A system comprises a resonant coupling having a first coil and a second coil, wherein the first coil is mounted to a first body that is stationary relative to a second body that is configured to rotate relative to the first body, and wherein the second coil is mounted to the second body to rotate relative to the first coil. The first and second coils are configured so that alternating current in the first coil induces an alternating current in the second coil to transfer electrical power from the first coil to the second coil wirelessly. The first and second coils do not contact one another regardless of whether the first and second bodies rotate relative to one another.

An electronic control system (30) for a turbopropeller engine (12) having a gas turbine (20) and a propeller assembly (13) coupled to the gas turbine (20), controls propeller operation based on a pilot input request, via generation of a driving quantity (Ip) for an actuation assembly (29) designed to adjust a pitch angle (β) of propeller blades (2) of the propeller assembly (13). The control system (30) envisages: a propeller speed regulator (39), receiving at its input a propeller speed error (ep), indicative of a difference between a propeller speed measure (Nr) and a propeller speed demand (Nrref), and generating at its output, based on the propeller speed error (ep), a first control quantity (Outi); a propeller pitch regulator (42), receiving at its input a propeller pitch error (ep), indicative of a difference between a propeller pitch demand ( ) and a pitch position measure (β), and generating at its output, based on the propeller pitch error (ep), a first control quantity (Out2); and a priority selection stage (45), configured to implement a priority selection between the first and the second control quantities, for providing at the output the driving quantity (IP), based on the priority selection between the first and the second control quantities.

An electronic control system (30) for a turbopropeller engine (12) having a gas turbine (20) and a propeller assembly (13) coupled to the gas turbine (20), controls propeller operation based on a pilot input request, via generation of a driving quantity (Ip) for an actuation assembly (29) designed to adjust a pitch angle (β) of propeller blades (2) of the propeller assembly (13). The control system (30) envisages: a propeller speed regulator (39), receiving at its input a propeller speed error (ep), indicative of a difference between a propeller speed measure (Nr) and a propeller speed demand (Nrref), and generating at its output, based on the propeller speed error (ep), a first control quantity (Outi); a propeller pitch regulator (42), receiving at its input a propeller pitch error (ep), indicative of a difference between a propeller pitch demand ( ) and a pitch position measure (β), and generating at its output, based on the propeller pitch error (ep), a first control quantity (Out2); and a priority selection stage (45), configured to implement a priority selection between the first and the second control quantities, for providing at the output the driving quantity (IP), based on the priority selection between the first and the second control quantities.

The invention relates to a turbomachine module (1), comprising: —a rotating housing (7-8) supporting a propeller provided with a plurality of blades (5), —a system for varying the pitch of the propeller blades (5), the system comprising a control means, and a mechanism for varying the pitch of the propeller blades, characterised in that the system is supported by the rotary housing (7-8), in that the control means comprise an annular row of rotary actuators (16), and in that the mechanism for varying the pitch of the blades comprises a synchronisation ring (11) that is driven to rotate by rotary output shafts (17) of the actuators (16), the synchronisation ring (11) being guided in rotation relative to the rotary housing (7-8) by guide means and meshed by a first toothing (13) with pinions (14) of the blades (5).

The invention relates to a turbomachine module (1), comprising: —a rotating housing (7-8) supporting a propeller provided with a plurality of blades (5), —a system for varying the pitch of the propeller blades (5), the system comprising a control means, and a mechanism for varying the pitch of the propeller blades, characterised in that the system is supported by the rotary housing (7-8), in that the control means comprise an annular row of rotary actuators (16), and in that the mechanism for varying the pitch of the blades comprises a synchronisation ring (11) that is driven to rotate by rotary output shafts (17) of the actuators (16), the synchronisation ring (11) being guided in rotation relative to the rotary housing (7-8) by guide means and meshed by a first toothing (13) with pinions (14) of the blades (5).

The present invention relates to a rotor assembly where associated electric motors are configured to rotate the rotor, control the collective pitch of the rotor/assembly, and/or control the cyclic pitch of the rotor/assembly, by varying the relative rotational angle between two or more of the associated electric motors.

The present invention relates to a rotor assembly where associated electric motors are configured to rotate the rotor, control the collective pitch of the rotor/assembly, and/or control the cyclic pitch of the rotor/assembly, by varying the relative rotational angle between two or more of the associated electric motors.

The present invention relates to an aerially distributable communications device (ACCD) including one or more gyrochutes and communications module configured for wireless communication with external communication nodes. The communications module can be configured for mesh network type communication with similar aerially distributable communications device, or as a gateway type communications device to a wide area network such as a satellite network. The ACCD is for deployment in remote areas and/or areas where normal communications networks are down, such as disaster areas. The ACCD can be deployed from an aircraft or a spacecraft. The ACCD can further be configured with emergency equipment such as water purification equipment, power charging equipment, or the like.

An aircraft may include a body structure and a propulsion system coupled to the body structure and including a mounting shaft and a rotor. The rotor may include a rotor hub and a set of rotor blades, wherein the rotor is configured to orient the set of rotor blades at a first collective blade angle during a first flight mode and orient the set of rotor blades at a second collective blade angle during a second flight mode. The propulsion system may further include a motor coupled to the rotor and configured to rotate the rotor in a first rotational direction in the first flight mode to produce thrust in a first thrust direction and rotate the rotor in a second rotational direction opposite the first rotational direction in the second flight mode to produce thrust in a second thrust direction opposite the first thrust direction.

An aircraft may include a body structure and a propulsion system coupled to the body structure and including a mounting shaft and a rotor. The rotor may include a rotor hub and a set of rotor blades, wherein the rotor is configured to orient the set of rotor blades at a first collective blade angle during a first flight mode and orient the set of rotor blades at a second collective blade angle during a second flight mode. The propulsion system may further include a motor coupled to the rotor and configured to rotate the rotor in a first rotational direction in the first flight mode to produce thrust in a first thrust direction and rotate the rotor in a second rotational direction opposite the first rotational direction in the second flight mode to produce thrust in a second thrust direction opposite the first thrust direction.