An aircraft propulsion system comprises first and second co-axial propulsors, one of the first and second propulsor being positioned forward of the other propulsor. A first electric motor is configured to drive the first propulsor, and a second electric motor is configured to drive the second propulsor. The first electric motor comprising a rotor radially inwardly of the stator, and the second electric motor comprises a rotor radially outwardly of the stator. The stator of the first electric motor is mounted to the stator of the second electric motor.

An aircraft propulsion system comprises first and second co-axial propulsors, one of the first and second propulsor being positioned forward of the other propulsor. A first electric motor is configured to drive the first propulsor, and a second electric motor is configured to drive the second propulsor. The first electric motor comprising a rotor radially inwardly of the stator, and the second electric motor comprises a rotor radially outwardly of the stator. The stator of the first electric motor is mounted to the stator of the second electric motor.

The invention relates to an aircraft thruster (30) comprising at least a first propeller (32) provided with a plurality of radial blades (34) extending about an axis (A) of rotation of the said first propeller (32), which is driven in rotation by a first electric motor (36), the electrical supply means of which comprise power circuits (42) carried by a fairing of the thruster characterised in that the power circuits (42) are arranged in an annular manner in an annular part (40) integral with the fairing of the thruster (30), this annular part (40) being arranged around the said first propeller (32).

The invention relates to an aircraft thruster (30) comprising at least a first propeller (32) provided with a plurality of radial blades (34) extending about an axis (A) of rotation of the said first propeller (32), which is driven in rotation by a first electric motor (36), the electrical supply means of which comprise power circuits (42) carried by a fairing of the thruster characterised in that the power circuits (42) are arranged in an annular manner in an annular part (40) integral with the fairing of the thruster (30), this annular part (40) being arranged around the said first propeller (32).

The invention relates to an electric propulsion unit for an aircraft comprising at least one first propulsion member, a second propulsion member and a single electric motor configured to drive the first propulsion member and the second propulsion member in a counter-rotating manner, the electric motor comprising a peripheral stator element comprising a first peripheral stage and a second peripheral stage which are offset along an axis, the first peripheral stage comprising at least a first phase, a second phase and a third phase which are alternated according to a first sequence in such a way as to allow a rotation of the first rotor element in the first direction of rotation, the second peripheral stage comprising phases which are alternated according to a second sequence in such a way as to allow a counter-rotating rotation of the second rotor element.

The invention relates to an electric propulsion unit for an aircraft comprising at least one first propulsion member, a second propulsion member and a single electric motor configured to drive the first propulsion member and the second propulsion member in a counter-rotating manner, the electric motor comprising a peripheral stator element comprising a first peripheral stage and a second peripheral stage which are offset along an axis, the first peripheral stage comprising at least a first phase, a second phase and a third phase which are alternated according to a first sequence in such a way as to allow a rotation of the first rotor element in the first direction of rotation, the second peripheral stage comprising phases which are alternated according to a second sequence in such a way as to allow a counter-rotating rotation of the second rotor element.

In one aspect, described herein is an aircraft capable of carrying at least 400 pounds of payload. An embodiment has four rotors systems, each of the rotor systems being independently driven by an electric motor or other torque-producing source. Each of the rotor systems provide sufficient thrust such that the aircraft is capable of controlled vertical takeoff and landing, even if one of the variable pitch rotor systems is inoperable. An electronic control system is configured to control the rotational speed and pitch of at least one of the rotor systems.

Devices and methods for activating a flight-enable beacon configured to provide a light beacon or data signal comprising capability to establish and maintain a fixed set of coordinates. The flight-enabled beacon is configured with a processor, memory, motor, gimbal or swashplate and light emitting source and can be configured to attain and maintain a target altitude and emit a light over a fixed period of time. The flight-enabled beacon is configured to be light and with small form factor for easy portable transport in cases of emergency or to provide a signal easily locatable by parties located a distance from the activated light-enabled beacon.

A ducted fan assembly for generating thrust during edgewise forward flight. The ducted fan assembly includes a duct having an inlet with a leading portion and a diffuser with a trailing portion during the edgewise forward flight. A fan disposed within the duct is configured to rotate relative to the duct about a fan axis to generate an airflow through the duct from the inlet to the diffuser. An active flow control system includes a plurality of injectors including a first injector configured to inject pressurized air substantially tangential with the leading portion of the inlet and a second injector configured to inject pressurized air substantially tangential with the trailing portion of the diffuser such that when the injectors are injecting pressurized air, flow separation of the airflow at the leading portion of the inlet and the trailing portion of the diffuser is reduced.

A ducted fan assembly for generating thrust during edgewise forward flight. The ducted fan assembly includes a duct having an inlet with a leading portion and a diffuser with a trailing portion during the edgewise forward flight. A fan disposed within the duct is configured to rotate relative to the duct about a fan axis to generate an airflow through the duct from the inlet to the diffuser. An active flow control system includes a plurality of injectors including a first injector configured to inject pressurized air substantially tangential with the leading portion of the inlet and a second injector configured to inject pressurized air substantially tangential with the trailing portion of the diffuser such that when the injectors are injecting pressurized air, flow separation of the airflow at the leading portion of the inlet and the trailing portion of the diffuser is reduced.