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 aircraft electrical propulsion system, the electrical propulsion system comprising:
at least one electrical engine having:
an electrical motor having a stator and a rotor;
a gearbox assembly comprising:
a sun gear;
at least one planetary gear;
a ring gear; and
a planetary carrier; and
a baffle assembly connected to a housing of the electrical engine, the baffle assembly comprising a first modular layer and a second modular layer stacked on the first modular layer, wherein the baffle assembly is configured to allow air to escape the housing of the electrical engine.
2 . The system of claim 1 , wherein the baffle assembly comprises a circuitous path with a first opening inside the electrical engine and a second opening to an environment external to the electrical engine housing, wherein the circuitous path includes at least one bend, turn, or twist.
3 . The system of claim 1 , wherein the baffle assembly comprises at least two circuitous paths.
4 . The system of claim 1 , wherein the baffle assembly is removably coupled to the electrical engine housing.
5 . The system of claim 1 , wherein the baffle assembly comprises a circuitous path to deter debris from entering the electrical engine.
6 . The system of claim 1 , wherein the baffle assembly is removably coupled to the electrical engine housing by a snap ring.
7 . The system of claim 1 , further comprising a cooling system configured to cool the electrical engine using oil, wherein the baffle assembly comprises a circuitous path that prevents oil from exiting the baffle assembly.
8 . The system of claim 1 , further comprising a cooling system configured to cool the electrical engine using oil, wherein the baffle assembly comprises a removable fill port for the cooling system.
9 . The system of claim 1 , wherein the baffle assembly comprises a thermally conductive material.
10 . The system of claim 1 , wherein the baffle assembly comprises at least two layers of circuitous paths stacked on each other.
11 . The system of claim 1 , further comprising
a propeller assembly; and
an external port of the baffle assembly,
wherein the external port of the baffle assembly is located outside of the electrical engine housing and below the propeller assembly.
12 . An aircraft electrical propulsion system, the electrical propulsion system comprising:
at least one electrical engine electrical engine having:
an electrical motor having a stator and a rotor;
an inverter assembly that provides power to the electrical motor;
a main shaft, wherein a first end of the main shaft is mechanically coupled to the rotor; and
a baffle assembly connected to a housing of the electrical engine, the baffle assembly comprising a first modular layer and a second modular layer stacked on the first modular layer, wherein the baffle assembly is configured to allow air to escape the housing of the electrical engine.
13 . The system of claim 12 , wherein the baffle assembly comprises a circuitous path with a first opening inside the electrical engine and a second opening to an environment external to the electrical engine housing, wherein the circuitous path includes at least one bend, turn, or twist.
14 . The system of claim 12 , wherein the baffle assembly comprises at least two circuitous paths.
15 . The system of claim 12 , wherein the baffle assembly is removably coupled to the electrical engine housing.
16 . The system of claim 12 , wherein the baffle assembly comprises a circuitous path deterring debris from entering the electrical engine.
17 . The system of claim 12 , wherein the baffle assembly is removably coupled to the electrical engine housing by a snap ring.
18 . The system of claim 12 , further comprising a cooling system configured to cool the electrical engine using oil, wherein the baffle assembly comprises a circuitous path that prevents oil from exiting the baffle assembly.
19 . The system of claim 12 , further comprising a cooling system configured to cool the electrical engine using oil, wherein the baffle assembly comprises a removable fill port for the cooling system.
20 . The system of claim 12 , wherein the baffle assembly comprises at least two layers of circuitous paths stacked on each other.
21 . The system of claim 12 , further comprising
a propeller assembly; and
an external port of the baffle assembly,
wherein the external port of the baffle assembly is located outside of the electrical engine housing and below the propeller assembly.