Floating wind turbine multi-degree-of-freedom aerodynamic load simulation device and test method thereof

Abstract

This invention provides a multi-degree-of-freedom aerodynamic load simulation device and its testing method for floating wind turbines, including a nacelle, an aerodynamic load generation module, an aerodynamic load control module, and a gyroscopic torque generation module. The load generation unit of the aerodynamic load generation module is mounted outside the nacelle via a support arm, and is used to generate aerodynamic loads along the length and width directions of the nacelle. The gyroscopic torque generation module includes a motor and a mass rod mounted on the nacelle; the motor drives the mass rod to rotate, generating a moment of inertia. The aerodynamic load control module controls the magnitude of the generated aerodynamic loads. This invention eliminates the need for complex and expensive physical wind fields, enabling accurate simulation of multi-degree-of-freedom aerodynamic loads on floating wind turbines under various operating conditions. It eliminates dependence on physical wind fields and model blades, solving the problems of needing to readjust the load application direction for different wind directions and the difficulty in accurately simulating complex loads under extreme and fault conditions.

Description

Technical Field

[0001] This invention relates to the field of wind power technology, specifically to a floating wind turbine multi-degree-of-freedom aerodynamic load simulation device and its testing method. Background Technology

[0002] Floating wind turbine technology is considered a key means of developing deep-sea wind power. However, unlike traditional offshore oil and gas platforms and other structures, the system coupling dynamics of floating wind turbines are more complex, posing entirely new challenges to design, construction, installation, and maintenance. Therefore, conducting pool model tests of floating wind turbines in the early design phase is essential.

[0003] In floating wind turbine tank model tests, accurately simulating the aerodynamic loads on the floating wind turbine model under various operating conditions is crucial for correctly evaluating the motion response of the floating body. Currently, the commonly used aerodynamic load simulation method in floating wind turbine tank model tests involves setting up a physical wind field above the water surface and constructing a physical wind turbine model based on the Froude number similarity law. Alternatively, other methods include simplifying the wind turbine by applying equivalent forces using cables, thrust fans, etc., to replace the physical wind turbine model and physical wind field, or using a rotating disk in the wind field to generate thrust and gyroscopic torque for aerodynamic load simulation.

[0004] However, the aforementioned existing technical methods all have their own simplifications and limitations, and cannot truly and completely reflect the aerodynamic loads of floating wind turbines under various operating conditions.

[0005] The method combining physical wind field and physical wind turbine models is one of the most commonly used and most faithful methods for floating wind turbine tank model testing. It can simulate the main aerodynamic loads under certain operating conditions, such as the axial thrust of the wind turbine at steady wind speed, while neglecting other secondary aerodynamic loads such as aerodynamic torque. However, due to the dissimilarity of Reynolds numbers, model tests cannot achieve complete similarity to real-scale wind turbines, and strict weight requirements limit the feasibility of adding more complex control mechanisms and measuring equipment to simulate and monitor more complex operating conditions.

[0006] Simplified methods such as cables and thrust fans further simplify the simulation of aerodynamic loads. While avoiding the need to build physical wind fields with high costs, these methods only consider the equivalent of steady axial thrust and ignore the coupling between aerodynamic loads and floating body motion. They cannot simulate aerodynamic characteristics such as aerodynamic torque, blade-to-tower aerodynamic interaction, aerodynamic damping, and gyroscopic effects generated by blade rotation. They can only meet the experimental verification needs of a very small number of simplified steady operating conditions.

[0007] Although the rotating disk method in the wind field takes into account the gyro effect, it can only simulate the steady axial thrust in a single direction and cannot fully take into account the fluctuations in the aerodynamic load of the floating wind turbine and the characteristic differences under different operating conditions.

[0008] Therefore, those skilled in the art are dedicated to developing a floating wind turbine aerodynamic load simulation device, which can simulate forces and torques whose magnitude and direction can be adjusted and controlled in real time within a certain range, without the need to set up a physical wind field in the floating wind turbine pool model test, thus avoiding the Reynolds number dissimilarity problem, and thus accurately and reliably reflect the aerodynamic load characteristics of floating wind turbines under various operating, survival and failure conditions. Summary of the Invention

[0009] To address the shortcomings of existing technologies, the purpose of this invention is to provide a floating wind turbine multi-degree-of-freedom aerodynamic load simulation device and its testing method.

[0010] The floating wind turbine multi-degree-of-freedom aerodynamic load simulation device provided by the present invention includes a nacelle and an aerodynamic load generation module, an aerodynamic load control module, and a gyro torque generation module installed on the nacelle;

[0011] The aerodynamic load generation module includes a support arm and a load generation unit. The load generation unit is installed outside the cabin via the support arm and is used to generate aerodynamic loads along the length and width directions of the cabin.

[0012] The gyro torque generation module includes a motor and a mass rod installed on the nacelle. The mass rod is connected to the output shaft of the motor, and the motor is used to drive the mass rod to rotate and generate rotational inertia.

[0013] The pneumatic load control module is connected to the load generation unit and is used to control the size of the pneumatic load generated by the load generation unit.

[0014] Preferably, the nacelle includes a nacelle shell, which is a hollow cuboid, and the bottom of the nacelle shell is fixedly mounted on an external tower.

[0015] Preferably, the support arm includes a first support arm and a second support arm, and the outer ends of both the first support arm and the second support arm are used to install the load generating unit;

[0016] There are multiple first arms, which are circumferentially mounted on the outside of the cabin shell. The load generation unit on the first arm is used to generate a load along the length direction of the cabin shell.

[0017] The second arm is a Y-shaped structure, and the two outer ends of the Y-shaped structure are respectively used to install two load generation units. The second arm is symmetrically installed on both sides of the cabin shell, and the load generation units on the second arm are used to generate loads along the width direction of the cabin shell.

[0018] Preferably, the load generating unit includes a duct fan, which is installed at the outer ends of the first arm and the second arm via duct fixing members;

[0019] One end of the duct fixing component is mounted on the support arm, and the other end of the duct fixing component is a ring-shaped fixing structure. The ring-shaped fixing structure is used to clamp the duct fan and fix it to the duct fan.

[0020] Preferably, the first support arm is a hollow, frustum-shaped vertical metal part, which is fixedly installed on the outside of the cabin shell by bolts, and the hollow structure of the first support arm is used to carry the cables of the load generation unit.

[0021] The second arm is a hollow Y-shaped metal part, which is fixedly installed on the side of the cabin shell by bolts. The hollow structure of the second arm is used to carry the cables of the load generation unit.

[0022] Preferably, the gyro torque generation module includes a brushless geared motor and multiple mass rods, the multiple mass rods being arranged circumferentially and extending radially along the output shaft of the brushless geared motor;

[0023] The brushless geared motor is installed inside the cabin shell, and the mass bar is located at one end of the cabin shell along its length.

[0024] Preferably, the gyro torque generation module further includes a Y-shaped tee connector.

[0025] The mass rod consists of three rods, which are respectively connected to the three interfaces of the Y-shaped tee connector and are evenly installed on the output shaft of the brushless geared motor along the circumference through the Y-shaped tee connector.

[0026] Preferably, the pneumatic load control module includes an electronic control chamber, an electronic speed controller, a heat sink, and a cooling fan;

[0027] The electronic speed controller (ESC) compartment is installed inside the engine compartment shell. The ESC and heat sink are both installed inside the ESC compartment. The ESC is connected to an external computer and is used to adjust the magnitude of the aerodynamic load generated by the load generation unit.

[0028] The heat sink is used to dissipate heat from the electronic speed controller, the cooling fan is mounted on the electronic speed controller compartment, and the outer shell of the chassis is provided with heat dissipation holes corresponding to the cooling fan.

[0029] The test method for the floating wind turbine multi-degree-of-freedom aerodynamic load simulation device provided by the present invention, using the aforementioned floating wind turbine multi-degree-of-freedom aerodynamic load simulation device, includes the following steps:

[0030] Step 1: Adjust the counterweight on the mass bar to adjust the moment of inertia of the gyro torque generation module to the preset target value;

[0031] Step 2: The brushless geared motor of the gyro torque generation module drives the mass rod to rotate until the rotation speed of the mass rod reaches the preset speed;

[0032] Step 3: The computer begins to perform numerical simulation of the corresponding working conditions, obtains the aerodynamic load on the actual wind turbine unit at each moment, decomposes the load into forces and moments in two vertical directions, obtains the stress and moment of the model scale after using the Froude number similarity scaling, and calculates the aerodynamic load that the load generation unit in the two directions needs to generate.

[0033] Step 4: The computer sends instructions to the pneumatic load control module at preset time intervals. After receiving the instructions, the electronic speed controller in the pneumatic load control module adjusts the speed of the ducted fan in real time.

[0034] Step 5: After the simulation ends, the computer sends a termination command to both the aerodynamic load control module and the gyro torque generation module. The aerodynamic load control module controls the aerodynamic load generated by the load generation unit to decrease to 0, and the brushless geared motor controls the speed of the mass bar to decrease to 0.

[0035] Preferably, a coordinate system is constructed with the midpoint of the cabin as the origin, the length direction of the outer shell as the X-axis, the width direction of the cabin outer shell as the Y-axis, and the height direction of the cabin outer shell as the Z-axis;

[0036] On the projection along the X-axis, four load generation units for generating X-axis aerodynamic loads are respectively arranged in the positive Y-direction, negative Y-direction, positive Z-direction, and negative Z-direction of the cabin shell. Two sets of load generation units for generating Y-axis aerodynamic loads are respectively arranged on both sides of the cabin shell along the Y-direction.

[0037] Compared with the prior art, the present invention has the following beneficial effects:

[0038] 1. This invention provides an aerodynamic load simulation device with a multi-array load active generation unit layout. It can accurately simulate multi-degree-of-freedom aerodynamic loads of floating wind turbines under various operating conditions without relying on complex and expensive physical wind fields. It eliminates the dependence of existing technology methods on physical wind fields and model blades, solves the problem that it is cumbersome and inaccurate to readjust the load application direction every time the operating conditions change to different wind directions, and solves the problem that existing technology methods cannot accurately simulate complex loads under extreme and fault conditions.

[0039] 2. This invention selects a ducted fan as the active load generation unit and designs a corresponding duct fixing component to avoid obstruction of the air intake and exhaust direction of the ducted fan, thereby improving the accuracy of load simulation and solving the problem that the fan array and fan connection method in the prior art would obstruct the air intake or exhaust direction of the fan.

[0040] 3. This invention adds a gyroscopic torque simulation device to the array-type layout of the active load generation unit. This device uses a set of mass rods to represent the rotational inertia of the wind turbine rotor in the wind turbine model. Through active and continuous rotation, it can simulate the gyroscopic torque exerted on the nacelle by the rotation of the wind turbine rotor. This solves the problem of the lack of gyroscopic effect simulation in the prior art.

[0041] 4. Based on the aerodynamic load simulation device, this invention proposes a control system and control method that independently controls each load generation unit, enabling real-time and accurate simulation of aerodynamic loads of different degrees of freedom of the fan under different operating conditions. This solves the problem that existing technologies can only simulate steady loads and single-degree-of-freedom loads under some operating conditions. Attached Figure Description

[0042] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0043] Figure 1 This is a schematic diagram illustrating a usage scenario of the present invention;

[0044] Figure 2 This is a schematic diagram of the overall structure of the present invention;

[0045] Figure 3 This is a structural schematic diagram of the present invention viewed from the front.

[0046] Figure 4 This is a schematic diagram of the structure of the present invention from a side view angle;

[0047] Figure 5 This is a schematic diagram of the internal structure of the cabin shell in this invention;

[0048] Figure 6 This is a schematic diagram of the output allocation of different ducted fans in this invention.

[0049] The diagram shows:

[0050] Cabin 1, Electrical Control Container 301

[0051] Cabin exterior 100, electronic speed controller 302

[0052] Aerodynamic load generation module 2, heat sink 303

[0053] First arm 201 Gyro torque generation module 4

[0054] Duct fixing component 202, brushless geared motor 401

[0055] Second support arm 203 Y-type tee connector 402

[0056] Load generation unit 204 Mass rod 403

[0057] Pneumatic load control module 3 Detailed Implementation

[0058] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0059] This invention discloses a multi-degree-of-freedom aerodynamic load simulation device for floating wind turbines and its testing method. By setting up an aerodynamic load simulation device with a multi-array load active generation unit layout, it can accurately simulate the multi-degree-of-freedom aerodynamic loads of floating wind turbines under various operating conditions without relying on complex and expensive physical wind fields, thus eliminating the dependence of existing technical methods on physical wind fields and model blades.

[0060] The floating wind turbine multi-degree-of-freedom aerodynamic load simulation device provided by the present invention, such as Figure 1 As shown, it includes a nacelle 1 and an aerodynamic load generation module 2, an aerodynamic load control module 3, and a gyro torque generation module 4 installed on the nacelle 1; the nacelle 1 is installed on an external tower 5, and the external tower 5 is installed on an external float 6, forming an aerodynamic load simulation device for a floating wind turbine.

[0061] like Figures 2-4 As shown, the aerodynamic load generation module 2 includes a support arm and a load generation unit 204. The load generation unit 204 is installed outside the cabin 1 via the support arm. The load generation unit 204 is used to generate aerodynamic loads along the length and width directions of the cabin 1. The gyroscopic torque generation module 4 includes a motor and a mass rod installed on the cabin 1. The mass rod is connected to the output shaft of the motor. The motor is used to drive the mass rod to rotate and generate rotational inertia. The aerodynamic load control module 3 is connected to the load generation unit 204 and is used to control the magnitude of the aerodynamic load generated by the load generation unit 204.

[0062] Specifically, the nacelle 1 includes a nacelle shell 100, which is used to install and house the aerodynamic load generation module 2, the aerodynamic load control module 3, and the gyro torque generation module 4. The nacelle shell 100 is a hollow, irregularly shaped cuboid metal part, preferably CNC machined from aluminum alloy to ensure precision and weight control. The shell has numerous holes for mounting on the wind turbine tower 5 and for installing components such as the first arm 201, the second arm 203, and the brushless geared motor 401. A large ventilation hole is left at the bottom of the shell to allow the cooling fan 304 to quickly remove the heat from the electric control chamber 301.

[0063] pneumatic load generation module 2, such as Figure 2 , Figure 3 and Figure 4 As shown, the assembly includes a first support arm 201, a duct fixing member 202, a second support arm 203, and a load generating unit 204, wherein the load generating unit 204 is preferably a duct fan. The first support arm 201 is a hollow, frustum-shaped, vertical metal part, preferably CNC machined from aluminum alloy, and is bolted to the nacelle shell 100. It is bolted to one duct fixing member 202, and its hollow interior facilitates cable passage. The second support arm 203 is a hollow, Y-shaped metal part with a forked end, preferably CNC machined from aluminum alloy, and is bolted to the nacelle shell 100. It is bolted to two duct fixing members 202, and its hollow interior facilitates cable passage. The duct fixing member 202 is a handle-shaped metal part with a ring structure at one end. The handle has multiple holes for connection to the first support arm 201 or the second support arm 203. The ring structure is used to clamp the duct fan, and the duct fan is fixed with bolts. The ducted fan is an active load generation unit, selected according to the target aerodynamic load value of the target wind turbine scheme. Its cables can pass through the holes in the nacelle shell 100 and the first arm 201 or the second arm 203.

[0064] Pneumatic load control module 3, such as Figure 5 As shown, the device includes an electronic speed controller (ESC) compartment 301, an ESC 302, a heat sink 303, and a cooling fan 304. The ESC compartment 301 houses the ESC 302 and the heat sink 303. The ESC 302 adjusts the ducted fan speed, and the heat sink 303 is preferably a thin, lightweight finned metal sheet used to quickly dissipate heat from the densely arranged ESC 302. The cooling fan 304 is bolted to the ESC compartment 301 to quickly remove heat accumulated within the ESC compartment 301.

[0065] Gyroscope torque generation module 4, as shown Figure 5As shown, the device includes a brushless geared motor 401, a Y-shaped tee connector 402, and mass rods 403. The brushless geared motor 401 is fixed to the tail of the nacelle 100 by bolts and fastened to the Y-shaped tee connector 402 by screws, used to drive the mass rods 403 to rotate. The Y-shaped tee connector 402 is a metal coupling with a Y-shaped tee tube, preferably CNC machined from aluminum alloy, and is fastened to the three mass rods 403 by screws. The mass rods 403 are long hollow aluminum tubes, selected according to the rotational inertia of the wind turbine rotor in the target wind turbine design. Their rotational inertia can be adjusted by adding counterweights such as binding lead wires.

[0066] According to the test method of the floating wind turbine multi-degree-of-freedom aerodynamic load simulation device provided by the present invention, based on the above-mentioned load generation module, a set of aerodynamic load simulation operation procedures for floating wind turbine models under different working conditions is designed, specifically including the following steps:

[0067] Step 1: Before starting the simulation test, adjust the counterweight on the mass bar 403 to adjust the moment of inertia of the gyro torque generation module 4 to the target value, thereby ensuring that the moment of inertia is similar.

[0068] Step 2: The brushless geared motor 401 of the gyro torque generation module 4 drives the mass rod 403 to rotate. Its rotation speed is similar to the actual rotation speed of the wind turbine rotor, thereby simulating an accurate gyro torque.

[0069] Step 3: The computer begins to perform numerical simulation of the corresponding operating conditions, calculates the aerodynamic load on the actual wind turbine unit at each moment, decomposes the load into forces and moments in two directions, obtains the stress and moment of the model scale after using the Froude number similarity scaling, and calculates the output task to be undertaken by different duct fans.

[0070] In a preferred embodiment, such as Figure 6 Taking the eight ducted fans shown as an example, a rectangular coordinate system is established with the paper facing outwards as the positive x-axis, rightward as the positive y-axis, and upward as the positive z-axis. The right-hand rule is used to determine the positive and negative directions of torque. The four ducted fans at the top, bottom, left, and right of the nacelle are responsible for simulating aerodynamic thrust in the negative x-axis direction. The ducted fan directly to the right can also simulate torque in the positive z-axis direction, and the ducted fan directly to the left can also simulate torque in the negative z-axis direction. The two ducted fans at the top left and bottom left of the nacelle are responsible for simulating aerodynamic thrust in the positive y-axis direction, and the two ducted fans at the top right and bottom right are responsible for simulating aerodynamic thrust in the negative y-axis direction. The two ducted fans at the top right and bottom left can also simulate torque in the positive x-axis direction, and the two ducted fans at the top left and bottom right can also simulate torque in the negative x-axis direction.

[0071] If, at a certain moment, the aerodynamic load on the wind turbine obtained from computer simulation is a thrust Fx along the negative X-axis, a thrust Fy along the positive y-axis, a torque Mx along the positive x-axis, and a torque Mz along the positive z-axis, then the right duct should generate... The thrust should be generated by the upper and lower ducts respectively. The thrust should generate in the upper left duct. The thrust should generate in the lower left duct. The thrust. Among them, l1 is the lever arm of the right duct relative to the nacelle axis, and l2 is the lever arm of the upper left and lower left ducts relative to the nacelle axis.

[0072] Step 4: The computer sends commands to the aerodynamic load control module 3 at fixed time intervals. After receiving the commands, the electronic speed controller 302 in the aerodynamic load control module 3 adjusts the rotational speed of the ducted fan 204 in real time, thereby simulating accurate multi-degree-of-freedom aerodynamic loads.

[0073] Step 5: After the simulation ends, the computer simultaneously sends a termination command to the aerodynamic load control module 3 and the gyro torque generation module 4. Upon receiving the termination command, the output force of the aerodynamic load generation module 2 is reduced to 0, and it stops working. Preferably, the speed of the ducted fan is reduced to 0, and the speed of the brushless geared motor 401 is reduced to 0, and it stops working.

[0074] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0075] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A floating wind turbine multi-degree-of-freedom aerodynamic load simulation device, characterized in that, It includes a cabin (1) and an aerodynamic load generation module (2), an aerodynamic load control module (3), and a gyro torque generation module (4) installed on the cabin (1). The aerodynamic load generation module (2) includes a support arm and a load generation unit (204). The load generation unit (204) is installed outside the cabin (1) via the support arm. The load generation unit (204) is used to generate aerodynamic loads along the length and width directions of the cabin (1). The gyro torque generation module (4) includes a motor and a mass rod installed on the cabin (1). The mass rod is connected to the output shaft of the motor. The motor is used to drive the mass rod to rotate and generate rotational inertia. The pneumatic load control module (3) is connected to the load generation unit (204) and is used to control the size of the pneumatic load generated by the load generation unit (204); A coordinate system is constructed with the midpoint of the cabin as the origin, the length direction of the cabin shell (100) as the X-axis, the width direction of the cabin shell (100) as the Y-axis, and the height direction of the cabin shell (100) as the Z-axis. On the projection along the X-axis, four load generation units (204) for generating X-direction aerodynamic loads are respectively provided in the positive Y direction, negative Y direction, positive Z direction and negative Z direction of the cabin shell (100), and two sets of load generation units (204) for generating Y-direction aerodynamic loads are respectively provided on both sides of the cabin shell (100) along the Y direction. The cabin (1) includes a cabin shell (100), which is a hollow cuboid component. The bottom of the cabin shell (100) is fixedly installed on the external tower (5). The arm includes a first arm (201) and a second arm (203), the outer ends of which are used to install a load generating unit (204). There are multiple first arms (201), and multiple first arms (201) are installed circumferentially on the outside of the cabin shell (100). The load generation unit (204) on the first arm (201) is used to generate loads along the length direction of the cabin shell (100). The second arm (203) is a Y-shaped structure. The two outer ends of the Y-shaped structure are used to install two load generating units (204). The second arm (203) is symmetrically installed on both sides of the cabin shell (100). The load generating units (204) on the second arm (203) are used to generate loads along the width direction of the cabin shell (100).

2. The floating wind turbine multi-degree-of-freedom aerodynamic load simulation device according to claim 1, characterized in that, The load generation unit (204) includes a duct fan, which is installed at the outer ends of the first arm (201) and the second arm (203) by means of a duct fixing member; One end of the duct fixing component is mounted on the support arm, and the other end of the duct fixing component is a ring-shaped fixing structure. The ring-shaped fixing structure is used to clamp the duct fan and fix it to the duct fan.

3. The floating wind turbine multi-degree-of-freedom aerodynamic load simulation device according to claim 1, characterized in that, The first support arm (201) is a hollow frustum-shaped vertical metal piece, which is fixedly installed on the outside of the cabin shell (100) by bolts. The hollow structure of the first support arm (201) is used for the cable of the load generation unit (204). The second arm (203) is a hollow Y-shaped metal part, which is fixedly installed on the side of the cabin shell (100) by bolts. The hollow structure of the second arm (203) is used for the cable of the load generation unit (204).

4. The floating wind turbine multi-degree-of-freedom aerodynamic load simulation device according to claim 1, characterized in that, The gyro torque generation module (4) includes a brushless geared motor (401) and multiple mass rods (403), which are arranged circumferentially and extend radially along the output shaft of the brushless geared motor (401); The brushless geared motor (401) is installed inside the cabin shell (100), and the mass bar (403) is located at one end of the cabin shell (100) along its length.

5. The floating wind turbine multi-degree-of-freedom aerodynamic load simulation device according to claim 4, characterized in that, The gyro torque generation module (4) also includes a Y-type tee connector (402). There are three mass rods (403), which are respectively connected to the three interfaces of the Y-type tee connector (402) and are evenly installed on the output shaft of the brushless geared motor (401) in the circumferential direction through the Y-type tee connector (402).

6. The floating wind turbine multi-degree-of-freedom aerodynamic load simulation device according to claim 4, characterized in that, The pneumatic load control module (3) includes an electric control chamber (301), an electronic speed controller (302), a heat sink (303), and a cooling fan (304). The electronic speed controller (301) is installed inside the cabin shell (100). The electronic speed controller (302) and the heat sink (303) are both installed inside the electronic speed controller (301). The electronic speed controller (302) is connected to an external computer and is used to adjust the size of the aerodynamic load generated by the load generation unit (204). The heat sink (303) is used to dissipate heat from the electronic speed controller (302), the cooling fan (304) is installed on the electronic speed controller compartment (301), and the outer shell of the engine compartment (100) is provided with heat dissipation holes corresponding to the cooling fan (304).

7. A test method for a floating wind turbine multi-degree-of-freedom aerodynamic load simulation device, characterized in that, The floating wind turbine multi-degree-of-freedom aerodynamic load simulation device according to claim 6 includes the following steps: Step 1: Adjust the counterweight on the mass bar (403) to adjust the moment of inertia of the gyro torque generation module (4) to the preset target value; Step 2: The brushless geared motor (401) of the gyro torque generation module (4) drives the mass rod (403) to rotate until the rotation speed of the mass rod (403) reaches the preset speed; Step 3: The computer starts to perform numerical simulation of the corresponding working conditions, obtains the aerodynamic load on the actual wind turbine unit at each moment, decomposes the load into forces and moments in two vertical directions, obtains the stress and moment of the model scale after using the Froude number similarity scaling, and calculates the aerodynamic load to be generated by the load generation unit (204) in the two directions. Step 4: The computer sends instructions to the pneumatic load control module (3) at preset time intervals. After receiving the instructions, the electronic speed controller (302) in the pneumatic load control module (3) adjusts the speed of the ducted fan in real time. Step 5: After the simulation ends, the computer sends an end command to the aerodynamic load control module (3) and the gyroscope torque generation module (4) at the same time. The aerodynamic load control module (3) controls the aerodynamic load generated by the load generation unit (204) to decrease to 0, and the brushless geared motor (401) controls the speed of the mass bar (403) to decrease to 0.

8. The test method for the floating wind turbine multi-degree-of-freedom aerodynamic load simulation device according to claim 7, characterized in that, A coordinate system is constructed with the midpoint of the cabin as the origin, the length direction of the outer shell (100) as the X-axis, the width direction of the cabin outer shell (100) as the Y-axis, and the height direction of the cabin outer shell (100) as the Z-axis. On the projection along the X-axis, four load generation units (204) for generating X-direction aerodynamic loads are respectively provided in the positive Y direction, negative Y direction, positive Z direction and negative Z direction of the cabin shell (100), and two sets of load generation units (204) for generating Y-direction aerodynamic loads are respectively provided on both sides of the cabin shell (100) along the Y direction.

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