IP Library › Patent Application 19396240
Patent Application
App. No. 19/396,240

Propulsion System for Electric Aircraft

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Quick Facts
Patent No.
US None
App. No.
19/396,240
Abstract

In a first aspect, described herein is a direct drive electric aircraft propulsion wherein the propulsion rotor torque is decoupled from the primary proprotor mast moment forces. A hub shaft locates the propulsion proprotor assembly in space relative to the aircraft nacelle, while a motor torque coupler transfers torque from the electric motor to the propulsion rotor while resolving a negligible amount of mast moment through the electric motor.

Claims (32)

1 - 18 . (canceled)

19 . An aircraft propulsion system, comprising:

a rotor hub;

an electric motor;

a first load path configured to connect a proprotor to the rotor hub; and

a second load path configured to transfer torque of the electric motor to the proprotor,

wherein the first load path is configured to resolve most of a mast moment from the proprotor.

20 . The aircraft propulsion system of claim 19 additionally comprising a nacelle, wherein the first load path is configured to resolve most of the mast moment from the proprotor through the nacelle.

21 . The aircraft propulsion system of claim 20 , wherein the nacelle comprises a first nacelle structural layer, and a second nacelle structural layer, and a composite web between the first nacelle structural layer and the second nacelle structural layer.

22 . The aircraft propulsion system of claim 19 additionally comprising a first and a second hub bearing wherein the first and second hub bearings are separated along an axis of rotation of the rotor hub.

23 . The aircraft propulsion system of claim 22 wherein the first and second hub bearings are configured in the first load path to resolve the mast moment from the proprotor.

24 . The aircraft propulsion system of claim 19 wherein the second load path comprises a motor torque coupler that connects the electric motor's housing to the rotor hub.

25 . The aircraft propulsion system of claim 24 wherein the motor torque coupler is configured to transfer torque of the electric motor to the proprotor.

26 . The aircraft propulsion system of claim 19 additionally comprising a second electric motor.

27 . The aircraft propulsion system of claim 19 wherein the aircraft propulsion system is configured for a tiltrotor aircraft.

28 . The aircraft propulsion system of claim 19 wherein an rpm of the electric motor is equal to an rpm of a propulsion rotor.

29 . An aircraft, comprising:

a rotor hub;

an electric motor;

a proprotor;

a nacelle;

a first load path configured to connect the proprotor to the rotor hub; and

a second load path configured to transfer torque of the electric motor to the proprotor, wherein the first load path is configured to resolve most of a mast moment from the proprotor.

30 . The aircraft of claim 29 wherein the first load path is configured to resolve most of the mast moment from the proprotor through the nacelle.

31 . The aircraft propulsion system of claim 30 , wherein the nacelle comprises a first nacelle structural layer, and a second nacelle structural layer, and a composite web between the first nacelle structural layer and the second nacelle structural layer.

32 . The aircraft propulsion system of claim 29 additionally comprising a first and a second hub bearing wherein the first and second hub bearings are separated along an axis of rotation of the rotor hub.

33 . The aircraft of claim 32 wherein the first and second hub bearings are configured in the first load path to resolve the mast moment from the proprotor.

34 . The aircraft of claim 29 wherein the second load path comprises a motor torque coupler that connects the electric motor's housing to the rotor hub.

35 . The aircraft of claim 34 wherein the motor torque coupler is configured to transfer torque of the electric motor to the proprotor.

36 . The aircraft of claim 29 additionally comprising a second electric motor.

37 . The aircraft of claim 29 wherein the aircraft a tiltrotor aircraft.

38 . The aircraft of claim 29 wherein an rpm of the electric motor is equal to an rpm of a propulsion rotor.