A system and method for pilot assistance in an electric vertical takeoff and landing (eVTOL) aircraft. The system generally includes a pilot control and a flight controller. The pilot control is attached to the eVTOL aircraft. The pilot control is configured to transmit an input relating to the flight path of the aircraft. The flight controller is communicatively connected to the pilot control. The flight controller is configured to receive the input relating to the flight path, generate an output of a recommended flight maneuver as a function of the input, and display the recommended flight maneuver.

The present invention relates to an electronic test device for at least one avionic function to be tested, intended to be embedded in an aircraft, the aircraft comprising at least one avionic equipment item, the test device being intended to be connected to the at least one avionic equipment item and comprising: an acquisition module, configured to acquire flight data from the at least one avionic equipment item, and a computing module, configured to compute simulated output data, from acquired flight data and via an implementation of the avionic function to be tested, the avionic function to be tested being able, from the flight data, to deliver the output data.

A hydraulic propulsion system is disclosed which includes an input interface configured to receive mechanical power from a power source, a pressure source comprising one or more fixed or variable displacement pumps coupled to the input interface and adaptable to convert mechanical power to hydraulic power and controlling outlet pressure of the pressure source (system pressure), one or more variable displacement motors coupled to the pressure source via a corresponding high-pressure line configured to be mechanically coupled to one or more aerodynamic rotors of an aircraft and comprising a closed loop speed control arrangement in response to a commanded rotor speed, and a controller configured to control the speed of one or more variable displacement motors by providing a control signal for controlling the system pressure.

A hydraulic propulsion system is disclosed which includes an input interface configured to receive mechanical power from a power source, a pressure source comprising one or more fixed or variable displacement pumps coupled to the input interface and adaptable to convert mechanical power to hydraulic power and controlling outlet pressure of the pressure source (system pressure), one or more variable displacement motors coupled to the pressure source via a corresponding high-pressure line configured to be mechanically coupled to one or more aerodynamic rotors of an aircraft and comprising a closed loop speed control arrangement in response to a commanded rotor speed, and a controller configured to control the speed of one or more variable displacement motors by providing a control signal for controlling the system pressure.

Drones with propulsions systems supported in a housing are provided where the orientation of the housing is independent from the orientation of the propulsion system. Drones are provided where a propulsion system is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the propulsion system to assume substantially any position with a sphere. Drones are provided where a bladeless inner tube is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the inner tube to assume substantially any position within a sphere. Drone systems are provided with connectable unit drones. An unmanned land vehicle is provided having a wheel assembly that is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the wheel assembly to assume substantially any position with a sphere.

Drones with propulsions systems supported in a housing are provided where the orientation of the housing is independent from the orientation of the propulsion system. Drones are provided where a propulsion system is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the propulsion system to assume substantially any position with a sphere. Drones are provided where a bladeless inner tube is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the inner tube to assume substantially any position within a sphere. Drone systems are provided with connectable unit drones. An unmanned land vehicle is provided having a wheel assembly that is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the wheel assembly to assume substantially any position with a sphere.

Aircraft electric power distribution systems and methods of operating aircraft electrical power distribution systems are provided. One such method comprises determining a measure of an electrical power demand of a power and propulsion system of the aircraft; setting a target operating voltage of the aircraft electrical power distribution system based at least in part on the measure of the electrical power demand; and controlling the operating voltage in accordance with the set target operating voltage. In some embodiments the measure of the electrical power is a measure of an operating parameter of a gas turbine engine or propulsor of the aircraft.

Aircraft electric power distribution systems and methods of operating aircraft electrical power distribution systems are provided. One such method comprises determining a measure of an electrical power demand of a power and propulsion system of the aircraft; setting a target operating voltage of the aircraft electrical power distribution system based at least in part on the measure of the electrical power demand; and controlling the operating voltage in accordance with the set target operating voltage. In some embodiments the measure of the electrical power is a measure of an operating parameter of a gas turbine engine or propulsor of the aircraft.

An engine system for an aircraft comprising a propulsor configured to drive the aircraft, a thermal combustion engine configured to drive the propulsor, an electric motor connected to the thermal combustion engine and configured to drive the propulsor, a power converter configured to apply a torque to the electric motor and generate electric energy from the torque applied to the electric motor, and an engine controller, the engine controller being configured to determine a current power output of the thermal combustion engine, determine an optimum power output of the thermal combustion engine based on current operating conditions, and vary the torque applied to the electric motor so as to vary a load on the thermal combustion engine, wherein the torque may be varied by an amount required to vary the power output of the thermal combustion engine to the determined optimum power output.

An engine system for an aircraft comprising a propulsor configured to drive the aircraft, a thermal combustion engine configured to drive the propulsor, an electric motor connected to the thermal combustion engine and configured to drive the propulsor, a power converter configured to apply a torque to the electric motor and generate electric energy from the torque applied to the electric motor, and an engine controller, the engine controller being configured to determine a current power output of the thermal combustion engine, determine an optimum power output of the thermal combustion engine based on current operating conditions, and vary the torque applied to the electric motor so as to vary a load on the thermal combustion engine, wherein the torque may be varied by an amount required to vary the power output of the thermal combustion engine to the determined optimum power output.