A wind-powered aircraft and its control method

Abstract

This invention discloses a wind-powered aircraft and its control method, belonging to the field of new energy aviation technology, and is adaptable to narrow-body and wide-body civil aircraft as well as medium and large-sized UAVs. The invention retains the original fuselage frame and cabin / payload layout of the aircraft, symmetrically arranging compatible horizontal-axis wind turbines at the original engine locations on the wings. Modular power battery energy storage modules store electricity, and multi-motor drive modules provide flight thrust and attitude control power. Medium and large-sized UAVs can be equipped with electric hubs for zero-emission ground taxiing. A distributed flight control module dynamically allocates power according to flight stage and aircraft type, adjusts wind turbine and motor parameters in real time, and sets differentiated fault protection. This invention integrates wind power generation, energy storage, and multi-motor drive, adapting to all types of aircraft by adjusting component specifications. It solves the problems of high carbon emissions from fuel-powered aircraft, short range of electric aircraft, and insufficient integration of wind power with aviation, possessing advantages such as zero carbon emissions, long range, strong compatibility, low cost, and safety and reliability, providing a universal technical solution for new energy aviation.

Description

Technical Field

[0001] This invention relates to the field of new energy aircraft technology, specifically to a wind-powered aircraft and its control method that are compatible with narrow-body aircraft, wide-body aircraft and medium-to-large-sized UAVs. Background Technology

[0002] With the global energy crisis and environmental problems becoming increasingly severe, traditional fuel-powered aircraft (including narrow-body and wide-body civil aircraft) face numerous pain points such as high carbon emissions, large fluctuations in fuel costs, and reliance on fossil fuels. Medium and large-sized drones mostly use fuel or conventional lithium batteries for propulsion. Fuel-powered drones have significant carbon emission problems, while lithium-ion drones suffer from technical bottlenecks such as short flight time and slow charging. Existing electric aircraft mostly rely on lithium battery energy storage, which also suffers from technical bottlenecks such as short flight time, slow charging, large battery weight, and poor low-temperature performance. Pure solar-powered aircraft are significantly limited by sunlight conditions and cannot achieve stable all-weather flight. Hybrid aircraft still rely on fuel, and their emission reduction effects are limited.

[0003] In the field of ground transportation, wind power has been widely used in scenarios such as auxiliary power supply for new energy vehicles and bicycle assist systems. Its core technologies include high-efficiency wind turbines, electric hub drives, and power battery management, and it has advantages such as being clean, renewable, and having no additional fuel consumption. However, there is currently no mature solution for deeply integrating ground-based wind power technology with aircraft, and there is no universal wind-powered aircraft architecture suitable for narrow-body, wide-body, and medium-to-large-sized UAVs. How to utilize the kinetic energy of airflow during flight to convert into electrical energy to provide continuous power for various aircraft, while solving the power distribution problems in multiple scenarios such as ground taxiing, aerial flight, and attitude control, is a technical challenge that urgently needs to be overcome in this field.

[0004] In existing technologies, some solutions attempt to install small wind turbines on the aircraft surface for auxiliary power supply, but fail to achieve core power drive; some electric aircraft use hub motors for ground taxiing, but these do not form coordinated control with the in-flight propulsion system. This invention addresses these technological gaps by proposing a novel wind-powered aircraft architecture that integrates wind power generation, energy storage, and multi-motor drive, providing a new technological path for new energy aviation. Summary of the Invention

[0005] The purpose of this invention is to provide a wind-powered aircraft and its control method that are compatible with narrow-body aircraft, wide-body aircraft and medium-to-large-sized UAVs, thereby solving the technical problems of high carbon emissions, short range, low integration of wind power technology and lack of universal adaptability architecture in existing aircraft.

[0006] To achieve the above objectives, the present invention provides the following technical solution: A wind-powered aircraft includes a fuselage, a wind power generation module, a power battery energy storage module, a multi-motor drive module, a ground taxiing module, and a flight control module; The main fuselage retains the original aircraft fuselage structure, without altering the fuselage frame and cabin / payload layout, and is compatible with the fuselage architecture of narrow-body aircraft, wide-body aircraft, and medium-to-large-sized UAVs. The wind power generation modules are symmetrically arranged at the original engine installation positions on the wings according to the aircraft model specifications. Narrow-body aircraft are equipped with two medium-sized horizontal axis wind turbines, wide-body aircraft are equipped with two or more medium / large horizontal axis wind turbines, and medium and large UAVs are equipped with one or more horizontal axis wind turbines of the appropriate specifications, which are used to capture air kinetic energy during flight and convert it into electrical energy. The power battery energy storage module replaces the original fuel tank / energy storage area and is used to store the electrical energy generated by the wind turbine. The multi-motor drive module includes a number of wing propulsion motors adapted to the wind power generation module and at least one tail fin attitude control motor, which are used to provide flight thrust and adjust flight attitude, respectively. The ground taxiing module is an electric landing gear hub, which can be selected for medium and large UAVs according to their needs. The flight control module is used to collect flight data in real time and dynamically allocate the power output of the power battery to each motor to achieve full-scenario power control.

[0007] Furthermore, the wind turbine rotor of the wind power generation module is made of lightweight composite material, and the blade angle can be automatically adjusted according to the flight speed and airflow direction. The rotor diameter and rated power are designed to be adapted to the fuselage load and flight requirements. Multiple wind turbines can achieve synchronous or independent parameter adjustment.

[0008] Furthermore, the power battery energy storage module adopts a modular design and is conventionally distributed in the bottom of the fuselage, inside the wings, and in the tail compartment area. The placement of the energy storage module can be adjusted for medium and large UAVs. All energy storage modules are equipped with a thermal management system and a battery management system to achieve comprehensive monitoring of battery temperature, power, and charging / discharging status.

[0009] Furthermore, the wing propulsion motor and tail attitude control motor of the multi-motor drive module are both permanent magnet synchronous motors, which can independently control the speed to achieve differential steering and attitude adjustment. The wing propulsion motors of wide-body aircraft adopt multiple distributed arrangements, and the drive motors of medium and large UAVs are miniaturized and high power density adapted designs.

[0010] Furthermore, the electric wheel hub of the ground taxiing module has a built-in brushless DC motor that integrates drive and braking functions. The electric wheel hub of wide-body aircraft increases the rated power and torque according to the landing gear load, while the electric wheel hub of medium and large UAVs is a miniaturized adaptation design.

[0011] Furthermore, the flight control module adopts a distributed control architecture, which realizes power distribution, attitude adjustment and fault protection through a central control unit. It can be adapted to the control algorithms and power distribution thresholds of narrow-body, wide-body aircraft and medium and large UAVs.

[0012] Furthermore, the power distribution strategy of the flight control module is as follows: during takeoff, power is preferentially allocated to the electric hub and wing propulsion motors, and wide-body aircraft / large UAVs distribute power evenly according to the number of drive motors; during cruise, the battery power is supplemented by wind turbines, and multiple wind turbines work together to maintain stable output of the propulsion motors; during landing, the propulsion motor power is reduced, and electric hub auxiliary braking is activated. Medium and large UAVs can combine propeller reverse thrust to achieve compound braking.

[0013] Furthermore, the wind turbine adopts variable pitch control technology, which can automatically adjust the blade angle according to the flight speed to balance power generation efficiency and wind resistance. Multiple wind turbines can achieve synchronous or independent adjustment of blade angle.

[0014] Furthermore, the power battery energy storage module adopts lithium iron phosphate batteries, solid-state batteries, or other high-energy-density chemical batteries, which have high energy density and wide temperature range operating characteristics, and the total energy storage capacity is designed to be adapted to the model's load and range requirements.

[0015] A control method for a wind-powered aircraft, applied to the wind-powered aircraft according to any one of claims 1-9, includes the following steps: S1. Collect flight data such as flight speed, airflow intensity, remaining battery power, motor speed and aircraft model compatibility parameters; S2. Based on the flight stage and aircraft specifications, dynamically allocate the power output of the power battery to each motor to achieve balanced or differentiated power distribution. S3: Real-time adjustment of wind turbine blade angle and motor speed, with multiple wind turbines coordinating parameter adjustment to balance efficient power generation and stable flight; S4. Monitor the system's operating status, set differentiated fault protection thresholds according to aircraft type, and activate the corresponding protection mechanism when a fault occurs to ensure flight safety.

[0016] Compared with the prior art, the present invention provides a wind-powered aircraft and its control method, which has the following beneficial effects: 1. Zero-carbon and environmentally friendly: Using gas kinetic energy as the core energy source, there is no consumption of fossil fuels and zero carbon emissions throughout the entire process.

[0017] 2. Long-lasting range: Wind power generation continuously replenishes the battery, breaking through the range bottleneck of traditional electric aircraft.

[0018] 3. All-scenario power: Covering all scenarios including ground gliding, aerial flight, and attitude adjustment, with flexible power distribution and high control precision.

[0019] 4. Structural compatibility: Based on the existing chassis, no frame reconstruction is required; only component specifications need to be adjusted to adapt to multiple models.

[0020] 5. Low cost: Reduces R&D and manufacturing costs, and facilitates rapid promotion.

[0021] 6. Safe and reliable: Distributed control + differentiated fault protection comprehensively ensure flight safety. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the wind-powered aircraft of the present invention; Figure 2 This is a schematic diagram of the wind turbine aircraft of the present invention from an oblique angle. Figure 3 This is a schematic diagram of the wind turbine aircraft of the present invention from a low angle. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0024] The present invention proposes a wind-powered aircraft, comprising: The main body of the fuselage 1 retains the original fuselage structure of the aircraft without changing the fuselage frame and cabin / payload layout. The main body of the fuselage 1 is compatible with the fuselage architecture of narrow-body aircraft, wide-body aircraft and medium and large UAVs. There is no need to redesign the fuselage for different aircraft models. Only the number of core functional modules and adaptation parameters need to be adjusted according to the aircraft model specifications. Wind power generation module: Adapted to the main body of the fuselage, it is symmetrically arranged at the original engine mounting positions on both sides of the wings. Narrow-body aircraft are equipped with two medium-sized horizontal axis wind turbines. Wide-body aircraft, due to their larger fuselage load and higher flight requirements, are equipped with two or more medium / large horizontal axis wind turbines. Medium and large UAVs are equipped with one or more compatible horizontal axis wind turbines depending on their fuselage size and endurance requirements. The core function of this module is to capture the kinetic energy of the airflow during flight and convert it into electrical energy to provide continuous energy replenishment for the aircraft. Power battery energy storage module: Replaces the original fuel tank / energy storage area to store the electrical energy generated by the wind turbine. This module is modularly designed and its layout and total capacity can be adjusted according to the space and energy storage requirements of different models. Multi-motor drive module: includes a number of propulsion motors 2 adapted to the wind power generation module and at least one tail fin attitude control motor, which are used to provide flight thrust and adjust flight attitude respectively. Wide-body aircraft use multiple sets of distributed propulsion motors 2 to meet the high thrust requirements. Medium and large UAVs are adapted to the motor specifications and number according to flight requirements. Ground taxiing module 3: Replaces the landing gear tires with electric hubs. Medium and large UAVs can be equipped with this module according to their fuselage structure and usage scenarios (such as UAVs that do not require ground taxiing). The core function is to drive the aircraft to taxi on the ground and achieve zero-emission ground movement. Flight control module: Used to collect flight data in real time and dynamically allocate the power output of the power battery to each motor to achieve full-scenario power control. This module has built-in adaptive control algorithms for different aircraft models and can adjust the power distribution strategy and control threshold according to the flight characteristics of narrow-body, wide-body aircraft and medium and large UAVs.

[0025] Preferably, the wind turbine rotor of the wind power generation module is made of lightweight composite material, and the blade angle can be automatically adjusted according to the flight speed and airflow direction. The diameter and rated power of the wind turbine rotor of different aircraft are adapted to the fuselage load and flight requirements. Multiple wind turbines can achieve synchronous or independent parameter adjustment, taking into account both power generation efficiency and flight stability.

[0026] Preferably, the power battery energy storage module adopts a modular design and is conventionally arranged at the bottom of the fuselage body 1, inside the wings, and in the tail compartment area. For medium and large UAVs, the arrangement position of the energy storage module can be adjusted according to the compactness of the fuselage (such as the belly of the fuselage or the wingtip). All models are equipped with a thermal management system and a battery management system (BMS) for the energy storage module to achieve comprehensive monitoring of the battery temperature, power, and charge / discharge status.

[0027] Preferably, the propulsion motor 2 and the tail wing attitude control motor of the multi-motor drive module are both permanent magnet synchronous motors, which can independently control the speed and realize differential steering and attitude adjustment. The propulsion motor 2 of the wide-body aircraft is arranged in multiple distributed groups to meet the thrust requirements of high-load flight. The drive motor of the medium and large UAV is miniaturized and high power density adapted design, taking into account both power and lightweight fuselage.

[0028] Preferably, the electric wheel hub of the ground taxiing module 3 is based on an improvement of electric drive wheel hub technology, with a built-in brushless DC motor that integrates drive and braking functions. The electric wheel hub of wide-body aircraft increases the rated power and torque according to the landing gear load to adapt to the ground taxiing requirements of heavy fuselages. The electric wheel hub of medium and large UAVs is a miniaturized adaptation design to meet the installation and use requirements of small landing gear.

[0029] Preferably, the flight control module adopts a distributed control architecture, which realizes power distribution, attitude adjustment and fault protection through a central control unit. It can adapt the control algorithm and power distribution threshold according to the aircraft specifications (narrow-body / wide-body / medium-to-large UAV), and preset differentiated control parameters for the flight characteristics of different aircraft models, without the need to redevelop the control system.

[0030] Preferably, the power distribution strategy of the flight control module is adaptable to all flight phases of all aircraft types, including: Takeoff phase: priority is given to power distribution to the ground taxiing module 3 (if configured) and propulsion motor 2. Wide-body aircraft / large UAVs distribute power evenly according to the number of drive motors to ensure the taxiing acceleration capability of the heavy-load fuselage; Cruise phase: the battery power is replenished by wind turbines to maintain stable output of propulsion motor 2. Multiple wind turbines achieve coordinated power generation according to airflow distribution to improve energy capture efficiency; Landing phase: the power of propulsion motor 2 is reduced, and the ground taxiing module 3 (if configured) is activated for auxiliary braking. Medium and large UAVs can combine propeller reverse thrust to achieve compound braking to improve landing safety.

[0031] Preferably, the wind turbine adopts variable pitch control technology, which can automatically adjust the blade angle according to the flight speed to balance power generation efficiency and wind resistance. Multiple wind turbines can achieve synchronous or independent adjustment of blade angle, which is suitable for the collaborative operation of multiple wind turbines for wide-body aircraft and medium and large UAVs.

[0032] Preferably, the power battery energy storage module can use lithium iron phosphate batteries, solid-state batteries or other high-energy-density chemical batteries, which have high energy density and wide temperature range operating characteristics. The total energy storage capacity is designed to be adapted to the payload and range requirements of the aircraft (narrow-body / wide-body / medium-to-large UAV). Wide-body aircraft are equipped with large-capacity energy storage modules, while medium-to-large UAVs are equipped with lightweight, high-energy-density energy storage modules.

[0033] The present invention also provides a control method for a wind-powered aircraft, comprising the following steps: S1: Collects flight data such as flight speed, airflow intensity, remaining battery power, motor speed, and aircraft model compatibility parameters to achieve comprehensive perception of the flight status of different aircraft models; S2: Based on the flight phase (ground taxiing, takeoff, cruise, landing) and aircraft specifications (narrow-body / wide-body / medium-to-large UAV), the power output of the battery is dynamically allocated to each motor, and multiple motors can achieve balanced or differentiated power distribution to adapt to the power requirements of different models. S3: Real-time adjustment of wind turbine blade angle and motor speed; multiple wind turbines coordinate parameter adjustment according to airflow conditions to achieve efficient power generation and stable flight, taking into account both energy utilization and flight attitude control. S4: Monitor the system's operating status, set differentiated fault protection thresholds according to aircraft specifications, and activate corresponding protection mechanisms when a fault occurs. Narrow-body / wide-body aircraft focus on cabin safety protection, while medium and large UAVs focus on payload and fuselage protection, ensuring flight safety for all types of aircraft. Example

[0034] The basic wind-powered aircraft structure in this embodiment is based on a single-aisle narrow-body passenger aircraft, and the specific structure is as follows: Main fuselage 1: The original fuselage frame, cabin layout, and landing gear structure are retained, with only the fuel tanks and engine components removed; Wind turbines: A medium-sized horizontal axis wind turbine with a rated power of 500kW is installed in the original engine nacelle position on each side of the wing. The rotor diameter is 3.5m, the blades are made of carbon fiber composite material, and the blade angle adjustment range is 0°-30°. Power battery pack: It adopts lithium iron phosphate battery pack with a total capacity of 2000kWh, which is distributed in the bottom of the main body of the fuselage (accounting for 60%), the interior of the wings (accounting for 30%) and the tail compartment (accounting for 10%). It is equipped with a liquid-cooled thermal management system and the operating temperature range is -20℃ to 55℃. Drive motors: One propulsion motor with a rated power of 400kW is installed on each side of the wing, and one attitude control motor with a rated power of 100kW is installed on the tail. All of them adopt permanent magnet synchronous motor technology with an efficiency of ≥95%. Ground taxiing module 3: The main landing gear wheels and the front wheel are replaced with improved electric wheel hubs, with a single wheel rated power of 50kW and a maximum torque of 2000N・m, which can achieve a ground taxiing speed of 0-50km / h; Control system: The central control unit uses an ARM architecture processor to collect parameters such as wind speed, flight altitude, battery SOC (remaining power), and motor speed in real time, and realizes power distribution and attitude control through PID algorithm. Example

[0035] Flight control procedures, ground taxiing phase: The pilot inputs taxiing commands via the control stick, and the central control unit activates ground taxiing module 3 to drive the aircraft to taxi to the runway at a speed of 10-30 km / h. If the battery level is below 20%, it can be replenished through ground charging stations, or the wind turbine can be started to assist in charging during taxiing using low-speed airflow. Takeoff phase: The pilot pushes the throttle to the maximum, and the central control unit distributes 80% of the power to the propulsion motors 2 on both sides of the wing and 20% of the power to the ground taxiing module 3 to achieve acceleration during takeoff; when the flight speed reaches the takeoff wheel speed (Vr), the tail attitude control motor starts to adjust the speed of the tail propeller, and works with the elevator to achieve takeoff. Cruise Phase: After the aircraft enters level flight cruise, the airflow speed stabilizes at 800-900 km / h. The wind turbine rotor efficiently captures kinetic energy from the airflow, generating up to 800 kW of power to continuously charge the battery pack. The central control unit dynamically adjusts the power distribution based on the battery SOC: when SOC ≥ 80%, battery power is used first; when SOC < 80%, the wind turbine directly powers the propulsion motor 2, and the remaining power is stored in the battery. The tail attitude control motor adjusts its speed in real time based on flight attitude data to ensure stable flight. Landing phase: The pilot issues a landing command, the central control unit reduces the power of propulsion motor 2 to 30%, and activates the braking mode of ground taxiing module 3 to achieve deceleration in conjunction with air braking; after the aircraft touches the ground, the tail attitude control motor stops working, ground taxiing module 3 switches to taxiing mode, and drives the aircraft to the parking position to complete the flight process. Example

[0036] Key component optimization: Wind turbine optimization It adopts variable pitch control technology to automatically adjust the blade angle according to the flight speed. When flying at low speed, the pitch is increased to improve power generation efficiency, and when flying at high speed, the pitch is decreased to reduce wind resistance. Power battery optimization: Solid-state battery technology is used to replace lithium iron phosphate batteries, increasing the energy density to 300Wh / kg, further reducing battery weight and improving range; Ground skidding module 3 optimization: The electric wheel hub integrates electromagnetic braking function, which can realize rapid braking and energy recovery, converting braking kinetic energy into electrical energy and storing it in the battery, thereby improving energy utilization. Control system optimization: By introducing AI algorithms and training models with historical flight data, intelligent prediction and optimization of power distribution can be achieved, further improving flight efficiency and safety.

[0037] The above embodiments are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A wind-powered aircraft, characterized in that: it comprises a fuselage body, a wind power generation module, a power battery energy storage module, a multi-motor drive module, a ground taxiing module, and a flight control module; the fuselage body retains the original aircraft fuselage structure without changing the fuselage frame and passenger cabin / load layout, and is suitable for the fuselage architecture of narrow-body aircraft, wide-body aircraft, and medium / large unmanned aerial vehicles; the wind power generation module is symmetrically arranged at the original engine mounting position of the wing according to the specifications of the aircraft model, the narrow-body aircraft is equipped with two medium-sized horizontal-axis wind power generators, the wide-body aircraft is equipped with two or more medium-sized / large-sized horizontal-axis wind power generators, and the medium / large unmanned aerial vehicle is equipped with one or more horizontal-axis wind power generators of suitable specifications, which are used to capture the airflow kinetic energy during flight and convert it into electrical energy; the power battery energy storage module replaces the original fuel tank / energy storage area and is used to store the electrical energy generated by the wind power generator; the multi-motor drive module includes a number of wing propulsion motors and at least one tail attitude control motor that are adapted to the wind power generation module, and are used to provide flight thrust and adjust flight attitude, respectively; the ground taxiing module is an electric wheel hub for landing gear, which can be selected according to the requirements of medium / large unmanned aerial vehicles; the flight control module is used to collect flight data in real time, dynamically allocate power battery output power to each motor, and realize full-scene power control.

2. The wind powered aircraft of claim 1, wherein, The wind power generator impeller of the wind power generation module is made of lightweight composite materials, the blade angle can be automatically adjusted according to the flight speed and airflow direction, the impeller diameter and rated power are designed according to the fuselage load and flight requirements, and multiple wind power generators can realize synchronous or independent parameter adjustment.

3. The wind powered aircraft of claim 1, wherein, The power battery energy storage module adopts a modular design and is conventionally distributed at the bottom of the fuselage, inside the wing, and in the tail cabin area. The arrangement position of the energy storage module can be adjusted for medium / large unmanned aerial vehicles. All energy storage modules are equipped with a thermal management system and a battery management system to realize comprehensive monitoring of battery temperature, capacity, and charging and discharging state.

4. The wind powered aircraft of claim 1, wherein, The wing propulsion motor and tail attitude control motor of the multi-motor drive module are permanent magnet synchronous motors, which can be independently controlled to realize differential steering and attitude adjustment. The wing propulsion motor of the wide-body aircraft is arranged in multiple groups in a distributed manner, and the drive motor of the medium / large unmanned aerial vehicle is designed to be miniaturized and high-power density.

5. The wind powered aircraft of claim 1, wherein, The electric wheel hub of the ground taxiing module is built-in brushless DC motor, which integrates driving and braking functions. The electric wheel hub of the wide-body aircraft is designed to have increased rated power and torque according to the landing gear load, and the electric wheel hub selected for the medium / large unmanned aerial vehicle is designed to be miniaturized.

6. The wind powered aircraft of claim 1, wherein, The flight control module adopts a distributed control architecture and realizes power distribution, attitude adjustment, and fault protection through a central control unit, which can adapt to the control algorithm and power distribution threshold of narrow-body, wide-body aircraft, and medium / large unmanned aerial vehicles.

7. The wind powered aircraft of claim 1, wherein, The power distribution strategy of the flight control module is as follows: during takeoff, power is preferentially allocated to the electric hub and wing propulsion motors, and wide-body aircraft / large UAVs distribute power evenly according to the number of drive motors; during cruise, the battery power is supplemented by wind turbines, and multiple wind turbines work together to maintain stable output of the propulsion motors; during landing, the propulsion motor power is reduced, and electric hub auxiliary braking is activated. Medium and large UAVs can combine propeller reverse thrust to achieve compound braking.

8. The wind powered aircraft of claim 1, wherein, The wind turbine adopts variable pitch control technology, which can automatically adjust the blade angle according to the flight speed to balance power generation efficiency and wind resistance. Multiple wind turbines can achieve synchronous or independent adjustment of blade angle.

9. The wind powered aircraft of claim 1, wherein, The power battery energy storage module uses lithium iron phosphate batteries, solid-state batteries, or other high-energy-density chemical batteries, and has high energy density and wide temperature range operating characteristics. The total energy storage capacity is designed to be adapted to the model's load and range requirements.

10. A control method of a wind-powered aircraft, applied to the wind-powered aircraft according to any one of claims 1-9, characterized in that, Includes the following steps: S1. Collect flight data such as flight speed, airflow intensity, remaining battery power, motor speed and aircraft model compatibility parameters; S2. Based on the flight stage and aircraft specifications, dynamically allocate the power output of the power battery to each motor to achieve balanced or differentiated power distribution. S3: Real-time adjustment of wind turbine blade angle and motor speed, with multiple wind turbines coordinating parameter adjustment to balance efficient power generation and stable flight; S4. Monitor the system's operating status, set differentiated fault protection thresholds according to aircraft type, and activate the corresponding protection mechanism when a fault occurs to ensure flight safety.

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