Single-motor double-rotor direct-drive coaxial reverse propeller propulsion unit

Abstract

According to the single-motor double-rotor direct-drive coaxial reverse propeller propelling unit, two pairs of propeller blades are directly driven through the single motor with the inner rotor and the outer rotor, a transmission device is not needed, an inner rotor excitation set and an outer rotor excitation set generate a rotating magnetic field, and a first-stage propelling component and a second-stage propelling component are driven under the action of electromagnetic torque with the acting force equal to the counter-acting force; the deflection torque of one-way rotation is balanced, and coaxial reverse propeller movement is achieved; the inner and outer rotor outer side strengthening belts resist centrifugal force of high-speed rotation; an inner rotor internal heat conduction channel cools the inner rotor; the propulsive force change is realized by motor speed change; the propelling direction is changed by deflection of the motor base; the unit is simple in mechanism, light in structure, large in power-to-weight ratio, high in reliability and beneficial to rapid popularization and application of the coaxial reverse propeller technology on aircrafts, and particularly can promote improvement of the performance of small aircrafts and military high-reliability aircrafts.

Description

Technical Field

[0001] This application belongs to the field of aviation power technology, and specifically relates to a single-motor dual-rotor direct-drive coaxial counter-rotating propulsion unit. Background Technology

[0002] Coaxial counter-rotating rotor is an aviation propulsion technology that connects two propellers to a common axis, with one propeller facing the other back-to-back. The two layers of blades share a drive shaft but rotate in opposite directions. This balances and eliminates unidirectional rotational deflection torque, and the upper rotor disk provides "pre-compression" to the lower rotor disk, resulting in a larger "intake / exhaust volume" and "airflow density" for the second stage. While not doubling the efficiency, the improvement is significant. Coaxial counter-rotating rotors offer the following advantages: high efficiency (reducing the size of individual propellers decreases the required power input, thus improving overall system efficiency); large airflow (due to the opposite rotation direction, the first propeller provides pre-compression to the second, resulting in higher airflow density); lightweight structure (reducing the structure required to support two separate propellers helps reduce the overall weight of the helicopter); and space saving (reducing rotor length / rotation area for the same output power (helicopter to outside air), eliminating the need for a tail rotor, making it ideal for use in confined spaces on ships.

[0003] However, the coaxial counter-rotating propeller technology also has obvious drawbacks. The main drawback is that the coaxial and counter-rotating mechanism of the upper and lower blades is complex, heavy, and also deteriorates the reliability of the mechanism. For example, CN 110925364 A discloses a planetary reducer for coaxial counter-rotating helicopters. To achieve coaxial counter-rotation, it employs a two-layer, two-set planetary reducer structure, resulting in numerous parts, a long transmission chain, high weight, and poor reliability. CN 108791859 A, a fast-approaching rotorcraft; CN 110127043 A, a new energy coaxial counter-rotating aircraft; and CN 111392049 A, a coaxial counter-rotating helicopter transmission system, all utilize differential mechanisms. These mechanisms use a driving bevel gear to transmit motion to two large driven bevel gear disks, thereby driving the upper and lower blades to move in opposite directions. This type of mechanism is not only heavy but also difficult to manufacture, severely impacting reliability. CN 103552686 A, a combined ducted aerial reconnaissance robot; CN 108458892 A, a rotorcraft Mars drone with rock sample collection and handling functions; CN211196609 U, a tandem dual-motor coaxial counter-rotating aviation electric propulsion unit; and CN 117284522... A type of launch-oriented coaxial counter-rotating unmanned aerial vehicle (UAV) structure employs dual motors to achieve counter-rotating motion. While this simplifies the structure, the rotational speeds of the upper and lower rotors are not coordinated, reducing system reliability. Furthermore, the use of two motors inevitably increases weight. This results in a complex, heavy, and unreliable coaxial counter-rotating mechanism, making it difficult to manufacture for large helicopters, and excessively heavy for small helicopters. Its use in military helicopters is limited by reliability concerns. Summary of the Invention

[0004] The purpose of this invention is to provide a single-motor dual-rotor direct-drive coaxial counter-rotating propulsion unit to reduce the shortcomings of complex and heavy coaxial counter-rotating mechanisms, and in particular, to ensure the reliability of the propulsion unit.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit, comprising a first-stage blade assembly, a second-stage blade assembly, a dual-rotor single motor, and a guide cone. The first-stage blade assembly includes a first-stage hub, first-stage blades, and a first-stage blade coupling. The second-stage blade assembly includes a second-stage hub, second-stage blades, and a second-stage blade coupling. The dual-rotor single motor includes an inner rotor, an outer rotor, a support assembly, and an electrical interface. The outer rotor is coaxially mounted on the outside of the inner rotor. No transmission device is provided between the inner and outer rotors. The support assembly includes a support... The system includes a bearing, a motor frame, and a motor base. The inner and outer rotors are rotatably supported by the motor frame and the motor base. The motor frame is fixedly installed on the motor base, allowing both the inner and outer rotors to rotate independently. Under electromagnetic influence, the inner and outer rotors rotate coaxially with equal torque and in opposite directions. The inner rotor is directly connected to the first-stage blade assembly via a connector to form a first-stage propulsion unit. There is no transmission mechanism between the inner rotor and the first-stage blade assembly; the inner rotor directly drives the first-stage blade assembly. A heat-conducting channel is provided inside the inner rotor to cool it. The upper opening of the heat-conducting channel is below the connector. The upper opening is equipped with a flow guide switch that opens and closes according to temperature. When the temperature rises, the flow guide switch opens outward to draw in cold air, which then flows from top to bottom through the heat conduction channel to remove heat from the inner rotor. When the temperature is below the freezing point, the channel closes to prevent internal freezing. Preferably, the flow guide switch is a shape memory alloy flow guide switch. The outer rotor is directly connected to the secondary blade assembly via a connector to form a secondary propulsion unit. There is no transmission mechanism between the outer rotor and the secondary blades; the outer rotor directly drives the secondary blade assembly. The inner and outer rotors are reinforced with a reinforcing belt on the outside of the excitation assembly to overcome high-speed... The adverse effects of centrifugal force during rotation are mitigated; no transmission mechanism is provided between the first-stage and second-stage propulsion components; the guide cone is positioned in front of the first-stage blade, with its rotation center coinciding with the blade's rotation center, and includes a cone shell, an air sensor, and a data bus. The air sensor inside the guide cone collects real atmospheric data in front of the propulsion unit, such as atmospheric density, temperature, humidity, and velocity, and exports the data through a heat conduction channel via the data bus to optimize the control accuracy and propulsion efficiency of the propulsion unit; the electrical interface includes a continuous input / output device and a cable assembly to provide power and data transmission to the propulsion unit.

[0006] Furthermore, the first-stage propulsion component and the second-stage propulsion component have the same moment of inertia.

[0007] Furthermore, an excitation group for generating a rotating magnetic field is provided on the outer side of the inner rotor, and the inner rotor is provided with an inner rotor reinforcing belt to constrain the inner rotor excitation group to resist the centrifugal force caused by high-speed rotation; an excitation group for generating a rotating magnetic field is provided on the inner side of the outer rotor, and the outer rotor is provided with an outer rotor reinforcing belt to constrain the outer rotor excitation group to resist the centrifugal force caused by high-speed rotation; the rotating magnetic field generated by the inner and outer rotor excitation groups drives the first and second stage propulsion elements under the action of electromagnetic torque with equal action and reaction forces, balancing the deflection torque of unidirectional rotation and realizing the coaxial counter-propeller motion of the first and second stage propulsion elements; the number of outer rotor excitation groups is greater than the number of inner rotor excitation groups, and the number of excitation groups is generally a multiple of 3, while the difference between the number of inner and outer rotor excitation groups is 1, 2, or 3, in order to establish a reliable and stable rotating magnetic field.

[0008] Furthermore, a continuous input / output device is provided at the end of the inner rotor, preferably an electrical slip ring.

[0009] Furthermore, the two-stage blade assembly does not have a pitch control device, and the blade assembly is a rigid rotor with no hinge connection between the blades and the hub to simplify the structure.

[0010] Furthermore, the rotational speeds of the inner and outer rotors of the single motor in the dual-rotor system are variable, and the propulsion force of the propulsion unit is controlled by changing the rotational speeds of the inner and outer rotors.

[0011] Furthermore, the motor base is equipped with a sway mechanism, which allows the rotation axis of the dual-rotor single motor to swing within the sway cone angle, thereby changing the propulsion direction of the propulsion unit.

[0012] Furthermore, the motor base is connected to the aircraft to provide propulsion power for the aircraft.

[0013] The positive and beneficial technical effects of this invention are as follows: This invention employs a single motor with inner and outer dual rotors to directly drive two propeller blades, eliminating the need for intermediate transmission devices. Utilizing the electromagnetic torque principle—where the action and reaction forces of the rotating magnetic fields generated by the inner and outer rotor excitation groups are equal—it balances the reverse torque generated during unidirectional rotation, enabling the inner and outer rotors to rotate in opposite directions and balancing the unidirectional rotational deflection torque, thereby achieving coaxial counter-rotating propeller motion between the first-stage and second-stage propulsion components. The propulsion force is varied by increasing or decreasing the speed of the single motor with dual rotors; the propulsion direction is changed by the yaw motion of the motor base of the single motor with yawable dual rotors. This ensures reliable operation. This single-motor dual-rotor direct-drive coaxial counter-rotating propeller propulsion unit has a simple structure, lightweight design, high power-to-weight ratio, and high reliability, facilitating the rapid promotion and widespread application of coaxial counter-rotating propeller technology in aircraft, particularly promoting the performance improvement of small aircraft and high-reliability military aircraft. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the structure of the present invention.

[0015] Figure 2 The isometric view of the present invention with the guide cone and motor frame removed.

[0016] Figure 3 The isometric view of the present invention with the guide cone, motor frame and outer rotor removed.

[0017] Figure 4 This is a schematic diagram illustrating the change in propulsion direction (removal of the guide cone) according to the present invention.

[0018] Figure 5 This is a schematic diagram of the internal rotor structure of the present invention.

[0019] Figure 6 This is a schematic cross-sectional view of the inner rotor MM of the present invention, wherein the left figure shows the flow guide switch in the closed state and the right figure shows the flow guide switch in the open state.

[0020] Figure 7 This is a schematic diagram of Embodiment 2 of the present invention.

[0021] In the diagram: 10 First-stage blade assembly, 11 First-stage hub, 12 First-stage blade, 13 First-stage blade assembly connector; 20 Second-stage blade assembly, 22 Second-stage hub, 22 Second-stage blade, 23 Second-stage blade assembly connector; 30 Support assembly, 31 Bearing I, 32 Bearing II, 33 Bearing II, 34 Bearing IV, 35 Bearing V, 36 Motor frame, 36a Frame end neck, 36b Frame shell, 37 Motor base, 37a Yaw device, 37b Connecting device; 40 Guide cone, 41 Cone shell, 42 Temperature sensor, 43 Humidity sensor, 44 Density. 45 Data bus; 50 Outer rotor, 51 Upper journal of outer rotor, 52 Outer rotor housing, 53 Excitation assembly of outer rotor, 54 Reinforcing belt of outer rotor, 55 Lower journal of outer rotor; 60 Inner rotor, 61 Upper section of inner rotor, 62 Excitation assembly of inner rotor, 63 Lower journal of inner rotor, 64 Reinforcing belt of inner rotor, 65 Heat conduction channel, 66 Upper opening, 67 Flow guide switch; 70 Electrical interface, 71 Continuous input / output device; 72 Cable group; MM, inner rotor section; Straight arrow, air intake; Arc arrow, inner rotor rotation direction. Detailed Implementation

[0022] 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. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention. Where specific conditions are not specified in the embodiments, conventional conditions or conditions recommended by the manufacturer shall be followed. Reagents or instruments whose manufacturers are not specified are all conventional products that can be purchased commercially.

[0023] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for 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 the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0024] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0025] Example 1: As shown in the attached document Figure 1-6As shown, the single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit includes a first-stage blade assembly 10, a second-stage blade assembly 20, a dual-rotor single motor, and a guide cone 40. The first-stage blade assembly 10 includes a first-stage hub 11, first-stage blades 12, and a first-stage blade coupling 13. The second-stage blade assembly 20 includes a second-stage hub 21, second-stage blades 22, and a second-stage blade coupling 23. The dual-rotor single motor includes a support assembly 30, an outer rotor 50, an inner rotor 60, and an electrical interface 70. The outer rotor 50 is coaxially mounted on the outside of the inner rotor 60, and there is no transmission device between the inner rotor 60 and the outer rotor 50. The support assembly is a shell support, including support bearings 31-35, a motor frame 36, and a motor base 37. The support assembly 30 rotatably supports the inner rotor 60 and outer rotor 50 on the motor frame 36 and motor base 37. The motor frame 36 is fixedly installed on the motor base 37, allowing both the inner rotor 60 and outer rotor 50 to rotate independently. The inner rotor 60 is directly connected to the first-stage blade assembly 10 via the inner rotor upper shaft section 61 to form a first-stage propulsion unit. There is no transmission mechanism between the inner rotor upper shaft section 61 and the first-stage blade assembly 10; the inner rotor 60 directly drives the first-stage blade assembly 10. A heat conduction channel 65 is provided inside the inner rotor 60. The upper opening 66 of the heat conduction channel 65 is below the first-stage blade assembly 13, and the upper opening 66 is provided with... The flow guide switch 67 opens and closes according to temperature. When the temperature rises, the flow guide switch 67 opens outward to draw in cold air, which then flows from front to back through the heat conduction channel 65 to remove heat from the inner rotor 60. When the temperature is below the atmospheric freezing point, the channel closes to prevent internal freezing. Preferably, the flow guide switch 67 is a shape memory alloy flow guide switch. The outer rotor 50 is directly connected to the secondary blade assembly 20 via the upper journal 51 of the outer rotor to form a secondary propulsion unit. There is no transmission mechanism between the outer rotor 50 and the secondary blade assembly 20; the outer rotor 50 directly drives the secondary blade assembly 20. The inner rotor 60 has an inner rotor reinforcement belt 64 on the outside of the inner rotor excitation assembly 62 to overcome the centrifugal force of high-speed rotation. The outer rotor 50 is equipped with an outer rotor reinforcement belt 54 outside the outer rotor excitation group 53 to overcome the adverse effects of centrifugal force during high-speed rotation; the guide cone 40 is located in front of the first-stage blade group 10, and its center coincides with the blade rotation center. The guide cone 40 is equipped with air sensors to collect real atmospheric data in front of the propulsion unit, such as atmospheric density, temperature, and humidity. The air sensors are temperature sensor 42, humidity sensor 43, and density sensor 44. The data collected by the sensors is exported through the data bus 45 via the heat conduction channel to optimize the control accuracy and propulsion efficiency of the propulsion unit; the electrical interface 70 includes a continuous input / output device 71 and a cable group 72 to provide electrical support for the propulsion unit.

[0026] Furthermore, the first-stage propulsion component and the second-stage propulsion component have the same moment of inertia.

[0027] Furthermore, an inner rotor excitation group 62 for generating a rotating magnetic field is provided on the outer side of the inner rotor 60. The inner rotor is provided with an inner rotor reinforcing band 64 to constrain the inner rotor excitation group 62 to resist the centrifugal force caused by high-speed rotation. An outer rotor excitation group 53 for generating a rotating magnetic field is provided on the inner side of the outer rotor 50. The outer rotor is provided with an outer rotor reinforcing band 54 to constrain the outer rotor excitation group 53 to resist the centrifugal force caused by high-speed rotation. The number of outer rotor excitation groups is greater than the number of inner rotor excitation groups. The number of excitation groups is generally a multiple of 3. The difference between the number of inner and outer rotor excitation groups is 1, 2, or 3 to establish a reliable and stable rotating magnetic field.

[0028] Furthermore, a continuous input / output device 71 is provided at the end of the inner rotor 60. Preferably, the continuous input / output device 71 is an electrical slip ring.

[0029] Furthermore, neither the primary propulsion unit nor the secondary propulsion unit is equipped with a pitch control device, and the blade assembly is a rigid rotor with no hinge connection between the blades and the hub. Optimally, the blades and hub are an integral structure to simplify the structure.

[0030] Furthermore, the single motor control electrical parameters of the dual rotor change the rotational speed to change the propulsion force of the single motor dual rotor coaxial counter-rotor propulsion unit.

[0031] Furthermore, the motor base 37 is provided with a sway mechanism 37a, which allows the rotation axis of the dual-rotor single motor to swing within the sway cone angle, thereby changing the propulsion direction of the single-motor dual-rotor coaxial counter-propeller propulsion unit.

[0032] Furthermore, the motor base 37 is connected to the aircraft via a connecting device 37b to provide propulsion power to the aircraft.

[0033] Example 2: As shown in the attached document Figure 7 As shown, the single-motor dual-rotor direct-drive coaxial counter-rotating propulsion unit includes a first-stage blade assembly 10, a second-stage blade assembly 20, a dual-rotor single motor, and a guide cone 40. The dual-rotor single motor includes a support assembly 30, an outer rotor 50, an inner rotor 60, and an electrical interface 70. The outer rotor 50 is coaxially mounted on the outside of the inner rotor 60, and there is no transmission device between the inner rotor 60 and the outer rotor 50. The support assembly has an inner shaft support, including a support bearing, a motor frame, and a motor base. The support assembly 30 rotatably supports the inner rotor 60 and the outer rotor 50 on the motor frame and the motor base. The motor frame is fixed to the motor base, allowing the inner rotor 60 and the outer rotor 50 to rotate independently. The outer rotor is exposed to the air, which is more conducive to heat dissipation.

[0034] It should be noted that, in this specification, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a device comprising a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a device. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the device comprising said element.

[0035] The various embodiments in this specification are described in a related manner. The same or similar parts between the various embodiments can be referred to each other. Each embodiment focuses on describing the differences from other embodiments.

[0036] The above description is merely a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention are included within the scope of protection of the present invention.

[0037] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit, characterized in that: It includes a first-stage blade assembly, a second-stage blade assembly, a dual-rotor single motor, and a guide cone. The dual-rotor single motor consists of an inner rotor, an outer rotor, a support assembly, and an electrical interface. The outer rotor is coaxially mounted on the outside of the inner rotor. The support assembly rotatably supports the inner and outer rotors, allowing them to rotate independently. Under electromagnetic influence, the inner and outer rotors rotate coaxially and in opposite directions. The inner rotor is directly connected to the first-stage blade assembly to form a first-stage propulsion unit, and the outer rotor is directly connected to the second-stage blade assembly to form a second-stage propulsion unit. There is no transmission mechanism between the first-stage and second-stage propulsion units.

2. The single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit according to claim 1, characterized in that: An inner rotor excitation group that generates a rotating magnetic field is provided on the outer side of the inner rotor, and an inner rotor reinforcement belt is provided on the outer side of the inner rotor excitation group; an outer rotor excitation group that generates a rotating magnetic field is provided on the inner side of the outer rotor, and an outer rotor reinforcement belt is provided on the outer side of the outer rotor excitation group.

3. The single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit according to claim 1, characterized in that: The motor base is equipped with a sway mechanism, which allows the rotation axis of the dual-rotor single motor to swing within the sway cone angle, thereby changing the propulsion direction of the propulsion unit.

4. The single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit according to claim 1, characterized in that: The guide cone is positioned in front of the first-stage blade, with its rotation center coinciding with the blade's rotation center. It includes a cone shell, an air sensor, and a data bus.

5. A single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit according to any one of claims 1-4, characterized in that: The aforementioned support assembly is an outer shell support.

6. The single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit according to claim 5, characterized in that: The inner rotor is provided with a heat conduction channel inside, and the upper opening of the heat conduction channel is below the connector. The upper opening is provided with a flow guide switch that opens and closes with temperature.

7. A single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit according to claim 6, characterized in that: The aforementioned flow guide opening and closing device is a shape memory alloy flow guide opening and closing device.

8. A single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit according to any one of claims 1-4, characterized in that: The aforementioned support assembly is an inner shaft support.

9. A single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit according to claim 8, characterized in that: The outer rotor is directly exposed to the atmosphere.

10. A single-motor dual-rotor direct-drive coaxial counter-rotating propeller unit according to any one of claims 1-4, characterized in that: The blade assembly is a rigid rotor, with the blades and hub connected without hinges.

Images