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

Abstract

According to the single-motor double-rotor direct-drive coaxial reverse propeller propulsion 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 propulsion component and a second-stage propulsion 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] The present application belongs to the field of aviation power technology, and in particular relates to a single-motor dual-rotor direct-drive coaxial reverse propeller propulsion unit. Background Art

[0002] Coaxial counter-propeller is an aviation power technology that connects two propellers to a common axis, with one propeller arranged opposite to the other, that is, back to back. The double-layer blades share a transmission shaft, but rotate in opposite directions, which can balance and eliminate the unidirectional rotation deflection torque, and the upper propeller disc provides "pre-compression" for the lower propeller disc, so that the second stage of the lower layer has a larger "intake / exhaust volume" and "airflow density". Although it does not reach 2 times, the performance improvement is significant. In this way, coaxial counter-propeller has the following advantages: high efficiency, by reducing the size of a single propeller, the required power input can be reduced, thereby improving the efficiency of the entire system; large airflow, because the propellers rotate in opposite directions, the first layer of propellers can provide a pre-compression effect for the second layer, making the second layer of airflow density higher; light structure, reducing the structure of two independent propellers that need to be supported, which helps to reduce the overall weight of the helicopter; space saving, at the same output power (helicopter to external air), the rotor length / rotation area is reduced, and the tail rotor is omitted, which is very suitable for use in the narrow space of the ship.

[0003] However, the disadvantages of coaxial counter-propeller technology are also obvious, mainly reflected in the fact that the coaxial and reverse-rotating mechanism of the upper and lower blades is complex and heavy, which also deteriorates the reliability of the mechanism. For example, CN 110925364 A discloses a planetary reducer for a coaxial counter-propeller helicopter. In order to realize the coaxial counter-propeller, a two-layer two-set planetary reduction structure is adopted. The parts are many, the transmission chain is long, the weight is large, and the reliability is poor. CN 108791859 A, a fast approaching rotor UAV, CN 110127043 A, a new energy coaxial counter-propeller aircraft, and CN 111392049 A, a coaxial counter-propeller helicopter transmission system all adopt a differential mechanism, using an active bevel gear to transmit motion to two large driven bevel gear plates, thereby driving the upper and lower blades to achieve forward and reverse motion. This mechanism is not only heavy but also difficult to process, which seriously affects the reliability. CN 103552686 A, a combined ducted aerial reconnaissance robot, CN 108458892 A, a rotor-type Mars UAV with rock sample collection and transportation functions, CN211196609 U, a tandem dual-motor coaxial counter-propeller aviation electric propulsion unit, and CN 117284522 A coaxial counter-propeller UAV structure for launch uses dual motors to achieve counter-propeller movement. Although the structure is simplified, the rotation speed of the upper and lower propellers is not coordinated, which reduces the reliability of the system. In addition, two motors are bound to be heavy. This results in the coaxial counter-propeller technology mechanism being complex, the structure being too heavy, and the reliability being poor. The mechanism for large helicopters is difficult to manufacture, and the structure is obviously too heavy for small helicopters. As for military helicopters, the use is limited due to reliability. Utility Model Content

[0004] The utility model aims to provide a single-motor dual-rotor direct-drive coaxial reverse propeller propulsion unit to reduce the shortcomings of the coaxial reverse propeller mechanism being complex and heavy, and in particular to ensure the reliability of the propulsion unit.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a single-motor dual-rotor direct-drive coaxial reverse propeller propulsion unit, comprising a primary blade group, a secondary blade group, a dual-rotor single motor and a guide cone, the primary blade group comprises a primary hub, a primary blade, and a primary blade adapter, the secondary blade group comprises a secondary hub, a secondary blade, and a secondary blade adapter; the dual-rotor single motor comprises an inner rotor, an outer rotor, a support group and an electrical interface, the outer rotor is coaxially sleeved on the outer side of the inner rotor, no transmission device is provided between the inner rotor and the outer rotor, and the support group includes The invention comprises a supporting bearing, a motor frame and a motor base, wherein the inner and outer rotors are rotatably supported on the motor frame and the motor base, and the motor frame is fixedly mounted on the motor base so that the inner and outer rotors can rotate independently, and the inner and outer rotors rotate coaxially and in opposite directions with equal torque under electromagnetic action; the inner rotor is directly connected to the first-stage blade group through a connector to form a first-stage propulsion element, and no transmission mechanism is arranged between the inner rotor and the first-stage blade group, and the inner rotor directly drives the first-stage blade group; a heat conduction channel is arranged inside the inner rotor to cool the inner rotor, and the upper opening of the heat conduction channel is below the connector, The upper opening is provided with a guide switch which opens and closes with the temperature. When the temperature rises, the guide switch opens outwards to draw in cold air from top to bottom through the heat conduction channel to take away the heat of the inner rotor. When the temperature is lower than the freezing point, the channel is closed to avoid internal freezing. Preferably, the guide switch is a shape memory alloy guide switch; the outer rotor is directly connected to the secondary blade group through a connector to form a secondary propulsion component. No transmission mechanism is provided between the outer rotor and the secondary blades, and the outer rotor directly drives the secondary blade group; the inner rotor and the outer rotor are provided with strengthening belts on the outside of the excitation group to overcome high The adverse effects of high-speed rotation of the centrifugal force; no transmission mechanism is provided between the first-stage propulsion component and the second-stage propulsion component; the guide cone is arranged in front of the first-stage blade, and its rotation center coincides with the rotation center of the blade, including a cone shell, an air sensor, and a data bus. The guide cone is equipped with an air sensor to collect real atmospheric data in front of the propulsion unit, such as atmospheric density, temperature, humidity, speed, etc., and the data bus is used to export the data through the heat conduction channel to optimize the control accuracy and propulsion efficiency of the propulsion unit; the electrical interface includes a continuous input and output device and a cable group to provide power and data transmission for 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 arranged on the outer side of the inner rotor, and the inner rotor is provided with an inner rotor reinforcement 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 arranged on the inner side of the outer rotor, and the outer rotor is provided with an outer rotor reinforcement 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 primary and secondary propulsion components under the action of electromagnetic torques in which the action force and the reaction force are equal, balances the deflection torque of unidirectional rotation, and realizes the coaxial counter-propeller motion of the primary propulsion component and the secondary propulsion component; the number of the outer rotor excitation groups is greater than the number of the inner rotor excitation groups, and the number of the excitation groups is generally a multiple of 3, and the difference in the number of the inner and outer rotor excitation groups is 1, 2 or 3, so as 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, the continuous input-output device is an electrical slip ring.

[0009] Furthermore, the two-stage blade group is not provided with a pitch-changing device, the blade group is a rigid rotor, and the blades are connected to the hub without hinges to simplify the structure.

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

[0011] Furthermore, the motor base is provided with a yaw mechanism, so that the rotation axis of the dual-rotor single motor can swing within a yaw 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 the utility model are as follows: the present invention adopts a single motor with inner and outer double rotors to directly drive two pairs of blades, without the need for a transmission device in the middle, and uses the electromagnetic torque principle that the action force and reaction force of the rotating magnetic field generated by the inner and outer rotor excitation groups are equal, to balance the reverse torque generated during unidirectional rotation, so that the inner and outer rotors can rotate in the opposite direction and balance the unidirectional rotation deflection torque, thereby realizing the coaxial reverse propeller movement of the first-stage propulsion component and the second-stage propulsion component; using the increase or decrease of the speed of the single motor with dual rotors to realize the change of propulsion force; using the swaying movement of the motor base of the single motor with swayable dual rotors to realize the change of propulsion direction; thus, reliable operation is achieved. The single motor dual rotor direct drive coaxial reverse propeller propulsion unit has a simple structure, a light structure, a large power-to-weight ratio, and high reliability, which is conducive to the rapid promotion and popularization of coaxial reverse propeller technology in aircraft, especially to promote the performance improvement of small aircraft and military high-reliability aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a structural schematic diagram of the utility model.

[0015] Figure 2 This is an axonometric view of the utility model without the guide cone and the motor frame.

[0016] Figure 3 This is an axonometric view of the utility model without the guide cone, motor frame and outer rotor.

[0017] Figure 4 This is a schematic diagram of changing the propulsion direction of the utility model (removing the guide cone).

[0018] Figure 5 This is a schematic diagram of the inner rotor structure of the utility model.

[0019] Figure 6 It is a schematic cross-sectional view of the inner rotor MM of the utility model, wherein the left figure shows the closed state of the diversion switch, and the right figure shows the open state of the diversion switch.

[0020] Figure 7 This is a schematic diagram of the second embodiment of the present utility model.

[0021] In the figure: 10 a first-stage blade group, 11 a first-stage hub, 12 a first-stage blade, 13 a first-stage blade group adapter; 20 a second-stage blade group, 22 a second-stage hub, 22 a second-stage blade, 23 a second-stage blade group adapter; 30 a support group, 31 a bearing I, 32 a bearing II, 33 a bearing II, 34 a bearing IV, 35 a bearing V, 36 a motor frame, 36a a frame end neck, 36b a frame shell, 37 a motor base, 37a a yaw device, 37b a connecting device; 40 a guide cone, 41 a cone shell, 42 a temperature sensor, 43 a humidity sensor, 44 a density sensor, Sensor, 45 data bus; 50 outer rotor, 51 outer rotor upper journal, 52 outer rotor housing, 53 outer rotor excitation group, 54 outer rotor reinforcement belt, 55 outer rotor lower journal; 60 inner rotor, 61 inner rotor upper shaft section, 62 inner rotor excitation group, 63 inner rotor lower journal, 64 inner rotor reinforcement belt, 65 heat conduction channel, 66 upper opening, 67 diversion switch; 70 electrical interface, 71 continuous input and output device; 72 cable group; MM, inner rotor cut-away part; straight arrow, air intake; arc arrow, inner rotor rotation direction. DETAILED DESCRIPTION

[0022] The following is a clear and complete description of the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only partial embodiments of the present invention, rather than all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present invention. If the specific conditions are not specified in the embodiments, they are carried out according to conventional conditions or conditions recommended by the manufacturer. If the manufacturer is not specified for the reagents or instruments used, they are all conventional products that can be purchased commercially.

[0023] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0024] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0025] Embodiment 1: As shown in the attached Figure 1-6As shown, a single-motor dual-rotor direct-drive coaxial reverse propeller propulsion unit includes a first-stage blade group 10, a second-stage blade group 20, a single motor of the dual rotor and a guide cone 40; the first-stage blade group 10 includes a first-stage hub 11, a first-stage blade 12, and a first-stage blade adapter 13, and the second-stage blade group 20 includes a second-stage hub 21, a second-stage blade 22, and a second-stage blade adapter 23; the single motor of the dual rotor includes a support group 30, an outer rotor 50, an inner rotor 60, and an electrical interface 70, the outer rotor 50 is coaxially sleeved on the outside of the inner rotor 60, and no transmission device is provided between the inner rotor 60 and the outer rotor 50; the support group is a shell support, including support bearings 31-35, a motor frame 36, and a motor base 37. The support group 30 rotatably supports the inner rotor 60 and the outer rotor 50 on the motor frame 36 and the motor base 37. The motor frame 36 is fixedly installed on the motor base 37 so that the inner rotor 60 and the outer rotor 50 can rotate independently. The inner rotor 60 is directly connected to the first-stage blade connector 13 of the first-stage blade group 10 through the inner rotor upper shaft section 61 to form a first-stage propulsion component. No transmission mechanism is provided between the inner rotor upper shaft section 61 of the inner rotor 60 and the first-stage blade group 10, and the inner rotor 60 directly drives the first-stage blade group 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 connector 13. The upper opening 66 is provided with The flow guide shutter 67 opens and closes with the temperature. When the temperature rises, the flow guide shutter 67 opens outward to draw in cold air from front to back through the heat conduction channel 65 to take away the heat of the inner rotor 60. When the temperature is lower than the atmospheric condensation point, the channel is closed to prevent internal freezing. Preferably, the flow guide shutter 67 is a shape memory alloy flow guide shutter; the outer rotor 50 is directly connected to the secondary blade connector 23 of the secondary blade group 20 through the outer rotor upper shaft neck 51 to form a secondary propulsion component. There is no transmission mechanism between the outer rotor 50 and the secondary blade group 20. The outer rotor 50 directly drives the secondary blade group 20; the inner rotor 60 is provided with an inner rotor reinforcement belt 64 on the outer side of the inner rotor excitation group 62 to overcome the centrifugal force of high-speed rotation. The outer rotor 50 is provided with an outer rotor reinforcement belt 54 on the outer side of the outer rotor excitation group 53 to overcome the adverse effects of the centrifugal force of high-speed rotation; the guide cone 40 is arranged 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 an air sensor to collect real atmospheric data in front of the propulsion unit, such as atmospheric density, temperature, humidity, etc. The air sensors are temperature sensors 42, humidity sensors 43, and density sensors 44. The data collected by the sensors are exported by the data bus 45 through the heat conduction channel to optimize the control accuracy and propulsion efficiency of the propulsion unit; the electrical interface 70 includes a continuous input and 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 disposed on the outer side of the inner rotor 60, and an inner rotor reinforcement belt 64 is provided on the inner rotor 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 disposed on the inner side of the outer rotor 50, and an outer rotor reinforcement belt 54 is provided on the outer rotor to constrain the outer rotor excitation group 53 to resist the centrifugal force caused by high-speed rotation; the number of the outer rotor excitation groups is greater than the number of the inner rotor excitation groups, and the number of the excitation groups is generally a multiple of 3, and the difference in the number of the inner and outer rotor excitation groups is 1, 2 or 3, so as 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 first-stage propulsion component nor the second-stage propulsion component is provided with a pitch-changing device, and the blade group is a rigid rotor, and the blades are hinge-freely connected to the hub. Optimally, the blades and the hub are an integrated structure to simplify the structure.

[0030] Furthermore, the single motor of the dual-rotor controls electrical parameters to change the rotation speed so as to change the propulsion force of the single-motor dual-rotor coaxial counter-propeller propulsion unit.

[0031] Furthermore, a yaw mechanism 37a is provided under the motor base 37, so that the rotation axis of the dual-rotor single motor can swing within the yaw cone angle to change the propulsion direction of the single-motor dual-rotor coaxial reverse propeller propulsion unit.

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

[0033] Embodiment 2: As shown in the attached Figure 7 As shown, a single-motor dual-rotor direct-drive coaxial reverse propeller propulsion unit includes a first-stage blade group 10, a second-stage blade group 20, a dual-rotor single motor and a guide cone 40; the dual-rotor single motor includes a support group 30, an outer rotor 50, an inner rotor 60, and an electrical interface 70, the outer rotor 50 is coaxially sleeved on the outer side of the inner rotor 60, and no transmission device is provided between the inner rotor 60 and the outer rotor 50; the inner shaft support of the support group includes a support bearing, a motor frame, and a motor base, the support group 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, so that the inner rotor 60 and the outer rotor 50 can rotate independently, and 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, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprises" or any other variants thereof are intended to cover non-exclusive inclusion, so that a device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such a device. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the presence of other identical elements in the device including the element.

[0035] Each embodiment in this specification is described in a related manner, and the same or similar parts between the embodiments can be referenced to each other, and each embodiment focuses on the differences from other embodiments.

[0036] The above description is only a preferred embodiment of the present invention and is not intended to limit the protection scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention are included in the protection scope of the present invention.

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

Claims

1. A single-motor dual-rotor direct-drive coaxial reverse propeller propulsion unit, characterized in that: It includes a primary blade group, a secondary blade group, a dual-rotor single motor and a guide cone; the dual-rotor single motor consists of an inner rotor, an outer rotor, a support group and an electrical interface, the outer rotor is coaxially sleeved on the outside of the inner rotor; the support group includes a support bearing, a motor frame and a motor base, the support group rotatably supports the inner and outer rotors so that the inner and outer rotors can rotate independently, and the inner and outer rotors rotate coaxially in opposite directions under electromagnetic action; the inner rotor is directly connected to the primary blade group to form a primary propulsion component, the outer rotor is directly connected to the secondary blade group to form a secondary propulsion component, and there is no transmission mechanism between the primary propulsion component and the secondary propulsion component.

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

3. The single-motor dual-rotor direct-drive coaxial counter-propeller propulsion unit according to claim 1, characterized in that: A yaw mechanism is provided under the motor base, so that the rotation axis of the dual-rotor single motor can swing within the yaw cone angle, thereby changing the propulsion direction of the propulsion unit.

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

5. A single-motor dual-rotor direct-drive coaxial counter-propeller propulsion unit according to any one of claims 1 to 4, characterized in that: The support group is a shell support.

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

7. A single-motor dual-rotor direct-drive coaxial counter-propeller propulsion unit according to claim 6, characterized in that: The diversion switch is a shape memory alloy diversion switch.

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

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

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