Tilt actuator for aircraft
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 tilting rotor system, comprising a drive system enclosed within a nacelle, and including:
a truss mechanically coupled to the rotor hub;
a first actuator mechanically disposed between the rotor hub and the truss; and
separated second and third actuators disposed to exert second and third forces, respectively, through the truss and the first actuator, to the rotor hub, such that actuation of any of the first, second, and third actuators is configured to tilt the rotor hub.
2. The aircraft tilting rotor system of claim 1 , wherein the drive system includes an electric motor configured to drive a rotor.
3. The aircraft tilting rotor system of claim 2 , wherein the drive system includes a reduction gear mechanically coupled between the electric motor and the rotor.
4. The aircraft tilting rotor system of claim 1 , wherein each of the first, second, and third actuators are linear actuators.