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US 12,312,066 B2Granted
Propulsor assembly of an electric aircraft
AssigneeBeta Air, LLC
InventorKyle Brookes
Life of this patent
Estimating the term…
Abstract
A propulsor assembly of an electric aircraft is described. The propulsor assembly includes an electric motor, where the electric motor includes a stator and a rotor. The assembly further includes a propulsor mechanically connected to the rotor of the electric motor. The assembly also includes a cyclic control assembly including an electric actuator and a push rod, wherein the push rod is mechanically connected to the actuator and the propulsor, the push rod is configured to increase a blade angle of the propulsor when the push rod is displaced in a first direction, and the push rod is configured to decrease the blade angle of the propulsor when the push rod is displaced in a second direction.
Claims20
An aircraft, comprising:
- a plurality of vertical lift propulsor assemblies, each of the plurality of vertical lift propulsor assemblies comprising:
- a propulsor coupled to the aircraft and driven by an electric motor including a rotor and a stator, the rotor mechanically connected to the propulsor such that the rotor and the propulsor are configured to rotate about a rotational axis, the propulsor including a hub and a plurality of blades each extending outward from the hub, the hub being coupled to a shaft that is driven by the rotor, the hub and blades being formed as a single element such that a blade angle of the plurality of blades of the propulsor is not individually adjustable;
- a cyclic control assembly, comprising:
- an actuator;
- and
- a push rod extending through the shaft, wherein:
- the push rod is coupled to the actuator and the propulsor;
- the push rod is configured to increase the blade angle of the plurality of blades of the propulsor in response to a displacement of the push rod in a first direction;
- and
- the push rod is configured to decrease the blade angle of the plurality of blades of the propulsor in response to a displacement of the push rod in a second direction;
- and
- a flap mechanism mechanically connected to the propulsor, the flap mechanism configured to allow the propulsor to rotate about a pivot point of the flap mechanism, the flap mechanism comprising:
- a base rotatably attached to the aircraft and configured to rotate about the rotational axis;
- and
- a pair of hinges that couple the base and the hub of the propulsor, wherein the pair of hinges is configured to allow the propulsor to rotate about the pivot point of the flap mechanism, the pair of hinges comprising:
- a first hinge coupled on the base and received in a first recess defined in an interior facing surface of the hub, at a first side of the rotational axis;
- a second hinge coupled on the hub and received in a second recess defined in the interior facing surface of the hub, at a second side of the rotational axis opposite the first side;
- and
- a rod having a first end extending through the first hinge and into the hub, and a second end extending through the second hinge and into the hub.
16 more elements
An aircraft, comprising:
- a plurality of vertical lift propulsor assemblies, each of the plurality of vertical lift propulsor assemblies comprising:
- a propulsor coupled to the aircraft and driven by an electric motor including a rotor and a stator, the rotor mechanically connected to the propulsor such that the rotor and the propulsor are configured to rotate about a rotational axis, the propulsor including a hub and a plurality of blades each extending outward from the hub, the hub being coupled to a shaft that is driven by the rotor, the hub and blades being formed as a single element such that a blade angle of the plurality of blades of the propulsor is not individually adjustable;
- a cyclic control assembly, comprising:
- an actuator;
- and
- a push rod extending through the shaft, wherein:
- the push rod is coupled to the actuator and the propulsor;
- the push rod is configured to increase the blade angle of the plurality of blades of the propulsor in response to a displacement of the push rod in a first direction;
- and
- the push rod is configured to decrease the blade angle of the plurality of blades of the propulsor in response to a displacement of the push rod in a second direction;
- and
- a flap mechanism mechanically connected to the propulsor, the flap mechanism configured to allow the propulsor to rotate about a pivot point of the flap mechanism, the flap mechanism comprising:
- a base rotatably attached to the aircraft and configured to rotate about the rotational axis;
- a pair of hinges that couple the base and the hub of the propulsor, wherein the pair of hinges is configured to allow the propulsor to rotate about the pivot point of the flap mechanism, the pair of hinges comprising:
- a first hinge coupled on the base and received in a first recess defined in an interior facing surface of the hub, at a first side of the rotational axis;
- a second hinge coupled on the hub and received in a second recess defined in the interior facing surface of the hub, at a second side of the rotational axis opposite the first side;
- and
- a rod having a first end extending through the first hinge and into the hub, and a second end extending through the second hinge and into the hub;
- a first spring coupled between the base and the hub at a first side of a pivot axis of the flap mechanism defined by the rod;
- and
- a second spring coupled between the base and the hub at a second side of the pivot axis of the flap mechanism defined by the rod, wherein the first spring and the second spring limit an amount of rotation of the propulsor about the pivot axis.
18 more elements
Dependencies are inferred from the claim text.