Systems and methods for tilt propellers with tilt actuator gearbox and integrated inverter
AssigneeArcher Aviation Inc.
InventorsScott Graves, Nathan Daniel Storrs, Diego Alberto Silva Rodríguez, Stephen Michael Spiteri
Life of this patent
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Abstract
A tilt actuation apparatus for tilting a propulsion system of an aircraft, the tilt actuation apparatus comprising: a tilt actuator comprising a rotor; a gear set, wherein the rotor is coupled to the gear set, a worm gear concentrically coupled to an output of the gear set, a worm wheel meshed with the worm gear, a gear shaft concentrically coupled to the worm wheel, a pinion concentrically coupled to the gear shaft, and an output shaft coupled to an output of the pinion, the output shaft configured to be fixed to a frame of the aircraft.
Claims26
A tilt actuation apparatus comprising:
- a tilt actuator comprising a rotor;
- a gear set comprising a sun gear, a plurality of planetary gears, a planetary carrier, and a ring gear, wherein the rotor is coupled to the gear set;
- a worm gear concentrically coupled to an output of the gear set;
- a worm wheel meshed with the worm gear;
- a gear shaft concentrically coupled to the worm wheel;
- a pinion concentrically coupled to the gear shaft;
- and
- an output shaft coupled to an output of the pinion, the output shaft configured to be fixed to a frame of the aircraft,
- wherein the tilt actuation apparatus is configured to tilt a propulsion system of an aircraft.
An aircraft, comprising:
- a propulsion system;
- a tilt actuation apparatus for tilting the propulsion system, the tilt actuation apparatus comprising:
- a tilt actuator comprising a rotor;
- a gear set comprising a sun gear, a plurality of planetary gears, a planetary carrier, and a ring gear, wherein the rotor is coupled to the gear set;
- a worm gear concentrically coupled to an output of the gear set;
- a worm wheel meshed with the worm gear;
- a gear shaft concentrically coupled to the worm wheel;
- a pinion concentrically coupled to the gear shaft;
- and
- an output shaft coupled to an output of the pinion, the output shaft configured to be fixed to a frame of the aircraft.
Dependencies are inferred from the claim text.