Propulsion system blade with internal actuator
Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.
1 . An aircraft rotor system comprising:
a rotor assembly comprising a rotor hub and a rotor blade;
a rotor blade pitch actuator comprising a rotor and a stator configured to cooperate to produce a torque;
a coupling configured to transmit the torque to the rotor hub to effect rotation of the rotor blade relative to the rotor hub, wherein the coupling isolates a gearbox from a moment-induced deflection of the rotor blade; and
wherein the rotor blade pitch actuator is disposed within the rotor blade.
2 . The aircraft rotor system of claim 1 , wherein the rotor is a rigid rotor.
3 . The aircraft rotor system of claim 1 , wherein the rotor blade pitch actuator comprises an electric actuator.
4 . The aircraft rotor system of claim 1 , further comprising a second stator functionally coupled to the rotor blade pitch actuator.
5 . The aircraft rotor system of claim 1 , wherein the gearbox is functionally coupled between the rotor blade pitch actuator and the coupling.
6 . The aircraft rotor system of claim 5 , wherein the coupling is flexible.
7 . An aircraft propulsion system comprising:
a rotor assembly comprising a rotor hub and a rotor blade;
a rotor blade pitch actuator having a rotor and a stator mounted internal to the rotor blade and configured to cooperate to produce a torque;
a coupling configured to transmit the torque from the actuator to the rotor hub to effect rotation of the rotor blade relative to the rotor hub, wherein the coupling isolates a gearbox from a moment-induced deflection of the rotor blade.
8 . The aircraft propulsion system of claim 7 , wherein the rotor blade pitch actuator comprises an electric actuator.
9 . The aircraft propulsion system of claim 7 , wherein the rotor blade pitch actuator comprises first and second motors internal to the rotor blade.
10 . The aircraft propulsion system of claim 9 , wherein the first and second motors drive the gearbox.
11 . The aircraft propulsion system of claim 10 , wherein the gearbox is secured to a blade root of the rotor blade by one or more fastenings.