The present application relates to a propulsion device having a motor, a mast connected to the motor, an angle sensing device detecting the angle of the mast, a controller receiving the angle of the mast as an input and outputting a motor torque signal to the motor in response thereto, a hub attached to the mast via a single skewed hinge, and a propeller assembly with one or more blades connected to a hub.

The present application relates to a propulsion device having a motor, a mast connected to the motor, an angle sensing device detecting the angle of the mast, a controller receiving the angle of the mast as an input and outputting a motor torque signal to the motor in response thereto, a hub attached to the mast via a single skewed hinge, and a propeller assembly with one or more blades connected to a hub.

There is disclosed a rotor for an aircraft capable of hovering, comprising: a stator; a rotatable element, which is rotatable about an axis with respect to stator; a blade, which is connected with element; a support element, which supports a source of a magnetic field and is either stationary or driven in rotation at a first rotational speed; and a first electric circuit, which is angularly integral with element and can be driven in rotation at a second rotational speed different from first rotational speed; first electric circuit being electromagnetically coupled with source so that an electromotive force is magnetically induced in first electric circuit and an first electric current flows in first electric circuit; rotor further comprises a second electric circuit which is either stationary or driven in rotation at a first rotational speed, and a sensor generating a signal associated to a back electromotive force induced on second electric circuit.

In one aspect, the present disclosure provides a system for reducing vibrations or stresses in a rotor blade system. The system may include at least three rotor blades configured to be rotated about a main rotor axis, where each of the three rotor blades may be adjusted by at least one electrically-adjustable control rod of a plurality of control rods. The plurality of control rods may include a first number of control rods forming a first group, and the plurality of control rods may include a second number of control rods forming a second group. A first circuit for may activate or deactivate the first group of control rods, and a second circuit may activate or deactivate the second group of control rods.

In one aspect, the present disclosure provides a system for reducing vibrations or stresses in a rotor blade system. The system may include at least three rotor blades configured to be rotated about a main rotor axis, where each of the three rotor blades may be adjusted by at least one electrically-adjustable control rod of a plurality of control rods. The plurality of control rods may include a first number of control rods forming a first group, and the plurality of control rods may include a second number of control rods forming a second group. A first circuit for may activate or deactivate the first group of control rods, and a second circuit may activate or deactivate the second group of control rods.

An exemplary rotorcraft lockout system includes a main rotor lockout comprising a base operable to be attached to a bottom surface of a fuselage and a first and a second tension arm operable to be connected to the base and a main rotor hub, and a tail rotor lockout including a clamp operable to connect to a horizontal stabilizer, a rotor arm connector operable to connect to a tail rotor hub, and a tail rotor tension arm operable to interconnect the clamp and the rotor arm connector in tension.

An exemplary rotorcraft lockout system includes a main rotor lockout comprising a base operable to be attached to a bottom surface of a fuselage and a first and a second tension arm operable to be connected to the base and a main rotor hub, and a tail rotor lockout including a clamp operable to connect to a horizontal stabilizer, a rotor arm connector operable to connect to a tail rotor hub, and a tail rotor tension arm operable to interconnect the clamp and the rotor arm connector in tension.

A rotatable swashplate is rotatable relative to a stationary swashplate around a shaft and connects to a pitch control rod assembly. The rotatable swashplate includes an upper portion and a lower portion. The upper portion is extendable outside of a stationary swashplate and includes a plurality of lugs each configured to attach to a pitch control rod assembly, an innermost wall configured to receive a shaft, and a membrane. The lower portion is positionable within the stationary swashplate and has an outermost wall and at least one extension extending radially between the outermost wall and the innermost wall. The membrane extends radially over the at least one extension.

A rotatable swashplate is rotatable relative to a stationary swashplate around a shaft and connects to a pitch control rod assembly. The rotatable swashplate includes an upper portion and a lower portion. The upper portion is extendable outside of a stationary swashplate and includes a plurality of lugs each configured to attach to a pitch control rod assembly, an innermost wall configured to receive a shaft, and a membrane. The lower portion is positionable within the stationary swashplate and has an outermost wall and at least one extension extending radially between the outermost wall and the innermost wall. The membrane extends radially over the at least one extension.

A coaxial rotor system includes a center mast non-rotatably disposed at and extending from a helicopter. A rotation axis extends along the center mast. An inner mast is disposed along the center mast and is rotatable about the rotation axis in a first direction. A portion of the inner mast extends above an end of the center mast. An outer mast circumscribes the center mast and is rotatable about the rotation axis in an opposite second direction. The center mast extends above an end of the outer mast. An upper rotor blade assembly is rotatable with the inner mast. A lower rotor blade assembly is rotatable with the outer mast. A control system disposed at the center mast between the upper and lower rotor blade assemblies is operable to adjust pitch of a plurality of upper rotor blades and to adjust pitch of a plurality of lower rotor blades.