Shaftless vector electric rotor and helicopter

Abstract

The application discloses an axis-free vector electric rotor and a helicopter, and aims at solving the problems of the existing helicopter, such as large control difficulty, complex structure, large noise and high cost. The application comprises two rotor assemblies, the two rotor assemblies are arranged in an up-down mode, and a connecting piece is arranged between the two rotor assemblies; a posture adjusting assembly is arranged on the connecting piece to realize posture adjustment of the rotor assembly; wherein the rotor assembly comprises a stator and a rotor, a plurality of magnetic tiles are arranged on the rotor in a circumferential mode, a plurality of winding iron cores are arranged on the stator in a circumferential mode, and the magnetic poles of the two adjacent magnetic tiles on the side of the winding iron core are opposite; the posture adjusting assembly comprises a vector horizontal rod and a vector vertical rod, the vector horizontal rod is rotatably arranged on the connecting piece, the vector vertical rod is rotatably arranged on the vector horizontal rod, a horizontal rod steering engine is arranged between the connecting piece and the vector horizontal rod, and a vertical rod steering engine is arranged between the vector horizontal rod and the vector vertical rod. The aircraft can realize various motion posture adjustments in the air very flexibly, has simple structure, low cost and small noise.

Description

Technical Field

[0001] This invention relates to helicopter technology, and more specifically, to an shaftless vector electric rotor and a helicopter. Background Technology

[0002] Traditional helicopters generally employ an engine, gearbox, driveshaft, and variable pitch mechanism to achieve flight maneuvers such as takeoff, pitch, and roll. Most are single-rotor with a tail rotor, though some have coaxial counter-rotating rotors. Power is provided by the engine and transmitted to the rotor blades through a complex and bulky transmission mechanism. This transmission mechanism contains numerous bearings, driveshafts, and gears; these components require high precision machining, strong materials, and are heavy, necessitating regular maintenance. During flight, the transmission mechanism generates significant noise; gear meshing produces periodic noise and resonance, making it a major noise and vibration source for helicopters. Operating a helicopter is very difficult, requiring extensive professional training to fly safely. Furthermore, pilots must endure tremendous noise and vibration, resulting in a poor experience and rapid fatigue. Helicopter accidents are frequent, often leading to fatalities. Traditional helicopters suffer from drawbacks such as complex structure, poor safety, high energy consumption, high noise levels, and high maintenance costs. Summary of the Invention

[0003] To overcome the above shortcomings, this invention provides a shaftless vector electric rotor and helicopter that can easily achieve a series of actions such as takeoff, landing, pitch, roll, and hovering. Compared with traditional helicopters, it has low noise, no vibration generated by mechanical mechanisms, greatly improves the pilot's experience, and reduces fatigue. Moreover, its overall structure is simple, easy to maintain, easy to operate, and has low operating costs.

[0004] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: a shaftless vector electric rotor, comprising:

[0005] Two rotor assemblies are arranged vertically, and connectors are installed between the two rotor assemblies.

[0006] Attitude adjustment component, installed on connector to achieve attitude adjustment of rotor assembly;

[0007] The rotor assembly includes a stator and a rotor. Several magnetic tiles are evenly distributed around the rotor, and several winding cores are evenly distributed around the stator. The magnetic poles of two adjacent magnetic tiles facing the winding cores are opposite. The attitude adjustment assembly includes a vector crossbar and a vector vertical bar. The vector crossbar is rotatably mounted on a connector, and the vector vertical bar is rotatably mounted on the vector crossbar. A crossbar servo is installed between the connector and the vector crossbar, and a vertical bar servo is installed between the vector crossbar and the vector vertical bar.

[0008] The winding core is arranged in a circumferential ring. When energized, it generates an axial magnetic path. The magnetic field of the magnetic tiles interacts with the magnetic field generated by the winding core to produce torque, thereby driving the rotor to rotate and obtaining an upward thrust from the air. Depending on the application scenario, the rotation directions of the upper and lower rotor assemblies can be the same or opposite, and both rotor assemblies obtain upward lift. The rotors of the two rotor assemblies rotate in opposite directions to overcome the air's counter-torque. The horizontal servo drives the vector horizontal servo to rotate around the X-axis, and the vertical servo drives the vector vertical servo to rotate around the Y-axis. Since the lower end of the vector vertical servo is fixed to the nacelle, the entire shaftless vector electric rotor will tilt in the opposite direction, forming a certain tilt angle with the vector vertical servo. Assuming that the total lift F0 obtained by the entire electric rotor will produce a vector projection F1 in the vertical direction and a vector projection F2 in the horizontal direction. F1 gives the aircraft an upward lift, and F2 propels the aircraft forward, backward, left, and right. Because this invention is a omnidirectional vector structure, the aircraft can flexibly adjust its various motion attitudes in the air.

[0009] The shaftless vector electric rotor can easily perform a series of actions such as takeoff, landing, pitch, roll, and hovering of a helicopter. Compared with traditional helicopters, it has low noise, no vibration from mechanical mechanisms, greatly improves the pilot's experience, and reduces fatigue. Moreover, its overall structure is simple, easy to maintain, easy to operate, and has low operating costs.

[0010] Preferably, the upper end of the vector vertical rod is bent to form a connector, and a connecting post is provided on the connector. The connecting post is connected to the output shaft of the vertical rod servo, and the vertical rod servo is fixedly installed on the vector horizontal rod.

[0011] The connector design facilitates the connection between the vector vertical rod and the vertical rod servo.

[0012] Preferably, the axes of the vector horizontal rod axis, the vector vertical rod axis, and the vertical rod servo output shaft intersect perpendicularly at a single point.

[0013] This structural design makes helicopter attitude control more precise and reliable.

[0014] Preferably, the horizontal servo is fixedly mounted on the connector, and the output shaft of the horizontal servo is connected to the vector horizontal servo.

[0015] The horizontal servo motor operates to make the entire rotor assembly and connecting parts rotate together around the vector horizontal servo, thus achieving attitude adjustment.

[0016] Preferably, two opposing connectors are provided between the two rotor assemblies. The connectors are U-shaped with their openings facing away from each other.

[0017] The U-shaped connector facilitates connection to the rotor assembly.

[0018] Preferably, a positioning bearing is installed between the stator and the rotor.

[0019] During rotor rotation, the positioning bearing plays a good role in positioning the rotor, ensuring the smooth operation of the rotor and preventing radial displacement.

[0020] Preferably, the rotor inner wall is provided with a positioning protrusion ring, the upper part of the stator outer wall is provided with a stepped surface, the upper end of the stator is connected to a positioning cover, the upper end of the rotor is connected to a pressure plate, the inner ring of the positioning bearing is positioned between the stepped surface and the positioning cover, and the outer ring of the positioning bearing is positioned between the positioning protrusion ring and the pressure plate.

[0021] The inner ring of the locating bearing is axially positioned and installed on the stator, while the outer ring is axially positioned and installed on the rotor. This prevents axial movement between the rotor and the stator, ensuring smooth operation of the rotor.

[0022] In another configuration, an axial protection bearing and a fixed magnetic ring are mounted on the stator, while a rotating magnetic ring is mounted on the rotor. The rotating magnetic ring and the fixed magnetic ring are positioned opposite each other, with opposite magnetic poles on their opposite faces. The rotor is suspended between the fixed magnetic ring and the axial protection bearing.

[0023] When the winding core is energized, it drives the rotor to rotate at high speed. The rotor receives upward lift from the air, causing it to shift upwards and detach from the axial protection bearing, thus achieving axial suspension. As the lift force on the rotor increases, it moves closer to the fixed magnetic ring. Because the rotating magnetic ring on the rotor has opposite magnetic poles to the fixed magnetic ring on the stator, they repel each other, ensuring that they never come into contact within the design range, maintaining a constant axial suspension. The lift force on the rotor is transmitted to the stator through this set of rotating and fixed magnetic rings, and then to the aircraft cabin, enabling the aircraft to fly.

[0024] In this invention, the rotor of the helicopter rotor assembly is the only high-speed moving component, and it is completely suspended under normal operating conditions. There is no physical contact between the rotor and the aircraft fuselage via bearings, resulting in no friction, no mechanical noise, no need for lubrication, and no maintenance. This saves energy and extends the aircraft's flight time. The attitude adjustment assembly can easily and flexibly adjust the aircraft's flight attitude; it has a simple structure and is lightweight.

[0025] Preferably, a radial protection bearing is installed on the stator, and a gap is provided between the rotor and the radial protection bearing in the radial direction.

[0026] As long as the machining accuracy meets the design requirements and the dynamic balance is properly adjusted, due to the axial annular magnetic force, the rotor and the winding core's axis always remain overlapping or slightly offset, and the rotor's inner ring always maintains a gap with the radial protection bearing, exhibiting a radially suspended state. When the rotor simultaneously achieves axial and radial suspension, it can be completely suspended, with no physical contact with the stator. Both the axial and radial protection bearings are in a non-operating state, only serving a protective function in the event of accidental impact.

[0027] A helicopter includes an shaftless vector electric rotor, a cabin, and a vectoring vertical rod connected to the cabin.

[0028] Because the aircraft's main center of gravity is located in the cabin, below the aircraft, it is more stable during flight. In the event of a malfunction and descent, the propeller blades on the rotor above the aircraft will rotate against the wind, slowing the descent. The aircraft will maintain a cabin-down attitude during landing, minimizing damage.

[0029] The helicopter consists of two rotor assemblies, an attitude control assembly, and a cabin. Several blades are evenly distributed around the rotor; the two sets of blades rotate in opposite directions to overcome the air's anti-torque. The attitude control assembly is fixedly mounted on the cabin roof at its lower end. Under the command of the flight control and electronic control systems, it easily and flexibly tilts the rotor assembly to the horizontal plane, achieving various flight attitudes such as vertical takeoff and landing, hovering, forward and backward movement, and left and right movement.

[0030] Compared with existing technologies, the advantages of this invention are: the shaftless vector electric rotor can easily realize a series of actions such as takeoff, landing, pitch, roll, and hovering of a helicopter. Compared with traditional helicopters, it has low noise, no vibration generated by mechanical mechanisms, greatly improves the pilot's experience, and reduces fatigue. Moreover, its overall structure is simple, easy to maintain, easy to operate, and has low operating costs. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the shaftless vector electric rotor of Embodiment 1 of the present invention;

[0032] Figure 2 This is a schematic diagram of a helicopter according to Embodiment 1 of the present invention;

[0033] Figure 3 This is a schematic diagram of the connection structure of the vector crossbar of the present invention;

[0034] Figure 4 This is a schematic diagram of the vector vertical rod of the present invention;

[0035] Figure 5 This is a schematic diagram of the shaftless vector electric rotor of Embodiment 2 of the present invention;

[0036] Figure 6 This is a schematic diagram of a helicopter according to Embodiment 2 of the present invention;

[0037] Figure 7 This is a schematic diagram of the helicopter attitude adjustment state in Embodiment 2 of the present invention;

[0038] In the diagram: 1. Rotor assembly, 2. Connector, 3. Attitude adjustment assembly, 4. Stator, 5. Rotor, 6. Magnet, 7. Winding core, 8. Vector crossbar, 9. Vector vertical bar, 10. Crossbar servo, 11. Vertical bar servo, 12. Connector, 13. Connecting column, 14. Support, 15. Blade, 16. Magnetic guide ring, 17. Annular base plate, 18. Positioning bearing, 19. Positioning convex ring, 20. Stepped surface, 21. Positioning cover, 22. Pressure plate, 23. Nacelle, 24. Landing gear, 25. Axial protection bearing, 26. Fixed magnetic ring, 27. Rotating magnetic ring, 28. Radial protection bearing, 29. Support convex ring. Detailed Implementation

[0039] The technical solution of the present invention will be further described in detail below through specific embodiments and in conjunction with the accompanying drawings:

[0040] Example 1: A shaftless vector electric rotor (see appendix) Figure 1 To be continued Figure 4 ),include:

[0041] Two rotor assembly 1, the two rotor assemblies are arranged vertically, and a connector 2 is installed between the two rotor assemblies;

[0042] Attitude adjustment component 3 is installed on the connector to achieve attitude adjustment of the rotor assembly;

[0043] The rotor assembly includes a stator 4 and a rotor 5. The stator is fixedly connected to the connector. Several magnetic tiles 6 are evenly distributed around the rotor. Several winding iron cores 7 are evenly distributed around the stator. The magnetic poles of two adjacent magnetic tiles facing the winding iron core are opposite. The attitude adjustment assembly includes a vector horizontal bar 8 and a vector vertical bar 9. The vector horizontal bar is rotatably mounted on the connector. The vector vertical bar is rotatably mounted on the vector horizontal bar. A horizontal bar servo 10 is installed between the connector and the vector horizontal bar. A vertical bar servo 11 is installed between the vector horizontal bar and the vector vertical bar.

[0044] The upper end of the vector vertical rod is bent to form an L-shaped connector 12. A connecting post 13 is provided on the connector, which connects to the output shaft of the vertical rod servo. The vertical rod servo is fixedly mounted on the vector horizontal rod. The connecting post and the output shaft of the vertical rod servo are connected via a coupling. The connecting post is rotatably mounted on the vector horizontal rod. A support 14 is located at the middle of the vector horizontal rod. Both the horizontal rod servo and the connecting post are mounted on the support, and bearings are installed on the support. The connecting post is fitted with the bearings. The axes of the vector horizontal rod, the vector vertical rod, and the vertical rod servo output shaft intersect perpendicularly at a single point. The horizontal rod servo is fixedly mounted on the connector, and its output shaft is connected to the vector horizontal rod. The output shaft of the horizontal rod servo is connected to the end of the vector horizontal rod via a coupling.

[0045] Two opposing connectors are installed between the two rotor assemblies. The connectors are U-shaped with their openings facing away from each other. The two ends of the vector crossbar are rotatably mounted on the two connectors. Bearings are installed on the connectors and corresponding to the vector crossbar. The two ends of the vector crossbar are respectively adapted to connect with the bearings on the two connectors.

[0046] The stator has 10 winding cores, the rotor has 12 magnetic tiles, and several blades 15 are evenly distributed on the rotor. The winding cores are located below the rotor, and a magnetic ring 16 is installed on the lower surface of the rotor. The magnetic ring has mounting grooves corresponding to the magnetic tiles, and the magnetic tiles are fitted into the mounting grooves. The stator has a cylindrical structure, and an outwardly extending annular base plate 17 is provided at the lower end of the stator. The winding cores are mounted on the annular base plate.

[0047] A positioning bearing 18 is installed between the stator and the rotor. A positioning protrusion ring 19 is provided on the inner wall of the rotor. A stepped surface 20 is provided on the outer wall of the upper part of the stator. A positioning cover 21 is connected to the upper end of the stator. A pressure plate 22 is connected to the upper end of the rotor. The inner ring of the positioning bearing is positioned between the stepped surface and the positioning cover. The outer ring of the positioning bearing is positioned between the positioning protrusion ring and the pressure plate.

[0048] A helicopter includes an shaftless vectoring electric rotor, a cabin 23, and a vectoring vertical rod connected to the cabin. Landing gear 24 is mounted externally to the cabin. Power supply, electronic control system, flight control system, etc., are installed inside the cabin.

[0049] The winding core is arranged in a circumferential ring. When energized, it generates an axial magnetic path. The magnetic field of the magnetic tiles interacts with the magnetic field generated by the winding core to produce torque, thereby driving the rotor to rotate and obtaining an upward thrust from the air. Depending on the application scenario, the rotation directions of the upper and lower rotor assemblies can be the same or opposite, and both rotor assemblies obtain upward lift. The rotors of the two rotor assemblies rotate in opposite directions to overcome the air's counter-torque. The horizontal servo drives the vector horizontal servo to rotate around the X-axis, and the vertical servo drives the vector vertical servo to rotate around the Y-axis. Since the lower end of the vector vertical servo is fixed to the nacelle, the entire shaftless vector electric rotor will tilt in the opposite direction, forming a certain tilt angle with the vector vertical servo. Assuming that the total lift F0 obtained by the entire electric rotor will produce a vector projection F1 in the vertical direction and a vector projection F2 in the horizontal direction. F1 gives the aircraft an upward lift, and F2 propels the aircraft forward, backward, left, and right. Because this invention is a omnidirectional vector structure, the aircraft can flexibly adjust its various motion attitudes in the air.

[0050] Example 2: A shaftless vector electric rotor (see appendix) Figure 5 To be continued Figure 7Its structure is similar to that of Embodiment 1, with the main difference being that in this embodiment, an axial protection bearing 25 and a fixed magnetic ring 26 are installed on the stator, and a rotating magnetic ring 27 is provided on the rotor. The rotating magnetic ring and the fixed magnetic ring are arranged opposite to each other, and the magnetic poles of the opposite faces of the fixed magnetic ring and the rotating magnetic ring are opposite. The rotor is suspended between the fixed magnetic ring and the axial protection bearing. A radial protection bearing 28 is installed on the stator, and a gap is provided between the rotor and the radial protection bearing in the radial direction.

[0051] The stator has 10 winding cores, the rotor has 12 magnetic tiles, and several blades are evenly distributed on the rotor. The winding cores are located below the rotor, and a magnetic guide ring is installed on the lower surface of the rotor. The magnetic guide ring has mounting grooves corresponding to the magnetic tiles, and the magnetic tiles are fitted into these grooves. The stator has a cylindrical structure, with an outwardly extending annular base plate at its lower end, on which the winding cores are mounted. A support convex ring 29 is provided on the lower surface of the rotor, corresponding to the axial protection bearing. A gap exists between the support convex ring and the axial protection bearing, which is a planar bearing. The magnetic guide ring on the rotor is installed outside the rotating magnetic ring. Other structures are the same as in Embodiment 1.

[0052] A helicopter includes an shaftless vectoring electric rotor, a cabin, and a vectoring vertical rod connected to the cabin. Landing gear is mounted externally to the cabin. Power supply, electronic control systems, flight control systems, etc., are installed inside the cabin.

[0053] When the winding core is energized, it drives the rotor to rotate at high speed. The rotor receives upward lift from the air, causing it to shift upwards and detach from the axial protection bearing, thus achieving axial suspension. As the lift force on the rotor increases, it moves closer to the fixed magnetic ring. Because the rotating magnetic ring on the rotor has opposite magnetic poles to the fixed magnetic ring on the stator, they repel each other, ensuring that they never come into contact within the design range, maintaining a constant axial suspension. The lift force on the rotor is transmitted to the stator through this set of rotating and fixed magnetic rings, and then to the aircraft cabin, enabling the aircraft to fly.

[0054] In this invention, the rotor of the helicopter rotor assembly is the only high-speed moving component, and it is completely suspended under normal operating conditions. There is no physical contact between the rotor and the aircraft fuselage via bearings, resulting in no friction, no mechanical noise, no need for lubrication, and no maintenance. This saves energy and extends the aircraft's flight time. The attitude adjustment assembly can easily and flexibly adjust the aircraft's flight attitude; it has a simple structure and is lightweight.

[0055] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the present invention in any way. Other variations and modifications may be made without departing from the technical solutions described in the claims.

Claims

1. A shaftless vectoring electric rotor, characterized in that it comprises: Two rotor assemblies are arranged vertically, and connectors are installed between the two rotor assemblies. Attitude adjustment component, installed on connector to achieve attitude adjustment of rotor assembly; The rotor assembly includes a stator and a rotor. Several magnetic tiles are evenly distributed around the rotor, and several winding cores are evenly distributed around the stator. The magnetic poles of two adjacent magnetic tiles facing the winding cores are opposite. The attitude adjustment assembly includes a vector crossbar and a vector vertical bar. The vector crossbar is rotatably mounted on a connector, and the vector vertical bar is rotatably mounted on the vector crossbar. A crossbar servo is installed between the connector and the vector crossbar, and a vertical bar servo is installed between the vector crossbar and the vector vertical bar. An axial protection bearing and a fixed magnetic ring are installed on the stator, and a rotating magnetic ring is provided on the rotor. The rotating magnetic ring and the fixed magnetic ring are arranged opposite to each other, and the magnetic poles of the opposite faces of the fixed magnetic ring and the rotating magnetic ring are opposite. The rotor is suspended between the fixed magnetic ring and the axial protection bearing. A radial protection bearing is installed on the stator, and a gap is provided between the rotor and the radial protection bearing in the radial direction.

2. The shaftless vector electric rotor according to claim 1, characterized in that, The upper end of the vector vertical rod is bent to form a connector. A connecting post is provided on the connector. The connecting post is connected to the output shaft of the vertical rod servo. The vertical rod servo is fixedly installed on the vector horizontal rod.

3. The shaftless vector electric rotor according to claim 1, characterized in that, The axes of the vector horizontal rod, the vector vertical rod, and the vertical rod servo output shaft intersect perpendicularly at a single point.

4. The shaftless vector electric rotor according to claim 1, characterized in that, The horizontal servo is fixedly mounted on the connector, and the output shaft of the horizontal servo is connected to the vector horizontal servo.

5. The shaftless vector electric rotor according to claim 1, characterized in that, Two opposing connectors are provided between the two rotor assemblies. The connectors are U-shaped with their openings facing away from each other.

6. The shaftless vector electric rotor according to claim 1, characterized in that, A magnetic guide ring is installed on the lower surface of the rotor. The magnetic guide ring has a corresponding mounting groove, and the magnetic tile is fitted and installed in the mounting groove.

7. A helicopter, characterized in that, Includes the shaftless vector electric rotor and nacelle as described in any one of claims 1 to 6, with the vector vertical rod connected to the nacelle.

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