Rotor assembly including tapered magnets within a retaining sleeve and a method for assembling the same
A rotor assembly has a sleeve, a rotor hub, a lamination core, and a plurality of tapered magnets disposed circumferentially around an inner diameter of the sleeve. The plurality of tapered magnets are configured to abut on one another. The plurality of tapered magnets includes a first set of tapered magnets and a second set of tapered magnets. Insertion of the first set of tapered magnets axially relative to the second set of tapered magnets is configured to increase a diameter of the sleeve. The rotor hub is configured to retain at least one of the lamination core, the plurality of tapered magnets, or the sleeve.
1. A rotor assembly, comprising:
a sleeve;
a rotor hub; and
a plurality of tapered magnets disposed circumferentially around an inner diameter of the sleeve, each tapered magnet of the plurality of tapered magnets being configured to abut another tapered magnet of the plurality of tapered magnets,
wherein the plurality of tapered magnets includes a first set of tapered magnets inserted axially into the sleeve and a second set of tapered magnets inserted axially into the sleeve,
wherein insertion of the first set of tapered magnets axially relative to the second set of tapered magnets is configured to increase a diameter of the sleeve, and
wherein the rotor hub is configured to retain the plurality of tapered magnets.
2. The rotor assembly of claim 1 , wherein the sleeve comprises carbon fiber.
3. The rotor assembly of claim 1 , further comprising a core;
wherein the rotor hub is configured to retain the core.
4. The rotor assembly of claim 3 , wherein the core includes at least one notch.
5. The rotor assembly of claim 3 , wherein the rotor hub is a first rotor hub, and wherein the assembly comprises:
a second rotor hub;
wherein the first rotor hub is abutting a first side of the core in an axial direction, and the second rotor hub is abutting a second side of the core in the axial direction opposite the first side.
6. The rotor assembly of claim 3 , further comprising at least one cavity disposed between the plurality of tapered magnets and the core, wherein the at least one cavity is configured to guide a fluid for cooling.
7. The rotor assembly of claim 6 , wherein the core or the at least one cavity are configured to allow direct cooling of the plurality of tapered magnets.
8. An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system comprising:
at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft, the electrical engine comprising:
a gearbox assembly comprising:
a sun gear; and
an electrical motor having a stator and a rotor assembly;
the rotor assembly comprising:
a sleeve;
a rotor hub; and
a plurality of tapered magnets disposed circumferentially around an inner diameter of the sleeve, each tapered magnet of the plurality of tapered magnets being configured to abut another tapered magnet of the plurality of tapered magnets,
wherein the plurality of tapered magnets includes a first set of tapered magnets inserted axially into the sleeve and a second set of tapered magnets inserted axially into the sleeve,
wherein insertion of the first set of tapered magnets axially relative to the second set of tapered magnets is configured to increase a diameter of the sleeve,
wherein the rotor hub is configured to retain the plurality of tapered magnets, and
wherein the sun gear is attached to the rotor hub.
9. The system of claim 8 , wherein the sleeve comprises carbon fiber.
10. The system of claim 8 , wherein the rotor assembly further comprises a core;
wherein the rotor hub is configured to retain the core.
11. The system of claim 10 , wherein the core includes at least one notch.
12. The system of claim 10 , wherein the rotor hub is a first rotor hub, and wherein the system further comprises:
a second rotor hub;
wherein the first rotor hub is abutting a first side of the core in an axial direction, and the second rotor hub is abutting a second side of the core in the axial direction.
13. The system of claim 10 , further comprising at least one cavity disposed between the plurality of tapered magnets and the core, wherein the at least one cavity is configured to guide a fluid for cooling.
14. The system of claim 13 , wherein the core or the at least one cavity are configured to allow direct cooling of the plurality of tapered magnets.
15. The system of claim 8 , wherein the gearbox includes a bearing, wherein an outer diameter of the bearing contacts an inner diameter of the sun gear.
16. A method of assembling a rotor assembly, comprising:
inserting a first plurality of tapered magnets and a second plurality of tapered magnets into a stretchable sleeve from opposing axial directions such that each of the second plurality of tapered magnets is positioned between adjacent pairs of the first plurality of tapered magnets, the first plurality of tapered magnets and the second plurality of tapered magnets being arranged to abut an inner surface of the stretchable sleeve; and
engaging at least one rotor hub with the first plurality of tapered magnets or the second plurality of tapered magnets.
17. The method of claim 16 , wherein inserting the first plurality of tapered magnets and the second plurality of tapered magnets includes causing a diameter of the stretchable sleeve to increase.
18. The method of claim 16 , further comprising inserting a bearing into a sun gear, and attaching the sun gear to the at least one rotor hub.
19. The method of claim 16 , further comprising balancing the rotor assembly.
20. The method of claim 16 , wherein the at least one rotor hub is further configured to retain the stretchable sleeve.
21. The method of claim 16 , wherein the stretchable sleeve comprises carbon fiber.
22. A rotor assembly, comprising:
a sleeve;
a rotor hub; and
a plurality of tapered magnets disposed circumferentially around an inner diameter of the sleeve, each tapered magnet of the plurality of tapered magnets being configured to abut another tapered magnet of the plurality of tapered magnets, wherein the plurality of tapered magnets includes a first set of tapered magnets and a second set of tapered magnets;
wherein insertion into the sleeve of the first set of tapered magnets axially relative to the second set of tapered magnets is configured to increase a diameter of the sleeve, and
wherein the rotor hub is configured to retain the plurality of tapered magnets.
23. A rotor assembly, comprising:
a sleeve;
a rotor hub; and
a plurality of tapered magnets disposed circumferentially around an entire inner circumference of the sleeve, each tapered magnet of the plurality of tapered magnets being configured to abut another tapered magnet of the plurality of tapered magnets,
wherein the plurality of tapered magnets includes a first set of tapered magnets tapered in a first axial direction and a second set of tapered magnets tapered in a second axial direction opposite the first axial direction, such that each of the second plurality of tapered magnets is positioned between adjacent pairs of the first plurality of tapered magnets; and
wherein the rotor hub is configured to retain the plurality of tapered magnets.
24. The rotor assembly of claim 23 , wherein the plurality of tapered magnets have trapezoidal cross-sections.