Systems and methods for, and components of, gearboxes for eVTOL aircraft
An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.
1. An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system comprising:
an electrical motor having a stator and a rotor;
a main shaft possessing at least one shoulder on an outer surface of the main shaft;
a gearbox assembly comprising:
a sun gear that is concentrically aligned with the main shaft;
at least one planetary gear that interfaces with the sun gear;
a ring gear that interfaces with the at least one planetary gear, wherein a center of the ring gear is concentrically aligned with the main shaft; and
a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft;
a propeller flange assembly that travels through the rotor; and
an axial buttress positioned in the at least one shoulder located on the main shaft.
2. The system of claim 1 , wherein the axial buttress is in contact with the sun gear.
3. The system of claim 1 , wherein the axial buttress is removably coupled to the at least one shoulder of the main shaft.
4. The system of claim 1 , wherein the axial buttress is freely coupled to the at least one shoulder of the main shaft and the propeller flange assembly.
5. The system of claim 1 , wherein the axial buttress is freely coupled to the at least one shoulder of the main shaft and the rotor of the electric motor.
6. The system of claim 1 , wherein the axial buttress is freely coupled to the at least one shoulder of the main shaft, the propeller flange assembly, and the sun gear.
7. The system of claim 1 , wherein the axial buttress includes a material configured to bend to compensate for tolerances of mating parts of the gearbox.
8. The system of claim 1 , wherein the rotor of the electrical engine is configured to rotate the sun gear.
9. The system of claim 1 , wherein the axial buttress is made of stainless steel.
10. The system of claim 1 , wherein the axial buttress is made of a three-dimensional printing material.
11. 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 and electrically connected to an electrical power source, the electrical engine including:
an electrical motor having a stator and a rotor;
a main shaft assembly, wherein the main shaft assembly includes:
a main shaft that possesses at least one shoulder on an outer surface; and
a gearbox assembly comprising:
a sun gear;
at least one planetary gear;
a ring gear;
a planetary carrier; and
an axial buttress positioned in the at least one shoulder located on the main shaft; and
a propeller flange assembly, wherein the propeller flange assembly travels through the rotor.
12. The system of claim 11 , wherein the axial buttress is in contact with the sun gear.
13. The system of claim 11 , wherein the axial buttress is removably coupled to the at least one shoulder of the main shaft.
14. The system of claim 11 , wherein the axial buttress is freely coupled to the at least one shoulder of the main shaft and the propeller flange assembly.
15. The system of claim 11 , wherein the axial buttress is freely coupled to the at least one shoulder of the main shaft and the rotor.
16. The system of claim 11 , wherein the axial buttress is freely coupled to the at least one shoulder of the main shaft, the propeller flange assembly, and the sun gear.
17. The system of claim 11 , wherein the axial buttress includes a material configured to bend to compensate for tolerances of mating parts of the gearbox.
18. The system of claim 11 , wherein the axial buttress is made of stainless steel.
19. The system of claim 11 , wherein the axial buttress is made of a three-dimensional printing material.