of the power battery of the tiltrotor aircraft, determine the iterative value of the maximum takeoff weight; Based on the difference between the initial value of the maximum takeoff weight and the iterative value of the maximum takeoff weight, it is determined whether the iterative value of the maximum takeoff weight meets the convergence requirement.

3. The method according to claim 2, wherein, Based on the initial value of the maximum takeoff weight, determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode, and determine the power requirement of the tiltrotor aircraft in level flight mode, including: Based on the initial value of the maximum takeoff weight, determine the wing span and chord length, as well as the rotor diameter; The drag coefficient of the wing is determined based on its span and chord length. Based on the initial value of the maximum takeoff weight and the rotor diameter, determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode; Based on the initial value of the maximum takeoff weight and the drag coefficient of the wing, the power requirement of the tiltrotor aircraft in level flight mode is determined.

4. The method according to claim 1, wherein, The flight profile includes at least one of the following flight phases: pre-flight inspection phase, vertical takeoff and tilt transition phase, climb phase, cruise phase, descent phase, tilt transition and vertical landing phase.

5. The method according to claim 1, wherein, After determining the maximum takeoff weight of the tiltrotor aircraft, the method further includes: Based on the maximum takeoff weight of the tiltrotor aircraft, determine at least one of the following: wing area, wing aspect ratio, rotor diameter, and power system torque of the tiltrotor aircraft.

6. The method according to claim 1, wherein, The design requirements of the design method include at least one of the following: payload capacity, range, sea-level cruising speed, maximum level flight speed at sea level, maximum hovering altitude without ground effect, and sea-level hovering time; and / or The design parameters of the method include at least one of the following: maximum takeoff weight, wing area, wing aspect ratio, rotor diameter, and motor torque required.

7. The method according to claim 1, wherein, The vertical takeoff and landing modes include hovering at sea level and hovering in high-altitude areas, and / or the level flight modes include cruise flight at sea level and level flight at maximum speed.

8. The method according to claim 1, wherein, The step of determining the weight of the tiltrotor aircraft's power system based on the tiltrotor aircraft's power requirements in vertical takeoff and landing mode and in level flight mode includes: The relationship between temperature rise per unit time and torque is fitted based on the test data of the candidate power system. The temperature rise per unit time of the candidate power system is determined based on the torque requirement of the power system. Combined with the given hovering time, it is determined whether the temperature rise of the candidate power system exceeds a set threshold, and then it is determined whether the candidate power system meets the hovering time requirement. If the candidate power system meets the hovering time requirement, the weight of the power system of the tiltrotor aircraft is obtained based on the weight of the candidate power system.

9. A device for determining the design parameters of a tiltrotor aircraft, used for: Considering the vertical takeoff and landing mode and the level flight mode of the tiltrotor aircraft, determine the maximum takeoff weight of the tiltrotor aircraft; The device further includes: The system includes a power requirement determination module for determining the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode and in level flight mode; a power battery determination module for determining the weight of the power battery of the tiltrotor aircraft based on the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode, the power requirement of the tiltrotor aircraft in level flight mode, and the range index of the tiltrotor aircraft; and a maximum takeoff weight determination module for determining the maximum takeoff weight of the tiltrotor aircraft based on the weight of the power battery of the tiltrotor aircraft. The power battery determination module is further configured to: Step S201: Determine the required power for each flight stage based on the power requirements of the tiltrotor aircraft in vertical take-off and landing mode and the power requirements of the tiltrotor aircraft in level flight mode, as well as the flight profile of the tiltrotor aircraft; Step S202: Determine the weight of the power battery based on the power requirements of each flight stage and the range index of the tiltrotor aircraft; Step S201 further includes: determining the induced drag coefficient and lift coefficient of the tiltrotor aircraft based on the span and chord length; wherein, for a tandem wing configuration, the induced drag coefficient is determined based on the influence of the downwash airflow caused by the canard on the aft wing; The maximum takeoff weight determination module is further used for: step S301: determining the power system weight of the tiltrotor aircraft based on the power requirements of the tiltrotor aircraft in vertical takeoff and landing mode and the power requirements of the tiltrotor aircraft in level flight mode; step S302: determining the maximum takeoff weight based on the power system weight and the weight of the power battery; The tiltrotor aircraft's wings include at least two wings distributed along the length of the fuselage; The power demand determination module is further configured to: consider the influence of the downwash airflow caused by the forewing of the at least two wings on the rear wing, and determine the drag coefficient of the wing; and determine the power demand of the tiltrotor aircraft in level flight mode based on the drag coefficient of the wing; including: step S101: determining the first induced velocity of the rear wing based on the influence of the free vortex of the forewing on the rear wing; step S102: determining the second induced velocity of the rear wing based on the influence of the attached vortex of the forewing on the rear wing; step S103: determining the induced drag coefficient of the rear wing based on the first induced velocity and the second induced velocity; and step S104: determining the drag coefficient of the wing based on the induced drag of the rear wing.

10. The apparatus according to claim 9, wherein, The device further includes an iteration module, the iteration module being used for: Set the initial value for the maximum takeoff weight; Based on the initial value of the maximum takeoff weight, determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode, and determine the power requirement of the tiltrotor aircraft in level flight mode; The weight of the power battery of the tiltrotor aircraft is determined based on the power requirements of the tiltrotor aircraft in vertical take-off and landing mode, the power requirements of the tiltrotor aircraft in level flight mode, and the range index of the tiltrotor aircraft. Based on the weight of the power battery of the tiltrotor aircraft, determine the iterative value of the maximum takeoff weight; Based on the difference between the initial value of the maximum takeoff weight and the iterative value of the maximum takeoff weight, it is determined whether the iterative value of the maximum takeoff weight meets the convergence requirement.

11. The apparatus according to claim 10, wherein, The iteration module is also used for: Based on the initial value of the maximum takeoff weight, determine the wing span and chord length, and determine the rotor diameter; based on the wing span and chord length, determine the wing drag coefficient; Based on the initial value of the maximum takeoff weight and the rotor diameter, determine the power requirement of the tiltrotor aircraft in vertical takeoff and landing mode; Based on the initial value of the maximum takeoff weight and the drag coefficient of the wing, the power requirement of the tiltrotor aircraft in level flight mode is determined.

12. A computer program product comprising program code instructions that, when executed by a computer, cause the computer to perform the method of any one of claims 1-8.

13. A non-transitory computer-readable storage medium storing computer instructions, wherein, The computer instructions are used to cause the computer to perform the method according to any one of claims 1-8.

14. An electronic device comprising: processor, A memory that communicates electronically with the processor; as well as Instructions, which are stored in the memory and can be executed by the processor, to cause the electronic device to perform the method according to any one of claims 1-8.

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