Counter-rotating double-rotor electric propulsion motor for vertical take-off and landing electric aircraft

Abstract

The invention belongs to the field of electric propulsion motor systems for vertical take-off and landing electric aircrafts, and particularly relates to a contra-rotating double-rotor electric propulsion motor for a vertical take-off and landing electric aircraft, which comprises a motor shell assembly, a stator assembly and two rotor assemblies, a gap is formed between the two rotor assemblies; the stator assembly is arranged between the inner wall of the shell and the outer rings of the two rotor assemblies; wherein the axial length of the stator assembly is larger than the sum of the axial lengths of the two rotor assemblies, and the number of pole pairs of the permanent magnets of the two rotor assemblies is different. The device realizes contra-rotation and non-constant-speed operation of the double rotors.

Description

Technical Field

[0001] The invention belongs to the field of electric propulsion motor systems for vertical take-off and landing electric aircraft, and in particular relates to a counter-rotating dual-rotor electric propulsion motor for vertical take-off and landing electric aircraft. Background Art

[0002] As the main power component of vertical take-off and landing electric aircraft, the performance of the electric propulsion system directly affects the safety, operability, environmental protection and endurance of the aircraft. At present, the electric propulsion system mainly includes single-propeller propulsion scheme and counter-rotating twin-propeller scheme. Compared with the single-propeller scheme, the counter-rotating twin-propeller scheme effectively eliminates the influence of reaction torque and the asymmetric thrust generated during rotation, which greatly improves the stability of the aircraft. The counter-rotating twin-rotor electric propulsion motor has the advantages of small size, high power density and compact structure, and has great development potential, so it has attracted widespread attention.

[0003] At present, counter-rotating twin-rotor electric propulsion motors usually adopt the method of integrating two motors so that the rotational speeds of the two rotors are opposite in direction and equal in magnitude. However, in specific occasions with different propeller sizes, the rotational speeds of the two rotors are required to be opposite in direction and of different magnitudes, which poses new challenges to the motor structure and principle.

[0004] Therefore, it is necessary to provide a counter-rotating twin-rotor electric propulsion motor for a vertical take-off and landing electric aircraft to solve the above problems. Summary of the invention

[0005] The present invention provides a counter-rotating twin-rotor electric propulsion motor for a vertical take-off and landing electric aircraft, so as to solve the problem that the existing counter-rotating twin-rotor electric propulsion motor usually adopts a two-motor integration method to make the two rotors rotate in opposite directions and have equal speeds. However, in specific occasions with different propeller sizes, the two rotors are required to rotate in opposite directions and have different speeds. Therefore, the existing technology cannot solve the problem that the two rotors rotate in opposite directions and have different speeds.

[0006] The present invention provides a counter-rotating dual-rotor electric propulsion motor for a vertical take-off and landing electric aircraft using the following technical solutions, including: A motor housing assembly, wherein two rotor assemblies are sequentially arranged in the motor housing assembly along the axial direction, and there is a spacing between the two rotor assemblies, and the pole pairs of the permanent magnets of the two rotor assemblies are different; And a stator assembly is arranged between the inner wall of the shell and the outer rings of the two rotor assemblies, and is used to generate a forward rotating magnetic field and a reverse rotating magnetic field; wherein the axial length of the stator assembly is greater than the sum of the axial lengths of the two rotor assemblies.

[0007] Preferably, the rotor assembly comprises: A hollow shaft, one end of which is fitted with a rotor core and fixed thereon, and the other end of which passes through the motor housing assembly; and a permanent magnet, which is fixedly mounted on the rotor core and has a gap between its outer ring and the inner ring of the stator assembly; Wherein, the hollow shaft of the rotor assembly close to the front end cover of the motor housing assembly is coaxially sleeved on the hollow shaft of another rotor assembly.

[0008] Preferably, the pole pairs of the permanent magnets of the two rotor assemblies satisfy:

[0009] The rotor assembly close to the rear end cover of the motor housing assembly is the first rotor assembly, and the rotor assembly close to the front end cover of the motor housing assembly is the second rotor assembly. represents the number of pole pairs of the permanent magnets in the first rotor assembly; represents the number of pole pairs of the permanent magnets in the second rotor assembly; Indicates the number of main winding slots.

[0010] Preferably, an annular boss is provided at the end of the hollow shaft, and an annular mounting groove is provided on the outer ring of the annular boss, wherein the rotor core is sleeved and fixed in the annular mounting groove.

[0011] Preferably, the distance between the two rotor assemblies is the distance between adjacent surfaces of the annular bosses of the two rotor assemblies, and the distance is 5 mm-10 mm.

[0012] Preferably, the stator assembly comprises: a stator core, on which a main winding and a secondary winding are arranged, wherein the main winding and the secondary winding are both used to generate a forward rotating magnetic field and a reverse rotating magnetic field.

[0013] Preferably, the stator core comprises: an annular body, a plurality of teeth are evenly distributed on the inner ring of the annular body, a main winding slot is formed between every two adjacent teeth, and two secondary winding slots are opened on each tooth, wherein the opening direction of the secondary winding slot points to the center of the annular body.

[0014] Preferably, the distance between the center line of the secondary winding slot and the center line of the tooth is 0.2-0.25 times the tooth width.

[0015] The beneficial effects of the present invention are: By providing a single stator assembly and two rotor assemblies, and the pole pairs of the permanent magnets of the two rotor assemblies are different, the propulsion motor composed of the single stator assembly and the two rotor assemblies of the present invention is an electric propulsion motor with counter-rotation and unequal speeds, that is, when the main winding of the stator assembly is energized, the magnetic field modulation and magnetic pole filtering principles are utilized to realize the counter-rotation and unequal speed operation of the dual rotors. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only 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.

[0017] Figure 1 A cross-sectional view of a counter-rotating twin-rotor electric propulsion motor for a vertical take-off and landing electric aircraft according to the present invention; Figure 2 It is a schematic structural diagram of a stator core in a counter-rotating dual-rotor electric propulsion motor for a vertical take-off and landing electric aircraft according to the present invention; Figure 3 It is a schematic diagram of the direction of rotation of the rotating magnetic field extracted by the two rotor cores when the main winding is energized in an embodiment of the present invention.

[0018] In the figure: 1, cylindrical shell; 2, rear end cover; 3, first permanent magnet; 4, first rotor core; 5, first hollow shaft; 6, stator core; 7, main winding; 8, auxiliary winding; 9, front end cover; 10, second permanent magnet; 11, second rotor core; 12, second hollow shaft; 13, teeth; 14, main winding slot; 15, auxiliary winding slot; I, first rotor assembly; II, second rotor assembly; III, stator assembly. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only 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.

[0020] An embodiment of a counter-rotating dual-rotor electric propulsion motor for a vertical take-off and landing electric aircraft of the present invention comprises: a motor housing assembly, a stator assembly III and two rotor assemblies, wherein: Figure 1 As shown, the motor housing assembly includes a cylindrical housing 1, a front end cover 9 and a rear end cover 2, and the two ends of the cylindrical housing 1 are connected to the front end cover 9 and the rear end cover 2 to form a motor housing; two rotor assemblies are sequentially arranged in the motor housing assembly along the axial direction, and there is a gap between the two rotor assemblies; the stator assembly III is arranged between the inner wall of the housing 1 and the outer rings of the two rotor assemblies, and the stator assembly III is used to generate a forward rotating magnetic field and a reverse rotating magnetic field; wherein, the axial length of the stator assembly III is greater than the sum of the axial lengths of the two rotor assemblies, and the pole pairs of the permanent magnets of the two rotor assemblies are different.

[0021] like Figure 1As shown, the two rotor assemblies in the embodiment are a first rotor assembly I close to the rear end cover 2 of the motor housing assembly, and a second rotor assembly II close to the front end cover 9 of the motor housing assembly. The first rotor assembly I includes: a first hollow shaft 5, a first rotor core 4 and a first permanent magnet 3, wherein the first hollow shaft 5 is sleeved and fixed with the first rotor core 4 at one end, and the other end thereof passes through the front end cover 9 of the motor housing assembly, the first permanent magnet 3 is sleeved and fixed on the first rotor core 4, and there is a gap between the outer ring of the first permanent magnet 3 and the inner ring of the stator assembly III; the second rotor assembly II includes: a second hollow shaft 12, a second rotor core 11 and a second permanent magnet 10, wherein the second rotor core 11 is sleeved and fixed on both ends of the second hollow shaft 12, and the other end thereof passes through the front end cover 9 of the motor housing assembly, the second permanent magnet 10 is sleeved and fixed on the second rotor core 11, and the outer ring of the second permanent magnet 10 is slidably connected with the inner ring of the stator assembly III; wherein the number of pole pairs of the first permanent magnet 3 and the second permanent magnet 10 is different.

[0022] In this embodiment, the pole pairs of the first permanent magnet 3 and the second permanent magnet 10 satisfy:

[0023] in, represents the number of pole pairs of the first permanent magnet 3 in the first rotor assembly 1; represents the number of pole pairs of the second permanent magnet 10 in the second rotor assembly II; Indicates the number of main winding slots 14 of the stator assembly III.

[0024] In order to accurately install the rotor core, an annular boss is fixed at the end of the hollow shaft, and an annular mounting groove is provided on the outer ring of the annular boss, wherein the rotor core is fixed in the annular mounting groove. In this embodiment, the distance between the two rotor assemblies is the distance between the adjacent surfaces of the annular bosses of the two rotor assemblies, and in this embodiment, it is 5 mm.

[0025] like Figure 1 As shown, the stator assembly III in this embodiment includes: a stator core 6, on which a main winding 7 and an auxiliary winding 8 are arranged, and the main winding 7 and the auxiliary winding 8 are used to generate a forward rotating magnetic field and a reverse rotating magnetic field, as shown in FIG. Figure 2 As shown, the stator core 6 of this embodiment includes: a ring body, a plurality of teeth 13 are evenly distributed in the inner ring of the ring body, a main winding slot 14 is formed between every two adjacent teeth 13, and two auxiliary winding slots 15 are formed on each tooth 13, wherein the opening direction of the auxiliary winding slot 15 points to the center of the ring body, and the distance between the center line of the auxiliary winding slot 15 and the center line of the tooth 13 is 0.25 times the tooth width. The number of the main winding slots 14 is , the number of secondary winding slots 15 is , and satisfy: .

[0026] It should be noted that the main winding 7 is energized to generate a forward rotating magnetic field and a reverse rotating magnetic field by magnetic field modulation. According to the magnetic pole filtering principle, Figure 3 As shown, the first rotor assembly I extracts The positive rotating magnetic field, the second rotor assembly II extracts The reverse rotating magnetic field realizes the first rotor assembly I at a speed of Forward rotation, the second rotor assembly II at speed Reverse rotation, and satisfy The auxiliary winding 8 is energized in reverse to adjust the positive rotating magnetic field of the first rotor component I. and the counter-rotating magnetic field falling on the second rotor assembly II The size of the torque ratio is adjusted to achieve stable control of the motor speed. t Indicates time, θ Represents the spatial angle, ω represents the angular frequency, B p1 represents the amplitude of the positive rotating magnetic field, B p2 Represents the amplitude of the counter-rotating magnetic field.

[0027] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A counter-rotating twin-rotor electric propulsion motor for a vertical take-off and landing electric aircraft, characterized in that: include: A motor housing assembly, wherein two rotor assemblies are sequentially arranged in the motor housing assembly along the axial direction, and there is a spacing between the two rotor assemblies, and the pole pairs of the permanent magnets of the two rotor assemblies are different; And a stator assembly (III) is arranged between the inner wall of the housing (1) and the outer rings of the two rotor assemblies, and is used to generate a forward rotating magnetic field and a reverse rotating magnetic field; wherein the axial length of the stator assembly (III) is greater than the sum of the axial lengths of the two rotor assemblies.

2. The counter-rotating twin-rotor electric propulsion motor for a vertical take-off and landing electric aircraft according to claim 1, characterized in that: The rotor assembly includes: A hollow shaft, one end of which is fitted with a rotor core and fixed thereon, and the other end of which passes through the motor housing assembly; and a permanent magnet, which is fixedly mounted on the rotor core and has a gap between its outer ring and the inner ring of the stator assembly (III); The hollow shaft of the rotor assembly close to the front end cover (9) of the motor housing assembly is coaxially sleeved on the hollow shaft of another rotor assembly.

3. The counter-rotating twin-rotor electric propulsion motor for a vertical take-off and landing electric aircraft according to claim 2, characterized in that: The number of pole pairs of the permanent magnets of the two rotor assemblies satisfies: The rotor assembly close to the rear end cover (2) of the motor housing assembly is a first rotor assembly (I), and the rotor assembly close to the front end cover (9) of the motor housing assembly is a second rotor assembly (II). represents the number of pole pairs of the permanent magnets in the first rotor assembly (I); represents the number of pole pairs of the permanent magnets in the second rotor assembly (II); Indicates the number of main winding slots (14).

4. The counter-rotating twin-rotor electric propulsion motor for a vertical take-off and landing electric aircraft according to claim 2, characterized in that: An annular boss is arranged at the end of the hollow shaft, and an annular mounting groove is arranged on the outer ring of the annular boss, wherein the rotor core is sleeved and fixed in the annular mounting groove.

5. The counter-rotating twin-rotor electric propulsion motor for a vertical take-off and landing electric aircraft according to claim 4, characterized in that: The distance between the two rotor assemblies is the distance between adjacent surfaces of the annular bosses of the two rotor assemblies, and the distance is 5mm-10mm.

6. The counter-rotating twin-rotor electric propulsion motor for a vertical take-off and landing electric aircraft according to claim 1, characterized in that: The stator assembly (III) comprises: a stator core (6) on which a main winding (7) and a secondary winding (8) are arranged, wherein the main winding (7) and the secondary winding (8) are both used to generate a forward rotating magnetic field and a reverse rotating magnetic field.

7. The counter-rotating twin-rotor electric propulsion motor for a vertical take-off and landing electric aircraft according to claim 6, characterized in that: The stator core (6) comprises: an annular body, a plurality of teeth (13) being evenly distributed on the inner ring of the annular body, a main winding slot (14) being formed between every two adjacent teeth (13), and two secondary winding slots (15) being provided on each tooth (13), wherein the direction in which the secondary winding slots (15) are provided points to the center of the annular body.

8. The counter-rotating twin-rotor electric propulsion motor for a vertical take-off and landing electric aircraft according to claim 7, characterized in that: The distance between the center line of the secondary winding slot (15) and the center line of the tooth (13) is 0.2-0.25 times the tooth width.

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