Propulsion system blade with internal actuator
AssigneeArcher Aviation Inc.
InventorsWilliam Martin Waide, Abraham Karem
Life of this patent
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Abstract
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.
Claims11
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.
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.
Dependencies are inferred from the claim text.