Motor and duct integrated device, unmanned aerial vehicle and test method

Abstract

The invention belongs to the technical field of unmanned aerial vehicles, and provides a motor and duct integrated device, an unmanned aerial vehicle and a test method.The motor and duct integrated device comprises a duct, a rotating ring, a rotor wing and a rim motor; the rim motor is mounted in the duct, and a magnetic flux path is parallel to the axis of the duct; the multiple rotor wings are installed on the inner surface of the rotating ring and located on the inner side of the duct. The rotating ring is fixedly connected with the inner surface of a rotor of the rim motor. The rim motor is installed in the duct, and the magnetic flux path is parallel to the axis of the duct, so that the installation space of the system is reduced, the power density of the system is improved, and compared with a traditional radial magnetic flux motor, the weight and the size of the motor are reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a motor and duct integrated device, an unmanned aircraft and a test method. Background Art

[0002] With the continuous development of UAV and aircraft technology, the efficiency, weight, volume and power consumption of the propulsion system have become key factors in determining the performance of the aircraft. At present, the propulsion systems widely used in the market mainly rely on radial flux motors, and the motors are usually installed in the center of the duct. The shaftless ducted propeller technology arranges the motor at the outer edge of the duct, avoiding the adverse effect of the motor installed in the center of the duct on the airflow, and demonstrating superior aerodynamic performance and design flexibility. In recent years, there have also been studies on the integration of motors and ducts in aviation, but they are mainly studies on the integration of radial flux motors and ducts, and the rotors all have a center axis. Therefore, there are still some technical bottlenecks in the research on the integration of motors and ducts:

[0003] Size and weight issues: The design of radial flux motors usually requires a larger radial dimension to achieve sufficient output power, which results in a larger motor size, increases the weight of the entire machine, and reduces the power density.

[0004] Installation complexity: Traditional radial flux motors usually need to be connected to the duct or aircraft body through multiple additional components such as bearings and brackets. This not only increases the complexity of the system, but also brings additional maintenance requirements, affecting the reliability and service life of the system. Summary of the invention

[0005] In order to solve the problems in the background technology, the present invention proposes a motor and duct integrated device, an unmanned aircraft and a test method.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A motor and duct integrated device, comprising a duct, a rotating ring, a rotor and a rim motor;

[0008] The wheel rim motor is installed inside the duct, and the magnetic flux path is parallel to the axis of the duct;

[0009] The rotors are provided in a plurality and are mounted on the inner surface of the rotating ring and located inside the duct;

[0010] The rotating ring is fixedly connected to the inner surface of the rotor of the rim motor.

[0011] Preferably, in the rim motor:

[0012] The rotor is installed along the axial direction of the duct;

[0013] Stators are installed on both sides of the rotor along the axial direction of the duct, and the stators are fixedly installed inside the duct.

[0014] Preferably, the stator and the rotor are both annular iron cores;

[0015] The outer surface of the rotor is connected to the duct via a bearing.

[0016] Preferably, permanent magnets are installed on both side surfaces of the rotor along the axial direction of the duct, and the permanent magnets generate torque with the stator.

[0017] Preferably, the rotors are distributed on the inner surface of the rotating ring and are integrally formed with the rotating ring.

[0018] Preferably, the bearing is a magnetic bearing.

[0019] An unmanned aircraft, wherein at least one of the above-mentioned motor and duct integrated devices is installed on the fuselage of the unmanned aircraft.

[0020] Preferably, at least one motor and duct integrated device is arranged around the pitch axis of the unmanned aircraft, and / or a plurality of motor and duct integrated devices are arranged transversely to the flow direction of the vortex airflow generated by the rotor;

[0021] In the cruising flight state, the thrust direction of the motor and duct integrated device is consistent with the longitudinal axis of the unmanned aircraft;

[0022] In the take-off and landing state, the thrust direction of the motor and duct integrated device forms a set inclination angle with the vertical axis of the unmanned aircraft.

[0023] Preferably, the number of the motor and duct integrated devices is 10 to 100.

[0024] A test method for the above-mentioned unmanned aircraft equipped with a motor and duct integrated device comprises the following steps:

[0025] A plurality of motor and duct integrated devices are arranged at the front section, middle section and rear section of the unmanned aircraft around the pitch axis of the unmanned aircraft and / or in the transverse direction of the flow direction of the vortex airflow generated by the rotor;

[0026] Record the size, weight and flight records of the drone after installing the motor and duct integrated device;

[0027] Analyze flight records and evaluate the impact of the motor and duct integration device on the flight performance of the unmanned aircraft, including flight speed, flight stability and energy consumption;

[0028] Determine whether the evaluation results meet the preset target. If not, adjust the position and quantity of the motor and duct integration device until the preset target is met;

[0029] Organize all evaluation results into a report.

[0030] Beneficial effects of the present invention:

[0031] 1. The present invention reduces the installation space of the system and improves the power density of the system by installing the rim motor into the duct and the magnetic flux path is parallel to the axis of the duct. Compared with the traditional radial flux motor, the weight and volume of the motor are reduced;

[0032] 2. The present invention installs the wheel rim motor into the duct, which reduces mechanical vibration. The design of the duct further weakens the aerodynamic noise, significantly reducing the noise level of the system and meeting application scenarios with high requirements for noise control. In addition, due to the high integration of the motor and the duct, the number of mechanical transmission components that require regular maintenance is reduced, the failure rate of the system is reduced, and the overall reliability of the system is improved.

[0033] Other features and advantages of the present invention will be described in the following description, and partly become obvious from the description, or be understood by implementing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0035] Figure 1 A three-dimensional structural schematic diagram of a motor and duct integrated device of the present invention is shown;

[0036] Figure 2 A cross-sectional view of a motor and duct integrated device of the present invention is shown;

[0037] Figure 3 The figure shows the coordination diagram of the stator and the rotor of the present invention;

[0038] Figure 4 A flow chart showing the test method of the present invention is shown.

[0039] In the figure: 1. duct; 2. rotating ring; 3. rotor; 4. stator; 5. bearing; 6. rotor. DETAILED DESCRIPTION

[0040] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0041] A motor and duct integrated device, such as Figure 1 As shown, it includes a duct 1, a rotating ring 2, rotors 3 and a rim motor. The rim motor is installed inside the duct 1, and the magnetic flux path is parallel to the axis of the duct 1; there are a plurality of rotors 3, which are installed on the inner surface of the rotating ring 2 and located inside the duct 1; the rotating ring 2 is fixedly connected to the inner surface of the rotor 6 of the rim motor.

[0042] It should be noted that Figure 1 In the structure, the stator 4 of the rim motor is fixed on the inner side of the outer shell of the duct 1, and the rotor 6 is connected to the rotor 3 through the rotating ring 2 to realize the integrated drive of the motor and the fan. This design not only reduces the volume of the system but also helps to improve the aerodynamic performance. In addition, the inner wall of the duct 1 is integrated with the stator 4 of the rim motor, and the stator coil is integrated with the structure of the duct 1, so that the rim motor and the duct 1 are combined into one, reducing the complexity of the system. The rotor 6 of the rim motor is connected to the rotor 3 to form an integral rotating component, which not only reduces the transmission components but also simplifies the installation and maintenance of the system.

[0043] It should be further explained that the rim motor adopts a design in which double stators 4 and rotors 6 are arranged axially. Compared with the traditional design, Figure 1 The magnetic flux path of the rim motor is parallel to the axial direction. This design can significantly reduce the radial size of the motor, thereby reducing the system volume and increasing the power density.

[0044] Furthermore, if Figure 2 As shown, in the rim motor, a rotor 6 is installed along the axial direction of the duct 1, and stators 4 are installed on both sides of the rotor 6. The stator 4 is fixedly installed inside the duct 1. The stator 4 and the rotor 6 are both annular iron cores, and the outer surface of the rotor 6 is connected to the duct 1 through a bearing 5. The bearing 5 adopts a magnetic bearing, and a part of the magnet is fixed on the inner side of the duct 1. The magnet connected to the rotor 6 is fixed with a composite material, and the rotor 6 and the rotor 3 are supported by the force between the magnets. In addition, combined with Figure 3 It can be seen that permanent magnets are installed on both sides of the rotor 6 along the axial direction of the duct 1, and the permanent magnets can generate torque with the stator 4. The rotors 3 are distributed on the inner surface of the rotating ring 2 and are integrally formed with the rotating ring 2.

[0045] It should be noted that in Figure 2 In the embodiment, the stator 4 is embedded in the inner wall of the duct 1 and is composed of stator teeth and multiple groups of stator coils. Each group of coils is fixed in the circumferential direction of the duct 1 at a certain angle to form a continuous magnetic field. This design can ensure that the magnetic field evenly covers the entire rotating area, thereby improving the working efficiency of the motor. The rotor 6 is directly glued to the rotating ring 2 and installed in the middle of the duct 1. In addition, the rotor 6 is made of composite materials, which not only ensures its strength but also reduces its weight, thereby reducing the moment of inertia. The permanent magnets on both sides of the rotor 6 interact with the coils of the stators 4 on both sides in the electromagnetic field to generate torque to drive the rotor 3.

[0046] It needs to be further explained that Figure 1 and Figure 2 The structure places the rim motor inside the duct 1. This integrated design reduces mechanical vibrations. The design of the duct 1 further weakens the aerodynamic noise, which significantly reduces the noise level of the system and can meet the application scenarios with high requirements for noise control. Secondly, by integrating the rim motor into the duct 1 and installing the stator 4 axially on both sides of the rotor 6, the magnetic flux path is parallel to the axis of the duct 1, while reducing the installation space of the system and improving the power density of the system. Compared with traditional design schemes, the weight and volume of the rim motor are reduced. In addition, the integrated design of the axial flux rim motor and the duct 1 optimizes the aerodynamic efficiency of the system, reduces airflow losses, and thus improves propulsion efficiency.

[0047] In some optional embodiments, multiple motors and duct integrated devices may be used in combination. The rotation axes of the multiple ducts 1 are arranged in parallel and rigidly connected through a high-strength connection structure, thereby ensuring the stability and reliability of the overall structure. An unmanned aircraft is introduced below based on this embodiment, as follows:

[0048] An unmanned aircraft having at least one Figure 1-Figure 3 A motor and duct integrated device. Specifically, at least one motor and duct integrated device is arranged around the pitch axis of the unmanned aircraft, and / or a plurality of motor and duct integrated devices are arranged transversely along the flow direction of the vortex airflow generated by the rotor 6. In the cruising flight state, the thrust direction of the motor and duct integrated device is consistent with the longitudinal axis of the unmanned aircraft; in the take-off and landing state, the thrust direction of the motor and duct integrated device forms a set inclination angle with the vertical axis of the unmanned aircraft. Specifically, the unmanned aircraft can be configured with different numbers of motor and duct integrated devices according to actual needs. In a preferred embodiment, the number of ducted 1 fan engines can be in the range of 10 to 100, more preferably in the range of 20 to 50.

[0049] For example, in an electric vertical take-off and landing aircraft, at least one motor and duct integrated device can be arranged, which can be controllably rotated relative to the fuselage around the pitch axis of the aircraft. This rotatable design enables the engine to achieve attitude adjustment between the cruising flight position and the take-off and landing position: in the cruising flight state, the thrust direction of the engine is consistent with the longitudinal axis of the aircraft; in the take-off and landing state, the thrust direction of the engine forms a specific inclination angle relative to the vertical axis of the aircraft.

[0050] In terms of engine layout, this embodiment provides a variety of optional schemes, among which the rear section layout scheme is: 2-4 pairs of motor and duct integrated devices can be set in the rear area of ​​the aircraft, and these devices can be set in combination with the aileron structure. Front layout scheme: 1-2 pairs of motor and duct integrated devices can be set in the front of the aircraft, which can be arranged in a canard-type or combined with a canard structure. Mid-section layout scheme: The motor and duct integrated device is set in the central section extending longitudinally of the aircraft, which can be combined with lift structures such as wings, winglets or canards. In addition, multiple motor and duct integrated devices can be arranged linearly along the lateral and / or pitch axis direction of the flow direction. This design scheme of a distributed power system can effectively reduce the overall noise radiation level of the aircraft.

[0051] Specifically, a certain electric vertical take-off and landing aircraft uses a 6-tilt duct 1 layout, 4 ducts 1 are arranged at the leading edge of the wing and can be tilted, and 2 ducts 1 are arranged at the tail and can be tilted, which has both vertical take-off and landing and cruising efficiency. In addition, a distributed layout of duct 1 fans can be used, with a total of 36 duct 1 fans, 12 ducts 1 installed on the front wing, and 24 ducts 1 installed on the main wing, and all ducts 1 can be tilted to achieve vector thrust control, thereby achieving uniform thrust distribution and high redundancy.

[0052] like Figure 4 As shown, a test method for the above-mentioned unmanned aircraft equipped with a motor and duct integrated device includes the following steps:

[0053] S1: a plurality of motor and duct integrated devices are arranged at the front section, middle section and rear section of the unmanned aircraft around the pitch axis of the unmanned aircraft and / or in the lateral direction of the vortex airflow generated by the rotor 6;

[0054] S2: Record the volume, weight and flight records of the unmanned aircraft after installing the motor and duct integrated device;

[0055] S3: Analyze flight records and evaluate the impact of the motor and duct integration device on the flight performance of the unmanned aircraft, including flight speed, flight stability and energy consumption;

[0056] S4: Determine whether the evaluation results meet the preset goals. If not, adjust the position and quantity of the motor-ducted fan integrated device until the preset goals are met.

[0057] S5: Collate all the evaluation results to form a report.

[0058] The specific test situations are given below in combination with S1 - S5:

[0059] Test 1: Motor-ducted fan integrated devices are respectively arranged at the front, middle, and rear sections of the unmanned aircraft. One pair of motor-ducted fan integrated devices is arranged at the front section, with a canard configuration. The motor model is M1, and the diameter of duct 1 is D1. Two motor-ducted fan integrated devices are arranged in the central section in the middle section, combined with the wing structure. The motor model is M2, and the diameter of duct 1 is D2. Two pairs of motor-ducted fan integrated devices are arranged in the rear area, combined with the aileron structure. The motor model is M3, and the diameter of duct 1 is D3. Record the volume of the unmanned aircraft after installation as V1 cubic meters and the weight as W1 kilograms. Conduct a flight test, with a flight speed of Vs1, good flight stability, an energy consumption of E1, and a flight noise of N1.

[0060] Test 2: Two pairs of motor-ducted fan integrated devices are arranged at the front section of the unmanned aircraft, combined with the canard structure. The motor model is M4, and the diameter of duct 1 is D4. Three motor-ducted fan integrated devices are arranged in the middle section, combined with the winglet structure. The motor model is M5, and the diameter of duct 1 is D5. Three pairs of motor-ducted fan integrated devices are arranged in the rear area, combined with the aileron structure. The motor model is M6, and the diameter of duct 1 is D6. Record the volume of the unmanned aircraft after installation as V2 and the weight as W2. Conduct a flight test, with a flight speed of Vs2, excellent flight stability, an energy consumption of E2, and a flight noise of N2.

[0061] Test 3: One pair of motor-ducted fan integrated devices is arranged at the front section of the unmanned aircraft, with a canard configuration. The motor model is M7, and the diameter of duct 1 is D7. Four motor-ducted fan integrated devices are arranged in the middle section, combined with the wing and winglet structures. The motor model is M8, and the diameter of duct 1 is D8. Four pairs of motor-ducted fan integrated devices are arranged in the rear area, combined with the aileron structure. The motor model is M9, and the diameter of duct 1 is D9. Record the volume of the unmanned aircraft after installation as V3 and the weight as W3. Conduct a flight test, with a flight speed of Vs3, good flight stability, but an energy consumption of E3 and a flight noise of N3.

[0062] Comparison results:

[0063] Volume: V1 < V2 < V3. As the quantity of the motor-ducted fan integrated device increases, the volume of the unmanned aircraft also increases.

[0064] Weight: W1 < W2 < W3. As the number of motor-ducted fan integrated devices increases, the weight of the unmanned aircraft also increases.

[0065] Flight noise: N1 < N2 < N3. As the number of motor-ducted fan integrated devices increases, the flight noise also increases accordingly. However, compared with the traditional power system, for the design scheme adopting the distributed power system, the flight noise of each scheme is reduced, which proves the effectiveness of this scheme.

[0066] Flight speed: Vs1 < Vs2 < Vs3, indicating that the number of motor-ducted fan integrated devices has little effect on the flight speed.

[0067] Flight stability: The flight stability of Scheme 2 is the best, followed by Scheme 1 and Scheme 3.

[0068] Energy consumption: E1 < E2 < E3. As the number of motor-ducted fan integrated devices increases, the energy consumption also increases accordingly. However, compared with the traditional power system, for the design scheme adopting the distributed power system, the energy consumption of each scheme is reduced, which proves the advantage of this scheme in reducing energy consumption. At the same time, the selection of different motor models and the diameter of duct 1 will also affect the energy consumption.

[0069] Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A motor and duct integrated device, characterized in that: It comprises a duct (1), a rotating ring (2), a rotor (3) and a rim motor; The wheel rim motor is installed inside the duct (1), and the magnetic flux path is parallel to the axis of the duct (1); The rotors (3) are provided in plurality and are mounted on the inner surface of the rotating ring (2) and located inside the duct (1); The rotating ring (2) is fixedly connected to the inner surface of the rotor (6) of the rim motor.

2. The motor and duct integrated device according to claim 1, characterized in that: In the rim motor: The rotor (6) is installed along the axial direction of the duct (1); Along the axial direction of the duct (1), stators (4) are installed on both sides of the rotor (6), and the stators (4) are fixedly installed inside the duct (1).

3. The motor and duct integrated device according to claim 2, characterized in that: The stator (4) and the rotor (6) are both circular iron cores; The outer surface of the rotor (6) is connected to the duct (1) via a bearing (5).

4. The motor and duct integrated device according to claim 2, characterized in that: Permanent magnets are installed on both side surfaces of the rotor (6) along the axial direction of the duct (1), and the permanent magnets generate torque with the stator (4).

5. The motor and duct integrated device according to claim 1, characterized in that: The rotors (3) are distributed on the inner surface of the rotating ring (2) and are integrally formed with the rotating ring (2).

6. The motor and duct integrated device according to claim 3, characterized in that: The bearing (5) is a magnetic suspension bearing.

7. An unmanned aircraft, characterized in that: At least one motor and duct integrated device as described in any one of claims 1-6 is installed on the fuselage of the unmanned aircraft.

8. The unmanned aircraft according to claim 7, characterized in that: At least one motor and duct integrated device is arranged around the pitch axis of the unmanned aircraft, and / or a plurality of motor and duct integrated devices are arranged transversely to the flow direction of the vortex airflow generated by the rotor (6); In the cruising flight state, the thrust direction of the motor and duct integrated device is consistent with the longitudinal axis of the unmanned aircraft; In the take-off and landing state, the thrust direction of the motor and duct integrated device forms a set inclination angle with the vertical axis of the unmanned aircraft.

9. The unmanned aircraft according to claim 8, characterized in that: The number of the motor and duct integrated devices is 10 to 100.

10. A test method, characterized in that: The unmanned aircraft equipped with a motor and duct integrated device as claimed in any one of claims 7 to 9 comprises the following steps: A plurality of motor and duct integrated devices are arranged at the front section, middle section and rear section of the unmanned aircraft around the pitch axis of the unmanned aircraft and / or in the transverse direction of the flow direction of the vortex airflow generated by the rotor (6); Record the size, weight and flight records of the drone after installing the motor and duct integrated device; Analyze flight records and evaluate the impact of the motor and duct integration device on the flight performance of the unmanned aircraft, including flight speed, flight stability and energy consumption; Determine whether the evaluation results meet the preset target. If not, adjust the position and quantity of the motor and duct integration device until the preset target is met; Organize all evaluation results into a report.

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